Research

21 pages, 17339 KiB

Open AccessArticle

Design and Dynamic Simulation Verification of an On-Orbit Operation-Based Modular Space Robot

by Dong Yang, Xiaokui Yue and Ming Guo

Appl. Sci. 2023, 13(23), 12949; https://doi.org/10.3390/app132312949 - 04 Dec 2023

Viewed by 584

Space robots have been playing an important role in space on-orbit operation missions. However, the traditional configuration of space robots only has a single function and cannot meet the requirements of different space missions, and the launch cost of space robots is very [...] Read more.

Space robots have been playing an important role in space on-orbit operation missions. However, the traditional configuration of space robots only has a single function and cannot meet the requirements of different space missions, and the launch cost of space robots is very high. Thus, the reconfigurable modular space robot system that can carry multiple loads and own mission adaptability is of great significance. Based on the analysis of a robot space mission, combined with the existing reconfigurable robots, this paper develops a configuration design scheme for a modular reconfigurable space robot, and carries out the prototype design. According to the configuration characteristics of the module, the dynamic modeling of the space robot is based on the graph theory analysis and principle of virtual work. Related application scenarios are set up. Function and feasibility of the dynamic modeling methods are verified through assembly experimentation and dynamic simulation. Full article

(This article belongs to the Special Issue Advanced Guidance and Control of Hypersonic Vehicles)

► Show Figures

Figure 1

16 pages, 2152 KiB

Open AccessArticle

Cooperative Guidance Law for the Mother-Cabin of the Anti-UAV Cluster Mother-Son Missile

by Ruining Luo, Guangjun He, Xiangwei Bu and Jianjun Shi

Appl. Sci. 2023, 13(9), 5397; https://doi.org/10.3390/app13095397 - 26 Apr 2023

Cited by 1 | Viewed by 1057

Abstract

This article investigates a novel operational pattern for intercepting UAV clusters over the range of middle and far distances using mother-son missiles. To address the guidance issue of the mother-cabin in the operational pattern, a special cooperative guidance law, which takes into account [...] Read more.

This article investigates a novel operational pattern for intercepting UAV clusters over the range of middle and far distances using mother-son missiles. To address the guidance issue of the mother-cabin in the operational pattern, a special cooperative guidance law, which takes into account acceleration constraint and satisfies the constraints of impact time, speed, and zero line of sight angle (LOS), is proposed. Based on consistency theory and sliding mode control theory, the proposed cooperative guidance law is specifically designed for the mother-cabin of the mother-son missile. This approach offers several advantages, including a simple structure and smooth controller output, and smooth flight trajectory. Finally, numerical simulations are presented to demonstrate the effectiveness and applicability of the cooperative guidance law. Full article

(This article belongs to the Special Issue Advanced Guidance and Control of Hypersonic Vehicles)

► Show Figures

Figure 1

16 pages, 3651 KiB

Open AccessArticle

Rapid Parametric Modeling and Robust Analysis for the Hypersonic Ascent Based on Gap Metrics

by Yiran Liu, Boyi Chen, Jinbao Chen and Yanbin Liu

Appl. Sci. 2023, 13(8), 5189; https://doi.org/10.3390/app13085189 - 21 Apr 2023

Viewed by 1105

Abstract

This paper investigates a rapid modeling method and robust analysis of hypersonic vehicles using multidisciplinary integrated techniques. First, the geometrical configuration is described using parametric methods based on the class–shape technique. Aerodynamic forces and moments are estimated for the specific configuration using engineering [...] Read more.

This paper investigates a rapid modeling method and robust analysis of hypersonic vehicles using multidisciplinary integrated techniques. First, the geometrical configuration is described using parametric methods based on the class–shape technique. Aerodynamic forces and moments are estimated for the specific configuration using engineering methods. Moreover, the nonlinear model is simplified by the polynomial fitting expressions, and the linear variable parameter model is obtained for the tracking control design and dynamic characteristic analysis with the aid of the sensitivity analysis and gap metric methods. A velocity-driven trajectory design method is deduced for hypersonic ascent, and the tracking control law is developed to realize the flight process from the initial point to the cruise point. Furthermore, a robust analysis process based on gap margin is proposed for climb trajectory tracking. Simulation results are provided to verify the feasibility of the proposed modeling method and show that the flight control of a hypersonic vehicle is more sensitive to altitude variation. Full article

(This article belongs to the Special Issue Advanced Guidance and Control of Hypersonic Vehicles)

► Show Figures

Figure 1

17 pages, 3520 KiB

Open AccessArticle

Dynamical Neural Network Based Dynamic Inverse Control Method for a Flexible Air-Breathing Hypersonic Vehicle

by Haiyan Gao, Zhichao Chen and Weiqiang Tang

Appl. Sci. 2023, 13(8), 5154; https://doi.org/10.3390/app13085154 - 20 Apr 2023

Cited by 1 | Viewed by 1057

Abstract

A novel dynamic inverse control method based on a dynamical neural network (DNN) is proposed for the trajectory tracking control of a flexible air-breathing hypersonic vehicle (FAHV). Firstly, considering that the accurate model of FAHV is difficult to obtain, the FAHV is regarded [...] Read more.

A novel dynamic inverse control method based on a dynamical neural network (DNN) is proposed for the trajectory tracking control of a flexible air-breathing hypersonic vehicle (FAHV). Firstly, considering that the accurate model of FAHV is difficult to obtain, the FAHV is regarded as a completely unknown system, and a DNN is designed to identify its nonlinear model. On the basis of Lyapunov’s second law, the weight vectors of the DNN are adaptively updated. Then, a dynamic inverse controller is designed based on the identification model, which avoids the transformation of the nonlinear model of FAHV, thereby simplifying the controller design process. The simulation results verify that the DNN can identify FAHV accurately, and velocity and altitude can track the given reference signal accurately with the proposed dynamic inverse control method. Compared with the back-stepping control method, the proposed method has better tracking accuracy, and the amplitude of the initial control law is smaller. Full article

(This article belongs to the Special Issue Advanced Guidance and Control of Hypersonic Vehicles)

► Show Figures

Figure 1

24 pages, 9093 KiB

Open AccessArticle

Analytic Time Reentry Cooperative Guidance for Multi-Hypersonic Glide Vehicles

by Hui Xu, Guangbin Cai, Yonghua Fan, Hao Wei, Xin Li and Yongchao Wang

Appl. Sci. 2023, 13(8), 4987; https://doi.org/10.3390/app13084987 - 15 Apr 2023

Cited by 2 | Viewed by 1294

Abstract

Aiming at the cooperative guidance problem of multi-hypersonic glide vehicles, a cooperative guidance method based on a parametric design and an analytical solution of time-to-go is proposed. First, the hypersonic reentry trajectory optimization problem was transformed into a parameter optimization problem. The parameters [...] Read more.

Aiming at the cooperative guidance problem of multi-hypersonic glide vehicles, a cooperative guidance method based on a parametric design and an analytical solution of time-to-go is proposed. First, the hypersonic reentry trajectory optimization problem was transformed into a parameter optimization problem. The parameters were optimized to determine the angle of attack profile and the time to enter the altitude velocity reentry corridor. Then, using the quasi-equilibrium glide condition, the estimation form of the remaining flight time was analytically derived to satisfy accurately the cooperative time constraint. Using the remaining time-to-go and range-to-go, combined with the heading angle deviation corridor, the bank angle command was further calculated. Finally, the swarm intelligence optimization algorithm was used to optimize the design parameters to obtain the cooperative guidance trajectory satisfying the time constraint. Simulations showed that the analytical time reentry cooperative guidance algorithm proposed in this paper can accurately meet the time constraints and cooperative flight accuracy. Monte Carlo simulation experiments verified that the proposed algorithm demonstrates a robust performance. Full article

(This article belongs to the Special Issue Advanced Guidance and Control of Hypersonic Vehicles)

► Show Figures

Figure 1

20 pages, 1727 KiB

Open AccessArticle

Research on Head Pursuit Interception Strategy for Hypersonic Target

by Zhihan Li and Ying Nan

Appl. Sci. 2023, 13(8), 4772; https://doi.org/10.3390/app13084772 - 10 Apr 2023

Viewed by 1518

Abstract

In the wake of countries competing to develop high-efficiency offensive weapons, high-precision systems have also developed. Due to the high speed and high maneuverability of hypersonic targets, it is always difficult to meet the accuracy and rapidity requirements by using the traditional interception [...] Read more.

In the wake of countries competing to develop high-efficiency offensive weapons, high-precision systems have also developed. Due to the high speed and high maneuverability of hypersonic targets, it is always difficult to meet the accuracy and rapidity requirements by using the traditional interception mode. In order to improve the accuracy of the hypersonic target interception, a head pursuit guidance strategy is developed for hypersonic target interception in this study. Firstly, a dynamic model is established by analyzing the relative motion between the interceptor and the target, which needs to place the low-speed interceptor before the high-speed target. Subsequently, a head pursuit interception guidance strategy is presented, which controls the interceptor flight trajectory by controlling its normal acceleration to achieve a successful interception target. Finally, for the maneuvering and non-maneuvering targets, the dynamic characteristics of interceptor are analyzed, respectively, and full trajectory dynamic simulations under different conditions for the hypersonic target interception are worked out to illustrate the feasibility and robustness of the proposed guidance strategy. Full article

(This article belongs to the Special Issue Advanced Guidance and Control of Hypersonic Vehicles)

► Show Figures

Figure 1

18 pages, 2428 KiB

Open AccessArticle

A Fast Prediction Method for the Target Reachable Zone of Boosting Gliding Vehicle Based on Database

by Qiwei Huang, Zexiao Deng and Luhua Liu

Appl. Sci. 2023, 13(3), 1848; https://doi.org/10.3390/app13031848 - 31 Jan 2023

Cited by 2 | Viewed by 1202

Abstract

This paper presents an effective method for the fast prediction of the target reachable zone of a boosting gliding vehicle in the gliding phase. Firstly, a six-point method is proposed for the rapid determination of the reachable zone and the feasible discrimination of [...] Read more.

This paper presents an effective method for the fast prediction of the target reachable zone of a boosting gliding vehicle in the gliding phase. Firstly, a six-point method is proposed for the rapid determination of the reachable zone and the feasible discrimination of the target. The method chooses six boundary points with notable features to characterize the reachable zone and considerably reduces the computational consumption. Furthermore, taking into account the need for a rapid launch and safety against unexpected events during the gliding phase, a database method for the prediction of the reachable zone is presented, which builds the database with time nodes and six boundary points and employs interpolation methods to calculate the reachable zone. The results suggest that online planning by the database method has significant potential for predicting the target reachable zone. The accuracy error is less than 1%, and the computational efficiency is increased by 90% when compared to the six-point approach. Full article

(This article belongs to the Special Issue Advanced Guidance and Control of Hypersonic Vehicles)

► Show Figures

Figure 1

25 pages, 10652 KiB

Open AccessArticle

Intelligent Trajectory Prediction Algorithm for Reentry Glide Target Based on Intention Inference

by Mingjie Li, Chijun Zhou, Lei Shao, Humin Lei and Changxin Luo

Appl. Sci. 2022, 12(21), 10796; https://doi.org/10.3390/app122110796 - 25 Oct 2022

Cited by 1 | Viewed by 1164

Abstract

Aimed at the problem of the insufficient utilization of intention information and flight data for the trajectory prediction of a reentry glide target, an intelligent trajectory prediction algorithm based on intention inference was proposed. Firstly, a control parameter prediction network was developed to [...] Read more.

Aimed at the problem of the insufficient utilization of intention information and flight data for the trajectory prediction of a reentry glide target, an intelligent trajectory prediction algorithm based on intention inference was proposed. Firstly, a control parameter prediction network was developed to predict the variation of the control parameter values. Secondly, based on the Gaussian mixture model and Dubins circle, the importance of strategic places was modeled, the functional relationship between the strategic places and trajectories was established, and the influence factors of target threat were analyzed. Subsequently, an intention inference network was designed, which can accurately identify the key point the target intends to attack and realize the nonlinear calculation of the target’s threat value. Finally, according to the common guidance law of reentry glide target, the lateral sign-variation rule was designed to carry out the target trajectory prediction based on intention inference. Simulation revealed that the parameter prediction network designed in this paper can realize the modification of filtering control parameters and effectively predict the value of these parameters. Moreover, taking the result of intention inference network, trajectory prediction in different prediction cases was accomplished. The maximal error of spatial distance (MESD) of the proposed method was less than 9 km when the prediction time was 100 s, and the best result was obtained in the long-term prediction. Compared with other mainstream prediction methods, the proposed method obtained the best prediction accuracy. Full article

(This article belongs to the Special Issue Advanced Guidance and Control of Hypersonic Vehicles)

► Show Figures

Figure 1

Journal Menu

Journal Browser

Advanced Guidance and Control of Hypersonic Vehicles

Share This Special Issue

Special Issue Editors

Special Issue Information

Keywords

Published Papers (8 papers)

Research

Further Information

Guidelines

MDPI Initiatives

Follow MDPI