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Magnetic control and air injection control combined high-accuracy attitude control method capable of saving working medium

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, and achieve the effect of saving jet working medium and avoiding low precision

Active Publication Date: 2016-11-09
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

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  • Magnetic control and air injection control combined high-accuracy attitude control method capable of saving working medium
  • Magnetic control and air injection control combined high-accuracy attitude control method capable of saving working medium
  • Magnetic control and air injection control combined high-accuracy attitude control method capable of saving working medium

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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] T c x = K p x φ c + ...

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Abstract

The invention relates to a magnetic control and air injection control combined high-accuracy attitude control method capable of saving a working medium. The method includes the steps that firstly, according to a three-axis attitude error and an angular speed error, the expected control moment is calculated through the PID control law; secondly, according to real-time distribution of three-axis coordinate components of a terrestrial magnetic induction intensity vector in a satellite body coordinate system, which axial attitudes are subjected to magnetic control and which axial attitudes are subjected to air injection control are determined; thirdly, the three-axis magnetic moment is calculated through a small-disturbance magnetic moment allocation algorithm, so that the requirement for the expected control moment of a magnetic control shaft is fully met, and meanwhile the disturbance moment generated by magnetic control is reduced; and fourthly, the air injection pulse width of an air injection control shaft is calculated through an air injection phase plane algorithm. By the adoption of the method, the attitude control accuracy is high, the working medium consumption is low, calculation is simple, and a project is easy to achieve.

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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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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