A Method for Determining Low-Earth Orbit Based on Measurement of Atmospheric Drag Acceleration
A technology of acceleration measurement and atmospheric resistance, which is applied in the field of navigation, can solve the problems of being unable to get rid of the threat of electronic weapons, being susceptible to interference and deception, and weak GNSS signals, so as to achieve the effects of low cost, avoiding errors, and avoiding orbit determination errors
Active Publication Date: 2021-09-28
BEIHANG UNIV
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[0083] The following will combine figure 1 and the technical solution further describe the specific implementation process of the present invention in detail.
[0084] The present invention is based on a method for determining low-Earth orbit based on atmospheric resistance acceleration measurement, see figure 1 As shown, the steps are as follows:
[0085] Step 1: Atmospheric resistance acceleration measurement
[0086] The non-conservative force suffered by the spacecraft is measured by the three-axis accelerometer, and the component array of the non-conservative force suffered by the spacecraft in the spacecraft body coordinate system is obtained:
[0087]
[0088] In the above formula, a bx Indicates the component of the non-conservative force suffered by the spacecraft in the x-axis direction of the spacecraft body coordinate system, similarly a by , a bz are the components of the non-conservative force suffered by the spacecraft in the y and z directions of the spac...
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A low-Earth orbit determination method based on atmospheric resistance acceleration measurement, the steps are as follows: 1: preparation work; 2: measurement of atmospheric resistance acceleration; 3: non-conservative force acceleration vector unitization; : Construct the orbit determination equation; Sixth: Solve the orbit determination equation. Through the above steps, the present invention uses the three-axis accelerometer and star sensor carried by the spacecraft to obtain the non-conservative force acceleration and the coordinate transformation matrix of the spacecraft body relative to the earth-centered inertial coordinate system when the spacecraft is in orbit. Under the orbit assumption, the initial value of the iterative calculation of orbit determination is obtained, and the acceleration of the non-conservative force is corrected by the atmospheric rotation term to obtain the velocity unit vector. The orbit determination equation is constructed and solved by orbit predictor and numerical method to achieve high-precision orbit determination. The method can be used independently on the spacecraft without being disturbed by the electromagnetic environment, is low in cost and easy to implement, and is widely applicable to low-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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IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 孙秀聪张睿
Owner BEIHANG UNIV