Coordinated attitude control of hypersonic flight vehicles based on the coupling analysis

2017 ◽  
Vol 232 (5) ◽  
pp. 1002-1011
Author(s):  
Wubin Zhen ◽  
Yuhui Wang ◽  
Qingxian Wu ◽  
Peng Shao
Keyword(s):  
Attitude Control ◽  
Sampling Method ◽  
Hypersonic Vehicle ◽  
Flight Vehicle ◽  
Statistical Sampling ◽  
Hypersonic Flight ◽  
Flight Vehicles ◽  
Attitude Tracking ◽  
Simulation Results ◽  
Negative Impacts

At hypersonic speed, strong nonlinear couplings will bring enormous challenges to the attitude control of a hypersonic flight vehicle. To reduce the negative impacts of the couplings, a hierarchical coordinated controller is proposed for a generic hypersonic vehicle in this paper. By using a statistical sampling method, a series of coupling analyses between any two different attitude variables groups are studied firstly, and the matrices that describe the coupling degrees are provided. Based on the coupling degree matrices, two coordinated controllers are designed for the attitude angles and angular rates, respectively. The simulation results indicate that the proposed controller can effectively coordinate the coupling impacts, and achieve smooth attitude tracking.

scholarly journals Disturbance observer-based L1 robust tracking control for hypersonic vehicles with T-S disturbance modeling

2016 ◽  
Vol 13 (6) ◽  
pp. 172988141667111 ◽  
Author(s):  
Yang Yi ◽  
Lubing Xu ◽  
Hong Shen ◽  
Xiangxiang Fan
Keyword(s):  
Disturbance Observer ◽  
Tracking Error ◽  
Flight Vehicle ◽  
Longitudinal Models ◽  
Robust Tracking Control ◽  
Hypersonic Flight Vehicle ◽  
Hypersonic Flight ◽  
Flight Vehicles ◽  
Unknown Disturbances ◽  
Exogenous Disturbances

This article concerns a disturbance observer-based L1 robust anti-disturbance tracking algorithm for the longitudinal models of hypersonic flight vehicles with different kinds of unknown disturbances. On one hand, by applying T-S fuzzy models to represent those modeled disturbances, a disturbance observer relying on T-S disturbance models can be constructed to track the dynamics of exogenous disturbances. On the other hand, L1 index is introduced to analyze the attenuation performance of disturbance for those unmodeled disturbances. By utilizing the existing convex optimization algorithm, a disturbance observer-based proportional-integral-controlled input is proposed such that the stability of hypersonic flight vehicles can be ensured and the tracking error for velocity and altitude in hypersonic flight vehicle models can converge to equilibrium point. Furthermore, the satisfactory disturbance rejection and attenuation with L1 index can be obtained simultaneously. Simulation results on hypersonic flight vehicle models can reflect the feasibility and effectiveness of the proposed control algorithm.

scholarly journals Fluid Dynamic Actuators For Satellite Attitude Control

2021 ◽  
Author(s):  
Sobhan Etemadi
Keyword(s):  
Thermal Management ◽  
Thermal Transport ◽  
Attitude Control ◽  
Fluid Dynamic ◽  
Independent Solution ◽  
Design Modification ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Attitude Tracking ◽  
Simulation Results

In this thesis, the application of fluid based actuators for satellite attitude control and thermal management is investigated. The actuator named Pumped Fluid Loop Actuator (PFLA) is examined to satisfy the need for integrated attitude and thermal management systems while considering strict mass and power budgets. A nonlinear voltage-driven control law is formulated and the feasibility of the PFLA for satellite attitude maneuvers is addressed. A high-fidelity PFLA model is developed. The power consumption of the PFLA is examined in the presence of sensor noise. Simulation results demonstrate its feasibility for attitude tracking capabilities of up to ± 0.01° with slew rates of up to 10 °/s. Next, the limitations of existing fluid dynamic actuators are overcome through the design of a novel Patent Pending Pumped Fluid Spherical Actuator (PFSA). The PFSA extends the capabilities of fluid dynamic actuators and allows for satellite attitude control about any arbitrary axis through spherical design, and introduces a fault-tolerant functionality that allows it to be used as a sensor in the event of rate-gyro failure of the attitude determination subsystem. The dynamic model of the PFSA is obtained through computational fluid-dynamics and finite-element analysis using the grid-independent solution. The passive stabilization capabilities of the PFSA are investigated. Simulation results show an order of three-fold reduction in settling time in comparison to existing fluid dynamic actuators. Lastly, a design modification is proposed for PFLA in order to examine its thermal management capabilities. A comprehensive investigation is carried out to perform thermal transport from onboard electronics through conduction and convection. Simulation results demonstrate the advantages of thermal transport while considering fluid rotation inside the PFLA as opposed to stationary fluid.

scholarly journals Guardian Map Approach to Feasible Range of Static Stability Margin of Hypersonic Flight Vehicles with Input Saturation

2020 ◽  
Vol 2020 ◽  
pp. 1-11
Author(s):  
Hao Lei ◽  
Boyi Chen ◽  
Yanbin Liu ◽  
Yuping Lu
Keyword(s):  
Flight Control ◽  
Attitude Control ◽  
Integrated Control ◽  
Input Saturation ◽  
Stability Margin ◽  
Static Stability ◽  
Linear Matrix ◽  
Hypersonic Flight ◽  
Flight Vehicles ◽  
Feasible Range

Static stability margin is a critical parameter in flight control design. The feasible range of it must cover the uncertainty through the flight. To reasonably identify the feasible range of static stability margin in advance, an approach based on guardian maps is proposed for flight control of hypersonic flight vehicles with input saturation. First, the model of hypersonic flight vehicle (HFV) is established as a parametric plant. Then, flying quality requirements for the closed-loop system are formulated as inequality constraints using guardian maps. Moreover, by using linear matrix inequality, the saturation of elevators is taken into account in the integrated control of attitude control. The prescribed minimum of static stability margin that ensures the flying quality of hypersonic flight vehicles with input saturation is obtained. Furthermore, from the prospective of integrated control, it is shown that the feasible range of static stability margin can be enlarged by changing aerodynamic characteristics. The effectiveness of the proposed approach is validated by numerical simulation.

scholarly journals Neural Back-Stepping Control of Hypersonic Flight Vehicle with Actuator Fault

2018 ◽  
Vol 2018 ◽  
pp. 1-5 ◽  
Author(s):  
Qi Wu ◽  
Yuyan Guo
Keyword(s):  
Controller Design ◽  
Fault Tolerant ◽  
Actuator Fault ◽  
Flight Vehicle ◽  
Hypersonic Flight Vehicle ◽  
Hypersonic Flight ◽  
Fault Parameters ◽  
Simulation Results ◽  
Back Stepping Control ◽  
Adaptive Signal

This paper addresses the fault-tolerant control of hypersonic flight vehicle. To estimate the unknown function in flight dynamics, neural networks are employed in controller design. Moreover, in order to compensate the actuator fault, an adaptive signal is introduced in the controller design to estimate the unknown fault parameters. Simulation results demonstrate that the proposed approach could obtain satisfying performance.

scholarly journals Fluid Dynamic Actuators For Satellite Attitude Control

2021 ◽  
Author(s):  
Sobhan Etemadi
Keyword(s):  
Thermal Management ◽  
Thermal Transport ◽  
Attitude Control ◽  
Fluid Dynamic ◽  
Independent Solution ◽  
Design Modification ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Attitude Tracking ◽  
Simulation Results

In this thesis, the application of fluid based actuators for satellite attitude control and thermal management is investigated. The actuator named Pumped Fluid Loop Actuator (PFLA) is examined to satisfy the need for integrated attitude and thermal management systems while considering strict mass and power budgets. A nonlinear voltage-driven control law is formulated and the feasibility of the PFLA for satellite attitude maneuvers is addressed. A high-fidelity PFLA model is developed. The power consumption of the PFLA is examined in the presence of sensor noise. Simulation results demonstrate its feasibility for attitude tracking capabilities of up to ± 0.01° with slew rates of up to 10 °/s. Next, the limitations of existing fluid dynamic actuators are overcome through the design of a novel Patent Pending Pumped Fluid Spherical Actuator (PFSA). The PFSA extends the capabilities of fluid dynamic actuators and allows for satellite attitude control about any arbitrary axis through spherical design, and introduces a fault-tolerant functionality that allows it to be used as a sensor in the event of rate-gyro failure of the attitude determination subsystem. The dynamic model of the PFSA is obtained through computational fluid-dynamics and finite-element analysis using the grid-independent solution. The passive stabilization capabilities of the PFSA are investigated. Simulation results show an order of three-fold reduction in settling time in comparison to existing fluid dynamic actuators. Lastly, a design modification is proposed for PFLA in order to examine its thermal management capabilities. A comprehensive investigation is carried out to perform thermal transport from onboard electronics through conduction and convection. Simulation results demonstrate the advantages of thermal transport while considering fluid rotation inside the PFLA as opposed to stationary fluid.

Sign in / Sign up

Export Citation Format

Share Document