CN108454887A - A kind of the bipropellant propulsion device and control method of balance discharge - Google Patents
A kind of the bipropellant propulsion device and control method of balance discharge Download PDFInfo
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- CN108454887A CN108454887A CN201810117071.8A CN201810117071A CN108454887A CN 108454887 A CN108454887 A CN 108454887A CN 201810117071 A CN201810117071 A CN 201810117071A CN 108454887 A CN108454887 A CN 108454887A
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 239000003380 propellant Substances 0.000 claims description 15
- 238000005259 measurement Methods 0.000 claims description 6
- 239000007789 gas Substances 0.000 description 26
- 239000003795 chemical substances by application Substances 0.000 description 5
- 230000003287 optical effect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 241001310793 Podium Species 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
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- 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
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- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
A kind of the bipropellant propulsion device and control method of balance discharge, are related to optics earth observation satellite technical field；Including the first tank, the second tank, the first latching valve, the second latching valve, third latching valve, the gentle road latching valve of the 4th latching valve；The lower end of gas circuit latching valve is connected to the vertical top of inverted T fonts pipeline；The horizontal both ends of T font pipelines are connected to the first latching valve, third latching valve respectively；First latching valve is connected to by pipeline with the first tank top；Third latching valve is connected to by pipeline with the second tank top；First tank bottom end passes through pipeline and the second latching valve unicom；Second tank bottom end is connected to by pipeline with the 4th latching valve；The horizontal both ends of T font pipelines are connected to the second latching valve, the 4th latching valve respectively；The vertical bottom end of T font pipelines is connected to external thrust device；Project Realization of the present invention is simple, reliability is high, and has had been subjected to in-orbit examination, is applicable to subsequently using the high rail remote sensing satellite of tank in parallel.
Description
Technical field
The present invention relates to a kind of optics earth observation satellite technical field, especially a kind of bipropellant propulsion of balance discharge
Device and control method.
Background technology
Geostationary orbit (GEO) Optical remote satellite is that one of future optical earth observation satellite technology development is important
Field.To realize that high-resolution earth observation, satellite will use the optics payload of heavy caliber, long-focus in stationary orbit,
Bulky dimensions.Due to receiving the limitation of carrier rocket transmission envelop size, when satellite system design, it has to shorten podium level
The bearing space of bigger is provided for payload.
No. four satellites of high score are the static rail optical remote sensing satellite of first of China high-resolution, high to shorten satellite platform
The two big tank placed up and down in DFH-4 platform loaded cylinders is revised as place side by side one big two small tank, big tank by degree
Built-in oxygen carrier agent, two small tanks are interior to load incendiary agent.When satellite operation on orbit, incendiary agent need to be discharged in two small tanks simultaneously
And mixed in equal volume with oxidant, it burns in thruster or engine, required torque is provided for attitude of satellite adjustment.But such as
Propellant space emission is uneven in fruit tank, it will leads to the whole star centroid motion of satellite, orbit maneuver motor will when point is lighted a fire in distant
Extra interference torque is generated, if centroid offset is smaller, the disturbance torque of generation is less than adjustment posture torque, then becomes rail efficiency
Lowly, it needs additionally to expend some propellants more；If centroid offset is larger, the disturbance torque of generation is more than adjustment posture power
Square, it will lead to that satellite gravity anomaly is not restrained or posture is out of control, apogee can not be completed and become rail, reach planned orbit, defend
Star launch mission fails.Therefore, the balance discharge in parallel for how realizing the propellant in two small tanks, before becoming satellite launch
The critical issue for needing emphasis to solve.
No. four satellites of high score are high rail satellite of first of the China using discharge tank in parallel, at present both at home and abroad without open letter
Breath, which is introduced, ensures that tank propellant in parallel balances discharge method.Meanwhile as the geostationary orbit of follow-up higher resolution is detectd
The development of surveillance satellite, high rail wide area imaging surveillance satellite is examined, the application of tank in parallel will become inexorable trend, it would therefore be highly desirable to
There is provided that a kind of reliability is high, Project Realization tank propellant balance discharge method simply in parallel.
Invention content
It is an object of the invention to overcome the above-mentioned deficiency of the prior art, a kind of bipropellant propulsion dress of balance discharge is provided
It sets and control method, Project Realization is simple, reliability is high, and has had been subjected to in-orbit examination, is applicable to subsequently using storage in parallel
The high rail remote sensing satellite of case.
The above-mentioned purpose of the present invention is achieved by following technical solution：
A kind of bipropellant propulsion device of balance discharge, including the first tank, the second tank, the first latching valve, second are certainly
Locking-valve, third latching valve, the gentle road latching valve of the 4th latching valve；Wherein, the external gas cylinder of upper end connection of gas circuit latching valve；Gas circuit
The lower end of latching valve is connected to the vertical top of inverted T fonts pipeline；The horizontal left end of T font pipelines and the first latching valve connect
It is logical；The horizontal right end of T font pipelines is connected to third latching valve；First latching valve is connected to by pipeline with the first tank top；The
Three latching valves are connected to by pipeline with the second tank top；First tank bottom end passes through pipeline and the second latching valve unicom；Second
Tank bottom end is connected to by pipeline with the 4th latching valve；Second latching valve is connected to the horizontal left end of T font pipelines；4th self-locking
Valve is connected to the horizontal right end of T font pipelines；The vertical bottom end of T font pipelines is connected to external thrust device.
In the bipropellant propulsion device that a kind of above-mentioned balance is discharged, the propulsion device further includes first pressure sensor
With second pressure sensor；Wherein, first pressure sensor is fixedly mounted on the first tank, is realized to being pressed inside the first tank
The measurement of power；Second tank is fixedly mounted on the second tank, realizes the measurement to the second tank internal pressure.
In the bipropellant propulsion device that a kind of above-mentioned balance is discharged, the propulsion device is fixedly mounted on external satellite
The control to satellite transit posture is realized in bottom.
Include following step in the control method of the bipropellant propulsion device that a kind of above-mentioned balance is discharged, the propulsion device
Suddenly：
When step (1), original state, gas circuit latching valve, the first latching valve and the second latching valve are in an open state；Third
Latching valve and the 4th latching valve are in off state；
Step (2) sets the satellite first time kick-in-the-apogee moment as T1, then satellite first time apogee becomes the flow of rail
It is as follows：
S1：Propellant inside T1-4min moment, the first tank and the second tank is sunk to the bottom；
S2：The T1-t1 moment opens third latching valve；
S3：The T1-t2 moment opens the 4th latching valve；
S4：The T1 moment, engine ignition, when igniting a length of Δ T1；
S5：T1+ Δ T1 moment, engine cutoff；
S6：The T1+ Δ T1+t3 moment closes the second latching valve；
S7：The T1+ Δ T1+t4 moment closes gas circuit latching valve；
S8：The T1+ Δ T1+t5 moment closes the first latching valve；
Step (3) sets second of kick-in-the-apogee moment of satellite as T2, then second of apogee of satellite becomes the flow of rail
It is as follows：
S1：Propellant inside T2-4min moment, the first tank and the second tank is sunk to the bottom；
S2：The T2-t1 moment opens the first latching valve；
S3：The T2-t2 moment opens the second latching valve；
S4：The T2 moment, engine ignition, when igniting a length of Δ T2；
S5：T2+ Δ T2 moment, engine cutoff；
S6：The T2+ Δ T2+t3 moment closes the 4th latching valve；
S7：The T2+ Δ T1+t4 moment closes gas circuit latching valve；
S8：The T2+ Δ T1+t5 moment closes third latching valve；
Step (4) repeats step (2), completes satellite third time apogee change rail；
Step (5) repeats step (3), completes the 4th apogee change rail of satellite；
Before step (6), satellite enter near-synchronous orbit；In propulsion device, gas circuit latching valve, third latching valve and the 4th
Latching valve is in off state, and the first latching valve and the second latching valve are in an open state；Then satellite enters the flow of near-synchronous orbit
It is as follows：
S1：When the temperature of the first tank and the second tank is stable state, opening gas circuit latching valve realizes external gas cylinder pair
First tank is inflated；
S2：After first pressure sensor numerical stability, third latching valve is opened, realizes that external the second tank of gas cylinder pair fills
Gas；
S3：When second pressure sensor values stabilization, and first pressure sensor is identical as second pressure sensor values,
Open gas circuit latching valve；
S4：After waiting for t6 durations, the 4th latching valve is opened, closes gas circuit latching valve.
In the bipropellant propulsion device that a kind of above-mentioned balance is discharged, the step (2) and step (3), t1 2-
3min；T2 is 1-2min；T3 is 30-40s；T4 is 4-6min；T5 is 5-7min, and t4 ＜ t5.
In the bipropellant propulsion device that a kind of above-mentioned balance is discharged, the S1 of the step (6), the first tank and the
The temperature of two tanks is that stable state refers to that the range of temperature of the first tank and the second tank is less than 0.01 DEG C.
In the bipropellant propulsion device that a kind of above-mentioned balance is discharged, the S2 of the step (6), first pressure sensing
The numerical stability of device refers to that the variation range of first pressure sensor is less than 0.01MP.
In the bipropellant propulsion device that a kind of above-mentioned balance is discharged, the S4 of the step (6), t6 2-3min.
The present invention has the following advantages that compared with prior art：
(1) present invention proposes that the bipropellant propulsion system composition of balance discharge is simple, on traditional bipropellant propulsion system
Pipe-line layout is optimized, and increases the equipment dependabilities such as latching valve and pressure sensor height；
(2) design method Project Realization of the invention is simple, reliability is high, and has had been subjected to in-orbit examination, is applicable to
The follow-up high rail remote sensing satellite using tank in parallel.
Description of the drawings
Fig. 1 is propulsion device schematic diagram of the present invention.
Specific implementation mode
The present invention is described in further detail in the following with reference to the drawings and specific embodiments：
Four latching valves are respectively configured in two tank upstream and downstream in the present invention, main to realize that satellite launch and change rail etc. are different
Stage propellant isolation and tank between two tanks in parallel distinguish function of increasing pressure, and when one of tank propellant is remaining
When measuring larger, the tank that can be used alone carries out incendiary agent supply；
Respectively increase a pressure sensor in each tank upstream, for monitoring propellant tank pressure changing and essence
Really calculate the surplus of propellant in tank；
The tank and the second latching valve 4, the 4th latching valve 6 for selecting flow resistance matching good；Make tank liquid mouth to second simultaneously
Latching valve 4,6 pipeline of the 4th latching valve, the second latching valve 4, the 4th latching valve 6 arrive the complete phase of downstream pipe meet pipe-line layout
Together, to avoid issuable differences in flow resistance between two incendiary agent tanks.
It is propulsion device schematic diagram as shown in Figure 1, as seen from the figure, a kind of bipropellant propulsion device of balance discharge, including
First tank 1, the second tank 2, the first latching valve 3, the second latching valve 4, third latching valve 5, the 4th latching valve 6, gas circuit self-locking
Valve 7, first pressure sensor 8 and second pressure sensor 9；Wherein, the external gas cylinder of upper end connection of gas circuit latching valve 7；Gas circuit
The lower end of latching valve 7 is connected to the vertical top of inverted T fonts pipeline；The horizontal left end of T font pipelines and the first latching valve 3 connect
It is logical；The horizontal right end of T font pipelines is connected to third latching valve 5；First latching valve 3 is connected to by pipeline with 1 top of the first tank；
Third latching valve 5 is connected to by pipeline with 2 top of the second tank；First tank, 1 bottom end passes through pipeline and the second latching valve 4
It is logical；Second tank, 2 bottom end is connected to by pipeline with the 4th latching valve 6；The horizontal left end of second latching valve 4 and T font pipelines connects
It is logical；4th latching valve 6 is connected to the horizontal right end of T font pipelines；The vertical bottom end of T font pipelines is connected to external thrust device.
First pressure sensor 8 is fixedly mounted on the first tank 1, realizes the measurement to 1 internal pressure of the first tank；Second tank 2
It is fixedly mounted on the second tank 2, realizes the measurement to 2 internal pressure of the second tank.
The propulsion device is fixedly mounted on the bottom of external satellite, realizes the control to satellite transit posture.
The control method for balancing the bipropellant propulsion device of discharge includes the following steps：
When step (1), original state, gas circuit latching valve 7, the first latching valve 3 and the second latching valve 4 are in an open state；The
Three latching valves 5 and the 4th latching valve 6 are in off state；
Step (2) sets the satellite first time kick-in-the-apogee moment as T1, then satellite first time apogee becomes the flow of rail
It is as follows：
S1：Propellant inside T1-4min moment, the first tank 1 and the second tank 2 is sunk to the bottom；
S2：The T1-t1 moment opens third latching valve 5；
S3：The T1-t2 moment opens the 4th latching valve 6；
S4：The T1 moment, engine ignition, when igniting a length of Δ T1；
S5：T1+ Δ T1 moment, engine cutoff；
S6：The T1+ Δ T1+t3 moment closes the second latching valve 4；
S7：The T1+ Δ T1+t4 moment closes gas circuit latching valve 7；
S8：The T1+ Δ T1+t5 moment closes the first latching valve 3；
Wherein, t1 2-3min；T2 is 1-2min；T3 is 30-40s；T4 is 4-6min；T5 is 5-7min, and t4 ＜ t5
Step (3) sets second of kick-in-the-apogee moment of satellite as T2, then second of apogee of satellite becomes the flow of rail
It is as follows：
S1：Propellant inside T2-4min moment, the first tank 1 and the second tank 2 is sunk to the bottom；
S2：The T2-t1 moment opens the first latching valve 3；
S3：The T2-t2 moment opens the second latching valve 4；
S4：The T2 moment, engine ignition, when igniting a length of Δ T2；
S5：T2+ Δ T2 moment, engine cutoff；
S6：The T2+ Δ T2+t3 moment closes the 4th latching valve 6；
S7：The T2+ Δ T1+t4 moment closes gas circuit latching valve 7；
S8：The T2+ Δ T1+t5 moment closes third latching valve 5；
Step (4) repeats step (2), completes satellite third time apogee change rail；
Step (5) repeats step (3), completes the 4th apogee change rail of satellite；
Before step (6), satellite enter near-synchronous orbit；In propulsion device, gas circuit latching valve 7, third latching valve 5 and
Four latching valves 6 are in off state, and the first latching valve 3 and the second latching valve 4 are in an open state；Then satellite enters near-synchronous orbit
Flow is as follows：
S1：When the temperature of the first tank 1 and the second tank 2 is stable state, the temperature of the first tank 1 and the second tank 2
It is less than 0.01 DEG C for the range of temperature that stable state refers to the first tank 1 and the second tank 2；Gas circuit latching valve 7 is opened, it is real
The first tank of existing external gas cylinder pair 1 is inflated；
S2：After 8 numerical stability of first pressure sensor, the numerical stability of first pressure sensor 8 refers to first pressure
The variation range of sensor 8 is less than 0.01MP；Third latching valve 5 is opened, realizes that the second tank of external gas cylinder pair 2 is inflated；
S3：When 9 numerical stability of second pressure sensor, and first pressure sensor 8 and 9 numerical value phase of second pressure sensor
Together, gas circuit latching valve 7 is opened；
S4：After waiting for t6 durations, t6 2-3min；The 4th latching valve 6 is opened, gas circuit latching valve 7 is closed.
The content that description in the present invention is not described in detail belongs to the known technology of those skilled in the art.
Claims (8)
1. a kind of bipropellant propulsion device of balance discharge, it is characterised in that：Including the first tank (1), the second tank (2),
One latching valve (3), the second latching valve (4), third latching valve (5), the 4th latching valve (6) and gas circuit latching valve (7)；Wherein, gas
The external gas cylinder of upper end connection of road latching valve (7)；The vertical top of the lower end of gas circuit latching valve (7) and inverted T fonts pipeline
Connection；The horizontal left end of T font pipelines is connected to the first latching valve (3)；The horizontal right end of T font pipelines connects with third latching valve (5)
It is logical；First latching valve (3) is connected to by pipeline with the first tank (1) top；Third latching valve (5) passes through pipeline and the second tank
(2) top is connected to；First tank (1) bottom end passes through pipeline and the second latching valve (4) unicom；Second tank (2) bottom end passes through pipe
Tetra- latching valves of Lu Yu (6) are connected to；Second latching valve (4) is connected to the horizontal left end of T font pipelines；4th latching valve (6) and T
The horizontal right end of font pipeline is connected to；The vertical bottom end of T font pipelines is connected to external thrust device.
2. a kind of bipropellant propulsion device of balance discharge according to claim 1, it is characterised in that：The propulsion device
Further include first pressure sensor (8) and second pressure sensor (9)；Wherein, first pressure sensor (8) is fixedly mounted on
On one tank (1), the measurement to the first tank (1) internal pressure is realized；Second tank (2) is fixedly mounted on the second tank (2)
On, realize the measurement to the second tank (2) internal pressure.
3. a kind of bipropellant propulsion device of balance discharge according to claim 2, it is characterised in that：The propulsion device
It is fixedly mounted on the bottom of external satellite, realizes the control to satellite transit posture.
4. a kind of bipropellant propulsion device of balance discharge according to claim 3, it is characterised in that：The propulsion device
Control method include the following steps：
When step (1), original state, gas circuit latching valve (7), the first latching valve (3) and the second latching valve (4) are in an open state；
Third latching valve (5) and the 4th latching valve (6) are in off state；
Step (2) sets the satellite first time kick-in-the-apogee moment as T1, then the flow of satellite first time apogee change rail is as follows：
S1：The internal propellant of T1-4min moment, the first tank (1) and the second tank (2) is sunk to the bottom；
S2：The T1-t1 moment opens third latching valve (5)；
S3：The T1-t2 moment opens the 4th latching valve (6)；
S4：The T1 moment, engine ignition, when igniting a length of Δ T1；
S5：T1+ Δ T1 moment, engine cutoff；
S6：The T1+ Δ T1+t3 moment closes the second latching valve (4)；
S7：The T1+ Δ T1+t4 moment closes gas circuit latching valve (7)；
S8：The T1+ Δ T1+t5 moment closes the first latching valve (3)；
Step (3) sets second of kick-in-the-apogee moment of satellite as T2, then the flow of second of apogee change rail of satellite is as follows：
S1：The internal propellant of T2-4min moment, the first tank (1) and the second tank (2) is sunk to the bottom；
S2：The T2-t1 moment opens the first latching valve (3)；
S3：The T2-t2 moment opens the second latching valve (4)；
S4：The T2 moment, engine ignition, when igniting a length of Δ T2；
S5：T2+ Δ T2 moment, engine cutoff；
S6：The T2+ Δ T2+t3 moment closes the 4th latching valve (6)；
S7：The T2+ Δ T1+t4 moment closes gas circuit latching valve (7)；
S8：The T2+ Δ T1+t5 moment closes third latching valve (5)；
Step (4) repeats step (2), completes satellite third time apogee change rail；
Step (5) repeats step (3), completes the 4th apogee change rail of satellite；
Before step (6), satellite enter near-synchronous orbit；In propulsion device, gas circuit latching valve (7), third latching valve (5) and
Four latching valves (6) are in off state, and the first latching valve (3) and the second latching valve (4) are in an open state；Then satellite enters plesiochronous
The flow of track is as follows：
S1：When the temperature of the first tank (1) and the second tank (2) is stable state, opening gas circuit latching valve (7) is realized external
The first tank of gas cylinder pair (1) is inflated；
S2：After first pressure sensor (8) numerical stability, third latching valve (5) is opened, realizes the second tank of external gas cylinder pair
(2) it inflates；
S3：When second pressure sensor (9) numerical stability, and first pressure sensor (8) and second pressure sensor (9) numerical value
It is identical, open gas circuit latching valve (7)；
S4：After waiting for t6 durations, the 4th latching valve (6) is opened, closes gas circuit latching valve (7).
5. a kind of bipropellant propulsion device of balance discharge according to claim 4, it is characterised in that：The step (2)
In step (3), t1 2-3min；T2 is 1-2min；T3 is 30-40s；T4 is 4-6min；T5 is 5-7min, and t4 ＜ t5.
6. a kind of bipropellant propulsion device of balance discharge according to claim 4, it is characterised in that：The step (6)
S1 in, the temperature of the first tank (1) and the second tank (2) is that stable state refers to the first tank (1) and the second tank (2)
Range of temperature is less than 0.01 DEG C.
7. a kind of bipropellant propulsion device of balance discharge according to claim 4, it is characterised in that：The step (6)
S2 in, the numerical stability of first pressure sensor (8) refers to that the variation range of first pressure sensor (8) is less than 0.01MP.
8. a kind of bipropellant propulsion device of balance discharge according to claim 4, it is characterised in that：The step (6)
S4 in, t6 2-3min.
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| CN201810117071.8A CN108454887B (en) | 2018-02-06 | 2018-02-06 | Balanced-discharge two-component propulsion device and control method |
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| CN201810117071.8A CN108454887B (en) | 2018-02-06 | 2018-02-06 | Balanced-discharge two-component propulsion device and control method |
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| CN109188129A (en) * | 2018-08-31 | 2019-01-11 | 中国空间技术研究院 | The electric polarity test method of satellite double elements chemical propulsion subsystem |
| CN111605738A (en) * | 2020-05-15 | 2020-09-01 | 北京控制工程研究所 | Double-component propulsion orbital transfer method suitable for low-orbit agile satellite |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109188129A (en) * | 2018-08-31 | 2019-01-11 | 中国空间技术研究院 | The electric polarity test method of satellite double elements chemical propulsion subsystem |
| CN109188129B (en) * | 2018-08-31 | 2020-09-18 | 中国空间技术研究院 | Electric polarity test method for satellite two-component chemical propulsion subsystem |
| CN111605738A (en) * | 2020-05-15 | 2020-09-01 | 北京控制工程研究所 | Double-component propulsion orbital transfer method suitable for low-orbit agile satellite |
| CN111605738B (en) * | 2020-05-15 | 2022-01-04 | 北京控制工程研究所 | Double-component propulsion orbital transfer method suitable for low-orbit agile satellite |
| CN112648110A (en) * | 2020-12-24 | 2021-04-13 | 上海空间推进研究所 | Processing method, system and medium for abnormal shutdown of spacecraft orbit control engine |
| CN112648110B (en) * | 2020-12-24 | 2021-12-28 | 上海空间推进研究所 | Processing method, system and medium for abnormal shutdown of spacecraft orbit control engine |
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