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A high-precision attitude control method combining magnetic control and jet control with low working fluid

A technology of jet control and attitude control, applied in attitude control, control/adjustment system, non-electric variable control, etc., can solve problems such as unsatisfactory results, save jet working fluid, reduce disturbance torque, and avoid low precision Effect

Active Publication Date: 2019-04-09
BEIJING INST OF CONTROL ENG
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Problems solved by technology

For this reason, in the stage of carrying out the key technology research and ground demonstration of a gravity field measurement satellite in my country, the research group has grasped the key link of magnetron control, and has tried the PID magnetron control method based on the traditional magnetic moment distribution and the magnetron control method based on the H∞ theory. method and magnetic control method based on convex polyhedron theory and other control algorithms, but the results are not ideal, and the consumption of propulsion fluid is much higher than that of similar foreign satellites GRACE

Method used

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  • A high-precision attitude control method combining magnetic control and jet control with low working fluid
  • A high-precision attitude control method combining magnetic control and jet control with low working fluid
  • A high-precision attitude control method combining magnetic control and jet control with low working fluid

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Embodiment 1

[0033] Take a low-orbit satellite with an orbital inclination around 90 degrees as an example, such as figure 1 Shown, concrete steps of the present invention are as follows:

[0034] (1) According to the three-axis attitude error and angular velocity error, use the PID control law to calculate the expected control torque; set the attitude error along the three axes of the body coordinate system (rolling, pitching, and yaw axes in turn, the same below) as [φ c θ c ψ c ], the angular velocity error is The PID coefficients of the three axes are proportional coefficients K px , K py , K pz , differential coefficient K dx , K dy , K dz , integral coefficient K ix , K iy , K iz , then the desired control torque of the three axes is calculated as follows:

[0035]

[0036]

[0037]

[0038] (2) According to the size of the geomagnetic induction intensity vector in the three-axis coordinate component of the satellite body coordinate system, determine which axis...

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Abstract

The invention relates to a high-precision attitude control method combining magnetic control and jet control with labor-saving. The steps are: (1) calculate the expected control torque by using the PID control law according to the three-axis attitude error and the angular velocity error; (2) calculate the expected control torque according to the geomagnetic induction The real-time distribution of the intensity vector in the three-axis coordinate components of the satellite body coordinate system determines which axis attitudes implement magnetic control and which axis attitudes implement jet control; (3) use the small disturbance magnetic moment distribution algorithm to calculate the three-axis magnetic moments to fully satisfy the magnetic control The desired control torque of the shaft, while reducing the disturbance torque generated by the magnetron; (4) Using the jet phase plane algorithm to calculate the jet pulse width of the jet control shaft. The attitude control of the present invention has high accuracy, low working medium consumption, simple calculation and easy engineering realization.

Description

technical field [0001] The invention relates to a high-precision attitude control method combining magnetic control and jet control, which saves working fluid, and is suitable for all spacecraft that use the combination of magnetic control and jet control to achieve high-precision three-axis attitude stability, such as gravity field measurement satellites and high-speed aircraft. Safe scientific exploration satellites, etc. This method can also be applied to all other spacecraft with momentum wheels or CMGs that require magnetic control or specific operating modes of spacecraft. Background technique [0002] For gravimetric satellites, the task of the accelerometer is to measure the effect of non-conservative forces on the motion of the star's center of mass. It is characterized by high sensitivity and strict requirements on the amplitude and frequency of high-frequency and low-frequency vibrations, disturbances, etc. encountered in the task. Based on this requirement, the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/32B64G1/10G05D1/08
CPCG05D1/0825B64G1/10B64G1/1021B64G1/105B64G1/24B64G1/32B64G1/245
Inventor 刘其睿苟兴宇涂俊峰谈树萍
Owner BEIJING INST OF CONTROL ENG
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