CN106777469B - Ground physical simulation verification system and method for flexible vibration evaluation of flexible satellite - Google Patents
Ground physical simulation verification system and method for flexible vibration evaluation of flexible satellite Download PDFInfo
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Abstract
The invention discloses a ground physical simulation verification system for flexible satellite flexible vibration evaluation, which comprises: the simulation solar cell array simulates different coupling interference effects of the solar cell array on a satellite central body by adjusting different installation angles of the simulation solar cell array and the satellite central body; and the flexible characteristic measurement and identification subsystem is connected with the simulation solar cell array through a circuit and is used for measuring the flexible vibration deformation information of the simulation solar cell array. The invention designs a brand new flexible vibration physical test model; on the basis of a flexible vibration physical simulation test model, a high-precision zero-gravity simulation system, a pose following system and an interference excitation simulation subsystem are added to ensure that the simulation system is matched with the outer space working environment of a satellite; and a test performance evaluation subsystem and a monitoring subsystem are added to evaluate the flexible vibration result and perform simulation test evaluation on the control precision of the satellite control system.
Description
Technical Field
The invention relates to the field of flexible satellite control precision simulation evaluation research, in particular to a ground physical simulation verification system and a ground physical simulation verification method for flexible satellite flexible vibration evaluation.
Background
When the satellite runs in outer space or performs maneuvering, maneuvering speed is high, maneuvering tracks are not smooth enough, flexible vibration occurs to the solar cell array, the attitude motion and the orbital motion of the satellite are affected, normal maneuvering of the satellite cannot be achieved, expected attitude and expected position cannot be achieved, and higher requirements are provided for flexible vibration of the flexible satellite. For the requirement, the traditional flexible vibration analysis cannot provide a complete quantification scheme, cannot further evaluate the precise control of the flexible satellite, and cannot realize ground real-time simulation on the consequences caused by the flexible vibration of the satellite.
Disclosure of Invention
The invention provides a ground physical simulation verification system and a ground physical simulation verification method for flexible vibration evaluation of a flexible satellite, which solve the problem of quantification of flexible vibration of a solar cell array in the space movement or maneuvering process of the flexible satellite and improve the precision of a control system.
In order to achieve the above object, the present invention provides a ground physics simulation verification system for flexible satellite flexural vibration estimation, which is characterized in that the system comprises:
the simulation solar cell array simulates different coupling interference effects of the solar cell array on a satellite central body by adjusting different installation angles of the simulation solar cell array and the satellite central body;
and the flexible characteristic measurement and identification subsystem is connected with the simulation solar cell array through a circuit and is used for measuring the flexible vibration deformation information of the simulation solar cell array.
The above system further comprises:
the interference excitation simulation subsystem simulates and outputs coupling interference torque of flexible vibration of the simulated solar cell array on a satellite central body;
the system comprises a high-precision zero-gravity simulation system and a pose follow-up subsystem, wherein the high-precision zero-gravity simulation system provides a zero-gravity environment for simulating the solar cell array in a suspension mode;
and the input end of the triaxial air floating platform is connected with the simulation solar cell array, the interference excitation simulation subsystem, the high-precision zero-gravity simulation system and the pose follow-up subsystem through a circuit, and interference torque generated by flexible vibration of the simulation solar cell array on a satellite central body under the condition of zero gravity is obtained through integration and analysis.
The above system further comprises: and the input end of the test evaluation subsystem is connected with the triaxial air-floating platform through a circuit, receives interference torque generated by flexible vibration of the simulated solar cell array on a satellite central body under the zero gravity condition, performs filtering analysis on vibration measurement information of the simulated solar cell array, triaxial attitude angles and triaxial attitude angular velocity information of the triaxial air-floating platform, and compares the vibration measurement information with expected vibration information of the simulated solar cell array and the triaxial attitude angles and triaxial attitude angular velocity information of the triaxial air-floating platform, so that the effects of the flexible vibration suppression method and the attitude control method are evaluated.
The above system further comprises: and the monitoring subsystem is in communication connection with the three-axis air floating platform, detects the real-time three-axis attitude angle and three-axis attitude angular velocity information of the three-axis air floating platform, compares the information with an expected attitude angle and an expected attitude angular velocity instruction, and determines the attitude control precision of the satellite attitude control system.
The monitoring subsystem is also in communication connection with and detects working states of the simulation solar cell array, the high-precision zero-gravity simulation system, the pose following subsystem and the interference excitation simulation subsystem, and the simulation solar cell array, the high-precision zero-gravity simulation system, the pose following subsystem and the interference excitation simulation subsystem are respectively adjusted in real time, or work is suspended or stopped according to the working states.
The system also comprises a monitoring subsystem, wherein the input end of the monitoring subsystem is in communication connection with the three-axis air floatation platform, the simulated solar cell array, the high-precision zero-gravity simulation system, the pose following subsystem and the interference excitation simulation subsystem, the output end of the monitoring subsystem is in communication connection with the test evaluation subsystem, and the working states of the three-axis air floatation platform, the simulated solar cell array, the high-precision zero-gravity simulation system, the pose following subsystem and the interference excitation simulation subsystem are output to the test evaluation subsystem, carrying out filter analysis on the vibration measurement information of the analog solar cell array and the three-axis attitude angle and the three-axis attitude angular velocity information of the three-axis air floating platform, and comparing the three-axis attitude angle information with the three-axis attitude angular velocity information of the three-axis air floatation platform with the expected simulated solar cell array vibration information, thereby evaluating the effects of the flexible vibration suppression method and the attitude control method.
The verification method of the ground physical simulation verification system for the flexible satellite flexible vibration assessment is characterized by comprising the following steps:
simulating a solar cell array to set an angle;
the flexibility characteristic measurement and identification subsystem measures the flexibility vibration deformation information of the simulated solar cell array.
The verification method further comprises:
the interference excitation simulation subsystem simulates and outputs coupling interference torque of flexible vibration of the simulation solar cell array on a satellite central body;
the high-precision zero-gravity simulation system and the pose following subsystem provide a zero-gravity environment for simulating the solar cell array in a suspension mode;
the triaxial air flotation platform integrates and analyzes the interference torque generated by the flexible vibration of the simulated solar cell array on the satellite central body under the condition of zero gravity received by the interference excitation simulation subsystem, the simulated solar cell array, the high-precision zero-gravity simulation system and the pose follow-up subsystem.
The verification method further comprises: the test evaluation subsystem receives an interference moment generated by flexible vibration of a simulated solar cell array on a satellite central body under the condition of zero gravity output by the triaxial air floating platform, and working states of the triaxial air floating platform, the simulated solar cell array, the high-precision zero-gravity simulation system, the pose servo subsystem and the interference excitation simulation subsystem, carries out filtering analysis on vibration measurement information of the simulated solar cell array, triaxial attitude angles and triaxial attitude angular speed information of the triaxial air floating platform, and compares the vibration measurement information with expected vibration information of the simulated solar cell array and the triaxial attitude angles and triaxial attitude angular speed information of the triaxial air floating platform, so that effects of a flexible vibration suppression method and a pose control method are evaluated. .
The verification method further comprises: the monitoring subsystem monitors the working states of the simulation solar cell array, the high-precision zero-gravity simulation system, the pose follow-up subsystem and the interference excitation simulation subsystem, respectively adjusts the simulation solar cell array, the high-precision zero-gravity simulation system, the pose follow-up subsystem and the interference excitation simulation subsystem in real time, or stops working according to the working states, detects the real-time three-axis attitude angle and three-axis attitude angular velocity information of the three-axis air floatation platform, compares the information with expected attitude angle and attitude angular velocity instructions, and determines the attitude control precision of the satellite attitude control system.
Compared with the prior art, the ground physical simulation verification system and the verification method for flexible vibration evaluation of the flexible satellite have the advantages that firstly, a brand new flexible vibration physical test model is designed according to the reason that the flexible vibration of the flexible satellite occurs; secondly, on the basis of a flexible vibration physical simulation test model, a high-precision zero-gravity simulation system, a pose following system and an interference excitation simulation subsystem are added to ensure that the simulation system is matched with the outer space working environment of the satellite, and the test result is more convincing; and finally, adding a test performance evaluation subsystem and a monitoring subsystem, evaluating a flexible vibration result, and carrying out simulation test evaluation on the control precision of the satellite control system.
Drawings
FIG. 1 is a system block diagram of a first embodiment of a ground physics simulation verification system for flexural vibration estimation of a flexible satellite according to the present invention;
FIG. 2 is a system block diagram of a second embodiment of the ground physics simulation verification system for flexural vibration estimation of flexible satellites according to the present invention;
FIG. 3 is a schematic structural diagram of a vibration test frame suitable for the ground physics simulation verification system of the present invention;
FIG. 4 is a system block diagram of the trial evaluation subsystem of the present invention;
FIG. 5 is a schematic diagram of a testing method of a performance verification and analysis system of a high-precision attitude control system.
Detailed Description
The following further describes specific embodiments of the present invention with reference to the drawings.
As shown in fig. 1, the present invention discloses a first embodiment of a ground physics simulation verification system for flexural vibration evaluation of a flexible satellite, the system comprising: the system comprises a simulation solar cell array, a high-precision zero-gravity simulation system 120, a pose following subsystem 130, an interference excitation simulation subsystem 140, a flexibility characteristic measurement and identification subsystem 150, a test evaluation subsystem 160 and a three-axis air floatation platform 180.
The simulated solar array 110 simulates different coupling interference effects of the solar array on a satellite central body by adjusting different installation angles of the simulated solar array and the satellite central body, thereby providing a plurality of verification system characteristics for the attitude control system.
The flexible characteristic measurement and identification subsystem 150 is electrically connected to the simulated solar cell array 110, and is configured to measure the flexible vibration deformation information of the simulated solar cell array 110, analyze the mechanical characteristics of the simulated solar cell array 110, including the natural frequency and the modal damping, and provide data input for the subsequent flexible vibration characteristic identification system.
The output end of the interference excitation simulation subsystem 140 is connected to the triaxial air-floating platform 180, and is used for simulating and outputting the coupling interference moment of the flexible vibration of the simulated solar cell array 110 to the central body of the satellite according to the installation angle and the flexible bending condition of the simulated solar cell array 110.
The high-precision zero-gravity simulation system 120 and the pose tracking subsystem 130 provide a zero-gravity environment for the simulated solar cell array 110 by means of suspension. The high-precision zero-gravity simulation system 120 and the pose tracking subsystem 130 form a test frame as shown in fig. 3, and the test frame comprises a portal frame 313, an air floatation shaft system 310, an air floatation bearing 311, an air foot 312, an air floatation ring 309, a sling 306, a force sensor 307, a hanger 305 and a connecting point 308.
The input end circuit of the triaxial air-floating platform 180 is connected with the analog solar cell array 110, the interference excitation analog subsystem 140, the high-precision zero-gravity analog system 120 and the pose follower subsystem 130, receives the analog interference torque output by the interference excitation analog subsystem 140, and the position, attitude angle and attitude angular velocity data of the high-precision zero-gravity analog system 120 and the pose follower subsystem 130, integrates the data, and analyzes to obtain the interference torque generated by the flexible vibration of the analog solar cell array 110 on the central body of the satellite under the condition of zero gravity.
The input end of the test evaluation subsystem 160 is connected with the triaxial air-floating platform 180 through a circuit, receives the interference torque generated by the flexible vibration of the simulated solar cell array on the central body of the satellite under the condition of zero gravity output by the triaxial air-floating platform 180, performs filtering analysis on the vibration measurement information of the simulated solar cell array, the triaxial attitude angle and the triaxial attitude angular velocity information of the triaxial air-floating platform, compares the vibration measurement information with the expected vibration information of the simulated solar cell array and the triaxial attitude angle and the triaxial attitude angular velocity information of the triaxial air-floating platform, and further evaluates the effects of the flexible vibration suppression method and the attitude control method.
The verification method of the first embodiment of the ground physical simulation verification system for flexural vibration evaluation of the flexible satellite comprises the following steps:
the flexible vibration simulation test platform first angles the simulated solar array 110. The flexural characteristics measurement and identification subsystem 150 measures flexural vibration deformation information of the solar cell array 110.
In addition, the disturbance excitation simulation subsystem 140 simulates and outputs a coupling disturbance moment simulating the flexible vibration of the solar cell array 110 to the satellite hub. The high-precision zero-gravity simulation system 120 and the pose tracking subsystem 130 provide a zero-gravity environment for the simulated solar cell array 110 by means of suspension. The triaxial air-bearing platform 180 integrates and analyzes the interference moment generated by the flexible vibration of the simulated solar cell array 110 on the central body of the satellite under the condition of zero gravity received from the interference excitation simulation subsystem 140, the simulated solar cell array 110, the high-precision zero-gravity simulation system 120 and the pose following subsystem 130.
The test evaluation subsystem 160 receives the interference moment generated by the flexible vibration of the simulated solar cell array on the central body of the satellite under the condition of zero gravity output by the triaxial air floating platform 180, and the working states of the triaxial air floating platform 180, the simulated solar cell array 110, the high-precision zero-gravity simulation system 120, the pose following subsystem 130 and the interference excitation simulation subsystem 140, and performs filtering analysis and evaluation.
As shown in fig. 2, the present invention discloses a second embodiment of a ground physics simulation verification system for flexural vibration evaluation of a flexible satellite, the system comprising: the system comprises a simulation solar cell array 210, a high-precision zero-gravity simulation system 220, a pose following subsystem 230, an interference excitation simulation subsystem 240, a flexibility characteristic measurement and identification subsystem 250, a test evaluation subsystem 260, a monitoring subsystem 270 and a three-axis air floatation platform 280.
The simulated solar array 210 simulates different coupling interference effects of the solar array on a satellite central body by adjusting different installation angles of the simulated solar array and the satellite central body, thereby providing a plurality of verification system characteristics for the attitude control system.
The flexible characteristic measurement and identification subsystem 250 is electrically connected to the analog solar cell array 210, and is configured to measure flexible vibration deformation information of the analog solar cell array 210, analyze mechanical characteristics of the analog solar cell array 210, including natural frequency and modal damping, and provide data input for a subsequent flexible vibration characteristic identification system.
The output end of the interference excitation simulation subsystem 240 is connected to the triaxial air floating platform 280, and is used for simulating and outputting the coupling interference moment of the flexible vibration of the simulated solar cell array 210 to the central body of the satellite according to the installation angle and the flexible bending condition of the simulated solar cell array 210.
The high-precision zero-gravity simulation system 220 and the pose tracking subsystem 230 provide a zero-gravity environment for the simulated solar cell array 210 in a suspended manner.
The input end circuit of the triaxial air-floating platform 280 is connected with the simulated solar cell array 210, the interference excitation simulation subsystem 240, the high-precision zero-gravity simulation system 220 and the pose follower subsystem 230, receives the simulated interference torque output by the interference excitation simulation subsystem 240, and the position, attitude angle and attitude angular velocity data of the high-precision zero-gravity simulation system 220 and the pose follower subsystem 230, integrates the data, and analyzes to obtain the interference torque generated by the flexible vibration of the simulated solar cell array 210 on the central body of the satellite under the condition of zero gravity.
The monitoring subsystem 270 is in communication connection with the three-axis air-floating platform 280, and is used for simulating the solar cell array 210, the high-precision zero-gravity simulation system 220, the pose tracking subsystem 230 and the interference excitation simulation subsystem 240. The monitoring subsystem 270 detects the working states of the simulated solar cell array 210, the high-precision zero-gravity simulation system 220, the pose tracking subsystem 230 and the interference and excitation simulation subsystem 240, and respectively adjusts, suspends or stops the working of the simulated solar cell array 210, the high-precision zero-gravity simulation system 220, the pose tracking subsystem 230 and the interference and excitation simulation subsystem 240 in real time according to the working states.
The monitoring subsystem 270 also detects and detects the three-axis attitude angle and the three-axis attitude angular velocity information of the three-axis air-floating platform 280 in real time for filtering analysis, and compares the three-axis attitude angle and the three-axis attitude angular velocity information with the expected three-axis attitude angle and the three-axis attitude angular velocity information of the three-axis air-floating platform, thereby evaluating the effect of the attitude control method.
The output end of the monitoring subsystem 270 is in communication connection with the test evaluation subsystem 260, and outputs the working states of the three-axis air floatation platform 280, the simulated solar cell array 210, the high-precision zero-gravity simulation system 220, the pose tracking subsystem 230 and the interference excitation simulation subsystem 240 to the test evaluation subsystem 260.
The input end of the test evaluation subsystem 260 is electrically connected with the triaxial air floating platform 280 and the monitoring subsystem 270, receives the interference moment generated by the flexible vibration of the simulated solar cell array on the central body of the satellite under the condition of zero gravity output by the triaxial air floating platform 280, and the working state of each module output by the monitoring subsystem 270, and carries out filtering analysis on the vibration measurement information of the simulated solar cell array, the triaxial attitude angle and the triaxial attitude angular velocity information of the triaxial air floating platform, and compares the vibration measurement information with the expected vibration information of the simulated solar cell array and the triaxial attitude angle and the triaxial attitude angular velocity information of the triaxial air floating platform, so as to evaluate the effects of the flexible vibration suppression method and the attitude control method.
The second verification method of the ground physical simulation verification system for flexible satellite flexural vibration assessment includes:
the simulated solar array 210 is angled. The flexural characteristics measurement and identification subsystem 250 measures flexural vibration deformation information of the simulated solar cell array 210.
In addition, the disturbance excitation simulation subsystem 240 simulates and outputs a coupling disturbance moment simulating the flexible vibration of the solar array 210 to the satellite hub. The high-precision zero-gravity simulation system 220 and the pose tracking subsystem 230 provide a zero-gravity environment for the simulated solar cell array 210 in a suspended manner.
The triaxial air-bearing platform 280 integrates and analyzes the interference torque generated by the flexible vibration of the simulated solar cell array 210 on the satellite central body under the condition of zero gravity received from the interference excitation simulation subsystem 240, the simulated solar cell array 210, the high-precision zero-gravity simulation system 220 and the pose tracking subsystem 230.
The test evaluation subsystem 260 receives the interference moment generated by the flexible vibration of the simulated solar cell array on the central body of the satellite under the zero gravity condition output by the triaxial air floating platform 280, and the working states of the triaxial air floating platform 280, the simulated solar cell array 210, the high-precision zero-gravity simulation system 220, the pose following subsystem 230 and the interference excitation simulation subsystem 240, and performs filtering analysis and evaluation.
The monitoring subsystem 270 monitors the working states of the simulated solar cell array 210, the high-precision zero-gravity simulation system 220, the pose tracking subsystem 230 and the interference excitation simulation subsystem 240, respectively adjusts, suspends or stops the simulated solar cell array 210, the high-precision zero-gravity simulation system 220, the pose tracking subsystem 230 and the interference excitation simulation subsystem 240 in real time according to the working states, and detects the motion of the three-axis air-floating platform 280 and the performance of the satellite attitude control system.
Fig. 3 is a schematic structural diagram of a vibration test frame suitable for an embodiment of the ground physics simulation verification system. The vibration test frame, i.e., the high-precision zero-gravity simulation system 120 and the pose tracking subsystem 130, comprises: a gantry 313, an air bearing shafting 310, an air bearing 311, an air foot 312, an air ring 309, a sling 306, a force sensor 307, a hanger 305 and a connection point 308.
The gantry 313 comprises a support and a disc structure mounted on top of the support.
The air floating ring 309 is arranged on the gantry 313 disc structure corresponding to the edge of the disc structure.
The air-floating shaft system 310 is disposed at the center of the disk structure.
The air foot 312 is disposed on the air floating ring 309.
A cross bar is arranged between the air floating shaft system 310 and the air foot 312.
The air bearing 311 is sleeved outside the cross rod.
The sling 306 is hung below the air bearing 311, the sling 306 is divided into two sections, and the two sections are connected through a connecting point 308.
The force sensor 307 is arranged at the location of the connection point 308.
The simulated solar cell array 301 is suspended below the hanger 305.
The three-axis air bearing platform 302 includes a base 304 fixed on a plane, and a stage 303 supported on the base 304 by air bearing. The analog solar cell array 301 is fixedly connected with the platform 303 in a mechanical mode.
Fig. 4 shows an embodiment of a test evaluation subsystem of the ground physics simulation verification system for flexural vibration evaluation of flexible satellites according to the present invention. The test evaluation subsystem comprises: theoretical model unit 401, experimental data storage and processing unit 402, performance criterion unit 403, data processing and analysis unit 404 and output display unit 405.
The output end of the theoretical model unit 401 is connected with the input end of the performance criterion unit 403, the output end of the performance criterion unit 403 is connected with the input end of the performance criterion unit 403, and the performance criterion unit 403 receives theoretical data and test data to obtain the relationship between the theoretical data and the test data. The input end circuit of the data processing and analyzing unit 404 is connected with the output end of the performance criterion unit 403, and the output polarity of the performance criterion unit 403 is processed to obtain the evaluation result of the test data. The input end circuit of the output display unit 405 is connected with the output end of the data processing and analyzing unit 404, and receives the evaluation result to display and output the evaluation result.
As shown in fig. 5 and fig. 2, a schematic diagram of a testing method of a performance verification and analysis system of a high-precision attitude control system is shown.
Wherein, the simulated solar cell array 511 and the triaxial air-floating platform 512 form a rigid-flexible coupling system 510.
The three-axis air-bearing platform 512 is connected with an interference excitation simulation subsystem 520. The disturbance excitation simulation subsystem 520 simulates and outputs the coupling disturbance moment of the flexible vibration of the simulated solar cell array 511 to the satellite central body according to the installation angle and the flexible bending condition of the simulated solar cell array 511.
The three-axis air floating platform 512 and the output end are connected to a high-precision attitude control system 530, and the three-axis air floating platform 512 integrates and analyzes to obtain the interference moment of the flexible vibration of the solar cell array 210 on the central body of the satellite under the condition of zero gravity. The high-precision attitude control system 530 performs attitude control on the analog solar cell array 511 according to the output of the triaxial air-floating platform 512.
The output end of the high-precision attitude control system 530 is connected to an attitude control system performance verification system 540, and the attitude control system performance verification system 540 receives the control performance data of the high-precision attitude control system 530 for verification and feeds the control performance data back to the high-precision attitude control system 530.
The output of the attitude control system performance verification system 540 is connected to the attitude control system performance analysis system 550, which receives the control performance data for analysis to obtain performance analysis evaluation and parameter optimization improvement signals, which are fed back to the high-precision attitude control system 530 to optimize the control of the analog solar cell array 511 and the satellite attitude.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (9)
1. A ground physics simulation verification system for flexural vibration assessment of a flexible satellite, the system comprising:
the simulation solar cell array simulates different coupling interference effects of the solar cell array on a satellite central body by adjusting different installation angles of the simulation solar cell array and the satellite central body;
the flexible characteristic measurement and identification subsystem is connected with the simulation solar cell array through a circuit and used for measuring the flexible vibration deformation information of the simulation solar cell array;
the interference excitation simulation subsystem simulates and outputs coupling interference torque of flexible vibration of the simulated solar cell array on a satellite central body;
the system comprises a high-precision zero-gravity simulation system and a pose follow-up subsystem, wherein the high-precision zero-gravity simulation system provides a zero-gravity environment for simulating the solar cell array in a suspension mode;
and the input end of the triaxial air floating platform is connected with the simulation solar cell array, the interference excitation simulation subsystem, the high-precision zero-gravity simulation system and the pose follow-up subsystem through a circuit, and interference torque generated by flexible vibration of the simulation solar cell array on a satellite central body under the condition of zero gravity is obtained through integration and analysis.
2. The ground physics simulation verification system for flexural vibration evaluation of flexible satellites of claim 1 further comprising: and the input end of the test evaluation subsystem is connected with the triaxial air-floating platform through a circuit, receives interference torque generated by flexible vibration of the simulated solar cell array on a satellite central body under the zero gravity condition, performs filtering analysis on vibration measurement information of the simulated solar cell array, triaxial attitude angles and triaxial attitude angular velocity information of the triaxial air-floating platform, and compares the vibration measurement information with expected vibration information of the simulated solar cell array and the triaxial attitude angles and triaxial attitude angular velocity information of the triaxial air-floating platform, so that the effects of the flexible vibration suppression method and the attitude control method are evaluated.
3. The ground physics simulation verification system for flexural vibration evaluation of flexible satellites of claim 1 further comprising: and the monitoring subsystem is in communication connection with the three-axis air floating platform, detects the real-time three-axis attitude angle and three-axis attitude angular velocity information of the three-axis air floating platform, compares the information with an expected attitude angle and an expected attitude angular velocity instruction, and determines the attitude control precision of the satellite attitude control system.
4. The ground physics simulation verification system for flexural vibration evaluation of flexible satellites of claim 3 wherein said monitoring subsystem is further communicatively coupled to and detects the operating conditions of the simulated solar array, the high accuracy zero gravity simulation system, the pose following subsystem and the disturbance excitation simulation subsystem, and adjusts, suspends or stops the operation of the simulated solar array, the high accuracy zero gravity simulation system, the pose following subsystem and the disturbance excitation simulation subsystem in real time according to the operating conditions.
5. The ground physics simulation verification system for flexural vibration evaluation of flexible satellites of claim 2, further comprising a monitoring subsystem, wherein the input end of the monitoring subsystem is communicatively connected with the triaxial air-floating platform, the simulated solar cell array, the high-precision zero-gravity simulation system, the pose following subsystem and the interference excitation simulation subsystem, the output end of the monitoring subsystem is communicatively connected with the test evaluation subsystem, the working states of the triaxial air-floating platform, the simulated solar cell array, the high-precision zero-gravity simulation system, the pose following subsystem and the interference excitation simulation subsystem are output to the test evaluation subsystem, the vibration measurement information of the simulated solar cell array and the triaxial attitude angle and triaxial attitude angular velocity information of the triaxial air-floating platform are filtered and analyzed, and compared with the expected vibration information of the simulated solar cell array and the triaxial attitude angle and triaxial attitude angular velocity information of the triaxial air-floating platform, thereby evaluating the effects of the flexural vibration suppression method and the attitude control method.
6. A verification method of a ground physics simulation verification system for flexural vibration evaluation of flexible satellites according to any one of claims 1 to 5, comprising:
simulating a solar cell array to set an angle;
the flexibility characteristic measurement and identification subsystem measures the flexibility vibration deformation information of the simulated solar cell array.
7. The method of claim 6, further comprising:
the interference excitation simulation subsystem simulates and outputs coupling interference torque of flexible vibration of the simulation solar cell array on a satellite central body;
the high-precision zero-gravity simulation system and the pose following subsystem provide a zero-gravity environment for simulating the solar cell array in a suspension mode;
the triaxial air flotation platform integrates and analyzes the interference torque generated by the flexible vibration of the simulated solar cell array on the satellite central body under the condition of zero gravity received by the interference excitation simulation subsystem, the simulated solar cell array, the high-precision zero-gravity simulation system and the pose follow-up subsystem.
8. The method of claim 7, further comprising: the test evaluation subsystem receives an interference moment generated by flexible vibration of a simulated solar cell array on a satellite central body under the condition of zero gravity output by the triaxial air floating platform, and working states of the triaxial air floating platform, the simulated solar cell array, the high-precision zero-gravity simulation system, the pose servo subsystem and the interference excitation simulation subsystem, carries out filtering analysis on vibration measurement information of the simulated solar cell array, triaxial attitude angles and triaxial attitude angular speed information of the triaxial air floating platform, and compares the vibration measurement information with expected vibration information of the simulated solar cell array and the triaxial attitude angles and triaxial attitude angular speed information of the triaxial air floating platform, so that effects of a flexible vibration suppression method and a pose control method are evaluated.
9. The method of claim 7, further comprising: the monitoring subsystem monitors the working states of the simulation solar cell array, the high-precision zero-gravity simulation system, the pose follow-up subsystem and the interference excitation simulation subsystem, respectively adjusts the simulation solar cell array, the high-precision zero-gravity simulation system, the pose follow-up subsystem and the interference excitation simulation subsystem in real time, or stops working according to the working states, detects the real-time three-axis attitude angle and three-axis attitude angular velocity information of the three-axis air floatation platform, compares the information with expected attitude angle and attitude angular velocity instructions, and determines the attitude control precision of the satellite attitude control system.
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| CN112115545B (en) * | 2020-08-11 | 2021-08-24 | 北京航空航天大学 | Flexible satellite attitude maneuver control method based on binomial approximate model |
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