Profile-Following Entry Guidance Using Linear Quadratic Regulator Theory

Dukeman, Greg A.; Fogle, Frank R.

doi:10.2514/6.2002-4457

Cited by 145 publications

(66 citation statements)

References 2 publications

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“…Whatever the model is, steering the state to a desired trim condition along some reference trajectories is the main problem for AHV. Many of control methods and techniques have been applied to flight control design of AHV, such as linear quadratic regulator control [18], robust control [19], adaptive control [20], sequential loop closure controller design [21], slid-ing mode control (SMC) [22][23] [24], disturbance-observerbased control [25], intelligent control algorithm [26] [27], etc.…”

Section: Introductionmentioning

confidence: 99%

Modeling and nonlinear control for air-breathing hypersonic vehicle with variable geometry inlet

Dou

Ding

2017

Aerospace Science and Technology

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This paper develops a control method for an air-breathing hypersonic vehicle with variable geometry inlet (AHV-VGI). For the AHV-VGI, a movable translating cowl is used to track the shock on lip conditions to capture enough air mass flow, which can ensure a more powerful thrust. Compared with traditional air-breathing hypersonic vehicle with fixed geometry inlet (AHV-FGI), this AHV-VGI extends the velocity range, which is favorable to the acceleration and maneuvering flight. However, the VGI causes the unknown changes of the aerodynamic forces, moment and the thrust in the meanwhile. Therefore, we firstly establish a longitudinal dynamic for AHV-VGI, which includes the uncertain changes induced by VGI. A conception of the optimal elongation distance of translating cowl is introduced, and its estimated value is obtained by curve fitted approximation. And then, the control process for AHV-VGI is divided into two subsystems. For each subsystem, a sliding mode controller is designed, and interval type-2 fuzzy logic systems (FLSs) are adopted to approximate nonlinear parts including the uncertain changes induced by VGI. Furthermore, uniformly stability of the whole system is proved by Lyapunov approach. Finally, simulation results demonstrate that AHV have a better control performance under the condition of VGI compared to the FGI.

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Section: Introductionmentioning

confidence: 99%

Modeling and nonlinear control for air-breathing hypersonic vehicle with variable geometry inlet

Dou

Ding

2017

Aerospace Science and Technology

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“…methods (e.g. LQR design [8,9], LQR followed by gain scheduling [24,27], receding horizon control [17], LOG, etc.). Irrespective of the control design method used, a major drawback of these approach, is the over-dependence on the reference profile.…”

Section: Introductionmentioning

confidence: 99%

Suboptimal reentry guidance of a reusable launch vehicle using pitch plane maneuver

Chawla

Sarmah

Padhi

2010

Aerospace Science and Technology

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“…Dukeman designed a linear control law using state feedback with energy scheduled gains, which were obtained offline based on a linear quadratic regulator function. 8 Saraf et al proposed a guidance method including a trajectory planner and a tracking law. 9 The planner generated reference drag acceleration and heading angle profiles, while the tracking law commanded the bank angle and the angle of attack to follow the reference profiles.…”

Section: Introductionmentioning

confidence: 99%

Robust entry guidance using linear covariance-based model predictive control

Luo

Jin

Wang

et al. 2017

International Journal of Advanced Robotic Systems

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For atmospheric entry vehicles, guidance design can be accomplished by solving an optimal issue using optimal control theories. However, traditional design methods generally focus on the nominal performance and do not include considerations of the robustness in the design process. This paper proposes a linear covariance-based model predictive control method for robust entry guidance design. Firstly, linear covariance analysis is employed to directly incorporate the robustness into the guidance design. The closed-loop covariance with the feedback updated control command is initially formulated to provide the expected errors of the nominal state variables in the presence of uncertainties. Then, the closed-loop covariance is innovatively used as a component of the cost function to guarantee the robustness to reduce its sensitivity to uncertainties. After that, the models predictive control is used to solve the optimal problem, and the control commands (bank angles) are calculated. Finally, a series of simulations for different missions have been completed to demonstrate the high performance in precision and the robustness with respect to initial perturbations as well as uncertainties in the entry process. The 3s confidence region results in the presence of uncertainties which show that the robustness of the guidance has been improved, and the errors of the state variables are decreased by approximately 35%.

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Profile-Following Entry Guidance Using Linear Quadratic Regulator Theory

Cited by 145 publications

References 2 publications

Modeling and nonlinear control for air-breathing hypersonic vehicle with variable geometry inlet

Modeling and nonlinear control for air-breathing hypersonic vehicle with variable geometry inlet

Suboptimal reentry guidance of a reusable launch vehicle using pitch plane maneuver

Robust entry guidance using linear covariance-based model predictive control

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