CN110525693A - A kind of parallel connection tank propulsion system overall balance emissions adjustment method - Google Patents
A kind of parallel connection tank propulsion system overall balance emissions adjustment method Download PDFInfo
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- CN110525693A CN110525693A CN201910667365.2A CN201910667365A CN110525693A CN 110525693 A CN110525693 A CN 110525693A CN 201910667365 A CN201910667365 A CN 201910667365A CN 110525693 A CN110525693 A CN 110525693A
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- 238000000034 method Methods 0.000 title claims abstract description 53
- 239000003380 propellant Substances 0.000 claims abstract description 200
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 141
- 239000001301 oxygen Substances 0.000 claims abstract description 141
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 141
- 238000002485 combustion reaction Methods 0.000 claims abstract description 126
- 238000004364 calculation method Methods 0.000 claims abstract description 28
- 230000001105 regulatory effect Effects 0.000 claims abstract description 21
- 239000007789 gas Substances 0.000 claims description 361
- 230000006835 compression Effects 0.000 claims description 62
- 238000007906 compression Methods 0.000 claims description 62
- 239000003795 chemical substances by application Substances 0.000 claims description 49
- 238000011144 upstream manufacturing Methods 0.000 claims description 43
- 239000007800 oxidant agent Substances 0.000 claims description 29
- 230000001590 oxidative effect Effects 0.000 claims description 29
- 238000011017 operating method Methods 0.000 claims description 23
- 239000001307 helium Substances 0.000 claims description 18
- 229910052734 helium Inorganic materials 0.000 claims description 18
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 18
- 238000007664 blowing Methods 0.000 claims description 16
- 239000012530 fluid Substances 0.000 claims description 4
- 238000012544 monitoring process Methods 0.000 claims description 3
- 238000005303 weighing Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 5
- 239000000126 substance Substances 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 230000007812 deficiency Effects 0.000 description 2
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011067 equilibration Methods 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D16/00—Control of fluid pressure
- G05D16/028—Controlling a pressure difference
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a kind of tank propulsion system overall balance emissions adjustment method in parallel, state parameter setting before (1) is adjusted, (2) carry out oxygen case and balance emissions adjustment, and (3) carry out combustion case balance emissions adjustment.The present invention considers spacecraft parallel connection tank actual installation position can discrepant actual conditions, two tank residual propellant quality are independently of the quality before adjusting after adjusting in the tank propulsion system in parallel balance discharge regulation flow process of proposition, and the overall balance regulatory demand for adapting to " propellant mass × tank distance of shaft centers " may be implemented.Main flow and sub-process are Full Parameterizeds, introduce the calculations such as iterative cycles, interpretation branch, are convenient for factorization, and then reduce the time for determining control parameter.
Description
Technical field
The present invention relates to a kind of tank propulsion system overall balance emissions adjustment method in parallel, state ginseng before system is adjusted
Number adjusts target component, the intrinsic design parameter of tank, working medium property parameters as input quantity, accurately and rapidly calculates progress
The pressure of tank overall balance emissions adjustment the needs tank inflated and inflation.
Background technique
Spacecraft double elements parallel connection tank chemical propulsion system uses 2 kinds of working medium of oxidant and incendiary agent as propellant.
The propulsion system generally amounts to 4 parts by high-pressure gas circuit module, propellant receptacle storing module, engine block, electronic circuit module
Composition.High-pressure gas circuit functions of modules is storing high pressure gas and provides the pressurization gas of steady flow to propellant tank, makes to store
Case pressure in a certain range, to guarantee that propellant flow rate and flowing pressure meet engine ignition demand.Propellant stores mould
Block function is storage and distribution management propellant, and oxidant and incendiary agent are seated in respectively in 2 tanks, the setting of tank upstream and downstream
Latching valve, pressure sensor are used to control and monitor the use of propellant, and temperature sensor measurement tank is posted in tank outer surface
Temperature.2 kinds of propellants finally flow to the engine in engine block according to the flow of design and pressure, in engine combustion
Chemical energy is converted to kinetic energy, thrust output or torque.Electronic circuit module provides power supply, the various valves of drive control for system
And obtain pressure sensor and temperature sensor reading etc..
In order to meet the design requirement of spacecraft centroid, 2 tanks of propellant of the same race in general are placed in spacecraft
Mass center two sides symmetric position, 2 tanks of propellant of the same race in Spacecraft Launch the close propellant of charge weitght and
Etc. propellant is used in parallel when rail, i.e., propellant is discharged in quality.Due to 2 tank downstream pipes of propellant of the same race in propulsion system
The not reasons such as Striking symmetry, 2 tanks of propellant of the same race are not strictly balance discharge propellant when in-orbit, that is, are occurred in parallel
Tank balance discharge deviation.
Therefore, deviation is discharged for the balance of tank propulsion system in parallel, is carried out when most effective measure is exactly in-orbit flat
The adjusting of weighing apparatus discharge.The basic ideas being adjusted are adjusted separately to the pressure of 2 tanks in parallel, realize of the same race push away
Into the propellant flowing between agent tank, reach the mass balance of propellant between tank.
The method that the prior art proposes is primarily present following deficiency:
1) poor to the universality of tank propulsion system multiplicity in parallel and complex working condition.Specifically, method has been defaulted wait adjust
The propellant volume of section is to adjust the half of preceding two tanks residual propellant volume difference, that is, two tanks are surplus after having defaulted adjusting
Remaining propellant mass is equal.And two tank actual installation in parallel positions can be considered with the diversity of spacecraft structure in engineering
It is balanced emissions adjustment.2 tank positions of propellant i.e. of the same race are no longer symmetrical with respect to mass center, and when adjusting wishes apart from space flight
The propellant mass of the farther away tank in device axle center after adjustment is lower, realizes that the synthesis of " propellant mass × tank distance of shaft centers " is flat
Weighing apparatus.Different spacecraft parallel connection tank actual installations position can be variant, it is therefore desirable to two tank residual propellant matter after adjusting
Amount is independently of the quality before adjusting, and is diversified, but only adapting to adjust volume (multiply density after i.e. quality) is tune
Save the special case of preceding two tanks residual propellant volume difference half.
2) inadequate system and complete.This is embodied both ways, first is that how not providing according to state parameter before adjusting
The method for determining inflation tank；Second is that do not provide how to determine balance emissions adjustment after two tanks balance pressure, therefore
Lack certain guidance to the usage mode of system after adjusting.
Summary of the invention
Technology of the invention solves the problems, such as: in order to overcome the deficiencies of the prior art, it is comprehensive to provide a kind of tank propulsion system in parallel
Occlusal equilibration emissions adjustment method realizes the propellant flowing between propellant tank of the same race, reaches " propellant mass × tank axle center
Away from " overall balance.
Technical solution of the invention:
A kind of parallel connection tank propulsion system overall balance emissions adjustment method, specific steps are as follows:
(1) state parameter setting before being adjusted:
(a) fluid properties are set, comprising: the molal weight M of the gas that tank propulsion system in parallel uses, gas constant R,
Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2；Oxidant reference density ρ _ o_0, incendiary agent benchmark are close
Spend ρ _ f_0, oxidant bulkfactor a_o, incendiary agent bulkfactor a_f；
(b) tank parameter is set, comprising: oxygen case a volume V_o_a, oxygen case b volume V_o_b, combustion case a volume V_f_a, combustion
Case b volume V_f_b；
(c) solving precision parameter is set, comprising: pressures cycle step-length P_step, volume cycle step-length V_step, gas are close
Spend residual error convergence δ _ ρ _ min, gas pressure residual error convergence δ _ P_min；
It (d) is state 1, the lower tank state parameter of setting state 1, including oxygen case a pressure P_ before definition balance emissions adjustment
O_a_1, oxygen case b pressure P_o_b_1, combustion case a pressure P_f_a_1, combustion case b pressure P_f_b_1, oxygen case a temperature T_o_a_1, oxygen
Case b temperature T_o_b_1, combustion case a temperature T_f_a_1, combustion case b temperature T_f_b_1, oxygen case a propellant mass m_o_a_1, oxygen case b
Propellant mass m_o_b_1, combustion case a propellant mass m_f_a_1, combustion case b propellant mass m_f_b_1；
(2) it carries out oxygen case and balances emissions adjustment:
(a) it is state 2 after definition balance emissions adjustment, sets oxygen case quality adjustment target, is i.e. the lower oxygen case a of state 2 is promoted
Agent quality m_o_a_2, oxygen case b propellant mass m_o_b_2；
(b) numerical value of setting balance discharge regulating calculation required input parameter, including propellant type number is set as oxygen
The corresponding number 1 of agent and progress tank Parameter Switch assignment, oxygen case a volume V_o_a, oxygen case b volume V_o_b are converted respectively
It is assigned to tank a volume V_a and tank b volume V_b, by the propellant mass m_o_a_1/m_ of state 1 lower oxygen case a and oxygen case b
O_b_1, temperature T_o_a_1/T_o_b_1, pressure P_o_a_1/P_o_b_1 convert the propulsion for being assigned to tank a and tank b respectively
Agent quality m_a_1/m_b_1, temperature T_a_1/T_b_1, pressure P_a_1/P_b_1, by the propulsion of state 2 lower oxygen case a and oxygen case b
Agent quality m_o_a_2/m_o_b_2 converts the propellant mass m_a_2/m_b_2 for being assigned to tank a and tank b respectively；
(c) tank mark D_bal_buqi, the blowing pressure P_bal_ that need to be inflated according to balance discharge regulating calculation determination
The pressure P_bal and temperature T_bal of tank after buqi, balance；
(d) according to the difference for the tank mark D_bal_buqi that need to be inflated, different operating procedures is selected, if need to inflate
Tank mark D_bal_buqi is directed toward oxygen case a, thens follow the steps (e-1)；If the tank mark D_bal_buqi that need to be inflated is directed toward
Oxygen case b, thens follow the steps (e-2)；If the tank mark D_bal_buqi that need to be inflated is directed toward other, step (f) is directly jumped to；
(e-1) the latching valve LV1 of the upstream oxygen case a is opened by oxygen case a tonifying Qi, until pressure is to the blowing pressure P_bal_buqi,
The latching valve LV1 for closing the upstream oxygen case a later, opens the latching valve LV5 and LV7 in oxygen case a and the downstream tank b, until oxygen case a and oxygen case
Propellant mass reaches oxygen case quality adjustment target m_o_a_2/m_o_b_2 in b, completes to adjust；
(e-2) the latching valve LV3 of the upstream oxygen case b is opened by oxygen case b tonifying Qi, until pressure is to the blowing pressure P_bal_buqi,
The latching valve LV3 for closing the upstream oxygen case b later, opens the latching valve LV5 and LV7 in oxygen case a and the downstream tank b, until oxygen case a and oxygen case
Propellant mass reaches oxygen case quality adjustment target m_o_a_2/m_o_b_2 in b, completes to adjust；
(f) pressure P_bal, oxygen box temperature degree T_g_o are temperature after balance adjustment after setting oxygen case pressure P_o as balance adjustment
T_bal；
(3) combustion case balance emissions adjustment is carried out:
(a) the lower combustion case a propellant mass of setting combustion case quality adjustment target, i.e. state 2, combustion case b propellant mass m_f_
a_2/m_f_b_2；
(b) setting balance discharge regulating calculation required input parameter numerical value, including set propellant type number N_p as
The corresponding number 2 of incendiary agent and progress tank Parameter Switch assignment turn combustion case a volume V_f_a, combustion case b volume V_f_b respectively
It changes and is assigned to tank a volume V_a and tank b volume V_b, by the propellant mass m_f_a_1/ of state 1 lower combustion case a and combustion case b
M_f_b_1, temperature T_f_a_1/T_f_b_1, pressure P_f_a_1/P_f_b_1 are converted respectively is assigned to pushing away for tank a and tank b
Into agent quality m_a_1/m_b_1, temperature T_a_1/T_b_1, pressure P_a_1/P_b_1, by the lower combustion case a of state 2 and pushing away for case b is fired
Convert the propellant mass m_a_2/m_b_2 for being assigned to tank a and tank b respectively into agent quality m_f_a_2/m_f_b_2；
(c) tank mark D_bal_buqi, the blowing pressure P_bal_ that need to be inflated according to balance discharge regulating calculation determination
The pressure P_bal and temperature T_bal of tank after buqi, balance；
(d) according to the difference for the tank mark D_bal_buqi that need to be inflated, different operating procedures is selected, if need to inflate
Tank mark D_bal_buqi is directed toward combustion case a, thens follow the steps (e-1)；If the tank mark D_bal_buqi that need to be inflated is directed toward
Case b is fired, (e-2) is thened follow the steps；If the tank mark D_bal_buqi that need to be inflated is directed toward other, step (f) is directly jumped to；
(e-1) the latching valve LV2 for opening the combustion upstream case a will fire case a tonifying Qi, up to pressure is to the blowing pressure P_bal_buqi,
The latching valve LV2 for closing the combustion upstream case a later opens combustion case a and fires the latching valve LV6 and LV8 in the downstream case b, until combustion case a and combustion case
Propellant mass reaches combustion case quality adjustment target m_f_a_2/m_f_b_2 in b, completes to adjust；
(e-2) the latching valve LV4 for opening the combustion upstream case b will fire case b tonifying Qi, up to pressure is to the blowing pressure P_bal_buqi,
The latching valve LV4 for closing the combustion upstream case b later, opens the latching valve LV6 and LV8 of combustion case a and the downstream tank b, until combustion case a and combustion case
Propellant mass reaches combustion case quality adjustment target m_f_a_2/m_f_b_2 in b, completes to adjust；
(f) pressure P_bal, combustion box temperature degree T_g_f are temperature after balance adjustment after setting combustion case pressure P_f as balance adjustment
T_bal。
Balance discharge regulating calculation includes that process variable calculates, tonifying Qi tank mark calculates and tank superfeed pressure calculates；
It includes determining propellant temperature, propellant density, propellant volume, tank gas volume and matter that process variable, which calculates,
Amount, tank mean temperature, tank Gas Compression Factor；
It includes determining tank gas changeable volume and pressure, tank propellant mass that tonifying Qi tank mark, which calculates,.
Carry out process variable calculation method are as follows:
(a) according to the lower tank a temperature T_a_1 of state 1 and the lower tank b temperature T_b_1 of state 1, propellant temperature T_l is calculated
=0.5* (T_a_1+T_b_1)；
(b) according to the difference of propellant type number N_p, different operating procedures is selected, if propellant type number N_p
It is directed toward oxidant, thens follow the steps (c-1)；If propellant type number N_p is directed toward incendiary agent, (c-2) is thened follow the steps；
(c-1) it is calculated and is promoted according to oxidant reference density ρ _ o_0, propellant temperature T_l and oxidant bulkfactor a_o
Agent density p _ l=ρ _ o_0+a_o*T_l；
(c-2) it is calculated and is promoted according to incendiary agent reference density ρ _ f_0, propellant temperature T_l and incendiary agent bulkfactor a_f
Agent density p _ l=ρ _ f_0+a_f*T_l；
(d) the lower tank a of state 1 is calculated according to the lower tank a propellant mass m_a_1 and propellant density p _ l of state 1 to promote
Agent volume V_l_a_1=m_a_1/ ρ _ l calculates shape according to the lower tank b propellant mass m_b_1 and propellant density p _ l of state 1
The lower tank b propellant volume V_l_b_1=m_b_1/ ρ _ l of state 1；
(e) the lower tank a gas volume V_ of state 1 is calculated according to tank a volume V_a and tank a propellant volume V_l_a_1
G_a_1=V_a-V_l_a_1 calculates the lower tank b gas of state 1 according to tank b volume V_b and tank b propellant volume V_l_b_1
Body volume V_g_b_1=V_b-V_l_b_1；
(f) the lower tank a of state 2 is calculated according to the lower tank a propellant mass m_a_2 and propellant density p _ l of state 2 to promote
Agent volume V_l_a_2=m_a_2/ ρ _ l calculates shape according to the lower tank b propellant mass m_b_2 and propellant density p _ l of state 2
The lower tank b propellant volume V_l_b_2=m_b_2/ ρ _ l of state 2；
(g) the lower tank a gas of state 2 is calculated according to tank a volume V_a and the lower tank a propellant volume V_l_a_2 of state 2
Body volume V_g_a_2=V_a-V_l_a_2, according to tank b volume V_b and the lower tank b propellant volume V_l_b_2 meter of state 2
The lower tank b gas volume V_g_b_2=V_b-V_l_b_2 of calculation state 2；
(h) the lower tank a temperature T_a_2 of setting state 2 is equal to the lower tank a temperature T_a_1 of state 1, the lower tank b temperature of state 2
It spends T_b_2 and is equal to the lower tank b temperature T_b_1 of state 1, temperature is equal to being averaged for the lower tank a and tank b of state 2 after balance adjustment
Temperature T_bal=0.5* (T_a_2+T_b_2)；
(i) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank a pressure P_ of state 1
The lower tank a temperature T_a_1 of a_1, state 1 calculates the lower tank a Gas Compression Factor Z_g_a_1=1+a_Z_1*P_a_1* of state 1
T_a_1^a_Z_2；
(j) according to the lower tank a pressure P_a_1 of state 1, gas molar quality M, the lower tank a Gas Compression Factor Z_ of state 1
G_a_1, state 1 lower tank a temperature T_a_1, gas constant R calculate the lower tank a gas density ρ _ g_a_1=P_a_1* of state 1
M/(Z_g_a_1*T_a_1*R)；
(k) according to the lower tank a gas volume V_g_a_1 of state 1, the lower tank a gas density ρ _ g_a_1 of state 1, shape is calculated
The lower tank a gaseous mass m_g_a_1=V_g_a_1* ρ _ g_a_1 of state 1；
(l) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank b pressure P_ of state 1
The lower tank b temperature T_b_1 of b_1, state 1 calculates the lower tank b Gas Compression Factor Z_g_b_1=1+a_Z_1*P_b_1* of state 1
T_b_1^a_Z_2；
(m) according to the lower tank b pressure P_b_1 of state 1, gas molar quality M, the lower tank b Gas Compression Factor Z_ of state 1
G_b_1, state 1 lower tank b temperature T_b_1, gas constant R calculate the lower tank b gas density ρ _ g_b_1=P_b_1* of state 1
M/(Z_g_b_1*T_b_1*R)；
(n) according to the lower tank b gas volume V_g_b_1 of state 1, the lower tank b gas density ρ _ g_b_1 of state 1, shape is calculated
The lower tank b gaseous mass m_g_b_1=V_g_b_1* ρ _ g_b_1 of state 1；
Tonifying Qi tank mark calculation method are as follows:
(a) according to of different sizes between the lower tank a pressure P_a_1 of state 1 and the lower tank b pressure P_b_1 of state 1, selection is not
Same operating procedure thens follow the steps (b-1) if P_a_1 > P_b_1；If P_a_1 < P_b_1, (b-2) is thened follow the steps；If P_
A_1=P_b_1 thens follow the steps (b-3)；
(b-1) set tank a gas volume change flag D_a as 1, tank b gas volume change flag D_b be -1；
(b-2) set tank a gas volume change flag D_a as -1, tank b gas volume change flag D_b be 1；
(b-3) tank a propellant mass m_a_2 under tank a propellant mass m_a_1_bal is state 2 when setting balance,
It turns to step (n)；
(c) volume cycle serial number initial value i=1 is set；
(d) according to the lower tank a gas volume V_g_a_1 of state 1, volume cycle serial number i, tank a gas volume variation mark
Will D_a, volume cycle step-length V_step calculate the new volume V_g_a_ceshi=V_g_a_1+i*D_a*V_ of tank a gas
step；
(e) tank a pressure P_a_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are -1,
Gas temperature T is the lower tank a temperature T_a_1 of state 1, and it is the lower tank a gaseous mass m_g_ of state 1 that gas, which restrains density p _ g_0,
The ratio of a_1 and the new volume V_g_a_ceshi of tank a gas；
(f) the pressure P_a_ceshi=P_ceshi calculated under the new volume of tank a is solved by gas pressure；
(g) according to the lower tank b gas volume V_g_b_1 of state 1, volume cycle serial number i, tank b gas volume variation mark
Will D_b, volume cycle step-length V_step calculate the new volume V_g_b_ceshi=V_g_b_1+i*D_b*V_ of tank b gas
step；
(h) tank b pressure P_b_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1, gas
Temperature T is the lower tank b temperature T_b_1 of state 1, and it is the lower tank b gaseous mass m_g_b_1 of state 1 that gas, which restrains density p _ g_0,
With the ratio of the new volume V_g_b_ceshi of tank b gas；
(i) the pressure P_b_ceshi=P_ceshi calculated under the new volume of tank b is solved by gas pressure；
(j) according to the pressure P_b_ceshi under the pressure P_a_ceshi and the new volume of tank b under the new volume of tank a, meter
Calculate pressure residual error δ _ P=| P_a_ceshi-P_b_ceshi |/P_a_ceshi；
(k) according to of different sizes between pressure residual error δ _ P and gas pressure residual error convergence δ _ P_min, selection difference
Operating procedure；If δ _ P >=δ _ P_min thens follow the steps (k-1)；If δ _ P < δ _ P_min thens follow the steps (k-2)；
(k-1) it enables volume cycle serial number k add 1, returns and execute step (d)；
(k-2) pressure P_bal is the pressure P_a_ceshi under the new volume of tank a when setting two casees pressure balances；
(l) gas volume V_g_a_bal is the new volume V_g_a_ceshi of tank a gas when setting tank a pressure balance；
(m) according to gas volume V_g_a_bal, propellant density p _ l when tank a volume V_a, tank a pressure balance, meter
Tank a propellant mass m_a_1_bal=(V_a-V_g_a_bal) * ρ _ l when calculating balance；
(n) according to tank a propellant mass m_a_1_bal when the lower tank a propellant mass m_a_2 of state 2 and balance it
Between it is of different sizes, select different operating procedures；If m_a_2 < m_a_1_bal, set balance adjustment tonifying Qi tank mark as
Numerical value 1；If m_a_2 > m_a_1_bal, balance adjustment tonifying Qi tank mark is set as numerical value 2；If m_a_2=m_a_1_bal,
Balance adjustment tonifying Qi tank mark is then set as numerical value 0；
Tank superfeed pressure calculation method are as follows:
(a) different according to balance adjustment tonifying Qi tank mark D_bal_buqi, different operating procedures is selected, if D_bal_
Buqi=1 thens follow the steps (b-1)；If D_bal_buqi=2, (b-2) is thened follow the steps；If D_bal_buqi=0 is held
Row step (b-3)；
(b-1) tank b pressure P_b_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1,
Gas temperature T is the lower tank b temperature T_b_2 of state 2, and it is the lower tank b gaseous mass m_g_ of state 1 that gas, which restrains density p _ g_0,
The quotient of b_1 and the lower tank b gas volume V_g_b_2 of state 2；
(c-1) tank b pressure P_b_2=P_ceshi after calculating adjusting is solved by gas pressure；
(d-1) the lower tank a gas pressure P_a_2 of writ state 2 is the lower tank b gas pressure P_b_2 of state 2, balance adjustment
Pressure P_bal is the lower tank b gas pressure P_b_2 of state 2 afterwards；
(e-1) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank a gas of state 2
The lower tank a temperature T_a_2 of pressure P_a_2, state 2, calculates tank a Gas Compression Factor Z_g_a_2=1+a_Z_1* after adjusting
P_a_2*T_a_2^a_Z_2；
(f-1) according to tank a Gas Compression Factor after the lower tank a pressure P_a_2 of state 2, gas molar quality M, adjusting
Z_g_a_2, state 2 lower tank a temperature T_a_2, gas constant R, calculate tank a gas density ρ _ g_a_2=P_a_ after adjusting
2*M/(Z_g_a_2*T_a_2*R)；
(g-1) it according to tank a gas density ρ _ g_a_2 after the lower tank a gas volume V_g_a_2 of state 2, adjusting, calculates
Tank a helium mass m_g_a_2=V_g_a_2* ρ _ g_a_2 after adjusting；
(h-1) tank a pressure P_a_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1,
Gas temperature is the lower tank a temperature T_a_1 of state 1, and it is tank a helium mass m_g_a_2 after adjusting that gas, which restrains density p _ g_0,
With the quotient of the lower tank a gas volume V_g_a_1 of state 1；
(i-1) tank a when tank a helium mass m_g_a_2 is compressed into state 1 after calculating adjusting is solved by gas pressure
Corresponding pressure when volume V_g_a_1, and it is assigned to balance adjustment superfeed pressure P_bal_buqi；It turns to step (j)；
(b-2) tank a pressure P_a_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1,
Gas temperature T is the lower tank a temperature T_a_2 of state 2, and it is the lower tank a gaseous mass m_g_ of state 1 that gas, which restrains density p _ g_0,
The quotient of a_1 and the lower tank a gas volume V_g_a_2 of state 2；
(c-2) tank a pressure P_a_2=P_ceshi after calculating adjusting is solved by gas pressure；
(d-2) the lower tank b gas pressure P_b_2 of writ state 2 is the lower tank a gas pressure P_a_2 of state 2, balance adjustment
Pressure P_bal is the lower tank a gas pressure P_a_2 of state 2 afterwards；
(e-2) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank b gas of state 2
The lower tank b temperature T_b_2 of pressure P_b_2, state 2, calculates tank b Gas Compression Factor Z_g_b_2=1+a_Z_1* after adjusting
P_b_2*T_b_2^a_Z_2；
(f-2) according to tank b Gas Compression Factor after the lower tank b pressure P_b_2 of state 2, gas molar quality M, adjusting
Z_g_b_2, state 2 lower tank b temperature T_b_2, gas constant R, calculate tank b gas density ρ _ g_b_2=P_b_ after adjusting
2*M/(Z_g_b_2*T_b_2*R)；
(g-2) it according to tank b gas density ρ _ g_b_2 after the lower tank b gas volume V_g_b_2 of state 2, adjusting, calculates
Tank b helium mass m_g_b_2=V_g_b_2* ρ _ g_b_2 after adjusting；
(h-2) tank b pressure P_b_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1,
Gas temperature T is the lower tank b temperature T_b_1 of state 1, and it is tank b helium mass m_g_b_ after adjusting that gas, which restrains density p _ g_0,
The quotient of 2 and the lower tank b gas volume V_g_b_1 of state 1；
(i-2) tank b when tank b helium mass m_g_b_2 is compressed into state 1 after calculating adjusting is solved by gas pressure
Corresponding pressure when volume V_g_b_1, and it is assigned to balance adjustment superfeed pressure P_bal_buqi；It turns to step (j)；
(b-3) enabling balance adjustment superfeed pressure P_bal_buqi is the lower tank a pressure P_a_1 of state 1, is pressed after balance adjustment
Power P_bal is the lower tank a pressure P_a_1 of state 1, is turned to step (j)；
(j) balance adjustment tonifying Qi tank mark D_bal_buqi, balance adjustment superfeed pressure P_bal_buqi, balance are exported
Temperature T_bal after pressure P_bal, balance adjustment after adjusting；
(k) terminate.
Gas pressure method for solving comprises the steps of:
(a) pressures cycle serial number i is set as initial value 1；
(b) according to pressure change initial value P_0, pressures cycle serial number i, pressure change mark D_P, pressures cycle step-length P_
Step calculates the new pressure P_ceshi=P_0+i*D_P*P_step of gas；
(c) according to according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the new pressure P_ of gas
Cesh, gas temperature T calculate the new compressibility factor Z_ceshi=1+a_Z_1*P_ceshi*T^a_Z_2 of gas；
(d) according to the new pressure P_ceshi of gas, gas molar quality M, the new compressibility factor Z_ceshi of gas, gas temperature
T, gas constant R calculates the new density p _ g_ceshi=P_ceshi*M/ (Z_ceshi*T*R) of gas；
(e) according to the new density p _ g_ceshi of gas, gas restrain density p _ g_0, calculate gas density residual error δ _ ρ=| ρ _
g_ceshi-ρ_g_0|/ρ_g_0；
(f) according to of different sizes between gas density residual error δ _ ρ and gas density residual error convergence δ _ ρ _ min, selection is not
Same operating procedure；If δ _ ρ < δ _ ρ _ min, execute step (g_y)；If δ _ ρ >=δ _ ρ _ min, execute step (g_n)；
(g_y) the new pressure P_ceshi of output gas；
(g_n) it enables pressures cycle serial number i add 1, turns to step (b)；
(h) terminate.
Tank propulsion system in parallel includes 4 tanks, wherein 2 oxygen casees and 2 combustion casees, respectively oxygen case a MON-a, oxygen
Case b MON-b, combustion case a MMH-a, combustion case b MMH-b；Discharge oxidant in parallel, i.e. oxygen case a MON-a and oxygen between 2 oxygen casees
Tank downstream latching valve LV5 is respectively set together with connection after LV7 in the outlet of case b MON-b downstream propellant, and leads to and start
The oxidant inlet of machine Eng, to provide oxidant to engine Eng
After tank upstream latching valve LV1 and LV3 is respectively set in oxygen case a MON-a and oxygen case b MON-b upstream gas entrance
Connection is together.
Discharge incendiary agent in parallel between 2 combustion casees, i.e. combustion case a MMH-a and the outlet point of combustion case b MMH-b downstream propellant
Not She Zhi tank downstream latching valve LV6 together with connection after LV8, and lead to the incendiary agent entrance of engine Eng, with to starting
Machine Eng provides incendiary agent；Tank upstream latching valve LV2 is respectively set in combustion case a MMH-a and combustion case b MMH-b upstream gas entrance
Together with connection after LV4；High-pressure gas circuit module can be controlled to any one with every latching valve of independent switch tank upstream
Tank inflation；It can control any one tank with every latching valve in independent switch tank downstream and propellant is discharged.
A pressure sensor PT1~PT4 is respectively arranged in 4 tank upstream gas inlet, for monitoring the pressure in tank
Power.
Compared with prior art, the present invention has the following advantages:
(1) present invention consider spacecraft parallel connection tank actual installation position can discrepant actual conditions, proposition
Before two tank residual propellant quality are independently of adjusting after adjusting in tank propulsion system balance discharge regulation flow process in parallel
Quality, the overall balance regulatory demand for adapting to " propellant mass × tank distance of shaft centers " may be implemented；
It (2), can be convenient by " the tank mark that need to be inflated " variable of setting in present invention balance discharge regulating calculation
Identify the tank that needs are inflated when adjusting；
(3) present invention balance discharge regulating calculation gives the balance pressure of two tanks in parallel after balance emissions adjustment,
Convenient for carrying out other operations to the system after adjusting；
(4) gas pressure method for solving of the present invention, it is contemplated that the practical feelings that Gas Compression Factor changes in adjustment process
Condition improves the accuracy of adjusting；
(5) main flow of the invention and sub-process are Full Parameterizeds, introduce the calculating sides such as iterative cycles, interpretation branch
Formula is convenient for factorization, and then reduces the time for determining control parameter.
Detailed description of the invention
Fig. 1 is spacecraft parallel connection tank chemical propulsion system schematic diagram of the present invention；
Fig. 2 is main flow chart of the present invention；
Fig. 3 is that present invention balance discharges regulating calculation flow chart；
Fig. 4 is that gas pressure of the present invention solves flow chart.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawing.
As shown in Figure 1, spacecraft parallel connection tank chemical propulsion system generally comprises 4 tanks, wherein 2 oxygen casees and 2
Fire case, respectively oxygen case a MON-a, oxygen case b MON-b, combustion case a MMH-a, combustion case b MMH-b.Between 2 oxygen casees and townhouse
Oxidant out, i.e. oxygen case a MON-a and oxygen case b MON-b downstream propellant outlet be respectively set tank downstream latching valve LV5 and
Connection together, and leads to the oxidant inlet of engine Eng after LV7, to provide oxidant to engine Eng.Oxygen case a
Tank upstream latching valve LV1 is respectively set together with connection after LV3 with oxygen case b MON-b upstream gas entrance in MON-a.
Discharge incendiary agent in parallel between 2 combustion casees, i.e. combustion case a MMH-a and the outlet point of combustion case b MMH-b downstream propellant
Not She Zhi tank downstream latching valve LV6 together with connection after LV8, and lead to the incendiary agent entrance of engine Eng, with to starting
Machine Eng provides incendiary agent.Tank upstream latching valve LV2 is respectively set in combustion case a MMH-a and combustion case b MMH-b upstream gas entrance
Together with connection after LV4.High-pressure gas circuit module can be controlled to any one with every latching valve of independent switch tank upstream
Tank inflation.It can control any one tank with every latching valve in independent switch tank downstream and propellant is discharged.4 tanks
A pressure sensor PT1~PT4 is respectively arranged in upstream gas inlet, for monitoring the pressure in tank.
In order to adapt to more various and complex working condition, the systematicness and integrality of adjusting method are improved, and adapt to " propellant
The overall balance regulatory demand of quality × tank distance of shaft centers ", concrete scheme are as follows:
A kind of parallel connection tank propulsion system overall balance emissions adjustment method, main flow include that three parts are as shown in Figure 2.
Main_part_1, state parameter setting before being adjusted, steps are as follows:
(a) fluid properties are set, comprising: the molal weight M of the gas that tank propulsion system in parallel uses, gas constant R,
Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2；Oxidant reference density ρ _ o_0, incendiary agent benchmark are close
Spend ρ _ f_0, oxidant bulkfactor a_o, incendiary agent bulkfactor a_f.Fluid properties belong to gas, oxidant, incendiary agent
Intrinsic physical attribute parameter can be determined according to the gas, oxidant, incendiary agent Query technical standard used.
(b) tank parameter is set, comprising: oxygen case a volume V_o_a, oxygen case b volume V_o_b, combustion case a volume V_f_a, combustion
Case b volume V_f_b.Tank parameter can be surveyed on ground and be obtained.
(c) solving precision parameter is set, comprising: pressures cycle step-length P_step, volume cycle step-length V_step, gas are close
Spend residual error convergence δ _ ρ _ min, gas pressure residual error convergence δ _ P_min.Solving precision parameter can be according to required meter
Calculate duration, computational accuracy setting.Such as pressures cycle step-length is selected as 0.00001MPa, volume cycle step-length is selected as
0.001L, residual error convergence are selected as 0.001%.
It (d) is state 1, the lower tank state parameter of setting state 1, including oxygen case a pressure P_ before definition balance emissions adjustment
O_a_1, oxygen case b pressure P_o_b_1, combustion case a pressure P_f_a_1, combustion case b pressure P_f_b_1, oxygen case a temperature T_o_a_1, oxygen
Case b temperature T_o_b_1, combustion case a temperature T_f_a_1, combustion case b temperature T_f_b_1, oxygen case a propellant mass m_o_a_1, oxygen case b
Propellant mass m_o_b_1, combustion case a propellant mass m_f_a_1, combustion case b propellant mass m_f_b_1.The lower tank shape of state 1
State parameter can be obtained according to the in-orbit telemetering amount of spacecraft.
Main_part_2 carries out oxygen case and balances emissions adjustment, and steps are as follows:
(a) it is state 2 after definition balance emissions adjustment, sets oxygen case quality adjustment target, is i.e. the lower oxygen case a of state 2 is promoted
Agent quality m_o_a_2, oxygen case b propellant mass m_o_b_2.The propellant mass that the method for the prior art needs to adjust is state
The half of 1 lower oxygen case b propellant mass and oxygen case a propellant mass difference, and this patent can be and abide by under practical can be achieved
Arbitrary value, i.e., independent of the state before adjusting.
(b) numerical value of setting " balance discharge regulating calculation process " required input parameter, including setting propellant type are compiled
Number for the corresponding number 1 of oxidant and carry out tank Parameter Switch assignment, by oxygen case a volume V_o_a, oxygen case b volume V_o_b divide
It Zhuan Huan be assigned to tank a volume V_a and tank b volume V_b, by the propellant mass m_o_ of state 1 lower oxygen case a and oxygen case b
A_1/m_o_b_1, temperature T_o_a_1/T_o_b_1, pressure P_o_a_1/P_o_b_1 are converted respectively is assigned to tank a and tank b
Propellant mass m_a_1/m_b_1, temperature T_a_1/T_b_1, pressure P_a_1/P_b_1, by the lower oxygen case a and oxygen case b of state 2
Propellant mass m_o_a_2/m_o_b_2 convert the propellant mass m_a_2/m_b_2 for being assigned to tank a and tank b respectively.
(c) tank mark D_bal_buqi, inflation that determination need to inflate are calculated according to " balance discharge regulating calculation process "
The pressure P_bal and temperature T_bal of tank after pressure P_bal_buqi, balance.Different from document [1] do not provide how basis
State parameter determines inflation oxygen case before adjusting, and the tank mark of need inflation here is the oxygen case for specifying inflation.It need to inflate
The different numerical value of tank mark indicate that the tank that need to be inflated is that oxygen case a or oxygen case b or both do not need to inflate.
(d) according to the difference for the tank mark D_bal_buqi that need to be inflated, different operating procedures is selected.If need to inflate
Tank mark D_bal_buqi is directed toward oxygen case a, thens follow the steps (e-1)；If the tank mark D_bal_buqi that need to be inflated is directed toward
Oxygen case b, thens follow the steps (e-2)；If the tank mark D_bal_buqi that need to be inflated is directed toward other, step (f) is directly jumped to.
(e-1) the latching valve LV1 of the upstream oxygen case a is opened by oxygen case a tonifying Qi, until pressure is to the blowing pressure P_bal_buqi,
The latching valve LV1 for closing the upstream oxygen case a later, opens the latching valve LV5 and LV7 in oxygen case a and the downstream tank b, until oxygen case a and oxygen case
Propellant mass reaches oxygen case quality adjustment target m_o_a_2/m_o_b_2 in b, completes to adjust.
(e-2) the latching valve LV3 of the upstream oxygen case b is opened by oxygen case b tonifying Qi, until pressure is to the blowing pressure P_bal_buqi,
The latching valve LV3 for closing the upstream oxygen case b later, opens the latching valve LV5 and LV7 in oxygen case a and the downstream tank b, until oxygen case a and oxygen case
Propellant mass reaches oxygen case quality adjustment target m_o_a_2/m_o_b_2 in b, completes to adjust.
(f) pressure P_bal, oxygen box temperature degree T_g_o are temperature after balance adjustment after setting oxygen case pressure P_o as balance adjustment
T_bal。
Main_part_3 carries out combustion case balance emissions adjustment, and steps are as follows:
(a) the lower combustion case a propellant mass of setting combustion case quality adjustment target, i.e. state 2, combustion case b propellant mass m_f_
a_2/m_f_b_2.Similarly, the propellant mass that the method for the prior art needs to adjust, which is that state 1 is lower, fires case b propellant mass
With the half of combustion case a propellant mass difference, and this patent can be the arbitrary value abided by under practical can be achieved, i.e., independent of
State before adjusting.
(b) numerical value of setting " balance discharge regulating calculation process " required input parameter, including setting propellant type are compiled
Number N_p is the corresponding number 2 of incendiary agent and carries out tank Parameter Switch assignment, will combustion case a volume V_f_a, fire case b volume V_f_
B is converted respectively is assigned to tank a volume V_a and tank b volume V_b, by the propellant mass m_ of state 1 lower combustion case a and combustion case b
F_a_1/m_f_b_1, temperature T_f_a_1/T_f_b_1, pressure P_f_a_1/P_f_b_1 are converted respectively is assigned to tank a and storage
Propellant mass m_a_1/m_b_1, temperature T_a_1/T_b_1, the pressure P_a_1/P_b_1 of case b, by the lower combustion case a of state 2 and combustion
The propellant mass m_f_a_2/m_f_b_2 of case b converts the propellant mass m_a_2/m_ for being assigned to tank a and tank b respectively
b_2。
(c) tank mark D_bal_buqi, inflation that determination need to inflate are calculated according to " balance discharge regulating calculation process "
The pressure P_bal and temperature T_bal of tank after pressure P_bal_buqi, balance.Similarly, the prior art do not provide how
Inflation combustion case is determined according to state parameter before adjusting, and the tank mark of need inflation here is the combustion case for specifying inflation.It need to fill
The different numerical value of the tank mark of gas indicate that the tank that need to be inflated does not need to inflate for combustion case a or combustion case b or both.
(d) according to the difference for the tank mark D_bal_buqi that need to be inflated, different operating procedures is selected.If need to inflate
Tank mark D_bal_buqi is directed toward combustion case a, thens follow the steps (e-1)；If the tank mark D_bal_buqi that need to be inflated is directed toward
Case b is fired, (e-2) is thened follow the steps；If the tank mark D_bal_buqi that need to be inflated is directed toward other, step (f) is directly jumped to.
(e-1) the latching valve LV2 for opening the combustion upstream case a will fire case a tonifying Qi, up to pressure is to the blowing pressure P_bal_buqi,
The latching valve LV2 for closing the combustion upstream case a later opens combustion case a and fires the latching valve LV6 and LV8 in the downstream case b, until combustion case a and combustion case
Propellant mass reaches combustion case quality adjustment target m_f_a_2/m_f_b_2 in b, completes to adjust.
(e-2) the latching valve LV4 for opening the combustion upstream case b will fire case b tonifying Qi, up to pressure is to the blowing pressure P_bal_buqi,
The latching valve LV4 for closing the combustion upstream case b later, opens the latching valve LV6 and LV8 of combustion case a and the downstream tank b, until combustion case a and combustion case
Propellant mass reaches combustion case quality adjustment target m_f_a_2/m_f_b_2 in b, completes to adjust.
(f) pressure P_bal, combustion box temperature degree T_g_f are temperature after balance adjustment after setting combustion case pressure P_f as balance adjustment
T_bal。
Further, a kind of sub-process that tank propulsion system overall balance emissions adjustment requirements of process in parallel is called is " flat
Weigh emissions adjustment calculation process " it include three parts, as shown in Figure 3.
Sub_part_bal_1 carries out simple process quantity calculating, and steps are as follows:
(a) according to the lower tank a temperature T_a_1 of state 1 and the lower tank b temperature T_b_1 of state 1, propellant temperature T_l is calculated
=0.5* (T_a_1+T_b_1)；
(b) according to the difference of propellant type number N_p, different operating procedures is selected, if propellant type number N_p
It is directed toward oxidant, thens follow the steps (c-1)；If propellant type number N_p is directed toward incendiary agent, (c-2) is thened follow the steps；
(c-1) it is calculated and is promoted according to oxidant reference density ρ _ o_0, propellant temperature T_l and oxidant bulkfactor a_o
Agent density p _ l=ρ _ o_0+a_o*T_l；
(c-2) it is calculated and is promoted according to incendiary agent reference density ρ _ f_0, propellant temperature T_l and incendiary agent bulkfactor a_f
Agent density p _ l=ρ _ f_0+a_f*T_l；
(d) the lower tank a of state 1 is calculated according to the lower tank a propellant mass m_a_1 and propellant density p _ l of state 1 to promote
Agent volume V_l_a_1=m_a_1/ ρ _ l calculates shape according to the lower tank b propellant mass m_b_1 and propellant density p _ l of state 1
The lower tank b propellant volume V_l_b_1=m_b_1/ ρ _ l of state 1；
(e) the lower tank a gas volume V_ of state 1 is calculated according to tank a volume V_a and tank a propellant volume V_l_a_1
G_a_1=V_a-V_l_a_1 calculates the lower tank b gas of state 1 according to tank b volume V_b and tank b propellant volume V_l_b_1
Body volume V_g_b_1=V_b-V_l_b_1；
(f) the lower tank a of state 2 is calculated according to the lower tank a propellant mass m_a_2 and propellant density p _ l of state 2 to promote
Agent volume V_l_a_2=m_a_2/ ρ _ l calculates shape according to the lower tank b propellant mass m_b_2 and propellant density p _ l of state 2
The lower tank b propellant volume V_l_b_2=m_b_2/ ρ _ l of state 2；
(g) the lower tank a gas of state 2 is calculated according to tank a volume V_a and the lower tank a propellant volume V_l_a_2 of state 2
Body volume V_g_a_2=V_a-V_l_a_2, according to tank b volume V_b and the lower tank b propellant volume V_l_b_2 meter of state 2
The lower tank b gas volume V_g_b_2=V_b-V_l_b_2 of calculation state 2；
(h) the lower tank a temperature T_a_2 of setting state 2 is equal to the lower tank a temperature T_a_1 of state 1, the lower tank b temperature of state 2
It spends T_b_2 and is equal to the lower tank b temperature T_b_1 of state 1, temperature is equal to being averaged for the lower tank a and tank b of state 2 after balance adjustment
Temperature T_bal=0.5* (T_a_2+T_b_2)；
(i) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank a pressure P_ of state 1
The lower tank a temperature T_a_1 of a_1, state 1 calculates the lower tank a Gas Compression Factor Z_g_a_1=1+a_Z_1*P_a_1* of state 1
T_a_1^a_Z_2；
(j) according to the lower tank a pressure P_a_1 of state 1, gas molar quality M, the lower tank a Gas Compression Factor Z_ of state 1
G_a_1, state 1 lower tank a temperature T_a_1, gas constant R calculate the lower tank a gas density ρ _ g_a_1=P_a_1* of state 1
M/(Z_g_a_1*T_a_1*R)；
(k) according to the lower tank a gas volume V_g_a_1 of state 1, the lower tank a gas density ρ _ g_a_1 of state 1, shape is calculated
The lower tank a gaseous mass m_g_a_1=V_g_a_1* ρ _ g_a_1 of state 1；
(l) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank b pressure P_ of state 1
The lower tank b temperature T_b_1 of b_1, state 1 calculates the lower tank b Gas Compression Factor Z_g_b_1=1+a_Z_1*P_b_1* of state 1
T_b_1^a_Z_2；
(m) according to the lower tank b pressure P_b_1 of state 1, gas molar quality M, the lower tank b Gas Compression Factor Z_ of state 1
G_b_1, state 1 lower tank b temperature T_b_1, gas constant R calculate the lower tank b gas density ρ _ g_b_1=P_b_1* of state 1
M/(Z_g_b_1*T_b_1*R)；
(n) according to the lower tank b gas volume V_g_b_1 of state 1, the lower tank b gas density ρ _ g_b_1 of state 1, shape is calculated
The lower tank b gaseous mass m_g_b_1=V_g_b_1* ρ _ g_b_1 of state 1.
Sub_part_bal_2 carries out tonifying Qi tank mark and calculates, and steps are as follows:
(a) according to of different sizes between the lower tank a pressure P_a_1 of state 1 and the lower tank b pressure P_b_1 of state 1, selection is not
Same operating procedure thens follow the steps (b-1) if P_a_1 > P_b_1；If P_a_1 < P_b_1, (b-2) is thened follow the steps；If P_
A_1=P_b_1 thens follow the steps (b-3)；
(b-1) set tank a gas volume change flag D_a as 1, tank b gas volume change flag D_b be -1；
(b-2) set tank a gas volume change flag D_a as -1, tank b gas volume change flag D_b be 1；
(b-3) tank a propellant mass m_a_2 under tank a propellant mass m_a_1_bal is state 2 when setting balance,
It turns to step (n)；
(c) volume cycle serial number initial value i=1 is set；
(d) according to the lower tank a gas volume V_g_a_1 of state 1, volume cycle serial number i, tank a gas volume variation mark
Will D_a, volume cycle step-length V_step calculate the new volume V_g_a_ceshi=V_g_a_1+i*D_a*V_ of tank a gas
step；
(e) tank a pressure P_a_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are -1,
Gas temperature T is the lower tank a temperature T_a_1 of state 1, and it is the lower tank a gaseous mass m_g_ of state 1 that gas, which restrains density p _ g_0,
The ratio of a_1 and the new volume V_g_a_ceshi of tank a gas；
(f) the pressure P_a_ceshi=P_ceshi calculated under the new volume of tank a is solved by gas pressure；
(g) according to the lower tank b gas volume V_g_b_1 of state 1, volume cycle serial number i, tank b gas volume variation mark
Will D_b, volume cycle step-length V_step calculate the new volume V_g_b_ceshi=V_g_b_1+i*D_b*V_ of tank b gas
step；
(h) tank b pressure P_b_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1, gas
Temperature T is the lower tank b temperature T_b_1 of state 1, and it is the lower tank b gaseous mass m_g_b_1 of state 1 that gas, which restrains density p _ g_0,
With the ratio of the new volume V_g_b_ceshi of tank b gas；
(i) the pressure P_b_ceshi=P_ceshi calculated under the new volume of tank b is solved by gas pressure；
(j) according to the pressure P_b_ceshi under the pressure P_a_ceshi and the new volume of tank b under the new volume of tank a, meter
Calculate pressure residual error δ _ P=| P_a_ceshi-P_b_ceshi |/P_a_ceshi；
(k) according to of different sizes between pressure residual error δ _ P and gas pressure residual error convergence δ _ P_min, selection difference
Operating procedure；If δ _ P >=δ _ P_min thens follow the steps (k-1)；If δ _ P < δ _ P_min thens follow the steps (k-2)；
(k-1) it enables volume cycle serial number k add 1, returns and execute step (d)；
(k-2) pressure P_bal is the pressure P_a_ceshi under the new volume of tank a when setting two casees pressure balances；
(l) gas volume V_g_a_bal is the new volume V_g_a_ceshi of tank a gas when setting tank a pressure balance；
(m) according to gas volume V_g_a_bal, propellant density p _ l when tank a volume V_a, tank a pressure balance, meter
Tank a propellant mass m_a_1_bal=(V_a-V_g_a_bal) * ρ _ l when calculating balance；
(n) according to tank a propellant mass m_a_1_bal when the lower tank a propellant mass m_a_2 of state 2 and balance it
Between it is of different sizes, select different operating procedures；If m_a_2 < m_a_1_bal, set balance adjustment tonifying Qi tank mark as
Numerical value 1；If m_a_2 > m_a_1_bal, balance adjustment tonifying Qi tank mark is set as numerical value 2；If m_a_2=m_a_1_bal,
Balance adjustment tonifying Qi tank mark is then set as numerical value 0.
Sub_part_bal_3 carries out the calculating of tank superfeed pressure, and steps are as follows:
(a) different according to balance adjustment tonifying Qi tank mark D_bal_buqi, different operating procedures is selected, if D_bal_
Buqi=1 thens follow the steps (b-1)；If D_bal_buqi=2, (b-2) is thened follow the steps；If D_bal_buqi=0 is held
Row step (b-3)；
(b-1) tank b pressure P_b_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1,
Gas temperature T is the lower tank b temperature T_b_2 of state 2, and it is the lower tank b gaseous mass m_g_ of state 1 that gas, which restrains density p _ g_0,
The quotient of b_1 and the lower tank b gas volume V_g_b_2 of state 2；
(c-1) tank b pressure P_b_2=P_ceshi after calculating adjusting is solved by gas pressure；
(d-1) the lower tank a gas pressure P_a_2 of writ state 2 is the lower tank b gas pressure P_b_2 of state 2, balance adjustment
Pressure P_bal is the lower tank b gas pressure P_b_2 of state 2 afterwards；
(e-1) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank a gas of state 2
The lower tank a temperature T_a_2 of pressure P_a_2, state 2, calculates tank a Gas Compression Factor Z_g_a_2=1+a_Z_1* after adjusting
P_a_2*T_a_2^a_Z_2；
(f-1) according to tank a Gas Compression Factor after the lower tank a pressure P_a_2 of state 2, gas molar quality M, adjusting
Z_g_a_2, state 2 lower tank a temperature T_a_2, gas constant R, calculate tank a gas density ρ _ g_a_2=P_a_ after adjusting
2*M/(Z_g_a_2*T_a_2*R)；
(g-1) it according to tank a gas density ρ _ g_a_2 after the lower tank a gas volume V_g_a_2 of state 2, adjusting, calculates
Tank a helium mass m_g_a_2=V_g_a_2* ρ _ g_a_2 after adjusting；
(h-1) tank a pressure P_a_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1,
Gas temperature is the lower tank a temperature T_a_1 of state 1, and it is tank a helium mass m_g_a_2 after adjusting that gas, which restrains density p _ g_0,
With the quotient of the lower tank a gas volume V_g_a_1 of state 1；
(i-1) tank a when tank a helium mass m_g_a_2 is compressed into state 1 after calculating adjusting is solved by gas pressure
Corresponding pressure when volume V_g_a_1, and it is assigned to balance adjustment superfeed pressure P_bal_buqi；It turns to step (j)；
(b-2) tank a pressure P_a_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1,
Gas temperature T is the lower tank a temperature T_a_2 of state 2, and it is the lower tank a gaseous mass m_g_ of state 1 that gas, which restrains density p _ g_0,
The quotient of a_1 and the lower tank a gas volume V_g_a_2 of state 2；
(c-2) tank a pressure P_a_2=P_ceshi after calculating adjusting is solved by gas pressure；
(d-2) the lower tank b gas pressure P_b_2 of writ state 2 is the lower tank a gas pressure P_a_2 of state 2, balance adjustment
Pressure P_bal is the lower tank a gas pressure P_a_2 of state 2 afterwards；
(e-2) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank b gas of state 2
The lower tank b temperature T_b_2 of pressure P_b_2, state 2, calculates tank b Gas Compression Factor Z_g_b_2=1+a_Z_1* after adjusting
P_b_2*T_b_2^a_Z_2；
(f-2) according to tank b Gas Compression Factor after the lower tank b pressure P_b_2 of state 2, gas molar quality M, adjusting
Z_g_b_2, state 2 lower tank b temperature T_b_2, gas constant R, calculate tank b gas density ρ _ g_b_2=P_b_ after adjusting
2*M/(Z_g_b_2*T_b_2*R)；
(g-2) it according to tank b gas density ρ _ g_b_2 after the lower tank b gas volume V_g_b_2 of state 2, adjusting, calculates
Tank b helium mass m_g_b_2=V_g_b_2* ρ _ g_b_2 after adjusting；
(h-2) tank b pressure P_b_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1,
Gas temperature T is the lower tank b temperature T_b_1 of state 1, and it is tank b helium mass m_g_b_ after adjusting that gas, which restrains density p _ g_0,
The quotient of 2 and the lower tank b gas volume V_g_b_1 of state 1；
(i-2) tank b when tank b helium mass m_g_b_2 is compressed into state 1 after calculating adjusting is solved by gas pressure
Corresponding pressure when volume V_g_b_1, and it is assigned to balance adjustment superfeed pressure P_bal_buqi；It turns to step (j)；
(b-3) enabling balance adjustment superfeed pressure P_bal_buqi is the lower tank a pressure P_a_1 of state 1, is pressed after balance adjustment
Power P_bal is the lower tank a pressure P_a_1 of state 1, is turned to step (j)；
(j) balance adjustment tonifying Qi tank mark D_bal_buqi, balance adjustment superfeed pressure P_bal_buqi, balance are exported
Temperature T_bal after pressure P_bal, balance adjustment after adjusting；
(k) terminate.
Further, " gas pressure solves stream to the sub-process that sub-process " balance discharge regulating calculation process " needs to call
Journey " comprises the steps of, as shown in Figure 4:
(a) pressures cycle serial number i is set as initial value 1.
(b) according to pressure change initial value P_0, pressures cycle serial number i, pressure change mark D_P, pressures cycle step-length P_
Step calculates the new pressure P_ceshi=P_0+i*D_P*P_step of gas.
(c) according to according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the new pressure P_ of gas
Cesh, gas temperature T calculate the new compressibility factor Z_ceshi=1+a_Z_1*P_ceshi*T^a_Z_2 of gas.
(d) according to the new pressure P_ceshi of gas, gas molar quality M, the new compressibility factor Z_ceshi of gas, gas temperature
T, gas constant R calculates the new density p _ g_ceshi=P_ceshi*M/ (Z_ceshi*T*R) of gas.
(e) according to the new density p _ g_ceshi of gas, gas restrain density p _ g_0, calculate gas density residual error δ _ ρ=| ρ _
g_ceshi-ρ_g_0|/ρ_g_0。
(f) according to of different sizes between gas density residual error δ _ ρ and gas density residual error convergence δ _ ρ _ min, selection is not
Same operating procedure.If δ _ ρ < δ _ ρ _ min, execute step (g_y)；If δ _ ρ >=δ _ ρ _ min, execute step (g_n).
(g_y) the new pressure P_ceshi of output gas.
(g_n) it enables pressures cycle serial number i add 1, turns to step (b).
(h) terminate.
The above method consider spacecraft parallel connection tank actual installation position can discrepant actual conditions, proposition and
Two tank residual propellant quality are independently of the matter before adjusting after adjusting in connection tank propulsion system balance discharge regulation flow process
Amount, the overall balance regulatory demand for adapting to " propellant mass × tank distance of shaft centers " may be implemented.Main flow and sub-process are
Full Parameterized, introduce iterative cycles, the calculations such as interpretation branch, be convenient for factorization, and then reduce and determine control
The time of parameter processed.
The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (10)
1. a kind of parallel connection tank propulsion system overall balance emissions adjustment method, which is characterized in that specific steps are as follows:
(1) state parameter setting before being adjusted:
(a) fluid properties are set, comprising: molal weight M, the gas constant R, gas for the gas that tank propulsion system in parallel uses
Compressibility factor coefficient a_Z_1, Gas Compression Factor index a_Z_2；Oxidant reference density ρ _ o_0, incendiary agent reference density ρ _
F_0, oxidant bulkfactor a_o, incendiary agent bulkfactor a_f；
(b) tank parameter is set, comprising: oxygen case a volume V_o_a, oxygen case b volume V_o_b, combustion case a volume V_f_a, combustion case b hold
Product V_f_b；
(c) solving precision parameter is set, comprising: pressures cycle step-length P_step, volume cycle step-length V_step, gas density are residual
Poor convergence δ _ ρ _ min, gas pressure residual error convergence δ _ P_min；
It (d) is state 1, the lower tank state parameter of setting state 1, including oxygen case a pressure P_o_a_ before definition balance emissions adjustment
1, oxygen case b pressure P_o_b_1, combustion case a pressure P_f_a_1, combustion case b pressure P_f_b_1, oxygen case a temperature T_o_a_1, oxygen case b temperature
T_o_b_1, combustion case a temperature T_f_a_1, combustion case b temperature T_f_b_1 are spent, oxygen case a propellant mass m_o_a_1, oxygen case b are promoted
Agent quality m_o_b_1, combustion case a propellant mass m_f_a_1, combustion case b propellant mass m_f_b_1；
(2) it carries out oxygen case and balances emissions adjustment:
(a) it is state 2 after definition balance emissions adjustment, sets oxygen case quality adjustment target, the i.e. lower oxygen case a propellant matter of state 2
Measure m_o_a_2, oxygen case b propellant mass m_o_b_2；
(b) numerical value of setting balance discharge regulating calculation required input parameter, including propellant type number is set as oxidant
Corresponding number 1 and progress tank Parameter Switch assignment, convert assignment for oxygen case a volume V_o_a, oxygen case b volume V_o_b respectively
To tank a volume V_a and tank b volume V_b, by the propellant mass m_o_a_1/m_o_b_ of state 1 lower oxygen case a and oxygen case b
1, temperature T_o_a_1/T_o_b_1, pressure P_o_a_1/P_o_b_1 convert the propellant for being assigned to tank a and tank b respectively
Quality m_a_1/m_b_1, temperature T_a_1/T_b_1, pressure P_a_1/P_b_1, by the propellant of state 2 lower oxygen case a and oxygen case b
Quality m_o_a_2/m_o_b_2 converts the propellant mass m_a_2/m_b_2 for being assigned to tank a and tank b respectively；
(c) according to balance discharge regulating calculation determination need to inflate tank mark D_bal_buqi, the blowing pressure P_bal_buqi,
The pressure P_bal and temperature T_bal of tank after balance；
(d) according to the difference for the tank mark D_bal_buqi that need to be inflated, different operating procedures is selected, if the tank that need to be inflated
Indicate that D_bal_buqi is directed toward oxygen case a, thens follow the steps (e-1)；If the tank mark D_bal_buqi that need to be inflated is directed toward oxygen case
B thens follow the steps (e-2)；If the tank mark D_bal_buqi that need to be inflated is directed toward other, step (f) is directly jumped to；
(e-1) the latching valve LV1 of the upstream oxygen case a is opened by oxygen case a tonifying Qi, up to pressure to the blowing pressure P_bal_buqi, later
The latching valve LV1 for closing the upstream oxygen case a, opens the latching valve LV5 and LV7 in oxygen case a and the downstream tank b, until in oxygen case a and oxygen case b
Propellant mass reaches oxygen case quality adjustment target m_o_a_2/m_o_b_2, completes to adjust；
(e-2) the latching valve LV3 of the upstream oxygen case b is opened by oxygen case b tonifying Qi, up to pressure to the blowing pressure P_bal_buqi, later
The latching valve LV3 for closing the upstream oxygen case b, opens the latching valve LV5 and LV7 in oxygen case a and the downstream tank b, until in oxygen case a and oxygen case b
Propellant mass reaches oxygen case quality adjustment target m_o_a_2/m_o_b_2, completes to adjust；
(f) pressure P_bal, oxygen box temperature degree T_g_o are temperature T_ after balance adjustment after setting oxygen case pressure P_o as balance adjustment
bal；
(3) combustion case balance emissions adjustment is carried out:
(a) the lower combustion case a propellant mass of setting combustion case quality adjustment target, i.e. state 2, combustion case b propellant mass m_f_a_2/
m_f_b_2；
(b) numerical value of setting balance discharge regulating calculation required input parameter, including propellant type number N_p is set as burning
Combustion case a volume V_f_a, combustion case b volume V_f_b are converted tax by the corresponding number 2 of agent and progress tank Parameter Switch assignment respectively
It is worth to tank a volume V_a and tank b volume V_b, by the propellant mass m_f_a_1/m_f_ of state 1 lower combustion case a and combustion case b
B_1, temperature T_f_a_1/T_f_b_1, pressure P_f_a_1/P_f_b_1 convert the propellant for being assigned to tank a and tank b respectively
Quality m_a_1/m_b_1, temperature T_a_1/T_b_1, pressure P_a_1/P_b_1, by the propellant of state 2 lower combustion case a and combustion case b
Quality m_f_a_2/m_f_b_2 converts the propellant mass m_a_2/m_b_2 for being assigned to tank a and tank b respectively；
(c) according to balance discharge regulating calculation determination need to inflate tank mark D_bal_buqi, the blowing pressure P_bal_buqi,
The pressure P_bal and temperature T_bal of tank after balance；
(d) according to the difference for the tank mark D_bal_buqi that need to be inflated, different operating procedures is selected, if the tank that need to be inflated
Indicate that D_bal_buqi is directed toward combustion case a, thens follow the steps (e-1)；If the tank mark D_bal_buqi that need to be inflated is directed toward combustion case
B thens follow the steps (e-2)；If the tank mark D_bal_buqi that need to be inflated is directed toward other, step (f) is directly jumped to；
(e-1) the latching valve LV2 for opening the combustion upstream case a will fire case a tonifying Qi, up to pressure to the blowing pressure P_bal_buqi, later
The latching valve LV2 for closing the combustion upstream case a opens combustion case a and fires the latching valve LV6 and LV8 in the downstream case b, until in combustion case a and combustion case b
Propellant mass reaches combustion case quality adjustment target m_f_a_2/m_f_b_2, completes to adjust；
(e-2) the latching valve LV4 for opening the combustion upstream case b will fire case b tonifying Qi, up to pressure to the blowing pressure P_bal_buqi, later
The latching valve LV4 for closing the combustion upstream case b opens the latching valve LV6 and LV8 of combustion case a and the downstream tank b, until in combustion case a and combustion case b
Propellant mass reaches combustion case quality adjustment target m_f_a_2/m_f_b_2, completes to adjust；
(f) pressure P_bal, combustion box temperature degree T_g_f are temperature T_ after balance adjustment after setting combustion case pressure P_f as balance adjustment
bal。
2. a kind of tank propulsion system overall balance emissions adjustment method in parallel as described in claim 1, which is characterized in that flat
It includes that process variable calculates, tonifying Qi tank mark calculates and tank superfeed pressure calculates that the emissions adjustment that weighs, which calculates,；
It includes determining propellant temperature, propellant density, propellant volume, tank gas volume and quality, storage that process variable, which calculates,
Case mean temperature, tank Gas Compression Factor；
It includes determining tank gas changeable volume and pressure, tank propellant mass that tonifying Qi tank mark, which calculates,.
3. a kind of tank propulsion system overall balance emissions adjustment method in parallel as claimed in claim 2, which is characterized in that into
Row process variable calculation method are as follows:
(a) according to the lower tank a temperature T_a_1 of state 1 and the lower tank b temperature T_b_1 of state 1, propellant temperature T_l=is calculated
0.5*(T_a_1+T_b_1)；
(b) according to the difference of propellant type number N_p, different operating procedures is selected, if propellant type number N_p is directed toward
Oxidant thens follow the steps (c-1)；If propellant type number N_p is directed toward incendiary agent, (c-2) is thened follow the steps；
(c-1) close according to oxidant reference density ρ _ o_0, propellant temperature T_l and oxidant bulkfactor a_o calculating propellant
Spend ρ _ l=ρ _ o_0+a_o*T_l；
(c-2) close according to incendiary agent reference density ρ _ f_0, propellant temperature T_l and incendiary agent bulkfactor a_f calculating propellant
Spend ρ _ l=ρ _ f_0+a_f*T_l；
(d) the lower tank a propellant body of state 1 is calculated according to the lower tank a propellant mass m_a_1 and propellant density p _ l of state 1
Product V_l_a_1=m_a_1/ ρ _ l calculates state 1 according to the lower tank b propellant mass m_b_1 and propellant density p _ l of state 1
Lower tank b propellant volume V_l_b_1=m_b_1/ ρ _ l；
(e) the lower tank a gas volume V_g_a_ of state 1 is calculated according to tank a volume V_a and tank a propellant volume V_l_a_1
1=V_a-V_l_a_1 calculates the lower tank b gas body of state 1 according to tank b volume V_b and tank b propellant volume V_l_b_1
Product V_g_b_1=V_b-V_l_b_1；
(f) the lower tank a propellant body of state 2 is calculated according to the lower tank a propellant mass m_a_2 and propellant density p _ l of state 2
Product V_l_a_2=m_a_2/ ρ _ l calculates state 2 according to the lower tank b propellant mass m_b_2 and propellant density p _ l of state 2
Lower tank b propellant volume V_l_b_2=m_b_2/ ρ _ l；
(g) the lower tank a gas body of state 2 is calculated according to tank a volume V_a and the lower tank a propellant volume V_l_a_2 of state 2
Product V_g_a_2=V_a-V_l_a_2 calculates shape according to tank b volume V_b and the lower tank b propellant volume V_l_b_2 of state 2
The lower tank b gas volume V_g_b_2=V_b-V_l_b_2 of state 2；
(h) the lower tank a temperature T_a_2 of setting state 2 is equal to the lower tank a temperature T_a_1 of state 1, the lower tank b temperature T_ of state 2
B_2 is equal to the lower tank b temperature T_b_1 of state 1, and temperature is equal to the mean temperature of state 2 lower tank a and tank b after balance adjustment
T_bal=0.5* (T_a_2+T_b_2)；
(i) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank a pressure P_a_1 of state 1,
The lower tank a temperature T_a_1 of state 1 calculates the lower tank a Gas Compression Factor Z_g_a_1=1+a_Z_1*P_a_1*T_a_ of state 1
1^a_Z_2；
(j) according to the lower tank a pressure P_a_1 of state 1, gas molar quality M, the lower tank a Gas Compression Factor Z_g_a_ of state 1
1, state 1 lower tank a temperature T_a_1, gas constant R calculates the lower tank a gas density ρ _ g_a_1=P_a_1*M/ of state 1
(Z_g_a_1*T_a_1*R)；
(k) according to the lower tank a gas volume V_g_a_1 of state 1, the lower tank a gas density ρ _ g_a_1 of state 1, state 1 is calculated
Lower tank a gaseous mass m_g_a_1=V_g_a_1* ρ _ g_a_1；
(l) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank b pressure P_b_1 of state 1,
The lower tank b temperature T_b_1 of state 1 calculates the lower tank b Gas Compression Factor Z_g_b_1=1+a_Z_1*P_b_1*T_b_ of state 1
1^a_Z_2；
(m) according to the lower tank b pressure P_b_1 of state 1, gas molar quality M, the lower tank b Gas Compression Factor Z_g_b_ of state 1
1, state 1 lower tank b temperature T_b_1, gas constant R calculates the lower tank b gas density ρ _ g_b_1=P_b_1*M/ of state 1
(Z_g_b_1*T_b_1*R)；
(n) according to the lower tank b gas volume V_g_b_1 of state 1, the lower tank b gas density ρ _ g_b_1 of state 1, state 1 is calculated
Lower tank b gaseous mass m_g_b_1=V_g_b_1* ρ _ g_b_1.
4. a kind of tank propulsion system overall balance emissions adjustment method in parallel as claimed in claim 2, which is characterized in that mend
Gas-reservoir case mark calculation method are as follows:
(a) it according to of different sizes between the lower tank a pressure P_a_1 of state 1 and the lower tank b pressure P_b_1 of state 1, selects different
Operating procedure thens follow the steps (b-1) if P_a_1 > P_b_1；If P_a_1 < P_b_1, (b-2) is thened follow the steps；If P_a_1
=P_b_1 thens follow the steps (b-3)；
(b-1) set tank a gas volume change flag D_a as 1, tank b gas volume change flag D_b be -1；
(b-2) set tank a gas volume change flag D_a as -1, tank b gas volume change flag D_b be 1；
(b-3) tank a propellant mass m_a_1_bal is turned to as the lower tank a propellant mass m_a_2 of state 2 when setting balance
Step (n)；
(c) volume cycle serial number initial value i=1 is set；
(d) according to state 1 lower tank a gas volume V_g_a_1, volume cycle serial number i, tank a gas volume change flag D_
A, volume cycle step-length V_step calculates the new volume V_g_a_ceshi=V_g_a_1+i*D_a*V_step of tank a gas；
(e) tank a pressure P_a_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are -1, gas
Temperature T is the lower tank a temperature T_a_1 of state 1, gas restrain density p _ g_0 be the lower tank a gaseous mass m_g_a_1 of state 1 with
The ratio of the new volume V_g_a_ceshi of tank a gas；
(f) the pressure P_a_ceshi=P_ceshi calculated under the new volume of tank a is solved by gas pressure；
(g) according to state 1 lower tank b gas volume V_g_b_1, volume cycle serial number i, tank b gas volume change flag D_
B, volume cycle step-length V_step calculates the new volume V_g_b_ceshi=V_g_b_1+i*D_b*V_step of tank b gas；
(h) tank b pressure P_b_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1, gas temperature
Spending T is the lower tank b temperature T_b_1 of state 1, and it is the lower tank b gaseous mass m_g_b_1 of state 1 and storage that gas, which restrains density p _ g_0,
The ratio of the new volume V_g_b_ceshi of case b gas；
(i) the pressure P_b_ceshi=P_ceshi calculated under the new volume of tank b is solved by gas pressure；
(j) according to the pressure P_b_ceshi under the pressure P_a_ceshi and the new volume of tank b under the new volume of tank a, pressure is calculated
Power residual error δ _ P=| P_a_ceshi-P_b_ceshi |/P_a_ceshi；
(k) according to of different sizes between pressure residual error δ _ P and gas pressure residual error convergence δ _ P_min, different behaviour is selected
Make step；If δ _ P >=δ _ P_min thens follow the steps (k-1)；If δ _ P < δ _ P_min thens follow the steps (k-2)；
(k-1) it enables volume cycle serial number k add 1, returns and execute step (d)；
(k-2) pressure P_bal is the pressure P_a_ceshi under the new volume of tank a when setting two casees pressure balances；
(l) gas volume V_g_a_bal is the new volume V_g_a_ceshi of tank a gas when setting tank a pressure balance；
(m) it according to gas volume V_g_a_bal, propellant density p _ l when tank a volume V_a, tank a pressure balance, calculates flat
Tank a propellant mass m_a_1_bal=(V_a-V_g_a_bal) * ρ _ l when weighing apparatus；
(n) big between tank a propellant mass m_a_1_bal according to the lower tank a propellant mass m_a_2 of state 2 and when balancing
Small difference selects different operating procedures；If m_a_2 < m_a_1_bal, balance adjustment tonifying Qi tank mark is set as numerical value
1；If m_a_2 > m_a_1_bal, balance adjustment tonifying Qi tank mark is set as numerical value 2；If m_a_2=m_a_1_bal is set
Determining balance adjustment tonifying Qi tank mark is numerical value 0.
5. a kind of tank propulsion system overall balance emissions adjustment method in parallel as claimed in claim 2, which is characterized in that storage
Case superfeed pressure calculation method are as follows:
(a) different according to balance adjustment tonifying Qi tank mark D_bal_buqi, different operating procedures is selected, if D_bal_buqi
=1, then follow the steps (b-1)；If D_bal_buqi=2, (b-2) is thened follow the steps；If D_bal_buqi=0 executes step
Suddenly (b-3)；
(b-1) tank b pressure P_b_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1, gas
Temperature T is the lower tank b temperature T_b_2 of state 2, gas restrain density p _ g_0 be the lower tank b gaseous mass m_g_b_1 of state 1 with
The quotient of the lower tank b gas volume V_g_b_2 of state 2；
(c-1) tank b pressure P_b_2=P_ceshi after calculating adjusting is solved by gas pressure；
(d-1) the lower tank a gas pressure P_a_2 of writ state 2 is the lower tank b gas pressure P_b_2 of state 2, is pressed after balance adjustment
Power P_bal is the lower tank b gas pressure P_b_2 of state 2；
(e-1) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank a gas pressure of state 2
The lower tank a temperature T_a_2 of P_a_2, state 2, calculates tank a Gas Compression Factor Z_g_a_2=1+a_Z_1*P_a_ after adjusting
2*T_a_2^a_Z_2；
(f-1) according to tank a Gas Compression Factor Z_g_ after the lower tank a pressure P_a_2 of state 2, gas molar quality M, adjusting
A_2, state 2 lower tank a temperature T_a_2, gas constant R, calculate tank a gas density ρ _ g_a_2=P_a_2*M/ after adjusting
(Z_g_a_2*T_a_2*R)；
(g-1) it according to tank a gas density ρ _ g_a_2 after the lower tank a gas volume V_g_a_2 of state 2, adjusting, calculates and adjusts
Tank a helium mass m_g_a_2=V_g_a_2* ρ _ g_a_2 afterwards；
(h-1) tank a pressure P_a_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1, gas
Temperature is the lower tank a temperature T_a_1 of state 1, and it is tank a helium mass m_g_a_2 and shape after adjusting that gas, which restrains density p _ g_0,
The quotient of the lower tank a gas volume V_g_a_1 of state 1；
(i-1) tank a volume when tank a helium mass m_g_a_2 is compressed into state 1 after calculating adjusting is solved by gas pressure
Corresponding pressure when V_g_a_1, and it is assigned to balance adjustment superfeed pressure P_bal_buqi；It turns to step (j)；
(b-2) tank a pressure P_a_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1, gas
Temperature T is the lower tank a temperature T_a_2 of state 2, gas restrain density p _ g_0 be the lower tank a gaseous mass m_g_a_1 of state 1 with
The quotient of the lower tank a gas volume V_g_a_2 of state 2；
(c-2) tank a pressure P_a_2=P_ceshi after calculating adjusting is solved by gas pressure；
(d-2) the lower tank b gas pressure P_b_2 of writ state 2 is the lower tank a gas pressure P_a_2 of state 2, is pressed after balance adjustment
Power P_bal is the lower tank a gas pressure P_a_2 of state 2；
(e-2) according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the lower tank b gas pressure of state 2
The lower tank b temperature T_b_2 of P_b_2, state 2, calculates tank b Gas Compression Factor Z_g_b_2=1+a_Z_1*P_b_ after adjusting
2*T_b_2^a_Z_2；
(f-2) according to tank b Gas Compression Factor Z_g_ after the lower tank b pressure P_b_2 of state 2, gas molar quality M, adjusting
B_2, state 2 lower tank b temperature T_b_2, gas constant R, calculate tank b gas density ρ _ g_b_2=P_b_2*M/ after adjusting
(Z_g_b_2*T_b_2*R)；
(g-2) it according to tank b gas density ρ _ g_b_2 after the lower tank b gas volume V_g_b_2 of state 2, adjusting, calculates and adjusts
Tank b helium mass m_g_b_2=V_g_b_2* ρ _ g_b_2 afterwards；
(h-2) tank b pressure P_b_1 under setting pressure change initial value P_0 as state 1, pressure change mark D_P are 1, gas
Temperature T is the lower tank b temperature T_b_1 of state 1, gas restrain density p _ g_0 be after adjusting tank b helium mass m_g_b_2 with
The quotient of the lower tank b gas volume V_g_b_1 of state 1；
(i-2) tank b volume when tank b helium mass m_g_b_2 is compressed into state 1 after calculating adjusting is solved by gas pressure
Corresponding pressure when V_g_b_1, and it is assigned to balance adjustment superfeed pressure P_bal_buqi；It turns to step (j)；
(b-3) enabling balance adjustment superfeed pressure P_bal_buqi is the lower tank a pressure P_a_1 of state 1, pressure P_ after balance adjustment
Bal is the lower tank a pressure P_a_1 of state 1, is turned to step (j)；
(j) balance adjustment tonifying Qi tank mark D_bal_buqi, balance adjustment superfeed pressure P_bal_buqi, balance adjustment are exported
Temperature T_bal after pressure P_bal, balance adjustment afterwards；
(k) terminate.
6. a kind of tank propulsion system overall balance emissions adjustment method in parallel, feature exist as described in claim 4 or 5
In gas pressure method for solving comprises the steps of:
(a) pressures cycle serial number i is set as initial value 1；
(b) according to pressure change initial value P_0, pressures cycle serial number i, pressure change mark D_P, pressures cycle step-length P_
Step calculates the new pressure P_ceshi=P_0+i*D_P*P_step of gas；
(c) according to according to Gas Compression Factor coefficient a_Z_1, Gas Compression Factor index a_Z_2, the new pressure P_cesh of gas,
Gas temperature T calculates the new compressibility factor Z_ceshi=1+a_Z_1*P_ceshi*T^a_Z_2 of gas；
(d) according to the new pressure P_ceshi of gas, gas molar quality M, the new compressibility factor Z_ceshi of gas, gas temperature T, gas
Body constant R calculates the new density p _ g_ceshi=P_ceshi*M/ (Z_ceshi*T*R) of gas；
(e) according to the new density p _ g_ceshi of gas, gas restrain density p _ g_0, calculate gas density residual error δ _ ρ=| ρ _ g_
ceshi-ρ_g_0|/ρ_g_0；
(f) it according to of different sizes between gas density residual error δ _ ρ and gas density residual error convergence δ _ ρ _ min, selects different
Operating procedure；If δ _ ρ < δ _ ρ _ min, execute step (g_y)；If δ _ ρ >=δ _ ρ _ min, execute step (g_n)；
(g_y) the new pressure P_ceshi of output gas；
(g_n) it enables pressures cycle serial number i add 1, turns to step (b)；
(h) terminate.
7. a kind of tank propulsion system overall balance emissions adjustment method in parallel as described in claim 1, which is characterized in that simultaneously
Joining tank propulsion system includes 4 tanks, wherein 2 oxygen casees and 2 combustion casees, respectively oxygen case a MON-a, oxygen case b MON-b,
Fire case a MMH-a, combustion case b MMH-b；Discharge oxidant in parallel, i.e. oxygen case a MON-a and oxygen case b MON-b between 2 oxygen casees
Tank downstream latching valve LV5 is respectively set together with connection after LV7 in propellant outlet in downstream, and leads to the oxygen of engine Eng
Agent entrance, to provide oxidant to engine Eng.
8. a kind of tank propulsion system overall balance emissions adjustment method in parallel as claimed in claim 7, which is characterized in that oxygen
Tank upstream latching valve LV1 is respectively set together with connection after LV3 with oxygen case b MON-b upstream gas entrance in case a MON-a.
9. a kind of tank propulsion system overall balance emissions adjustment method in parallel as claimed in claim 8, which is characterized in that 2
Platform fires discharge incendiary agent in parallel between case, i.e. tank is respectively set in combustion case a MMH-a and the outlet of combustion case b MMH-b downstream propellant
Downstream latching valve LV6 leads to the incendiary agent entrance of engine Eng together with connection after LV8, to provide to engine Eng
Incendiary agent；Combustion case a MMH-a and combustion case b MMH-b upstream gas entrance join after tank upstream latching valve LV2 and LV4 is respectively set
Lead to together；It can control high-pressure gas circuit module with every latching valve of independent switch tank upstream and be inflated to any one tank；
It can control any one tank with every latching valve in independent switch tank downstream and propellant is discharged.
10. a kind of tank propulsion system overall balance emissions adjustment method in parallel as claimed in claim 9, which is characterized in that 4
A pressure sensor PT1~PT4 is respectively arranged in platform tank upstream gas inlet, for monitoring the pressure in tank.
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