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Initialization method of elliptical orbit satellite formation configuration under multiple constraints

An initialization method and satellite formation technology, applied in the field of spacecraft guidance and control, can solve problems such as difficulty in solving, application limitations, and small convergence radius

Active Publication Date: 2019-02-22
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

The indirect method strictly satisfies the first-order necessary condition of optimality in theory, but in the actual calculation process, due to the high sensitivity to the initial guess of the co-state, the convergence radius is small, and the solution is difficult, so the application is limited

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  • Initialization method of elliptical orbit satellite formation configuration under multiple constraints
  • Initialization method of elliptical orbit satellite formation configuration under multiple constraints
  • Initialization method of elliptical orbit satellite formation configuration under multiple constraints

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Embodiment 1

[0173] This embodiment discloses a method for initializing the formation configuration of elliptical orbit satellites under multi-constraint conditions. The parameters of the reference orbit are as follows: semi-major axis a=8378km, inclination i=15°, ascending node right ascension Ω=45° and perigee angle Distance ω=30°. At the beginning of control, assume that the initial true anomaly f 0 =0, the parameter k within the fly-around constraint is 0.5, and the FOV range of the surveillance camera is 60°×60°. The slave star is a micro-satellite with a mass of 10 kg, equipped with a three-dimensional electric propulsion device, and the maximum thrust value in each direction is 100mN. The time taken to release (denoted as t f ) is set to 1500 seconds, and the initial state of the slave star is orbital eccentricity e=0.05.

[0174] Step 1: Deduce the analytical solution of the T-H equation in the true anomaly domain through classical orbit dynamics and coordinate transformation. ...

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Abstract

The invention discloses an initialization method of an elliptical orbit satellite formation configuration under multiple constraints, relates to satellite formation configuration initialization methods, and belongs to the fields of spacecraft guidance and control. The method comprises that an analytical solution is derived from a T-H equation of a real anomaly domain via typical track dynamics andcoordinate transformation, dynamic constraint and periodic fly-around constraint are analyzed, monitoring camera visual field constraint and thrust amplitude constraint are established, a multi-constraint optimal control model of formation is established and solved in a Gaussian pseudo-spectral method, a co-state value in random time is obtained, the completeness of the spacecraft structure is monitored in real time, and the fuel consumption and highest amplitude of a propelling system are reduced by increasing the eccentricity and initialization time. Thus, the elliptical orbit satellite formation configuration can be initialized under multiple constraints, and effective optimal control is realized under the multiple constrains by initialization.

Description

technical field [0001] The invention relates to a satellite formation configuration initialization method, in particular to an optimal initialization method for establishing an elliptical orbit satellite formation under multi-constraint conditions, and belongs to the field of spacecraft guidance and control. Background technique [0002] In recent years, satellite formation technology has attracted much attention due to its broad application fields in the future. With its strong technical advantages and broad application prospects, the satellite cluster formation flight technology based on small satellites has been widely concerned and recognized by relevant institutions in the fields of military, industry, commerce, and scientific research. The double-star formation is the most basic form of satellite formation. The formation is composed of a main star and a slave star. The slave star performs on-orbit monitoring tasks around the main star. Risks of extravehicular activiti...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10
CPCG05D1/104
Inventor 翟光杨少伟张景瑞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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