CN101510094B - Non-towing control double-torsion pendulum test device - Google Patents
Non-towing control double-torsion pendulum test device Download PDFInfo
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- CN101510094B CN101510094B CN2009100611856A CN200910061185A CN101510094B CN 101510094 B CN101510094 B CN 101510094B CN 2009100611856 A CN2009100611856 A CN 2009100611856A CN 200910061185 A CN200910061185 A CN 200910061185A CN 101510094 B CN101510094 B CN 101510094B
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Abstract
The invention provides a drag-free control double torsion pendulum testing device, comprising a spacecraft simulation object, an inertial reference object, a drag-free controller and a capacitive displacement sensor; and a hanging device is respectively used for hanging the spacecraft simulation object and the inertial reference object. The capacitive displacement sensor measures and transmits the displacement information on the spacecraft simulation object relative to the inertial reference object to the drag-free controller; later the drag-free controller drives a propeller according to the displacement information; and then the propeller generates a thrust which is imposed on the spacecraft simulation object so as to finally realize displacement compensation. The invention truly simulates the space environment of an aircraft, achieves the overall performance test for a drag-free control system, and provides a basis for finally determining the on-orbit drag-free spaceflight.
Description
Technical field
The invention belongs to does not have towing Aerospace Control technical field, is specifically related to a kind of non-towing control double-torsion pendulum test device.
Background technology
Generally speaking, the remaining disturbance of satellite is microgravity level (10-4～10-6g0, g0 are the acceleration of gravity of earth surface), and it mainly is subjected to the restriction of atmospheric damping, satellite structure vibration and disturbances such as attitude adjusting and inside satellite moving-member.In order further to suppress the remaining disturbance of satellite, the human nothing towing satellite conception that just proposed as far back as the sixties in last century, its basic thought is to utilize the inertial reference object as benchmark, adopts micro-thruster to compensate the remaining disturbing force that satellite is subjected to, and makes Satellite Tracking inertial reference object.Simplified summary, not having towing satellite platform technology is exactly high-accuracy posture control and track control technology.It is significant for space basis scientific research, high precision microgravity experiment, earth observation and survey of deep space not have the towing spationautics.
Not having the towing spationautics comprises the inertial sensor Reference, does not have towing controller and micro-thruster three parts.Inertial sensor is made up of inertial reference object and displacement transducer, and displacement transducer is used for monitoring the displacement or the angle variation of inertial reference object and satellite platform.The inertial reference object provides reference data, and the remaining disturbing force of its non-gravitation that is subjected to must be as far as possible little, and its track is as far as possible along geodesic line move (movement locus that only is subjected to graviational interaction).Generally speaking, do not have the towing spacecraft and require the measuring accuracy of inertial sensor to reach 10-8g0 even lower, depend primarily on the scientific goal of experiment.Micro-thruster mainly produces small thrust and moment, is used for compensating the remaining disturbing force of satellite, and the thrust precision of micro-thruster relies on the satellite quality, generally speaking needs to reach little newton's magnitude level.Nothing towing controller is that micro-thruster is controlled in the output (being the motion that satellite departs from the inertial reference object) according to inertial sensor, does not have the towing controller and is equivalent to a multiple-input and multiple-output processor controls.
Not having towing control ground test technology at present also not to the unified test of total system, all is separately inertial sensor and thruster to be tested respectively, still takes the analogue simulation means to study to the test of not having the towing controller.Ground test means to inertial sensor are to utilize suspension to hang quality inspection formation precision to rock or torsion balance, study the performance index of inertial sensor by rocking response, angle of rake test utilization pendulum (comprise physical pendulum, rock and multi-thread pendulum) is tested parameters such as propeller thrust, specific impulse.
Summary of the invention
The object of the present invention is to provide a kind of non-towing control double-torsion pendulum test device, the space environment of real simulation aircraft is realized to there not being the overall performance test of towing control system, for determining that finally not having towing space flight at rail provides foundation.
A kind of non-towing control double-torsion pendulum test device, comprise spacecraft simulation object 3, inertial reference object 2, do not have towing controller 7 and capacitance displacement sensor, capacitance displacement sensor is measured the displacement information of spacecraft simulation object 3 relative inertness References 2, send it to nothing towing controller 7, do not have towing controller 7 and drive thruster 8 according to displacement information, thruster 8 produces thrust and imposes on spacecraft simulation object 3, realize bit shift compensation, described spacecraft simulation object 3 is suspended by first hitch, and described inertial reference object 2 is suspended by second hitch.
Technique effect of the present invention is embodied in: the present invention adopts first hitch spacecraft simulation object 3 that suspends, second hitch inertial reference object 2 that suspends, make spacecraft simulation object 3 and inertial reference object 2 can among a small circle, be in free state, the running status of simulated flight device in space truly, do not constitute a double-torsion pendulum test device together in conjunction with having towing controller and micro-thruster again, this device can not only be to inertial sensor, thruster and do not have the towing controller performance own test separately and study, can also carry out the whole synthesis test to the performance of aforementioned three members, the integration test result does not have towing aerospace system technology to the space and verifies on ground feasibility is provided that using for final space provides reliable basis.
Description of drawings
Fig. 1 is a non-towing control double-torsion pendulum example test system synoptic diagram of the present invention.
Embodiment
Utilize suspension 1 to hang an inertial reference object 2, utilize another root suspension 1 to hang the spacecraft simulation object 3 that contains capacitor plate again, spacecraft simulation object 3 is combined into capacitance displacement sensor probe 5 with inertial reference object 2, and capacitance displacement sensor probe 5 is measured 3 displacements with respect to inertial reference object 2 of spacecraft simulation object in conjunction with displacement transducer circuit 6.Displacement Measurement does not obtain feedback signal by there being towing controller 7, feedback signal imposes on thruster 8 then, thruster 8 produces thrust 9 and imposes on spacecraft simulation object 3, finally make spacecraft simulation object 3 keep and keep relative motionless with inertial reference object 2, realize not having towing like this in the laboratory and controlled, thereby can carry out the test of not having each part performance index of towing control and unified performance.For fear of with the interference of hanging the quality inspection suspension, hang transition bracing frame 4 by a spacecraft simulation object and connect the spacecraft simulation object.In addition, for rocking,, need be installed in the vacuum tank to reduce the disturbance of gas molecule because it is highly sensitive.
Claims (2)
1. non-towing control double-torsion pendulum test device, comprise vacuum tank, spacecraft simulation object (3), inertial reference object (2), there is not towing controller (7), thruster (8) and capacitance displacement sensor, spacecraft simulation object (3), inertial reference object (2) and thruster (8) are placed in the vacuum tank, capacitance displacement sensor is measured the displacement information of spacecraft simulation object (3) relative inertness Reference (2), send it to nothing towing controller (7), do not have towing controller (7) and drive thruster (8) according to displacement information, thruster (8) produces thrust and imposes on spacecraft simulation object (3), realize bit shift compensation, it is characterized in that, described spacecraft simulation object (3) is suspended by first hitch, and described inertial reference object (2) is suspended by second hitch.
2. a kind of non-towing control double-torsion pendulum test device according to claim 1 is characterized in that, described first and second hitches are suspension.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2009100611856A CN101510094B (en) | 2009-03-20 | 2009-03-20 | Non-towing control double-torsion pendulum test device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2009100611856A CN101510094B (en) | 2009-03-20 | 2009-03-20 | Non-towing control double-torsion pendulum test device |
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| Publication Number | Publication Date |
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| CN101510094A CN101510094A (en) | 2009-08-19 |
| CN101510094B true CN101510094B (en) | 2011-04-20 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102011018684B4 (en) | 2011-04-26 | 2019-05-16 | Manfred A. Gregor | Micro amplitude meters |
| CN102589917B (en) * | 2012-02-23 | 2014-09-24 | 华中科技大学 | Free-falling body verification device for drag-free spacecraft |
| CN104787362B (en) * | 2015-03-31 | 2017-01-18 | 中国科学院长春光学精密机械与物理研究所 | Sensor quantization method for space optics effective loading force disturbance simulation source actuator |
| CN111596648B (en) * | 2020-06-10 | 2021-09-24 | 中国科学院微小卫星创新研究院 | On-orbit experimental verification method for acceleration mode drag-free control |
| CN113447180B (en) * | 2021-05-10 | 2022-03-22 | 中山大学 | Torsion pendulum testing device based on differential capacitor and torsion pendulum decoupling reading method |
| CN113740929B (en) * | 2021-08-16 | 2022-06-21 | 华中科技大学 | Ground testing device and method for space inertial sensor |
| CN113848751A (en) * | 2021-09-22 | 2021-12-28 | 中山大学 | Ground simulation system of drag-free spacecraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5256942A (en) * | 1992-05-07 | 1993-10-26 | Wood Ross C | Stabilization system for a freely rotatable platform |
| CN2277094Y (en) * | 1996-12-27 | 1998-03-25 | 唐世明 | Combination navigation inertial platform |
| WO1999060425A1 (en) * | 1998-05-19 | 1999-11-25 | Manfred Alexander Gregor | One-armed torsion balance |
| CN2893758Y (en) * | 2005-12-07 | 2007-04-25 | 李智 | Torsional pendulum movement |
-
2009
- 2009-03-20 CN CN2009100611856A patent/CN101510094B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5256942A (en) * | 1992-05-07 | 1993-10-26 | Wood Ross C | Stabilization system for a freely rotatable platform |
| CN2277094Y (en) * | 1996-12-27 | 1998-03-25 | 唐世明 | Combination navigation inertial platform |
| WO1999060425A1 (en) * | 1998-05-19 | 1999-11-25 | Manfred Alexander Gregor | One-armed torsion balance |
| CN2893758Y (en) * | 2005-12-07 | 2007-04-25 | 李智 | Torsional pendulum movement |
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| CN101510094A (en) | 2009-08-19 |
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