CN104675562B - Can store pump pressure type upper stage rocket engine heat control method - Google Patents
Can store pump pressure type upper stage rocket engine heat control method Download PDFInfo
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- CN104675562B CN104675562B CN201410783781.6A CN201410783781A CN104675562B CN 104675562 B CN104675562 B CN 104675562B CN 201410783781 A CN201410783781 A CN 201410783781A CN 104675562 B CN104675562 B CN 104675562B
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Abstract
The invention belongs to Aeronautics and Astronautics technical field, be specifically related to one and can store pump pressure type upper stage rocket engine heat control method. The method comprising the steps of is: 1) determine temperature control target; 2) divide operating mode; 3) define the engine thermal Mathematical Modeling of thermal control measure; 4) formulate preliminary thermal control scheme; 5) verify preliminary thermal control scheme, obtain the test indication variations in temperature of the engine of taking preliminary thermal control scheme under each operating mode; 6) determining of final thermal control scheme. Effectively solve and can store pump pressure type upper stage rocket engine thermal control problem by method of the present invention.
Description
Technical field
The invention belongs to Aeronautics and Astronautics technical field, be specifically related to one and can store on pump pressure typeFace stage motor heat control method.
Background technology
Certain pump pressure type double elements can be stored engine and provide active force for carrier rocket Upper Stage, fortuneCarry rocket Upper Stage and require twice starting of engine, for a long time in-orbit. Engine operation on orbit andDuring sliding, face uniqueness, changeable spatial heat environment condition, again because complex structure,In igniting, produce the feature of high-temperature fuel gas, endogenous pyrogen and heat transfer path complexity. If engine is notTake thermal control measure, thermal environment and temperature are controlled, structure temperature exceeds the meeting of temperature control targetAffect engine start, work and shutdown performance.
Because the pump pressure type the stored upper stage rocket engine that meets twice starting still belongs at homeDevelopment first, lacks corresponding method for designing for engine thermal control design. With at present domesticRipe squash type engine thermal control design is compared, owing to can storing pump pressure type upper stage rocket engineTemperature control scope narrower, structure is more complicated, there is turbine pump " heat is counter soaks " in worst hot caseEtc. problem, cause being difficult to checking in the time of ground experiment, existing thermal control means are difficult to ensure againThe starting transient problem of starting.
Summary of the invention
In order to solve the problem in background technology, the present invention proposes a kind of applicable to pump pressure typeCan store the heat control method of upper stage rocket engine.
Concrete technical scheme of the present invention is:
One can be stored pump pressure type upper stage rocket engine heat control method, under it is characterized in that comprisingRow step:
1) determine temperature control target; The each assembly of described temperature control object representation engine meets engineThe temperature range of twice starting and ignition operation;
2) divide operating mode according to engine operation on orbit; Described operating mode comprises high temperature coast periodOperating mode, coast period worst cold case, worst hot case between burn period;
3) define the hot Mathematical Modeling of thermal control measure:
3.1) set up respectively the hot Mathematical Modeling without thermal control measure for each operating mode;
3.2) according to step 3.1) the hot Mathematical Modeling without thermal control measure, indication engineVariations in temperature under each operating mode;
3.3), according to variations in temperature under each operating mode of engine, define the heat of thermal control measureMathematical Modeling;
4) formulate preliminary thermal control scheme:
4.1) according to step 3.3) the hot Mathematical Modeling that has thermal control measure, indication engineVariations in temperature under each operating mode;
4.2) variations in temperature under each operating mode and the comparison of temperature control target by engine, if warmDegree variation meets temperature control target, according to the hot Mathematical Modeling that has thermal control measure, formulates preliminary thermal controlScheme;
If variations in temperature does not meet temperature control target, amendment has the hot Mathematical Modeling of thermal control measure, straightMeet temperature control target to variations in temperature, according to the amended hot Mathematical Modeling that has thermal control measure,Formulate preliminary thermal control scheme;
5) by step 4) in preliminary definite thermal control scheme on engine, implement, logical respectivelyCross Vacuum Heat blance test checking engine worst cold case coast period, high mould test run checking is startedWorst hot case between machine burn period, high mould test run " heat is counter soaks " verification experimental verification high temperature coast period workCondition, obtains the pre-temp. displaying function of the test of engine under each operating mode;
6) comparison step 5) in the engine that the obtains pre-temp. displaying function of test under each operating modeWhether consistent with temperature control target; If consistent, determining step 4) scheme formulated is finalThermal control scheme; If inconsistent, revise thermal control measure, amendment has the hot mathematical modulo of thermal control measureType and repeating step 4) and step 5).
Above-mentioned thermal control scheme comprises that multilayer insulation assembly is coated, initiatively electrical heating, thermal control coating withAnd engine start discharge; Described engine start discharge has solved turbine pump " heat is counter soaks " and has ledThe propellant of the starting again filling transient state two phase flow problem causing.
The invention has the advantages that:
1, the proposition of the inventive method, has determined that one can meet pump pressure type and can store Upper StageThe heat control method of engine temperature control target.
2, the thermal environment difference that the inventive method faces for engine, divides operating mode,Make the thermal control scheme that meets each operating mode, control meticulousr.
3, the inventive method adopts the mode of engine start discharge, has solved turbine pump " heatCounter soaking " propellant of the starting again filling transient state two phase flow problem brought.
Brief description of the drawings
Fig. 1 is the flow chart element that the present invention can store pump pressure type upper stage rocket engine heat control methodFigure.
Detailed description of the invention
The operation on orbit X second for certain Upper Stage, engine being proposed below, meet and once riseThe mission requirements of moving, two kinds of mode of operations of reignition, twice starting interval Y second, some firerDo Z second, the workflow of 1 pair of this method is described by reference to the accompanying drawings:
The concrete steps of the method are:
Step 1) determine temperature control target; The each assembly of described temperature control object representation engine meets to be sent outThe temperature range of twice starting of motivation and ignition operation; Specifically: thrust chamber to engine,The thermal adaptability of gas generator, turbine pump, gas cylinder, valve, explosive actuator dividesAnalyse, again engine start process is carried out to thermal adaptability analysis, analyze and meet normal startingEngine structure high temperature limit, low temperature limit.
The temperature of concrete each assembly is: thrust chamber (head and regeneration cooling section): >=0 DEG C; CombustionGas generator (head and body portion): >=0 DEG C;
Oxidant valve: 0 DEG C～55 DEG C; Fuel valve :-5 DEG C～60 DEG C
Oxidant pipeline: >=0 DEG C; Fuel conduit: >=-5 DEG C;
Valve positioner :-40 DEG C～60 DEG C.
Step 2) divide operating mode according to engine operation on orbit; Described operating mode comprises coast periodWorst hot case, coast period worst cold case, worst hot case between burn period;
Being described as follows of each operating mode: before coast period, worst cold case was mean engine one push startCoast period, under the severe heat-flux conditions of low temperature, the situation of internal/external heating, heat radiation.
Coast period, worst hot case was coast period after mean engine once shuts down, high temperature harsh thermalUnder stream condition, the situation of internal/external heating, heat radiation.
Between burn period, worst hot case is between twice burn period of mean engine, the severe heat-flux conditions of high temperatureUnder, the situation of internal/external heating, heat radiation.
Step 3) define the hot Mathematical Modeling of thermal control measure:
Step 3.1) set up respectively the hot Mathematical Modeling without thermal control measure for each operating mode;
Step 3.2) according to step 3.1) the hot Mathematical Modeling without thermal control measure, indication send outMotivation is variations in temperature under each operating mode;
Step 3.3) according to variations in temperature under each operating mode of engine, define thermal control measureHot Mathematical Modeling;
Wherein, thermal control measure is to take in temperature control target zone for guarantee engine operationMeans, comprising: the passive thermal control measures such as multilayer insulation assembly is coated, thermal control coating, electrical heatingThe Active thermal control measures such as control and engine start discharge;
Step 4) formulate preliminary thermal control scheme:
Step 4.1) according to step 3.3) have a thermal control measure Mathematical Modeling, indication engineVariations in temperature under each operating mode;
Step 4.2) variations in temperature and the comparison of temperature control target by engine under each operating mode,If variations in temperature meets temperature control target, according to the Mathematical Modeling that has thermal control measure, formulate preliminary heatProsecutor case; For example: coated if thermal control measure is multilayer insulation assembly, the preliminary thermal control of formulatingScheme is exactly that multilayer insulation assembly is coated; When coated, need to consider clad material, coating thicknessEtc. factor;
If variations in temperature does not meet temperature control target, amendment has the Mathematical Modeling of thermal control measure, untilVariations in temperature meets temperature control target, according to the amended Mathematical Modeling that has thermal control measure, formulatesPreliminary thermal control scheme; Step 5) by step 4) in preliminary definite thermal control scheme at engineUpper enforcement, respectively by Vacuum Heat blance test checking engine worst cold case coast period, heightWorst hot case during mould test run checking engine ignition, high mould test run " heat is counter soaks " verification experimental verificationCoast period, worst hot case, obtained the pre-temp. displaying function of the test of engine under each operating mode;
Step 6) comparison step 5) in the engine that the obtains pre-temperature indicating of test under each operating modeSpend whether consistent with temperature control target; If consistent, determine that it is final thermal control scheme; If noUnanimously, repeat to revise thermal control measure, amendment has hot Mathematical Modeling and the step of thermal control measure4) and step 5).
Specifically it should be noted that: in literary composition, said thermal control scheme comprises multilayer insulation assembly bagCover, initiatively electrical heating, thermal control coating and engine start discharge; Engine start discharge is separatedThe propellant of the starting again filling transient state two phase flow problem that turbine pump " heat is counter soaks " causes of having determined.
Claims (2)
1. can store a pump pressure type upper stage rocket engine heat control method, it is characterized in that bagDraw together the following step:
1) determine temperature control target; The each assembly of described temperature control object representation engine meets engineThe temperature range of twice starting and ignition operation;
2) divide operating mode according to engine operation on orbit; Described operating mode comprises high temperature coast periodOperating mode, coast period worst cold case, worst hot case between burn period;
3) define the hot Mathematical Modeling of thermal control measure:
3.1) set up respectively the hot Mathematical Modeling without thermal control measure for each operating mode;
3.2) according to step 3.1) the hot Mathematical Modeling without thermal control measure, indication engineVariations in temperature under each operating mode;
3.3), according to variations in temperature under each operating mode of engine, define the heat of thermal control measureMathematical Modeling;
4) formulate preliminary thermal control scheme:
4.1) according to step 3.3) have a hot Mathematical Modeling of thermal control measure, indication engine existsVariations in temperature under each operating mode;
4.2) variations in temperature under each operating mode and the comparison of temperature control target by engine, if warmDegree variation meets temperature control target, according to the hot Mathematical Modeling that has thermal control measure, formulates preliminary thermal controlScheme;
If variations in temperature does not meet temperature control target, revise in the hot Mathematical Modeling that has thermal control measureThermal control measure, until variations in temperature meets temperature control target, has a thermal control measure according to amendedHot Mathematical Modeling, formulates preliminary thermal control scheme;
5) by step 4) in preliminary definite thermal control scheme on engine, implement, logical respectivelyCross Vacuum Heat blance test checking engine worst cold case coast period, high mould test run checking is startedWorst hot case between machine burn period, high mould test run " heat is counter soaks " verification experimental verification coasting-flight phase worst hot case,Obtain the test indication variations in temperature of engine under each operating mode;
6) comparison step 5) in the engine that the obtains pre-temp. displaying function of test under each operating modeWhether consistent with temperature control target; If consistent, determining step 4) scheme formulated is finalThermal control scheme; If inconsistent, revise thermal control measure, amendment has the hot mathematical modulo of thermal control measureType and repeating step 4) and step 5).
2. the pump pressure type upper stage rocket engine thermal control side that stores according to claim 1Method, is characterized in that: described thermal control scheme comprises that multilayer insulation assembly is coated, initiatively electrical heating,Thermal control coating and engine start discharge; Described engine start discharge has solved turbine pumpThe propellant of the starting again filling transient state two phase flow problem that " heat is counter soaks " causes.
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Citations (2)
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|---|---|---|---|---|
| EP1826390A1 (en) * | 2006-01-31 | 2007-08-29 | United Technologies Corporation | Multipurpose gas generator ramjet/scramjet cold start system |
| RU2012104071A (en) * | 2012-02-06 | 2013-08-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | SYSTEM OF THERMOSTATING EQUIPMENT OF SPACE OBJECT |
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| US7984606B2 (en) * | 2008-11-03 | 2011-07-26 | Propulsion, Gas Turbine, And Energy Evaluations, Llc | Systems and methods for thermal management in a gas turbine powerplant |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1826390A1 (en) * | 2006-01-31 | 2007-08-29 | United Technologies Corporation | Multipurpose gas generator ramjet/scramjet cold start system |
| RU2012104071A (en) * | 2012-02-06 | 2013-08-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | SYSTEM OF THERMOSTATING EQUIPMENT OF SPACE OBJECT |
Non-Patent Citations (2)
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| 可贮存推进剂泵压式液体火箭发动机多次起动***研究;张涛等;《火箭推进》;20100630;第36卷(第3期);全文 * |
| 液体火箭上面级发动机***方案选择及典型***方案;张金容等;《导弹与航天运载技术》;20080430(第2期);全文 * |
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