Continuous-Time Predictive Control-Based Integrated Guidance and Control

Tsourdos

Progress in Aerospace Sciences

et al. 2019

107

For most atmospheric or exo-atmospheric spacecraft flight scenarios, a welldesigned trajectory is usually a key for stable flight and for improved guidance and control of the vehicle. Although extensive research work has been carried out on the design of spacecraft trajectories for different mission profiles and many effective tools were successfully developed for optimizing the flight path, it is only in the recent five years that there has been a growing interest in planning the flight trajectories with the consideration of multiple mission objectives and various model errors/uncertainties. It is worth noting that in many practical spacecraft guidance, navigation and control systems, multiple performance indices and different types of uncertainties must frequently be considered during the path planning phase. As a result, these requirements bring the development of multi-objective spacecraft trajectory optimization methods as well as stochastic spacecraft trajectory optimization algorithms. This paper aims to broadly review the state-of-the-art development in numerical multi-objective trajectory optimization algorithms and stochastic trajectory planning techniques for spacecraft flight operations. A brief description of the mathematical formulation of the problem is firstly introduced. Following that, various optimization methods that can be effective for solving spacecraft trajectory planning problems are reviewed, including the gradient-based methods, the convexification-based methods, and the evolutionary/metaheuristic methods. The multi-objective

Section: Design Of Integrated Spacecraft Guidance and Control Systemsmentioning

confidence: 99%

A review of optimization techniques in spacecraft flight trajectory design

Tsourdos

Progress in Aerospace Sciences

et al. 2019

107

International Journal of Aerospace Engineering

“…is piecewise continuous with respect to t, and S 1 satisfies the Lipschitz condition in ℝ + × N. If there exist two functions U ℝ l → ℝ + and V 1 S 1 → ℝ + that are continuous and positively definite in their domains, respectively, the following two expressions are valid when S 1 → −k a t or S 1 → k b t : Theorem 1. For the closed-loop system Equation 5, if the virtual control variables and the control law satisfy Equations (18), (25), and (30), then for any set M 0 z to which the initial condition y z 0 belongs, there always exists a sufficiently large…”

Section: Stability Analysis Of Control Law Formentioning

confidence: 99%

“…Methods of IGC design have been widely used in guidance and control systems of aircraft [10], missiles [11][12][13], and unmanned aerial vehicles [14,15]. In recent years, researchers have combined this method with modern control theories, such as dynamic surface control [16], optimal control [17], and predictive control [18], to generate methods of IGC design for aircrafts. However, most prevalent IGC design methods do not consider the coupling relationship between the pitch and the yaw channels.…”

Section: Introductionmentioning

confidence: 99%

Integrated Guidance and Control of Interceptor Missile Based on Asymmetric Barrier Lyapunov Function

Liu

Liang

2019

In this study, a novel integrated guidance and control (IGC) algorithm based on an IGC method and the asymmetric barrier Lyapunov function is designed; this algorithm is designed for the interceptor missile which uses a direct-force/aerodynamic-force control scheme. First, by considering the coupling between the pitch and the yaw channels of the interceptor missile, an IGC model of these channels is established, and a time-varying gain extended state observer (TVGESO) is designed to estimate unknown interferences in the model. Second, by considering the system output constraint problem, an asymmetric barrier Lyapunov function and a dynamic surface sliding-mode control method are employed to design the control law of the pitch and yaw channels to obtain the desired control moments. Finally, in light of redundancy in such actuators as aerodynamic rudders and jet devices, a dynamic control allocation algorithm is designed to assign the desired control moments to the actuators. Moreover, the results of simulations show that the IGC algorithm based on the asymmetric barrier Lyapunov function for the interceptor missile allows the outputs to meet the constraints and improves the stability of the control system of the interceptor missile.

“…IGC design using sliding mode control have been reported in [19,20] wherein the studies demonstrated improvements in the performance of the homing interceptor in terms of smaller response time, reduced miss distance and better dynamic behavior. A comprehensive Monte Carlo simulation was presented in [21] to demonstrate the effectiveness of IGC design over separate two-loop ones. In [22], the integrated design was studied from the perspective of optimal control formulations, wherein the autopilot design and the interceptor's guidance law were formulated in a unified state space framework.…”

Section: Introductionmentioning

confidence: 99%

“…We proceed in a similar fashion as in the proof of Theorem 2. Using the expressions of F, B c and B t , as in (25)-(26), minimization of the cost,(17), with B c δ c c + B t δ c t = −F − µ sign(s) = Υ as a constraint, results in the guidance commands as the ones given in(21). On substituting the values of Υ, B c and B t in(21), one may obtain the expressions of the canard and the tail surface deflections, given in(27) and (28), respectively.…”

mentioning

confidence: 99%

Integrated Guidance and Control Design For Time-Constrained Interception

Sinha¹,

Kumar²,

Mukherjee³

2020

Preprint

This paper proposes integrated guidance and control design to intercept a non-maneuvering target at a pre-specified time of interception. The problem is addressed considering nonlinear engagement kinematics and the interceptor is steered using the combined effects of canard as well as tail configurations (dual control interceptors). Different formulations of time-to-go, without the restrictive assumption of interceptor's small heading angle, have been used in deriving the guidance commands, allowing the proposed strategies to remain effective over a wide range of impact time values. A weighted effort allocation scheme, in canard and tail deflections, has been proposed to generate the required lateral acceleration. The overall design uses sliding mode control owing to its simplicity of design. Finally, simulations are presented for various scenarios, including impaired actuator, vindicating the efficacy of the proposed technique.