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Time division multiplexing manner based small satellite orbit control method

A time-division multiplexing and satellite orbit technology, which is applied to the propulsion system device of space navigation vehicle, the guidance device of space navigation vehicle, etc., can solve the problems of high cost and low efficiency, and achieve economical cost saving, easy installation, and simple and reliable system. Effect

Active Publication Date: 2018-01-19
CHANGGUANG SATELLITE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] In order to solve the problems of high cost and low efficiency in existing small satellite orbit control, the present invention provides a small satellite orbit control method based on time division multiplexing

Method used

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  • Time division multiplexing manner based small satellite orbit control method
  • Time division multiplexing manner based small satellite orbit control method
  • Time division multiplexing manner based small satellite orbit control method

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specific Embodiment approach 1

[0056] In order to verify the effectiveness of the orbit control method of the present invention, it can be verified by ground simulation flight experiments. Select a 1N thruster suitable for small satellite control, set the angular momentum of the three-axis momentum wheel to 1N.m.s, the control period of the thruster orbit control is 2s, the orbit control reference value is 1s, and the control period of the momentum wheel attitude control is 0.125 s, the switch line of the attitude control pulse unloading whole star angular momentum unilateral limit cycle is ±0.1N.m.s, the orbit control duration is 280s, and the ground simulation flight simulation is carried out.

[0057] The angular momentum change curve of the satellite is as follows Figure 5 shown. From Figure 5 It can be seen that the angular momentum of the whole star does not exceed 0.5N.m.s, which ensures that the attitude is controlled. In addition, because the system deviation setting of the X-axis is relativel...

specific Embodiment approach 2

[0060] It has been implemented on the in-orbit Jilin-1 video satellite of Changguang Satellite Technology Co., Ltd. Considering the actual task requirements, during the implementation, the satellite orbit was raised by 430m, the implementation time was from 13:03:54 to 13:04:10, and the calibrated control coefficient was 1.00.

[0061] During the orbit control process of the satellite, the angular momentum curve of the whole star changes as follows: Figure 8 shown. according to Figure 8 It can be seen that before the start of satellite orbit control, the angular momentum of the Y-axis is relatively high, and an attitude control pulse is unloaded to ensure the controllability of the reaction momentum wheel to the satellite.

[0062] The rotational speed of the reaction momentum wheel changes as Figure 9 shown. From Figure 9 It can be seen that when the orbit control method of the present invention is used for orbit control, the rotational speed of the reaction momentum...

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Abstract

The invention discloses a time division multiplexing manner based small satellite orbit control method, and relates to the mall satellite orbit control field, which can solve the problem that small satellite orbits are high in cost and low in efficiency. The method includes: obliquely arranging four thrusters on a lower surface of a small satellite in a symmetrical manner, wherein the first thruster and the second thruster are symmetrical with respect to an X axis, the third thruster and the fourth thruster are symmetrical with respect to the X axis, the first thruster and the fourth thrusterare symmetrical with respect to a Y axis, and the second thruster and the third thruster are symmetrical with respect to the Y axis; keeping the inclined angles of the four thrusters in a range of -55degrees-+55 degrees, wherein the inclined angles and directions of the first thruster and the second thruster are identical, and the inclined angles and directions of the third thruster and the fourth thruster are identical; using a retroaction momentum wheel to control an attitude of the small satellite, and using attitude control pulse to unload the angular momentum of the satellite; and correcting a control coefficient by using an on-orbit calibration manner. The time division multiplexing manner based small satellite orbit control method is low in cost, can save resources, and is simple and reliable.

Description

technical field [0001] The invention relates to the technical field of small satellite orbit control, in particular to a small satellite orbit control method based on time division multiplexing. Background technique [0002] As the development of small satellites becomes more and more popular, the problem of its orbit control (referred to as orbit control) needs to be solved urgently. The key to satellite orbit control is to solve the problem of attitude stability during the operation of the orbit control thruster. Traditional large satellites are generally equipped with about 10 to 16 attitude control thrusters for attitude stability during orbit control, plus 2 to 4 orbit control thrusters, making the design of the entire propulsion system complex and expensive. For small satellites, the required thrust is smaller, which means that its thrusters have higher requirements for precision machining than those with large thrusts, and the resulting economic costs are also higher...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/28B64G1/40
Inventor 范林东徐开戴路王国刚胡建龙刘萌萌
Owner CHANGGUANG SATELLITE TECH CO LTD
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