Combined attitude determination method for UPF (user port function) algorithm optimized by DNA (deoxyribonucleic acid) algorithm
An algorithm and attitude determination technology, applied in attitude control, instrumentation, adaptive control, etc., can solve problems such as nonlinear noise and non-Gaussian of the system
Inactive Publication Date: 2015-06-24
自然资源部国土卫星遥感应用中心
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Problems solved by technology
[0004] The technical problem of the present invention is: to overcome the deficiencies of the prior art, to propose a combined attitude determination method based on the UPF algorithm optimized by the DNA algorithm, to solve the problem of system nonlinearity and noise non-Gaussian, to quickly obtain high-precision attitude information , and can accurately estimate gyro drift, and realize long-term and high-precision combined attitude determination of various types of spacecraft
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[0079] Such as figure 1 Shown, the specific implementation steps of the present invention are as follows:
[0080] Step 1, using the inertial gyroscope to measure the inertial measurement data, using the gyroscope output data to compensate the inertial measurement data, and then obtaining the carrier attitude information through attitude calculation;
[0081] Preferably, using the gyro drift estimated by the information fusion algorithm to compensate ε in the inertial measurement data ω=K×V+ε+ζ.
[0082] Described step 1 specifically comprises the following steps:
[0083] Step 1.1. Set the initial pose as Calculate the initial attitude quaternion q(0) matrix:
[0084]
[0085] Step 1.2. Update the attitude quaternion matrix as:
[0086] q ( n + 1 ) = { cos Δφ 2 I + sin ...
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The invention discloses a combined attitude determination method for a UPF (user port function) algorithm optimized by a DNA (deoxyribonucleic acid) algorithm. The method comprises the following steps of compensating inertial measurement information by adopting gyro output data, and obtaining carrier attitude information through an attitude solution; obtaining special interval astronomic attitude information by utilizing astronomic measurement information and through a determination algorithm; and finally fusing the astronomic attitude information and the carrier attitude information by utilizing a UPF algorithm optimized by the DNA algorithm, solving system nonlinear and noise non-Gaussian problems, solving high precision carrier attitude information, estimating gyro drift, and feeding back and correcting the carrier attitude and compensating the gyro drift; finally realizing eliminating inert in real-time and on-line correction for the gyro random error of the astronomic combination navigation system based on the astronomic measurement information, and finishing long-term and high-precision combined attitude determination for a spacecraft..
Description
technical field [0001] The invention relates to the technical field of combined attitude determination of spacecraft, in particular to a combined attitude determination method based on a UPF algorithm optimized by a DNA algorithm, which can be used for high-precision combined attitude determination of various spacecraft. Background technique [0002] In order to meet the urgent needs of space-based earth observation, weapon precision strikes, and space exploration and development, spacecraft such as various earth satellites, deep space probes, manned spacecraft, ballistic missiles, and launch vehicles must have autonomous operation and management capabilities. High-precision autonomous attitude determination is the core technical bottleneck of spacecraft autonomous operation and management. At present, the high-precision autonomous attitude determination of spacecraft cannot be independently realized by any navigation method. The pure inertial navigation system can provide ...
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IPC IPC(8): G05D1/08G05B13/04
Inventor 唐新明全伟谢俊峰徐梁祝小勇赵利平付兴科
Owner 自然资源部国土卫星遥感应用中心