In flight control, the design objective and the aircraft dynamics may be different in low and high angle of attack regions. This paper presents a systematic switching LPV control design method to determine if it is practical to use for flight control designs over a wide angle of attack region. The approach is based on multiple parameter-dependent Lyapunov functions. A family of LPV controllers are designed, and each of them is suitable for a specific parameter subspace. The state of the controller is reset to guarantee the stability requirement of the Lyapunov function when the switching event occurs. Two parameter-dependent switching logics, hysteresis switching and switching with average dwell time, are examined. The proposed switching LPV control scheme is applied to an F-16 aircraft model with different design objectives and aircraft dynamics in low and high angle of attack regions. The nonlinear simulation results using both switching logics are compared.

Switching LPV control of an F-16 aircraft via controller state reset

The nation's goals to replace the aging Space Shuttle fleet and pursue exploration of our solar system and beyond will require more robust, less costly launch vehicles and spacecraft. This paper presents a novel Sliding Mode Control approach, Sliding Mode Control driven by Sliding Mode Disturbance Observers with Gain Adaptation, for the reusable launch vehicle (RLV) flight control system design as a way to improve robustness to many phenomena such as modeling uncertainties and disturbances, while retaining continuity of control without using high control gains. Due to the robustness to external disturbances (including wind gusts), mission guidance trajectories and modeling uncertainties, the proposed flight control system design also can reduce cost by requiring less time in design cycle and preflight analyses. This design is applied to Terminal Area Energy Management and Approach/Landing (TAL), a flight regime that has had little research effort in recent years. The multiple-loop, multiple time-scale design features low order disturbance observers that rely only on knowledge of the bounds of the disturbance. A gain adaptation algorithm is included in the disturbance observer design that provides the least gain needed for existence of the sliding mode. High fidelity 6 DOF computer simulations of the X-33 technology demonstration sub-orbital launch vehicle for nominal and severe wind-gust tests demonstrate improved performance over a more conventional, classical control system design.

Sliding Mode Disturbance Observer-Based Control for a Reusable Launch Vehicle

An integrated autopilot and guidance algorithm, robust to target maneuvers and missile’s model uncertainties, is developed using higher-order sliding mode control for interceptors steered by a combination of aerodynamic lift, sustainer thrust, and center-of-gravity divert thrusters. A smooth higher-order sliding mode guidance that is robust to target maneuvers generates flight-path trajectory angular rates and attitude rate commands. The attitude rate missilemaneuvers are aimed at producing desired aerodynamic lift and/or orienting the sustainer thrust. The lateral acceleration created by themissile attitudemaneuver is treated as a cooperative disturbance andaccounted for by the trajectory control. Robust to themissile’smodel uncertainties, higher-order (second-order) slidingmode autopilot is designed based on a nonlinear dynamic slidingmanifold. The proposed integrated autopilot and guidance algorithm also includes seeker/tracker bore-sight stabilization and estimation of target lateral acceleration. The algorithm is tested using computer simulations against a ballistic maneuvering target.

Integrated Higher-Order Sliding Mode Guidance and Autopilot for Dual Control Missiles

Traditional autopilot design for guided munitions requires an accurate aerodynamic model and relies on a gain schedule to account for system nonlinearities. This paper presents an approach that simplifies the autopilot design process by mating an inverting controller designed at a single flight condition with an on-line neural network to account for errors that arise due to the approximate inversion. This eliminates the need for an extensive design process and also the requirement for accurate aerodynamic data, which can be especially critical at high angles of attack or other regimes at which the aerodynamics become highly nonlinear. The choice of inversion process itself has been found to be critical in the implementation, and is therefore discussed at length. Finally, results from an application of this approach to a full nonlinear 6DOF guided munition simulation are presented.

Adaptive Autopilot Design for Guided Munitions

With the rapid development of computer technology, automatic control technology and communication technology, research on unmanned aerial vehicles (UAVs) has attracted extensive attention from all over the world during the last decades. Particularly due to the demand of various civil applications, the conceptual design of UAV and autonomous flight control technology have been promoted and developed mutually. This paper is devoted to providing a brief review of the UAV control issues, including motion equations, various classical and advanced control approaches. The basic ideas, applicable conditions, advantages and disadvantages of these control approaches are illustrated and discussed. Some challenging topics and future research directions are raised. 

https://figshare.com/articles/journal_contribution/Unmanned_aerial_vehicles_control_methods_and_future_challenges/19102517/1/files/33943673.pdf

Unmanned Aerial Vehicles: Control Methods and Future Challenges

This paper discusses the dynamics and control of missiles capable of high angle of attack flight. The missile control effectors discussed include thrust vectoring, reaction jet thrusters, and aerodynamic tail surfaces. A control power analysis that indicates the effectiveness of these control effectors over the missile's flight envelope is summarized. The 6-DOF dynamics for high angle of attack missile flight control are presented. Autopilot design models and nonlinear simulation results demonstrating high angle of attack flight are also presented. (Author)

Agile missile dynamics and control

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Agile missile dynamics and control