Small satellite orbit control optimization method based on orbit control deviation moment coefficient calibration

A technology of torque coefficient and optimization method, which is applied in the field of small satellites, can solve the problems of flywheel saturation and the influence of the attitude of the whole satellite, etc., and achieve the effect of improving the control amount

Active Publication Date: 2020-12-08
CHANGGUANG SATELLITE TECH CO LTD
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  • Description
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  • Application Information

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Problems solved by technology

Therefore, as the orbit control time becomes longer, the angular momentum of the deviation will lead to the saturation of the angular momentum of the flywheel group, which will affect the attitude security of the whole star.

Method used

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  • Small satellite orbit control optimization method based on orbit control deviation moment coefficient calibration
  • Small satellite orbit control optimization method based on orbit control deviation moment coefficient calibration
  • Small satellite orbit control optimization method based on orbit control deviation moment coefficient calibration

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Embodiment 1

[0056] A small satellite orbit control optimization method based on orbit control deviation moment coefficient calibration, the small satellite orbit control optimization method includes the following steps:

[0057] Step 1: Determine the telemetry data in the orbit control mission of the satellite in orbit;

[0058] Step 2: Calibrate the orbit control deviation moment coefficient according to the telemetry data in step 1;

[0059] Step 3: Carry out the orbit control task according to the calibration result of the orbit control deviation moment coefficient in step 2, and adjust the attitude of the satellite to the attitude of the orbit control task;

[0060] Step 4: Perform angular momentum bias on each axis according to the calibration result of the deviation moment coefficient;

[0061] Step 5: Execute the orbit control task. After the orbit control task is completed, adjust the satellite to a long-term working attitude.

[0062] Further, the calibration of the track contr...

Embodiment 2

[0107] Calibration example of deviation moment coefficient

[0108] During the open-loop orbit control mission of the small satellite, the angular momentum change caused by the deviation torque is absorbed by the flywheel set. Therefore, in the orbit control task, the change of angular momentum caused by the deviation torque is analyzed through the change of the rotational speed of the flywheel.

[0109] A certain type of small satellite is equipped with an orbit control thruster, and three flywheels are respectively installed on the X, Y, and Z axes. The relevant parameters of a certain orbit control process during its orbit are shown in the following table:

[0110] Table 1 Changes of relevant parameters in post-orbit tasks

[0111] serial number project value 1 Satellite mass / kg 67.7 2 Orbital semi-major axis / km 6944 3 flywheel angular momentum 500mNms@6000rpm 4 Orbit control time / s 134 5 Change of semi-major axis / m 352.54 ...

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Abstract

The invention discloses a small satellite orbit control optimization method based on orbit control deviation moment coefficient calibration. The method comprises the steps of step 1, determining telemetry data in an orbit control task of an on-orbit satellite; step 2, calibrating an orbit control deviation moment coefficient according to the telemetry data in step 1; step 3, performing the orbit control task according to the calibration result of the orbit control deviation moment coefficient in step 2, and adjusting the attitude of the satellite to an orbit control task attitude; step 4, performing angular momentum bias on all shafts according to the calibration result of the deviation moment coefficient; and step 5, executing the orbit control task, and after the orbit control task is completed, adjusting the satellite to a long-term working attitude. The orbit control task optimization method is targeted for the conditions that only an orbit control thruster is installed on a smallsatellite and the control capacity of a flywheel set is limited.

Description

technical field [0001] The invention belongs to the technical field of small satellites; in particular, it relates to an orbit control optimization method for small satellites based on calibration of orbit control deviation moment coefficients. Background technique [0002] Satellites with a mass less than 1000kg are called small satellites. In order to save development costs, the propulsion system of small satellites is usually equipped with only one orbit control thruster. Since there is no attitude control thruster, the orbit control mode of small satellites adopts open-loop control mode. Attitude stability in orbit control missions is ensured by flywheels. Due to various factors, the thrust vector of the thruster in the orbit control mission cannot strictly pass through the center of mass of the satellite, and the deviation of the thrust vector relative to the center of mass will form a bias moment. The bias moment acts on the star in the orbit control mission, which wi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242B64G1/244B64G1/245
Inventor 胡建龙范林东孟德利戴路徐开王国刚刘东宸
Owner CHANGGUANG SATELLITE TECH CO LTD
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