Identification and control integrated method for reconstructing fault satellite attitude control function through nanosatellite

A fault and satellite technology, which is applied in attitude control, space navigation equipment, space navigation aircraft, etc., can solve the problems such as the inability to obtain the attitude dynamics model of the combined body, and the failure of the satellite attitude control function reconstruction task to be carried out smoothly. Achieve the effect of improving efficiency and improving control accuracy

Active Publication Date: 2017-03-15
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

Since the mass characteristic parameter information of the faulty satellite is unknown in advance, the nano-satellite cannot obtain an accurate attitude dynamic model of the assembly, which makes the task of reconstructing the faulty satellite's attitude control function difficult to carry out smoothly

Method used

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  • Identification and control integrated method for reconstructing fault satellite attitude control function through nanosatellite
  • Identification and control integrated method for reconstructing fault satellite attitude control function through nanosatellite
  • Identification and control integrated method for reconstructing fault satellite attitude control function through nanosatellite

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Embodiment

[0094] Taking the task of attaching a nano-satellite to the surface of a faulty satellite to reconstruct its attitude control function as an example, the effectiveness of the integrated identification and control method in the present invention is illustrated. The moment of inertia matrix J of the combination is described in the calculation coordinate system as:

[0095]

[0096] At the beginning of identification, the initial attitude angular velocity of the assembly is ω 0 =[3 4 2] T (° / s), ie

[0097] ω 0 =[0.0524 0.0698 0.0349] T (rad / s)

[0098] The initial attitude angular acceleration is zero. Fundamental frequency ω of Fourier series f =0.01Hz, the total control time is 1000s, N m =4.

[0099] Consider the fitting constraints proposed by the initial angular velocity and initial angular acceleration of the assembly, the zero-value constraint conditions proposed by the terminal angular velocity and terminal angular acceleration of the assembly, and the state v...

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Abstract

The invention discloses an identification and control integrated method for reconstructing a fault satellite attitude control function through a nanosatellite. A nanosatellite is attached to the surface of a fault satellite with unknown kinetic parameters, and attitude motion control is studied. The method mainly comprises the following steps: establishing an identification equation of a nanosatellite-fault satellite combination rotational inertia matrix; designing a combination expected attitude motion track meeting an initial terminal state value constraint and a state value amplitude constraint; and designing a combination attitude tracking controller based on a real-time attitude dynamics model. While the combination rotational inertia matrix is obtained, the fault satellite can be de-spun by the nanosatellite. Through the identification and control integrated method, parameter identification and attitude control are realized, the efficiency of reconstruction of the fault satellite attitude control function through a nanosatellite is improved, and the control accuracy of the nanosatellite on the fault satellite is improved effectively. The method has important application in the task of cognizing and controlling a fault satellite with unknown parameters through a nanosatellite.

Description

【Technical field】 [0001] The invention belongs to the technical field of aerospace dynamics and control, and relates to an integrated identification and control method for nano-satellite reconstruction fault satellite attitude control functions. 【Background technique】 [0002] Satellites in space that fail due to thruster failure or fuel exhaustion are in an uncontrolled free-floating state, so they cannot continue to perform tasks effectively, but some payloads such as cameras and antennas can still continue to work. If the pointing function of the faulty satellite can be reconstructed and the payload on it can be reused, a new satellite that can work normally in orbit can be quickly obtained at a relatively low cost, thereby turning space junk into new resources and relaunching Compared with a new replacement satellite, this method of on-orbit reconstruction to obtain a new satellite will greatly reduce the development and launch costs of space equipment. [0003] Nano-sa...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 罗建军韩楠袁建平马卫华朱战霞王明明徐晨
Owner NORTHWESTERN POLYTECHNICAL UNIV
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