CN108877452A - Filled Spacecraft attitude dynamics full physical simulation test method - Google Patents
Filled Spacecraft attitude dynamics full physical simulation test method Download PDFInfo
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- CN108877452A CN108877452A CN201810617407.7A CN201810617407A CN108877452A CN 108877452 A CN108877452 A CN 108877452A CN 201810617407 A CN201810617407 A CN 201810617407A CN 108877452 A CN108877452 A CN 108877452A
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Abstract
Filled Spacecraft attitude dynamics full physical simulation test method of the invention, includes the following steps：S1, dynamics environment is freely rotated by the in-orbit microgravity of three-axis air-bearing table Simulated Spacecraft, three axis；S2, cold air propulsion system is used to provide gas puff Z-pinch torque for three-axis air-bearing table, the gas jet attitude control during Simulated Spacecraft transfer orbital control；S3, using liquid sloshing torque simulator Simulated Spacecraft liquid sloshing disturbance torque；S4, the influence using laser tracker and lasergyro analysis liquid sloshing to spacecraft attitude dynamics.Filled Spacecraft attitude dynamics full physical simulation test method of the invention is tested suitable for three-axis air-bearing table full physical simulation, and influence of the liquid sloshing to spacecraft attitude is analyzed under full physical simulation environment, can be examined more truly and effectively and access control system.Whole star mass center variation of the analogy method due to eliminating liquid sloshing generation can avoid occurring air floating table and fall from power phenomenon.
Description
Technical field
The present invention relates to attitude dynamics, imitative more specifically to a kind of full physics of filled Spacecraft attitude dynamics
True test method, this method can be used for spacecraft rail control and dynamics Optimization Design and verification experimental verification.
Background technique
Spacecraft is detached from terrestrial gravitation, into GEO transfer orbit or into transfer orbit between star ground and again to have
Enter planet, the abilities such as the planet that is diversion, be typically equipped with large-scale filling liquid tank, spaceborne liquid fuel amount and full star mass ratio are high sometimes
It is even higher up to 50%~60%.Therefore, liquid fuel shakes the coupling controlled with full star and greatly reinforces, and is to control
System stability Design proposes severe challenge.Especially becoming rail motorized segment, due to engine ignition and thrust direction is eccentric, or
Attitude control thruster jet may all evoke the Liquid sloshing or even large-amplitude sloshing of liquid fuel in tank, generate disturbance torque, from
And spacecraft firing attitude is influenced, cause orbits controlling to deviate, or even spacecraft is caused not can enter planned orbit, causes final
Mission failure.When serious, liquid fuel low frequency large-amplitude sloshing also results in full star control unstability even structure and destroys.Fly in space flight
In row history, due to tank fuel poverty of movement thoroughly being studied and being occurred the accident of attitude control system of the spacecraft failure, 1996
Near Earth Asteroid Rendezvous (NEAR) spacecraft of year U.S. NASA transmitting is executing near-Earth asteroid spy
When survey task, since the coupling between the attitude of satellite and shaking causes entire propulsion system to fail, task is made to delay 13 months.
As it can be seen that liquid sloshing influence research dynamic (dynamical) on whole star has apparent engineering application value, it is related to following multiple models
Success or failure, there is an urgent need to concentrating manpower carry out related fields research.
Currently, the impact analysis of filled Spacecraft attitude dynamics passes through theoretical modeling mostly and the method for mathematical simulation is opened
Exhibition, Lin Hong, Peng Huilian, Dong Kai " simulation study and verifying of propellant tank liquid sloshing " (see《Intensity and environment》, 2011
Year, the phase of volume 13 the 5th, page number 25-30) it proposes in paper a kind of to carry out the side that three-dimensional liquid shakes simulation calculation using CFD software
Method does not mention specific test method.
Wang Tianshu, Zhang Pengfei " LIQUID-FILLED SATELLITE ground physical emulation mode " (see《Tsinghua University's journal》, 2015,55
Roll up the 10th phase, page number 1130-1134) a kind of shaking for proposing to apply liquid in satellite filling liquid tank using flywheel is proposed in paper
The scheme of torque, this article introduce the analogy method of liquid sloshing torque, are not directed to filled Spacecraft to posture power
Impact analysis is learned, does not also introduce the specific implementation approach of ground physical emulation mode.
Summary of the invention
The purpose of the present invention is to provide a kind of filled Spacecraft attitude dynamics full physical simulation test method, true moulds
The gesture stability torque and liquid sloshing torque during spacecraft becomes rail are intended, it may be verified that liquid sloshing is to Spacecraft Attitude Control
Influence, provide foundation for the gesture stability and dynamics Optimization Design of spacecraft.
To achieve the above object, the present invention is realized especially by following technical scheme：
Filled Spacecraft attitude dynamics full physical simulation test method, includes the following steps：
S1, dynamics environment is freely rotated by the in-orbit microgravity of three-axis air-bearing table Simulated Spacecraft, three axis, it can be accurately anti-
Control moment and liquid sloshing disturbance torque are reflected to the kinetic effect characteristic of spacecraft；
S2, cold air propulsion system is used to provide gas puff Z-pinch torque, Simulated Spacecraft transfer orbital control phase for three-axis air-bearing table
Between gas jet attitude control；Wherein, the propellant of cold air propulsion system is gas, will not cause to shake during gesture stability dry
Disturb torque；
S3, using liquid sloshing torque simulator Simulated Spacecraft liquid sloshing disturbance torque；Specifically, by liquid sloshing
Torque simulator is mounted on three-axis air-bearing table, is generated torque using angular momentum exchange mode, is simulated by liquid sloshing torque
The situation of change of liquid sloshing disturbance torque during the angular momentum feedback monitoring test of device, wherein liquid sloshing torque simulator
Mass center variation when liquid sloshing is not simulated, in order to avoid three-axis air-bearing table is caused to be fallen from power；
S4, the influence using laser tracker and lasergyro analysis liquid sloshing to spacecraft attitude dynamics；Tool
Body, using the attitude angle and attitude angular velocity of laser tracker and laser gyro measurement three-axis air-bearing table, analyze liquid sloshing
Influence to spacecraft；By the gyro data of high sample frequency, the frequency domain characteristic of liquid sloshing disturbance torque is analyzed.
The invention has the advantages that：
Filled Spacecraft attitude dynamics full physical simulation test method of the invention is suitable for the full physics of three-axis air-bearing table
L-G simulation test is analyzed influence of the liquid sloshing to spacecraft attitude under full physical simulation environment, can be examined more truly and effectively
With access control system.Whole star mass center variation of the analogy method due to eliminating liquid sloshing generation, can avoid air bearing occur
Platform is fallen from power phenomenon.
Detailed description of the invention
Fig. 1 is the process principle figure of filled Spacecraft of embodiment of the present invention attitude dynamics full physical simulation test method.
Specific embodiment
The spacecraft attitude dynamics full physics proposed by the present invention that is suitable for is imitated below in conjunction with the drawings and specific embodiments
True test method is described in further detail.
As shown in Figure 1, the embodiment of the invention provides a kind of filled Spacecraft attitude dynamics full physical simulation test sides
Method includes the following steps：
S1, using the in-orbit dynamics environment of three-axis air-bearing table Simulated Spacecraft
It is free that three-axis air-bearing table passes through the in-orbit microgravity of the gas film lubrication analog spacecraft between air-floating ball bearing, three axis
Dynamics environment；Meanwhile three-axis air-bearing table has three direction rotary inertia regulating powers, protects with the in-orbit rotary inertia of spacecraft
It holds unanimously, control moment and liquid sloshing disturbance torque can be accurately reflected to the kinetic effect characteristic of spacecraft.
Gas jet attitude during S2, spacecraft transfer orbital control controls simulation
Cold air propulsion system is used to provide gas puff Z-pinch torque for three-axis air-bearing table, during Simulated Spacecraft transfer orbital control
Gas jet attitude control；The cold air propulsion system is mounted on three-axis air-bearing table, since propellant is gas, so during work
Shaking disturbance torque will not be generated；
S3, the simulation of liquid sloshing disturbance torque
Using liquid sloshing torque simulator Simulated Spacecraft liquid sloshing disturbance torque；The liquid sloshing torque simulation
Device is mounted on three-axis air-bearing table, is generated torque using angular momentum exchange mode, is acted directly on three-axis air-bearing table, and simulation becomes
Influence of the liquid sloshing disturbance torque to spacecraft during rail.During test, pass through the angular momentum of liquid sloshing torque simulator
The situation of change of feedback monitoring liquid sloshing disturbance torque.
The influence of S4, analysis liquid sloshing to spacecraft attitude dynamics
Liquid sloshing is mainly reflected in the attitude angle and attitude stability of spacecraft to the influence of spacecraft attitude dynamics
Variation on.The present invention is divided using the attitude angle and attitude angular velocity of laser tracker and laser gyro measurement three-axis air-bearing table
Analyse influence of the liquid sloshing to spacecraft；In addition, by the gyro data of high sample frequency, analysis liquid sloshing disturbance torque
Frequency domain characteristic.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (4)
1. filled Spacecraft attitude dynamics full physical simulation test method, which is characterized in that include the following steps：
S1, dynamics environment is freely rotated by the in-orbit microgravity of three-axis air-bearing table Simulated Spacecraft, three axis；
S2, cold air propulsion system is used to provide gas puff Z-pinch torque for three-axis air-bearing table, during Simulated Spacecraft transfer orbital control
Gas jet attitude control；
S3, using liquid sloshing torque simulator Simulated Spacecraft liquid sloshing disturbance torque；
S4, the influence using laser tracker and lasergyro analysis liquid sloshing to spacecraft attitude dynamics.
2. filled Spacecraft attitude dynamics full physical simulation test method as described in claim 1, which is characterized in that use
Cold air propulsion system and liquid sloshing torque simulator simulate attitude dynamics process when filled Spacecraft gas puff Z-pinch jointly,
The cold air propulsion system only provides gesture stability torque, does not generate liquid sloshing torque；The liquid sloshing torque simulator
Only output liquid shakes disturbance torque, does not simulate the centroid position variation of liquid, avoids introducing additional gravity disturbance torque.
3. filled Spacecraft attitude dynamics full physical simulation test method as described in claim 1, which is characterized in that described
Step S3 specifically comprises the following steps：
Liquid sloshing torque simulator is mounted on three-axis air-bearing table, torque is generated using angular momentum exchange mode, passes through liquid
The situation of change of liquid sloshing disturbance torque during the angular momentum feedback monitoring test of body slosh torque simulator.
4. filled Spacecraft attitude dynamics full physical simulation test method as described in claim 1, which is characterized in that described
Step S4 analyzes liquid sloshing using the attitude angle and attitude angular velocity of laser tracker and laser gyro measurement three-axis air-bearing table
Influence to spacecraft；By the gyro data of high sample frequency, the frequency domain characteristic of liquid sloshing disturbance torque is analyzed.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108873920A (en) * | 2018-06-15 | 2018-11-23 | 上海卫星工程研究所 | Filled Spacecraft attitude dynamics full physical simulation pilot system and method |
| CN110286607A (en) * | 2019-07-22 | 2019-09-27 | 中国人民解放军军事科学院国防科技创新研究院 | A kind of spacecraft attitude control jet pipe fault data generation system and method |
| CN112489521A (en) * | 2020-12-23 | 2021-03-12 | 覃睿 | Automobile driving simulation device and system |
| CN112525502A (en) * | 2020-11-04 | 2021-03-19 | 天津大学前沿技术研究院有限公司 | Device and method for testing performance of magnetohydrodynamic inertial momentum wheel |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108873920A (en) * | 2018-06-15 | 2018-11-23 | 上海卫星工程研究所 | Filled Spacecraft attitude dynamics full physical simulation pilot system and method |
| CN110286607A (en) * | 2019-07-22 | 2019-09-27 | 中国人民解放军军事科学院国防科技创新研究院 | A kind of spacecraft attitude control jet pipe fault data generation system and method |
| CN110286607B (en) * | 2019-07-22 | 2020-04-03 | 中国人民解放军军事科学院国防科技创新研究院 | Spacecraft attitude control spray pipe fault data generation system and method |
| CN112525502A (en) * | 2020-11-04 | 2021-03-19 | 天津大学前沿技术研究院有限公司 | Device and method for testing performance of magnetohydrodynamic inertial momentum wheel |
| CN112489521A (en) * | 2020-12-23 | 2021-03-12 | 覃睿 | Automobile driving simulation device and system |
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