CN106516165A - Method for improving bipropellant attitude control thruster pulse control precision - Google Patents

Method for improving bipropellant attitude control thruster pulse control precision Download PDF

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Publication number
CN106516165A
CN106516165A CN201610959739.4A CN201610959739A CN106516165A CN 106516165 A CN106516165 A CN 106516165A CN 201610959739 A CN201610959739 A CN 201610959739A CN 106516165 A CN106516165 A CN 106516165A
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China
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thruster
liquid collecting
collecting cavity
road
ejector filler
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CN106516165B (en
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毛晓芳
汪凤山
张榛
蔡坤
王平
姚兆普
官长斌
陈磊
卢国权
杨尚峰
张凤
何孟琪
杨柳
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Beijing Institute of Control Engineering
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Beijing Institute of Control Engineering
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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
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

The invention discloses a method for improving the bipropellant attitude control thruster pulse control precision. By establishing the relation between the bipropellant attitude control thruster pulse control precision and the propellant control valve switch response time as well as the relation between the injector liquid collection cavity volume and the filling time, the method for effectively improving the bipropellant attitude control thruster pulse control precision is put forward. Quantitative design and analysis of the pulse control precision of a bipropellant attitude control thruster can be achieved, the design difficulty of the bipropellant attitude control thruster high in pulse control precision can be lowered, and the product development quality is improved.

Description

A kind of method for improving double elements attitude control thruster Pulse Width Control precision
Technical field
The invention belongs to space Liquid Propellant Rocket Engine field, more particularly to a kind of to be used to improve double elements thruster The method of Pulse Width Control precision.
Background technology
Double elements attitude control thruster is the most important active execution unit of Spacecraft Attitude Control, and Pulse Width Control precision is to boat Its device attitude control accuracy has vital impact.As the complexity and precision requirement of space mission are increasingly carried Rise, the also more and more higher of the requirement to the attitude accuracy and degree of stability of spacecraft platform, and then also require that double elements thruster enters one Step improves Pulse Width Control precision.But double elements attitude control thruster pulsed operation process is sufficiently complex, is related to electromagnetism, transient flow The physical and chemical process of the Various Complex such as dynamic, nonequilibrium chemical reaction and unsteady-state heat transfer, further improves Pulse Width Control precision It is very difficult.
If thruster Pulse Width Control precision can not meet requirement, Spacecraft Attitude Control precision on the one hand will be caused to surpass Difference, it would be possible to cause payload to be difficult to normal work, so as to have influence on normally completing for task；On the other hand, due to thrust Device Pulse Width Control precision is not enough, causes occur substantial amounts of overshoot amendment operation in attitude and orbit adjusting in spacecraft, it will Substantial amounts of valuable propellant resource is wasted, so as to cause the decline in spacecraft in-orbit life-span.With the in-orbit attitude of spacecraft and rail The continuous lifting of road control accuracy requirement, and the continuous improvement that the in-orbit service life of spacecraft is required, double elements automatic control thrust Device Pulse Width Control ability has become the bottleneck that restriction spacecraft ability and quality are further lifted, and improves double elements thruster Pulse Width Control precision for spacecraft task smoothly complete and difficulty action accomplishment has great significance.
The content of the invention
Present invention solves the technical problem that being：Overcome the deficiencies in the prior art, propose a kind of raising double elements attitude control thrust The method of device Pulse Width Control precision, solves the problems, such as that existing double elements attitude control thruster Pulse Width Control precision is not enough.
The technical scheme is that：A kind of method for improving double elements attitude control thruster Pulse Width Control precision, it is described Thruster includes oxygen road control valve, combustion road control valve, ejector filler and thrust chamber, aerobic road fluid collection chamber wherein in ejector filler internal channel With combustion road fluid collection chamber, channel switching by the control Fa Heran roads control valve control of oxygen road, comprised the following steps respectively：
1) according to thruster Pulse Width Control required precision, thruster Pulse Width Control precision is set up with thrust magnitude F and valve Close response time ToffRelationship delta I=F (Toff-0.5)；The thruster Pulse Width Control required precision includes minimum pulse momentum Index Δ I；
2) according to step 1) in thruster Pulse Width Control precision and thrust magnitude and valve close the relation of response time, with reference to Engineering reality, selection meet thruster thrust magnitude and close the combination of response time requirement with valve；
3) according to thruster Pulse Width Control required precision, minimum pulse momentum index Δ I and thruster ejector filler collection are set up Relationship delta I=0.81V between sap cavity volumeo+0.48Vf；The thruster ejector filler liquid collecting cavity volume is divided into oxygen road liquid collecting cavity Volume VoWith combustion road liquid collecting cavity volume Vf；
4) according to step 3) in relation between minimum pulse momentum index and thruster ejector filler liquid collecting cavity volume, with reference to Engineering reality, selects satisfactory thruster ejector filler Yang Luheran roads liquid collecting cavity volume combination；
5) according to step 4) the middle thruster ejector filler Yang Luheran roads liquid collecting cavity volume for selecting, it is calculated ejector filler oxygen The road propellant filling timeAnd the combustion road liquid collecting cavity propellant filling timeIts Middle Po.inRepresent thruster oxygen road inlet pressure, Pf.inRepresent thruster combustion road inlet pressure；Ao.inRepresent that oxygen road runner channel cuts Area, Af.inRepresent combustion road runner channel sectional area；
6) according to step 5) in the calculated ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time, obtain spray Qi Yang roads and combustion road liquid collecting cavity propellant filling time difference absolute value delta t=| to-tf|；
7) according to step 6) in be calculated ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time time difference absolute Value, selects thruster oxygen road control Fa Heran roads control valve, it is desirable to which it is poor that oxygen road control Fa Heran roads control valve opens response time Absolute value is less than 0.5ms with ejector filler Yang Luheran roads liquid collecting cavity propellant filling time time difference absolute value error, is used in combination Open the passage of the fast Valve controlling filling time length of response.
The thruster propellant is the combination of methyl hydrazine and dinitrogen tetroxide.
Present invention advantage compared with prior art is：
(1) present invention proposes double elements attitude control thruster Propellant Control threshold switch response speed and thruster most scun Amount, the quantitative relationship of minimum pulse momentum repeatability mean square deviation, push away to high impulse control accuracy double elements attitude control thruster in a state of excitement Enter the development of agent control valve and select there is provided foundation and method；
(2) present invention proposes double elements attitude control thruster ejector filler liquid collecting cavity and thruster minimum pulse momentum, minimum The quantitative relationship of impulse repeatability mean square deviation, carries to the development of high impulse control accuracy double elements attitude control thruster ejector filler Foundation and method are supplied；
(3) present invention proposes a kind of method that can effectively improve double elements attitude control thruster Pulse Width Control precision, makes The Pulse Width Control precision of double elements attitude control thruster can realize Quantitative design and analysis, greatly reduce high impulse control accuracy The design difficulty of double elements attitude control thruster, improves the development quality of product.
Description of the drawings
Fig. 1 is flow chart of the present invention.
Specific embodiment
Below the specific embodiment of the present invention is further described in detail.
In the present embodiment, by taking high impulse control accuracy double elements attitude control thruster design process as an example.First according to thrust Device Pulse Width Control required precision, sets up thruster Pulse Width Control precision and closes the relation of response time with thrust magnitude and valve.Its In, minimum pulse momentum index is included in thruster Pulse Width Control required precision and minimum pulse momentum repeatability mean square deviation refers to Mark, minimum pulse momentum index Δ I represents, unit is mN.s, and minimum pulse momentum repeatability mean square deviation is represented with δ；Thrust Magnitude is the specified stable state thrust of thruster, is represented with F, and unit is N；Valve close response time be thruster switching control pilot from The signal of telecommunication is given to the time blocked in passage required for propellant flowing, T is usedoffRepresent, unit is ms；Step 1 thruster is most The relation that small-pulse effect momentum index closes response time with thrust magnitude and valve can use formula Δ I=F (Toff- 0.5) represent； The response time repeatability mean square deviation requirement of valve pass is identical with the mean square poor index of minimum pulse momentum repeatability, is δ；
After the completion of setting up the relation of thruster Pulse Width Control precision and thrust magnitude and valve pass response time, according to thrust Device Pulse Width Control precision closes the relation of response time with thrust magnitude and valve, and incorporation engineering reality selects suitable thruster Thrust magnitude and valve close response index and require combination；
After the completion of selecting suitable thruster thrust magnitude and valve to close response index requirement combination, according to thruster pulse Control accuracy requirement, the relation set up between minimum pulse momentum index and thruster ejector filler liquid collecting cavity volume；Wherein, thrust Device ejector filler liquid collecting cavity volume is divided into oxygen road liquid collecting cavity and combustion road liquid collecting cavity, oxygen road liquid collecting cavity volume VoRepresent, fire road liquid collecting Chamber volume VfRepresent, unit is mm3；Between thruster minimum pulse momentum index and thruster ejector filler liquid collecting cavity volume Relation can use formula Δ I=0.81Vox+0.48VfuRepresent；
After the completion of the relation set up between minimum pulse momentum index and thruster ejector filler liquid collecting cavity volume, according to minimum Relation between impulse index and thruster ejector filler liquid collecting cavity volume, incorporation engineering reality select suitable thruster Ejector filler Yang Luheran roads liquid collecting cavity volume combination.
After selecting suitable thruster ejector filler Yang Luheran roads liquid collecting cavity volume combination, according to the thruster spray for selecting Qi Yang roads and combustion road liquid collecting cavity volume, are calculated the ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time；Wherein, thrust Device ejector filler liquid collecting cavity volume is divided into oxygen road liquid collecting cavity and combustion road liquid collecting cavity, oxygen road liquid collecting cavity volume VoRepresent, fire road liquid collecting Chamber volume VfRepresent, unit is mm3；The thruster ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time uses toAnd tf Represent, unit is ms；Thruster Yang Luheran roads inlet pressure Po.inAnd Pf.inRepresent, unit is Pa；Flow on Yang Luheran roads Road channel cross-sectional area Ao.inAnd Af.in, unit is mm2；Thruster ejector filler oxygen road filling time formulaRepresent, thruster ejector filler combustion road filling time formulaRepresent；
After being calculated the ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time, according to calculated ejector filler oxygen Road and combustion road liquid collecting cavity propellant filling time, obtain ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time difference absolute value Δ t=| to-tf|；
After the completion of ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time difference absolute value is calculated, according to being calculated spray Zhu Qiyang roads and combustion road liquid collecting cavity propellant filling time time difference absolute value, select thruster Propellant Control valve group to close, Ask the nearly ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time time difference of differential of two valve opening response times absolute Value, and unlatching is responded into the longer passage open and close of Valve controlling filling time faster.
In addition, in a kind of method for improving double elements attitude control thruster Pulse Width Control precision proposed by the present invention, it is described to push away Power device propellant is that methyl hydrazine and dinitrogen tetroxide are combined.
Certainly, to each step of the invention, method and compound mode in the case where its function is not changed, the equivalent change for carrying out Change or substitute, also fall into protection scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.

Claims (2)

1. it is a kind of improve double elements attitude control thruster Pulse Width Control precision method, described thruster include oxygen road control valve, Combustion road control valve, ejector filler and thrust chamber, aerobic road fluid collection chamber and combustion road fluid collection chamber, channel switching wherein in ejector filler internal channel Respectively by the control Fa Heran roads control valve control of oxygen road, it is characterised in that comprise the following steps：
1) according to thruster Pulse Width Control required precision, set up thruster Pulse Width Control precision and close with thrust magnitude F and valve and ring T between seasonableoffRelationship delta I=F (Toff-0.5)；The thruster Pulse Width Control required precision includes minimum pulse momentum index ΔI；
2) according to step 1) in thruster Pulse Width Control precision and thrust magnitude and valve close the relation of response time, incorporation engineering Actual, selection meets thruster thrust magnitude and closes the combination of response time requirement with valve；
3) according to thruster Pulse Width Control required precision, minimum pulse momentum index Δ I and thruster ejector filler liquid collecting cavity are set up Relationship delta I=0.81V between volumeo+0.48Vf；The thruster ejector filler liquid collecting cavity volume is divided into oxygen road liquid collecting cavity volume VoWith combustion road liquid collecting cavity volume Vf；
4) according to step 3) in relation between minimum pulse momentum index and thruster ejector filler liquid collecting cavity volume, incorporation engineering It is actual, select satisfactory thruster ejector filler Yang Luheran roads liquid collecting cavity volume combination；
5) according to step 4) the middle thruster ejector filler Yang Luheran roads liquid collecting cavity volume for selecting, it is calculated ejector filler oxygen road and pushes away Enter the agent filling timeAnd the combustion road liquid collecting cavity propellant filling timeWherein Po.inRepresent thruster oxygen road inlet pressure, Pf.inRepresent thruster combustion road inlet pressure；Ao.inRepresent oxygen road runner channel section Product, Af.inRepresent combustion road runner channel sectional area；
6) according to step 5) in the calculated ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time, obtain ejector filler oxygen Road and combustion road liquid collecting cavity propellant filling time difference absolute value delta t=| to-tf|；
7) according to step 6) in be calculated ejector filler Yang Lujiran roads liquid collecting cavity propellant filling time time difference absolute value, select Select thruster oxygen road control Fa Heran roads control valve, it is desirable to which oxygen road control Fa Heran roads control valve opens response time difference absolute value 0.5ms is less than with ejector filler Yang Luheran roads liquid collecting cavity propellant filling time time difference absolute value error, and is rung with opening Answer the passage of fast Valve controlling filling time length.
2. it is according to claim 1 it is a kind of improve double elements attitude control thruster Pulse Width Control precision method, it is characterised in that：Institute State the combination that thruster propellant is methyl hydrazine and dinitrogen tetroxide.
CN201610959739.4A 2016-10-27 2016-10-27 A method of improving double elements attitude control thruster Pulse Width Control precision Active CN106516165B (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107908105A (en) * 2017-07-04 2018-04-13 上海宇航系统工程研究所 A kind of rope system assembly towing removing method based on thruster switch control
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
CN114889850A (en) * 2022-07-11 2022-08-12 北京宇航推进科技有限公司 Double-component attitude and orbit control power device and aircraft with same

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US20080173004A1 (en) * 2006-04-20 2008-07-24 Combustion Propulsion & Ballistic Technology Corp. Bi-propellant rocket motor having controlled thermal management
CN103662095A (en) * 2013-12-20 2014-03-26 北京控制工程研究所 Injector used for double-component attitude control thruster
CN103953464A (en) * 2014-05-06 2014-07-30 北京控制工程研究所 Ground calibration method for on-orbit performance of two-component attitude control thruster
US20150069188A1 (en) * 2011-11-15 2015-03-12 Macdonald, Dettwiler And Associates Inc. Propellant transfer system and method for resupply of fluid propellant to on-orbit spacecraft

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080173004A1 (en) * 2006-04-20 2008-07-24 Combustion Propulsion & Ballistic Technology Corp. Bi-propellant rocket motor having controlled thermal management
US20150069188A1 (en) * 2011-11-15 2015-03-12 Macdonald, Dettwiler And Associates Inc. Propellant transfer system and method for resupply of fluid propellant to on-orbit spacecraft
CN103662095A (en) * 2013-12-20 2014-03-26 北京控制工程研究所 Injector used for double-component attitude control thruster
CN103953464A (en) * 2014-05-06 2014-07-30 北京控制工程研究所 Ground calibration method for on-orbit performance of two-component attitude control thruster

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107908105A (en) * 2017-07-04 2018-04-13 上海宇航系统工程研究所 A kind of rope system assembly towing removing method based on thruster switch control
CN107908105B (en) * 2017-07-04 2020-10-23 上海宇航系统工程研究所 Method for removing dragging of rope system assembly based on thruster switch control
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
CN114889850A (en) * 2022-07-11 2022-08-12 北京宇航推进科技有限公司 Double-component attitude and orbit control power device and aircraft with same

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