A method of deflection satellite adaptive neural network sliding gesture control method
A flexible satellite and neural network technology, applied in the field of flexible satellite adaptive neural network sliding mode attitude control, can solve problems such as reducing system stability, flexible satellite attitude fluctuation, etc., and achieve high attitude control accuracy and stability, Reduce chattering, good robustness
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
Method used
Image
Examples
specific Embodiment approach 1
[0021] Specific embodiment one: a kind of flexible satellite self-adaptive neural network sliding mode attitude control method of this embodiment is specifically prepared according to the following steps:
[0022] Step 1, establishing a satellite attitude model with a moving antenna; establishing a dynamic model of a flexible satellite attitude by using a mixed coordinate method;
[0023] Step 2. According to the attitude dynamics model of the flexible satellite, ignore the high-order coupling items related to the mode in the attitude dynamic equation of the flexible satellite, consider the inertial directional flight of the satellite, and adopt the small angle assumption at the same time to obtain the simplified flexible Satellite attitude dynamic equation;
[0024] Step 3, according to the simplified attitude dynamic equation of the flexible satellite, utilize the RBF neural network to design the sliding mode attitude controller;
[0025] Step 4, further adopting the RBF ne...
specific Embodiment approach 2
[0029] Specific embodiment two: the difference between this embodiment and specific embodiment one is: set up the satellite attitude model with moving antenna in the step one; Adopt mixed coordinate method to establish flexible satellite attitude dynamics model specifically as follows:
[0030] (1), the attitude dynamics equation containing two sailboards and a moving antenna has the following form (in the equation (2-1), the first is the rotation equation of the satellite body, and the second is the rotation equation of the antenna):
[0031]
[0032]
[0033] Among them, I s ∈ R 3×3 is the moment of inertia matrix of the star; ω s =[ω 1 ,ω 2 ,ω 3 ] T ∈ R 3 is the attitude angular velocity vector of the system relative to the inertial system and projected and decomposed in the system; ω 1 , ω 2 and ω 3 Respectively, the attitude angular velocity of the system relative to the inertial system and the projection decomposition of the X, Y and Z axes in the system; ...
specific Embodiment approach 3
[0038] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is that in step two, according to the dynamic model of the flexible satellite attitude, the high-order coupling items related to the mode in the dynamic equation of the flexible satellite attitude are ignored, Considering the inertial directional flight of the satellite, and adopting the assumption of a small angle, the specific process of the simplified attitude dynamic equation of the flexible satellite is obtained as follows:
[0039] (1) Neglecting the high-order coupling items related to the mode in the dynamic equation of the flexible satellite attitude, the dynamic model of the flexible satellite attitude is simplified as:
[0040]
[0041] In the formula,
[0042]
[0043]
[0044]
[0045] D is the sum of interference and uncertainty, and D is bounded; F is an unknown nonlinear term;
[0046] (2) Considering the inertial directional flight of the sa...
PUM
Abstract
Description
Claims
Application Information
- R&D Engineer
- R&D Manager
- IP Professional
- Industry Leading Data Capabilities
- Powerful AI technology
- Patent DNA Extraction
Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.
© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com