Near-earth orbit determining method based on atmospheric drag acceleration measurement

A technology of acceleration measurement and atmospheric resistance, applied in the field of navigation, can solve the problems of weak GNSS signal, susceptibility to interference and spoofing, operation dependence, etc., achieve wide application prospects, achieve low cost, and improve the effect of anti-interference

Active Publication Date: 2018-09-18
BEIHANG UNIV
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Problems solved by technology

However, the operation of the GNSS system relies on expensive ground monitoring and maintenance facilities; and the

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  • Near-earth orbit determining method based on atmospheric drag acceleration measurement
  • Near-earth orbit determining method based on atmospheric drag acceleration measurement
  • Near-earth orbit determining method based on atmospheric drag acceleration measurement

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[0083] The following will combine figure 1 And the technical scheme further describes the specific implementation process of the present invention in detail.

[0084] The present invention is a method for determining low earth orbit based on atmospheric drag acceleration measurement, see figure 1 As shown, the steps are as follows:

[0085] Step 1: Measurement of atmospheric drag acceleration

[0086] The non-conservative force received by the spacecraft is measured by a three-axis accelerometer, and the component array of the non-conservative force received by the spacecraft in the spacecraft body coordinate system is obtained:

[0087]

[0088] In the above formula, a bx Represents the component of the non-conservative force received by the spacecraft in the x-axis direction of the spacecraft body coordinate system, similarly a by , A bz They are the components of the non-conservative force received by the spacecraft in the y and z directions of the spacecraft body coordinate sy...

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Abstract

The invention discloses a near-earth orbit determining method based on atmospheric drag acceleration measurement, comprising the following steps: 1, carrying out preparation work; 2, measuring atmospheric drag acceleration; 3, carrying out non-conservative acceleration vector unitization; 4, giving orbit determination initial value; 5, constructing an orbit determination equation; and 6, solving the orbit determination equation. Through the steps, a triaxial accelerometer and a star sensor loaded on a spacecraft are used for acquiring the non-conservative force accelerated speed suffered by the spacecraft during in-orbit operation and the coordinate transformation matrix of a spacecraft body relative to a geocentric inertial coordinate, an orbit determination iteration computation initialvalue is acquired under the circular orbit assumption, the non-conservative force acceleration is corrected by utilizing atmospheric to acquire rotation term speed unit vector, the orbit equation is constructed and is solved by utilizing an orbit predictor and a numerical method, so that high-precision orbit determination is realized. The method can be independently used on the spacecraft, and isnot disturbed by the electromagnetic environment, is low cost and easy to achieve and can be widely applied to low earth orbit spacecraft.

Description

technical field [0001] The invention provides a method for determining a near-earth orbit based on the measurement of atmospheric resistance acceleration, which relates to a method for determining the orbit of a near-earth aircraft by measuring the acceleration of atmospheric resistance, and belongs to the technical field of navigation. Background technique [0002] The automation, autonomy, and intelligence of spacecraft are important directions for future spacecraft development. The autonomous operation and self-management of the spacecraft, on the one hand, can greatly reduce the dependence on the ground system, while reducing the operating cost of the mission, and improve the operation efficiency; on the other hand, it can greatly enhance and improve the function and performance of the spacecraft . Autonomous navigation of spacecraft is one of the key technologies to realize the autonomy of spacecraft. For spacecraft operating in low-Earth orbit, navigation based on th...

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Application Information

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IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 孙秀聪张睿
Owner BEIHANG UNIV
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