CN106516165B - A method of improving double elements attitude control thruster Pulse Width Control precision - Google Patents
A method of improving double elements attitude control thruster Pulse Width Control precision Download PDFInfo
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- CN106516165B CN106516165B CN201610959739.4A CN201610959739A CN106516165B CN 106516165 B CN106516165 B CN 106516165B CN 201610959739 A CN201610959739 A CN 201610959739A CN 106516165 B CN106516165 B CN 106516165B
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- thruster
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- collecting cavity
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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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- 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 kind of methods improving double elements attitude control thruster Pulse Width Control precision, by establishing double elements attitude control thruster Pulse Width Control precision and Propellant Control threshold switch response time, the ejector filler liquid collecting cavity volume and relationship between the filling time, it is proposed that a kind of effective method for improving double elements attitude control thruster Pulse Width Control precision.So that the Pulse Width Control precision of double elements attitude control thruster is realized Quantitative design and analysis, the design difficulty of high impulse control accuracy double elements attitude control thruster can be reduced, improve the development quality of product.
Description
Technical field
The invention belongs to space Liquid Propellant Rocket Engine fields, more particularly to a kind of for improving 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 influence.With the complexity of space mission and increasingly carrying for precision requirement
It rises, the requirement of attitude accuracy and stability to spacecraft platform is also higher and higher, and then also requires double elements thruster into one
Step improves Pulse Width Control precision.However 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 Complexes such as dynamic, nonequilibrium chemical reaction and unsteady-state heat transfer, further increases Pulse Width Control precision
It is very difficult.
If thruster Pulse Width Control precision cannot be met the requirements, Spacecraft Attitude Control precision on the one hand will be caused super
Difference, it would be possible to cause payload to be difficult to work normally, to influence normally completing for task；On the other hand, due to thrust
Device Pulse Width Control precision is insufficient, leads to occur a large amount of overshoot amendment operation in posture and orbit adjusting in spacecraft, it will
The a large amount of valuable propellant resource of waste, so as to cause the decline of spacecraft in-orbit life-span.With the in-orbit posture of spacecraft and rail
The continuous improvement that the continuous promotion of road control accuracy requirement and the in-orbit service life of spacecraft require, double elements automatic control thrust
Device Pulse Width Control ability, which has become, restricts the bottleneck that spacecraft ability and quality are further promoted, and improves double elements thruster
Pulse Width Control precision has great significance for the quality that smoothly completes and complete of spacecraft task.
Invention content
Present invention solves the technical problem that being：Overcome the deficiencies in the prior art proposes 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 insufficient.
The technical scheme is that：A method of double elements attitude control thruster Pulse Width Control precision is improved, 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 switch by oxygen road control valve and combustion road control valve control, includes the following steps respectively：
1) according to thruster Pulse Width Control required precision, thruster Pulse Width Control precision and thrust magnitude F and valve are established
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) relationship that the response time is closed according to thruster Pulse Width Control precision in step 1) and thrust magnitude and valve, in conjunction with
Engineering is practical, and selection meets the combination that thruster thrust magnitude closes 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 established
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 the relationship between minimum pulse momentum index in step 3) and thruster ejector filler liquid collecting cavity volume, in conjunction with
Engineering is practical, selects the satisfactory roads thruster ejector filler Yang Luheran liquid collecting cavity volume combination；
5) according to the roads the thruster ejector filler Yang Luheran liquid collecting cavity volume selected in step 4), ejector filler oxygen is calculated
The road propellant filling timeAnd the combustion road liquid collecting cavity propellant filling timeIts
Middle Po.inIndicate thruster oxygen road inlet pressure, Pf.inIndicate that thruster fires road inlet pressure；Ao.inIndicate that oxygen road runner channel is cut
Area, Af.inIndicate combustion road runner channel sectional area；
6) according to the roads the ejector filler Yang Lujiran liquid collecting cavity propellant filling time being calculated in step 5), spray is obtained
The roads Qi Yang and combustion road liquid collecting cavity propellant filling time difference absolute value delta t=| to-tf|；
7) absolute according to the time difference roads ejector filler Yang Lujiran liquid collecting cavity propellant filling time is calculated in step 6)
Value selects thruster oxygen road control valve and combustion road control valve, it is desirable that it is poor that oxygen road control valve and combustion road control valve open the response time
Absolute value is no more than 0.5ms with the roads ejector filler Yang Luheran liquid collecting cavity propellant filling time time difference absolute value error, is used in combination
Open the channel for responding fast valve control filling time length.
The thruster propellant is the combination of methyl hydrazine and dinitrogen tetroxide.
The advantages of the present invention over the prior art are that：
(1) present invention proposes double elements attitude control thruster Propellant Control threshold switch response speed and thruster most scun
The quantitative relationship of amount, minimum pulse momentum repeatability mean square deviation in a state of excitement, pushes away to high impulse control accuracy double elements attitude control thruster
Development and selection into agent control valve provide 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 is carried 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 implementation mode
The specific implementation mode of the present invention is further described in detail below.
In the present embodiment, by taking high impulse control accuracy double elements attitude control thruster design process as an example.First according to thrust
The relationship that thruster Pulse Width Control precision closes the response time with thrust magnitude and valve is established in device Pulse Width Control required precision.Its
In, refer to comprising minimum pulse momentum index and minimum pulse momentum repeatability mean square deviation in thruster Pulse Width Control required precision
Mark, minimum pulse momentum index indicate that unit mN.s, minimum pulse momentum repeatability mean square deviation is indicated with δ with Δ I；Thrust
Magnitude is the specified stable state thrust of thruster, is indicated with F, unit N；Valve close the response time be thruster switching control pilot from
It provides electric signal and flows the required time to propellant in channel is blocked, use ToffIt indicates, unit ms；Step 1 thruster is most
Small-pulse effect momentum index closes the relationship of response time with thrust magnitude and valve can use formula Δ I=F (Toff- 0.5) it indicates；
The response time repeatability mean square deviation requirement of valve pass is identical as minimum pulse momentum repeatability mean square deviation index, is δ；
It establishes after the completion of the relationship that thruster Pulse Width Control precision closes the response time with thrust magnitude and valve, according to thrust
Device Pulse Width Control precision closes the relationship of response time with thrust magnitude and valve, and incorporation engineering is practical, 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 establishes the relationship 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 VoIt indicates, fires road liquid collecting
Chamber volume VfIt indicates, unit is mm3；Between thruster minimum pulse momentum index and thruster ejector filler liquid collecting cavity volume
Relationship can use formula Δ I=0.81Vox+0.48VfuIt indicates；
It establishes after the completion of the relationship between minimum pulse momentum index and thruster ejector filler liquid collecting cavity volume, according to minimum
Relationship between impulse index and thruster ejector filler liquid collecting cavity volume, incorporation engineering is practical, selects suitable thruster
The roads ejector filler Yang Luheran liquid collecting cavity volume combination.
After selecting the suitable roads thruster ejector filler Yang Luheran liquid collecting cavity volume combination, according to the thruster spray of selection
The roads Qi Yang and combustion road liquid collecting cavity volume, are calculated the roads the ejector filler Yang Lujiran 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 VoIt indicates, fires road liquid collecting
Chamber volume VfIt indicates, unit is mm3；The roads the thruster ejector filler Yang Lujiran liquid collecting cavity propellant filling time uses toAnd tf
It indicates, unit is ms；The roads thruster Yang Luheran inlet pressure Po.inAnd Pf.inIt indicates, unit Pa；It flows on the roads Yang Luheran
Road channel cross-sectional area Ao.inAnd Af.in, unit mm2；Thruster ejector filler oxygen road filling time formulaIt indicates, thruster ejector filler fires road filling time formulaIt indicates；
After the roads the ejector filler Yang Lujiran liquid collecting cavity propellant filling time is calculated, according to the ejector filler oxygen being calculated
Road and combustion road liquid collecting cavity propellant filling time, obtain the roads ejector filler Yang Lujiran liquid collecting cavity propellant filling time difference absolute value
Δ t=| to-tf|；
After the completion of the roads ejector filler Yang Lujiran liquid collecting cavity propellant filling time difference absolute value calculates, sprayed according to being calculated
The roads Zhu Qiyang and combustion road liquid collecting cavity propellant filling time time difference absolute value, select thruster Propellant Control valve group to close,
Ask the roads the differential of two valve opening response times nearly ejector filler Yang Lujiran time difference liquid collecting cavity propellant filling time absolute
Value, and will open and respond the longer channel open and close of faster valve control filling time.
In addition, in a kind of method 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 combine.
Certainly, to each step of the present invention, method and combination in the case where not changing its function, the equivalent change of progress
It changes or substitutes, also fall into protection scope of the present invention.
The content that description in the present invention is not described in detail 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, the thruster include oxygen road control valve,
Road control valve, ejector filler and thrust chamber are fired, aerobic road fluid collection chamber and combustion road fluid collection chamber, channel switch wherein in ejector filler internal channel
Respectively by oxygen road control valve and combustion road control valve control, it is characterised in that include the following steps：
1) it according to thruster Pulse Width Control required precision, establishes thruster Pulse Width Control precision and is closed with thrust magnitude F and valve and rung
T between seasonableoffRelationship delta I=F (Toff-0.5)；The thruster Pulse Width Control required precision includes minimum pulse momentum index
ΔI；
2) relationship of response time, incorporation engineering are closed according to thruster Pulse Width Control precision in step 1) and thrust magnitude and valve
Practical, selection meets the combination that thruster thrust magnitude closes 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 established
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 the relationship between minimum pulse momentum index in step 3) and thruster ejector filler liquid collecting cavity volume, incorporation engineering
It is practical, select the satisfactory roads thruster ejector filler Yang Luheran liquid collecting cavity volume combination；
5) according to the roads the thruster ejector filler Yang Luheran liquid collecting cavity volume selected in step 4), ejector filler oxygen road is calculated and pushes away
Into the agent filling timeAnd the combustion road liquid collecting cavity propellant filling timeWherein
Po.inIndicate thruster oxygen road inlet pressure, Pf.inIndicate that thruster fires road inlet pressure；Ao.inIndicate oxygen road runner channel section
Product, Af.inIndicate combustion road runner channel sectional area；ρoIndicate oxygen road fluid density, ρfIndicate combustion road fluid density；
6) according to the roads the ejector filler Yang Lujiran liquid collecting cavity propellant filling time being calculated in step 5), ejector filler oxygen is obtained
Road and combustion road liquid collecting cavity propellant filling time difference absolute value delta t=| to-tf|；
7) according to the roads ejector filler Yang Lujiran liquid collecting cavity propellant filling time difference absolute value is calculated in step 6), selection pushes away
The roads Li Qiyang control valve and combustion road control valve, it is desirable that oxygen road control valve and combustion road control valve open response time difference absolute value and spray
The roads Zhu Qiyang and combustion road liquid collecting cavity propellant filling time difference absolute value error are no more than 0.5ms, are used in combination and open the fast valve of response
The channel of gate filling time length processed.
2. a kind of method improving double elements attitude control thruster Pulse Width Control precision according to claim 1, it is characterised in that：Institute
State the combination that thruster propellant is methyl hydrazine and dinitrogen tetroxide.
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| 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 |
| 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 |
| CN114889850B (en) * | 2022-07-11 | 2022-10-14 | 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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| CA3037930C (en) * | 2011-11-15 | 2020-06-02 | Maxar Technologies Ltd. | Propellant transfer system and method for resupply of fluid propellent to on-orbit spacecraft |
| CN103662095B (en) * | 2013-12-20 | 2015-08-19 | 北京控制工程研究所 | A kind of injector for double elements appearance control thruster |
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