Hypersonic Vehicle Global Stabilization via Feedback Linearization
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Solution Overview
Problem
The global stabilization of non-minimum phase hypersonic vehicles remains a challenging problem due to the lack of specific design methods for dynamic compensators, which are necessary for stabilizing unstable internal dynamics.
Innovation Solution
A method and system for global stabilization control of hypersonic vehicles involving the construction of a longitudinal dynamic model, transformation of equilibrium points, variable decomposition, and determination of a control law based on feedback linearization theory to stabilize both external and internal dynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional stabilization methods are used for non-minimum phase systems, then system stabilization may be achieved under specific structure matching conditions, but no specific design method for dynamic compensator is provided and the assumption of stabilizability remains unconfirmed
Solution Approach 1:
The patent segments the control design into distinct modules: coordinate transformation to move equilibrium points, variable decomposition to separate state variables, and dynamic compensator construction with specific analytical forms. This segmentation provides a systematic design methodology that resolves the complexity issue by breaking down the unsolved dynamic compensator design into manageable steps with confirmed stabilizability conditions.
2Reliability
If the system is shifted to minimum phase after introducing dynamic compensator, then stabilization may be achieved, but the construction method and analytical form of dynamic compensator are not presented
Solution Approach 1:
The patent applies parameter changes by transforming the equilibrium points to the origin through coordinate transformation, and by defining specific analytical forms for the dynamic compensator parameters (γ1, γ2, λ11, λ10). These parameter transformations and specifications make the controller implementable by providing concrete design guidelines, thus resolving the ease of manufacture issue.
3Reliability
If global stabilization control is implemented for non-minimum phase hypersonic vehicle, then both external and internal states can be stabilized, but requires complex transformation and decomposition processes
Solution Approach 1:
The patent applies preliminary action by performing coordinate transformation to move equilibrium points to the origin before designing the control law, and by decomposing variables to separate state variables before constructing the dynamic compensator. These preliminary transformations simplify the subsequent control design and provide a systematic path to global stabilization, resolving the complexity issue through structured preparatory steps.
Data Source
AI summary
Method and system for global stabilization control of a hypersonic vehicle. The method can include constructing a longitudinal dynamic model of a non-minimum phase hypersonic vehicle; translating a non-zero equilibrium point of the hypersonic vehicle to the origin of coordinates by transformation of coordinates to transform the longitudinal dynamic model, where the transformed longitudinal dynamic model includes an output dynamic model and an internal dynamic model; performing variable decomposition on the transformed longitudinal dynamic model by state decomposition and constructing an auxiliary system model using decomposed variables, where the auxiliary system model includes output dynamics and internal dynamics; and determining a control law based on a feedback linearization theory according to the output dynamics and realizing the global stabilization control of the hypersonic vehicle with the control law. The present disclosure enables the global stabilization control of a non-minimum phase hypersonic vehicle.