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Spacecraft gravitational acceleration calculation method and orbit control method

A calculation method and technology of spacecraft, applied in the direction of aerospace vehicles, space vehicle guidance devices, aircraft, etc., can solve problems such as the singularity of the earth's gravitational acceleration

Active Publication Date: 2020-08-04
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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Problems solved by technology

[0016] The object of the present invention is to provide a method for calculating the gravitational acceleration of a spacecraft and a method for orbit control, so as to solve the problem that the gravitational acceleration of the spacecraft earth under the fixed connection of the earth calculated by the existing method has a singular problem

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  • Spacecraft gravitational acceleration calculation method and orbit control method
  • Spacecraft gravitational acceleration calculation method and orbit control method
  • Spacecraft gravitational acceleration calculation method and orbit control method

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Embodiment 1

[0053] This embodiment provides a method for calculating the gravitational acceleration of a spacecraft, such as figure 1 As shown, the spacecraft gravitational acceleration calculation method involves the spacecraft orbit control system, which is completed by the spacecraft orbit control system. The spacecraft orbit control system includes a parameter acquisition module and a spacecraft gravitational acceleration calculation module, wherein: the parameter acquisition The module obtains the spherical harmonic coefficient of the earth's gravitational field and The transformation matrix from the earth's inertial system to the earth's fixed connection and the position r of the spacecraft in the Earth's inertial system ECI , and sent to the spacecraft gravitational acceleration calculation module; the spacecraft gravitational acceleration calculation module is based on the conversion matrix from the earth's inertial system to the earth's fixed connection and the position r ...

Embodiment 2

[0077] This embodiment provides a spacecraft orbit control method based on the aerospace orbit control system in the previous embodiment, the spacecraft orbit control method includes the spacecraft gravitational acceleration calculation method in the previous embodiment, specifically including: parameter acquisition The module obtains the spherical harmonic coefficient of the earth's gravitational field and The transformation matrix from the earth's inertial system to the earth's fixed connection and the position r of the spacecraft in the Earth's inertial system ECI , and sent to the spacecraft gravitational acceleration calculation module; the spacecraft gravitational acceleration calculation module is based on the conversion matrix from the earth's inertial system to the earth's fixed connection and the position r of the spacecraft in the Earth's inertial system ECI , to calculate the position of the spacecraft under the fixed connection of the earth:

[0078]

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Abstract

The invention provides a spacecraft gravitational acceleration calculation method and an orbit control method, and provides a spacecraft gravitational acceleration calculation method for eliminating singularity, thereby avoiding a condition that the spacecraft gravitational acceleration calculated by a traditional method is singular. A kinetic model is the basis of spacecraft orbit design and control, and gravitational attraction is an important part forming a near-earth orbit kinetic model. When a traditional calculation method is used for calculating the gravitational acceleration of the spacecraft and the geocentric latitude of the spacecraft is close to 90 degrees, a singular condition exists. In order to enhance the robustness of the algorithm and avoid singularity, the invention provides a novel calculation method.

Description

technical field [0001] The invention relates to the technical field of spacecraft power, in particular to a method for calculating gravitational acceleration of a spacecraft and an orbit control method. Background technique [0002] The dynamic model is the basis of spacecraft orbit design and control, and the gravity of the earth is an important part of the low-Earth orbit dynamic model. Since the earth is an ellipsoid, there is a non-spherical gravitational component in addition to the gravitational force of the earth's gravitational force. Earth's gravity is usually determined using the spherical harmonic model. [0003] The spherical harmonic expansion of the earth's gravitational potential is [0004] [0005] Of which: GM e is the gravitational constant of the earth; R e is the average radius of the earth; r, φ and λ are the distance to the center of the earth, the latitude and longitude of the center of the earth respectively; and is the fully normalized sp...

Claims

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 本立言张锐谢祥华严玲玲刘剑祁海铭赵璟
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS
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