Semi-physical simulation test system for sun-oriented control

A semi-physical simulation and directional control technology, applied in general control systems, control/regulation systems, electrical testing/monitoring, etc., can solve problems such as inability to conduct ground simulation verification, high cost, and inconvenience in conducting tests.

Active Publication Date: 2016-06-15
SHANGHAI XINYUE METER FACTORY
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  • Application Information

AI Technical Summary

Problems solved by technology

This kind of simulation method has the best simulation accuracy and effectiveness, but the simulation environment is complicated to build, expensive, requires professional operators to operate the equipment, and is limited by the power supply and gas supply on the air flotation platform, so it cannot carry out simulation verification for a long time
At

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  • Semi-physical simulation test system for sun-oriented control
  • Semi-physical simulation test system for sun-oriented control
  • Semi-physical simulation test system for sun-oriented control

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Embodiment Construction

[0024] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the following examples are only used to illustrate the present invention but not to limit the scope of the present invention.

[0025] The schematic block diagram of an embodiment of the semi-physical simulation test system for sun-oriented control under any posture of the invention is as follows: figure 2 As shown, including solar sensor equivalents, geomagnetic field simulators, earth simulators, star simulators, motion simulators, PXI acquisition control computers, dynamics simulators, data distribution units, telemetry and remote injection machines, databases, Display terminal, CAN bus cable network, optical fiber reflective memory network and TCP / IP network, and on-board products (on-board computer system, gyroscope, infrared horizon, star sensor, three-axis magnetometer, jet thruster controller, Inertial whee...

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Abstract

A semi-physical simulation test system for sun-oriented control comprises a satellite-borne computer system, a gyro, an infrared horizon instrument, a star sensor, a three-axis magnetometer, an actuator and a target simulator. The target simulator simulates the space environment. A motion simulator simulates the attitude motion of an aircraft. The satellite-borne computer system performs attitude and control quantity calculation according to measurement data acquired by single measurement machines, and outputs the attitude and control quantity to the actuator. The semi-physical simulation test system further comprises a sun sensor equivalent device, a dynamic geomagnetic field simulator, a target simulator, a motion simulator, a PXI acquisition control computer, a dynamics simulator, a data distribution unit, a telemetry, remote control and remote injection machine, a database, a display terminal, a CAN bus network and an optical fiber reflective memory network. The problem that ground simulation verification of sun-oriented control cannot be carried out under abnormal attitude rolling of an aircraft in the prior art is solved. The semi-physical simulation test system has the beneficial effect that the test authenticity and effectiveness are improved.

Description

technical field [0001] The invention belongs to the technical field of ground simulation test and test of an aircraft attitude and orbit control system, in particular to a semi-physical simulation test system for sun-oriented control. Background technique [0002] The launch of the aircraft's solar panels into orbit and capture of the sun, as well as the long-term sun-oriented control of the aircraft's solar panels, are the fundamental guarantees for ensuring the energy supply required for the aircraft's orbit and the realization of its mission. Especially when the attitude of the aircraft is abnormal and the solar panels cannot be oriented to the sun normally, if it cannot be oriented to the sun for a long time, the flight cannot complete the scheduled on-orbit mission due to insufficient energy, or even the end of the life of the aircraft. Therefore, usually the aircraft attitude and orbit control system will design a corresponding emergency plan for the abnormal attitud...

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Application Information

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IPC IPC(8): G05B17/02G05B23/02B64G7/00
Inventor 陈浩桑小冲卢翔艾奇柳明旻黄海军
Owner SHANGHAI XINYUE METER FACTORY
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