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Journal ArticleDOI

Terminal guidance strategy for a hybrid thrust-tether lunar landing scheme

TL;DR: A hybrid thrust-tether lunar landing scheme and its terminal guidance strategy are proposed in this paper, which has potential application in avoiding the dusts aroused by the plume of thrusters.
About: This article is published in Advances in Space Research.The article was published on 2015-05-01. It has received 6 citations till now. The article focuses on the topics: Terminal guidance & Moon landing.
Citations
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Journal ArticleDOI
TL;DR: The implication of Evolving Intelligent System based model-free data-driven techniques can be a smart option since they can adapt their structure and parameters to cope with sudden changes in the behavior of RUAVs real-time flight.
Abstract: In recent times, technological advancement boosts the desire of utilizing the autonomous Unmanned Aerial Vehicle (UAV) in both civil and military sectors. Among various UAVs, the ability of rotary wing UAVs (RUAVs) in vertical take-off and landing, to hover and perform quick maneuvering attract researchers to develop models fully autonomous control framework. The majority of first principle techniques in modeling and controlling RUAV face challenges in incorporating and handling various uncertainties. Recently various fuzzy and neuro-fuzzy based intelligent systems are utilized to enhance the RUAV’s modeling and control performance. However, the majority of these fuzzy systems are based on batch learning methods, have static structure, and cannot adapt to rapidly changing environments. The implication of Evolving Intelligent System based model-free data-driven techniques can be a smart option since they can adapt their structure and parameters to cope with sudden changes in the behavior of RUAVs real-time flight. They work in a single pass learning fashion which is suitable for online real-time deployment. In this paper, state of the art of various fuzzy systems from the basic fuzzy system to evolving fuzzy system, their application in a RUAV namely quadcopter with existing limitations, and possible opportunities are analyzed. Besides, a variety of first principle techniques to control the quadcopter, their impediments, and conceivable solution with recently employed evolving fuzzy controllers are reviewed.

32 citations


Cites methods from "Terminal guidance strategy for a hy..."

  • ...They have also been employed on spacecrafts to control altitude and attitude in last few decades (Chen et al. 2000; Nam and Zhang 1997; Steyn 1994; Van Buijtenen et al. 1998; Xu et al. 2015)....

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Journal ArticleDOI
TL;DR: In this paper, a combined integral sliding mode control with an adaptive fuzzy logic system is proposed for the trajectory control of the probe soft landing on the asteroids with weak gravitational field, which not only guarantees the rapidity and accuracy of the desired trajectory tracking, but also enhances the robustness of the control system, improving the dynamic tracking performance for the probesoft landing on asteroids.
Abstract: For the trajectory control of the probe soft landing on the asteroids with weak gravitational field, this paper presents a combined integral sliding mode control with an adaptive fuzzy logic system, named adaptive fuzzy sliding mode control (AFSMC) scheme. Considering the uncertainty of the orbit dynamics model in the small body fixed coordinate system, and the polyhedron modeling uncertainty in the gravitational potential, a fuzzy logic system is adopted to approximate the upper bound of the uncertainties. In addition, a robust control item is introduced to compensate for the approximation error of fuzzy logic system. The designed adaptive law and robust item make the closed-loop control stable and the tracking errors are convergent to zero. The controller not only guarantees the rapidity and accuracy of the desired trajectory tracking, but also enhances the robustness of the control system, improving the dynamic tracking performance for the probe soft landing on asteroids. Finally, the contrastive simulation results are presented to show the feasibility and effectiveness of the proposed control scheme.

11 citations


Cites background from "Terminal guidance strategy for a hy..."

  • ...[14] combined the fuzzy and variablestructure control to guide the terminal landing for lunar landing; it wasmore robust than some classical guidance laws derived from the linearized dynamics....

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Journal ArticleDOI
TL;DR: In this paper, nonlinear oscillation of a space tether system connected to the Moon's surface, elongating along the Earth-Moon line at L 1 and L 2 sides respectively, was studied.
Abstract: This paper focuses on nonlinear oscillation of a space tether system connected to the Moon’s surface, elongating along the Earth-Moon line at L1 and L2 sides respectively. The full nonlinea...

7 citations

Journal ArticleDOI
TL;DR: In this article , a new guidance algorithm based on dynamic low-resolution image sequences is proposed to relieve the burden of obtaining high-precision lunar surface information during lunar soft landing, which enables the spacecraft to optimize the final landing site by rolling in orbit.

3 citations

Proceedings ArticleDOI
09 Jan 2017
TL;DR: In this paper, an explicit guidance algorithm for multi-constrained terminal descent phase of lunar soft landing is presented, where a minimum jerk guidance is designed and extended for this purpose to achieve the terminal control and state constraints.
Abstract: An explicit guidance algorithm for multi-constrained terminal descent phase of lunar soft landing is presented in this paper. A minimum jerk guidance is designed and extended for this purpose to achieve the terminal control and state constraints. The closed form jerk expression, obtained using the minimum jerk guidance is analyzed to obtain an explicit expression for acceleration command, which is the physical control variable for the guidance loop. The guidance formulation ensures the minimum rate of change of acceleration and vertical touchdown of the spacecraft towards a designated landing site with high terminal accuracy. The design features of the proposed guidance law are demonstrated using simulation results.

3 citations

References
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Journal ArticleDOI
TL;DR: A convexification of the control constraints that is proven to be lossless enables the use of interior point methods of convex optimization to obtain optimal solutions of the original nonconvex optimal control problem.
Abstract: Planetary soft landing is one of the benchmark problems of optimal control theory and is gaining renewed interest due to the increased focus on the exploration of planets in the solar system, such as Mars. The soft landing problem with all relevant constraints can be posed as a finite-horizon optimal control problem with state and control constraints. The real-time generation of fuel-optimal paths to a prescribed location on a planet's surface is a challenging problem due to the constraints on the fuel, the control inputs, and the states. The main difficulty in solving this constrained problem is the existence of nonconvex constraints on the control input, which are due to a nonzero lower bound on the control input magnitude and a nonconvex constraint on its direction. This paper introduces a convexification of the control constraints that is proven to be lossless; i.e., an optimal solution of the soft landing problem can be obtained via solution of the proposed convex relaxation of the problem. The lossless convexification enables the use of interior point methods of convex optimization to obtain optimal solutions of the original nonconvex optimal control problem.

212 citations

Journal ArticleDOI
TL;DR: A computational algorithm is devised for solving a class of functional inequality constrained optimization problems, based on a penalty function, for which a numerical example is solved.

167 citations

Journal ArticleDOI
01 Apr 2004
TL;DR: Some sufficient conditions are derived under which the parallel-distributed fuzzy control can stabilize the whole uncertain fuzzy time-delay system asymptotically and the tolerable bound of the perturbation is obtained.
Abstract: This paper investigates the problem of designing a fuzzy state feedback controller to stabilize an uncertain fuzzy system with time-varying delay. Based on Lyapunov criterion and Razumikhin theorem, some sufficient conditions are derived under which the parallel-distributed fuzzy control can stabilize the whole uncertain fuzzy time-delay system asymptotically. By Schur complement, these sufficient conditions can be easily transformed into the problem of LMIs. Furthermore, the tolerable bound of the perturbation is also obtained. A practical example based on the continuous stirred tank reactor (CSTR) model is given to illustrate the control design and its effectiveness.

121 citations

Proceedings ArticleDOI
15 Aug 2005
TL;DR: In this article, a performance assessment of the various types of powered descent guidance methods previously used for missions to the Moon and Mars is presented, and a general outline for future powered descent trajectory guidance is suggested.
Abstract: This study consists of a performance assessment of the various types of powered descent guidance methods previously used for missions to the Moon and Mars. The strengths and weaknesses of the various methods are discussed and simulation results are shown. Past methods have been used as a starting point for newer guidance schemes and one particular guidance scheme based on the Apollo Lunar Module Landing Guidance is discussed in greater detail. The guidance results are compared to optimal trajectory results, and a general outline for future powered descent trajectory guidance is suggested.

87 citations

01 Jun 1972
TL;DR: The development of the landing gear subsystem through the Apollo 11 lunar landing mission is described in this paper, where extensive analyses and tests are undertaken to verify the design adequacy techniques of landing performance analysis served as a primary tool in developing the subsystem hardware and in determining the adequacy of landing gear.
Abstract: The development of the lunar module landing gear subsystem through the Apollo 11 lunar landing mission is presented The landing gear design evolved from the design requirement, which had to satisfy the structural, mechanical, and landing performance constraints of the vehicle Extensive analyses and tests were undertaken to verify the design adequacy Techniques of the landing performance analysis served as a primary tool in developing the subsystem hardware and in determining the adequacy of the landing gear for toppling stability and energy absorption The successful Apollo 11 lunar landing mission provided the first opportunity for a complete flight test of the landing gear under both natural and induced environments

65 citations