Gain scheduling control method for space rendezvous system considering linearization error
A technology of gain scheduling control and space rendezvous, which is applied in the direction of adaptive control, general control system, control/regulation system, etc., and can solve the time-consuming problems of spacecraft orbit rendezvous missions, etc.
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
Method used
Image
Examples
specific Embodiment approach 1
[0067] Specific embodiment one: the gain scheduling control method of the space rendezvous system considering the linearization error, it comprises the following steps:
[0068] Step 1: When the two spacecraft are performing the rendezvous mission, one spacecraft passively flies in orbit, which is called the target spacecraft; the other spacecraft maneuvers under the action of the control force, and flies to the target spacecraft with different rules. It is called tracking spacecraft; assume that the target spacecraft is running on a circular orbit with a radius of R; for the convenience of description, the orbital coordinate system O-XYZ of the target spacecraft is introduced, its origin O is located at the center of mass of the target spacecraft, and the X axis is along the circular orbit The direction of the radius R, the Y axis is along the direction of tracking the flight of the spacecraft, and the Z axis points out of the orbital plane to form a right-handed coordinate sy...
specific Embodiment approach 2
[0124] Specific embodiment 2: γ corresponding to "the initial relative motion state vector is X(0)" in step 3 described in this embodiment 0 The solution process is:
[0125] For the initial relative motion state vector X(0), γ 0 is the only solution to the nonlinear equation (17):
[0126] ρ ( γ 0 ) X 0 T P ( γ 0 ) X 0 = 1 - - - ( 17 )
[0127] Since P(γ) is monotonic with respect to γ, the nonlinear equation (17) can be solved by dichotomy.
[0128] Other steps are the same as in the first embodiment.
specific Embodiment approach 3
[0129] Specific embodiment three: in the step 3 described in this embodiment mode " gain scheduling controller (15) begins to work in spacecraft orbit rendezvous system, controller (15) according to U 0 → U 1 →…→U N-1 → U N The order of is applied to formula (6)" and the realization process is as follows:
[0130] Set a current variable r, its initial value is r=0 and the corresponding controller is U=U 0 , if r≤N-1, for the relative motion state vector X(t) at each moment, calculate
[0131]
[0132] if Then the gain scheduling controller U=U r+1 And let r=r+1; otherwise gain-scheduled controller U=U r , the relative motion state vector X enters the inner ellipsoid sequentially from the outermost ellipsoid; when the gain scheduling controller switches to U=U N When , the relative motion state vector X enters the innermost ellipsoid, and finally converges to the equilibrium point, and the controller does not switch anymore, that is, there is no need to calculate for...
PUM
![No PUM](https://static-eureka-patsnap-com.libproxy1.nus.edu.sg/ssr/23.2.0/_nuxt/noPUMSmall.5c5f49c7.png)
Abstract
Description
Claims
Application Information
![application no application](https://static-eureka-patsnap-com.libproxy1.nus.edu.sg/ssr/23.2.0/_nuxt/application.06fe782c.png)
- 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