CN103171775B - Angular momentum coupling unloading method based on orbit control interference - Google Patents
Angular momentum coupling unloading method based on orbit control interference Download PDFInfo
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- CN103171775B CN103171775B CN201310037292.1A CN201310037292A CN103171775B CN 103171775 B CN103171775 B CN 103171775B CN 201310037292 A CN201310037292 A CN 201310037292A CN 103171775 B CN103171775 B CN 103171775B
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Abstract
The invention discloses an angular momentum coupling unloading method based on orbit control interference. According to the method, accumulated angular momentum generated in the process of satellite orbit control is absorbed through the method of momentum wheel control, the characteristic that the angular momentum of a momentum wheel in the X direction and the angular momentum of a momentum wheel in the Z direction of a satellite are exchanged every 1/4 period due to orbit control disturbance torque is utilized, the accumulated orbit control angular momentum generated in the Z direction is unloaded through air injection in the X direction, the purpose of orbit control under the condition without air injection control in the Z direction for the satellite is achieved, the accumulated orbit control angular momentum generated in the X direction is unloaded through air injection in the Z direction, the purpose of orbit control under the condition without air injection control in the X direction for the satellite is achieved, and high-precision capture of satellite trails can be achieved. The momentum coupling unloading technology based on the orbit control interference can be used in orbit control of common satellites and can also be used in orbit control of on-orbit under-actuated satellites without X-axis air injection control or Z-axis air injection control, the application fields of the momentum coupling unloading technology can be extended to magnetism unloading from air injection coupling unloading, air injection amounts in the process of satellite orbit control can be reduced, and satellite orbital transfer efficiency can be improved.
Description
Technical field
The present invention relates to a kind of angle momentum coupling discharging method, particularly relate to a kind of angle momentum coupling discharging method based on rail control interference, be mainly used in the momentum management in spacecraft orbit control process and Interference angle momentum discharge, belong to space-flight trajectory control technology.
Background technology
Catch to realize the high-precision recursive orbit that freezes of sun-synchronous orbit spacecraft, when determining to become rail strategy, general employing two pulse becomes the mode of rail, realizes the cooperation control of orbital eccentricity, argument of perigee, guarantees that spacecraft orbit meets the requirement freezing to return.In the long-time orbits controlling process of spacecraft, the general mode adopting direct gas jet attitude to control, eliminates the disturbance torque that precise tracking produces, realizes the gesture stability in spacecraft rail control process, ensures that in spacecraft orbit control process, attitude meets the demands.Once spacecraft loses precise tracking produce the gas puff Z-pinch ability of disturbance torque compared with general orientation, spacecraft cannot carry out orbits controlling, otherwise spacecraft attitude can be caused out of control, and orbits controlling stops.The Interference angle momentum produced in current track control process generally adopts the mode of jet direct unloading, mainly contains about the method for controlling scrolling of sun-synchronous orbit spacecraft and the pertinent literature of spacecraft angular momentum dumping: Wang Xudong etc. describe Chinese Brazilian earth resources satellite high-precision sun synchronization at 2000 18 volumes " Aerospace Control " " orbital acquisition of Chinese Brazilian earth resources satellite and trajectory intersection control " delivered, return Frozen Orbit control policy and scheme; Zhu Jun etc. 2009 18 volumes " Spacecraft TT&C journal " delivered " research of sun-synchronous orbit satellite initial orbit harvesting policy ", this achievement in research incorporation engineering application physical constraint, for the sun-synchronous orbit of characteristics such as there is recurrence, freeze, design its initial orbit harvesting policy; Liu Hui etc. 2004 22 volumes " Aerospace Control " delivered " utilizing air jet system to unload the minimize Propellant Consumption of spacecraft accumulation moment of momentum ", outer the disturbing in moment of momentum process utilizing air jet system to unload spacecraft accumulation is discussed, realizes the problem of minimum loss of working substance.But adopt the method for controlling scrolling of the momentum coupling Unloading Technology of rail control interference to have no report for losing the jet moment in certain direction.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of angle momentum coupling discharging method based on rail control interference is provided, solve when satellite loses X-axis or Z-direction gas puff Z-pinch and cannot carry out long-time orbits controlling problem, achieve satellite high-precision track and catch.
Technical solution of the present invention is: a kind of angle momentum coupling discharging method based on rail control interference, and step is as follows:
(1) ground sends telecommand to satellite, heats to precise tracking on star;
(2) target track data are injected to satellite in ground;
(3) nominal angular momentum and the unloading threshold value of momentum wheel is injected on ground to satellite;
(4) single impulse or two pulse change rail mode are injected to satellite in ground;
(5) the change rail mode injected of ground check, if correct, performs step (6), otherwise according to the process of step (4) again to satellite injection parameter;
(6) the change rail data comprising precise tracking array mode, become the rail time opening, become rail time span and change rail pulse spacing are injected on ground to satellite;
(7) latching valve that ground remote control is opened on star enables precise tracking normally work;
(8) satellite carries out the unloading of rail control interference angle momentum coupling according to the change rail mode received, if what receive is that single impulse becomes rail mode, when satellite waits for that becoming the rail time opening arrives, satellite starts independently to carry out change rail according to the precise tracking array mode received and change rail time span, become rail after 1/4 orbit period, satellite Autonomous judges whether the moment of momentum of satellite X-direction or Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, when satellite X-direction or the moment of momentum of Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, satellite Autonomous adopts the attitude control engine of satellite X-direction or Z-direction to carry out jet unloading, realize the unloading of rail control interference angle momentum coupling, if what accept is that two pulse becomes rail mode, satellite waits for that after completing the work of above-mentioned change rail second time becomes the arrival of rail time, second time become the rail time equal become the rail time opening add become the rail pulse spacing, when second time becomes the arrival of rail time, satellite starts independently to carry out second time according to the precise tracking array mode received and change rail time span and becomes rail, become rail through 1/4 orbit period, satellite Autonomous judges whether the moment of momentum of satellite X-direction or Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, when satellite X-direction or the moment of momentum of Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, satellite Autonomous adopts the attitude control engine of satellite X-direction or Z-direction to carry out jet unloading, realize the unloading of second time rail control interference angle momentum coupling,
(9) become after rail when satellite completes, ground remote control is closed latching valve on satellite, is stopped orbits controlling engine warm-up;
(10) unloading of rail control interference angle momentum coupling is completed.
The present invention's beneficial effect is compared with prior art: the mode that the present invention adopts momentum wheel to control absorbs the accumulation moment of momentum produced in satellite rail control process, utilize the characteristic that rail control disturbance torque makes the moment of momentum of satellite X and Z-direction momentum wheel exchange every 1/4 cycle, the rail control accumulation moment of momentum produced by the jet unloading Z-direction of X-direction, solve satellite without the orbits controlling difficult problem in-Z-direction gas puff Z-pinch situation, the rail control accumulation moment of momentum produced by the jet unloading X-direction of Z-direction, solve satellite without-X to the orbits controlling difficult problem in gas puff Z-pinch situation, achieve satellite high-precision track to catch.The momentum coupling Unloading Technology of rail control interference can adopt in the rail control of general satellite, also the rail control of the drive lacking satellite losing X-axis gas puff Z-pinch is in-orbit applicable to, magnetic dumping can be extended to from jet coupling unloading simultaneously, reduce the jet amount in satellite rail control process, promote Satellite Orbit Maneuver efficiency, there is the good market competitiveness.
Accompanying drawing explanation
Fig. 1 is the graph of a relation of inertial coordinates system and satellite body system of axes;
Fig. 2 is realization flow figure of the present invention.
Detailed description of the invention
Suppose the orbit angular velocity ω of satellite
0, the distrubing moment produced celestial body+Z axis during the work of rail control thruster is T
d.Suppose precise tracking continuous working on a circle track, control start time sets up inertial coordinates system in-orbit, the relation of this system of axes and satellite body system of axes as shown in Figure 1, in figure, Xb, Zb are the coordinate axle that satellite body system of axes is corresponding, X, Z are the coordinate axle that satellite inertial system of axes is corresponding, then the moment of momentum that rail control distrubing moment produces is:
Wherein H
x, H
zthe moment of momentum that after being respectively satellite transit θ angle, X-direction and Z-direction accumulate.
θ is the angle of satellite around orbital motion.
As can be seen here, rail control disturbance torque T
dthe moment of momentum of satellite X and Z-direction was exchanged once every 1/4 cycle, and the disturbance torque of short time rail control can make the angular momentum exchange of X and Z-direction momentum wheel equally.In order to set up fixed point Frozen Orbit, rail phase place etc. is become for change rail time opening, jet pulse length and two pulse and has strict restriction, rail control process considers momentum management technology, by arranging jet unloading threshold value, control satellite health X and Y-axis, coupling angle momentum is uninstalled in time, to recover nominal speed in time at the jet front momentum wheel of next attitude control engine, otherwise continuing rail control can make momentum wheel saturated, loses the ability of three arbor wheel controls.Design momentum coupling Unloading Technology to consider rail control open control point, precise tracking selection and jet time is determined, magnetic dumping ability and jet unloading threshold value, jet interval etc., be beneficial to obtain high-precision fixed point track and catch.
Such scheme, is still suitable for for losing the spacecraft of X to direct jet moment, controls celestial body Z and Y-axis, is uninstalled in time by coupling momentum, realize the long-time orbits controlling of spacecraft.
Realization flow of the present invention as shown in Figure 2, specifically describes as follows:
(1) ground sends telecommand to satellite, heats to precise tracking on star;
(2) target track data are injected to satellite in ground;
(3) nominal angular momentum and the unloading threshold value of momentum wheel is injected on ground to satellite;
(4) single impulse or two pulse change rail mode are injected to satellite in ground;
(5) the change rail mode injected of ground check, if correct, performs step (6), otherwise according to the process of step (4) again to satellite injection parameter;
(6) the change rail data comprising precise tracking array mode, become the rail time opening, become rail time span and change rail pulse spacing are injected on ground to satellite;
(7) latching valve that ground remote control is opened on star enables precise tracking normally work;
(8) satellite carries out the unloading of rail control interference angle momentum coupling according to the change rail mode received, if what receive is that single impulse becomes rail mode, when satellite waits for that becoming the rail time opening arrives, satellite according to receive precise tracking array mode (in order to improve the rail control ability of satellite, devise employing 4 precise tracking around barycenter in the mode of attachment face along satellite body rotational symmetry layout, injected by ground, realize 1, the change rail mode of 2 or 4 thruster various combinations) and become rail time span and start independently to carry out change rail according to target track, become rail after 1/4 orbit period, satellite Autonomous judges whether the moment of momentum of satellite X-direction or Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, when satellite X-direction or the moment of momentum of Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, satellite Autonomous adopts the attitude control engine of satellite X-direction or Z-direction to carry out jet unloading, realize the unloading of rail control interference angle momentum coupling, if what accept is that two pulse becomes rail mode, satellite waits for that after completing the work of above-mentioned change rail second time becomes the arrival of rail time, second time become the rail time equal become the rail time opening add become the rail pulse spacing, when second time becomes the arrival of rail time, satellite is according to the precise tracking array mode received and become rail time span and start independently that carrying out second time according to target track becomes rail, become rail through 1/4 orbit period, satellite Autonomous judges whether the moment of momentum of satellite X-direction or Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, when satellite X-direction or the moment of momentum of Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, satellite Autonomous adopts the attitude control engine of satellite X-direction or Z-direction to carry out jet unloading, realize the unloading of second time rail control interference angle momentum coupling,
The moment of momentum of satellite X-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, satellite Autonomous adopts the attitude control engine of satellite X-direction to carry out jet unloading, the moment of momentum of satellite Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, and satellite Autonomous adopts the attitude control engine of satellite Z-direction to carry out jet unloading.
(9) become after rail when satellite completes, ground remote control is closed latching valve on satellite, is stopped orbits controlling engine warm-up;
(10) unloading of rail control interference angle momentum coupling is completed.
Such as: certain remote sensing satellite loses in-orbit-fault of the jet moment of Z axis, have employed and invention has been 22 Post Orbits controls, complete jet accumulative 8563.8s, complete satisfactorily satellite sun synchronous, return, Frozen Orbit catches the control task with trajectory intersection.
The non-detailed description of the present invention is known to the skilled person technology.
Claims (1)
1., based on an angle momentum coupling discharging method for rail control interference, it is characterized in that step is as follows:
(1) ground sends telecommand to satellite, heats to precise tracking on star;
(2) target track data are injected to satellite in ground;
(3) nominal angular momentum and the unloading threshold value of momentum wheel is injected on ground to satellite;
(4) single impulse or two pulse change rail mode are injected to satellite in ground;
(5) whether the change rail mode injected of ground check is correct, if correct, performs step (6), otherwise according to the process of step (4) again to satellite injection parameter;
(6) the change rail data comprising precise tracking array mode, become the rail time opening, become rail time span and change rail pulse spacing are injected on ground to satellite;
(7) latching valve that ground remote control is opened on star enables precise tracking normally work;
(8) satellite carries out the unloading of rail control interference angle momentum coupling according to the change rail mode received, if what receive is that single impulse becomes rail mode, when satellite waits for that becoming the rail time opening arrives, satellite starts independently to carry out change rail according to the precise tracking array mode received and change rail time span, become rail after 1/4 orbit period, satellite Autonomous judges whether the moment of momentum of satellite X-direction or Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, when satellite X-direction or the moment of momentum of Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, satellite Autonomous adopts the attitude control engine of satellite X-direction or Z-direction to carry out jet unloading, realize the unloading of rail control interference angle momentum coupling, if what accept is that two pulse becomes rail mode, satellite waits for that after completing the work of above-mentioned change rail second time becomes the arrival of rail time, second time become the rail time equal become the rail time opening add become the rail pulse spacing, when second time becomes the arrival of rail time, satellite starts independently to carry out second time according to the precise tracking array mode received and change rail time span and becomes rail, become rail through 1/4 orbit period, satellite Autonomous judges whether the moment of momentum of satellite X-direction or Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, when satellite X-direction or the moment of momentum of Z-direction momentum wheel and the difference of nominal angular momentum exceed unloading threshold value, satellite Autonomous adopts the attitude control engine of satellite X-direction or Z-direction to carry out jet unloading, realize the unloading of second time rail control interference angle momentum coupling,
(9) become after rail when satellite completes, ground remote control is closed latching valve on satellite, is stopped orbits controlling engine warm-up;
(10) unloading of rail control interference angle momentum coupling is completed.
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| CN107499537A (en) * | 2017-07-03 | 2017-12-22 | 中国空间技术研究院 | The spacecraft orbit maneuver motor disturbance torque computational methods under the conditions of mount scheme |
| CN112607065B (en) * | 2020-12-23 | 2023-04-18 | 长春工业大学 | High-precision phase control method based on electric propulsion system |
| CN113212804B (en) * | 2021-04-30 | 2022-07-29 | 北京控制工程研究所 | Rope-tied satellite attitude and angular momentum integrated control method |
| CN115636110B (en) * | 2022-12-15 | 2023-04-07 | 北京航空航天大学 | Continuous orbit maneuvering method of pneumatic satellite |
| CN116280274B (en) * | 2023-04-27 | 2023-10-27 | 中国人民解放军32039部队 | Control method and device for automatic management of GEO satellite angular momentum |
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