Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
4.5
2.7
Journals
Applied Sciences
Special Issues
Intelligence Sense, Optimization, and Control in Space Vehicles
share announcement

Intelligence Sense, Optimization, and Control in Space Vehicles

A special issue of Applied Sciences (ISSN 2076-3417). This special issue belongs to the section "Aerospace Science and Engineering".

Deadline for manuscript submissions: closed (20 March 2023) | Viewed by 10890

Special Issue Editors

Prof. Dr. Shengping Gong

E-Mail Website
Guest Editor
School of Astronautics, Beihang University, Beijing 100191, China
Interests: solar sailing; interplanetary optimization; many-body dynamics
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Wen Yao

E-Mail Website
Guest Editor
Defense Innovation Institute, Academy of Military Sciences, Beijing 100097, China
Interests: system design and multidisciplinary optimization; uncertainty-based optimization; intelligent design
Dr. Xu Huang

E-Mail Website
Guest Editor
Department of Presision Instrument，Tsinghua University, Beijing 100084, China
Interests: intelligent control; trajectory optimizaiton; guidance

Special Issue Information

Dear Colleagues,

The topic of this Special Issue is space vehicles, which here include spacecraft, aircraft, missiles, rockets, etc. As missions become increasingly more complex, so do the environment and vehicle itself. Transitional design and optimization, modeling, navigation, guidance, and control methods may thus become unable to handle some of these complex situations. As such, during the design stage, a larger number of factors should be considered to optimize the flight performance of a vehicle during its lifetime. Additionally, during the service stage, navigation, guidance, and control should be more intelligent in order to be able to adapt to a changing environment or varying dynamics. Artificial intelligence has been successfully applied in many fields and proven to be more efficient in many aspects. Due to the particularity of space vehicles, however, AI is harder to take advantage of in the design and execution of space missions because real data are rare and expensive to obtain. This Special Issue explores new methods combining AI and traditional methods to handle multidisciplinary optimization, intelligent sensing, high-fidelity modeling, on-board decision, intelligent guidance, and adaptive and robust control.

Prof. Dr. Shengping Gong
Prof. Dr. Wen Yao
Dr. Xu Huang
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Applied Sciences is an international peer-reviewed open access semimonthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • space vehicle
  • artificial intelligence
  • multidisciplinary optimization
  • high-fidelity modeling
  • navigation
  • decision
  • guidance
  • control

Published Papers (7 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Research

23 pages, 8612 KiB  
Article
Linear/Nonlinear Active Disturbance Rejection Switching Control for Near-Space Morphing Vehicles Based on Type-2 Fuzzy Logic System
by Ouxun Li, Li Deng, Ju Jiang and Shutong Huang
Appl. Sci. 2023, 13(14), 8255; https://doi.org/10.3390/app13148255 - 16 Jul 2023
Viewed by 931
Abstract
This paper is concerned with the problems of robust switching control for near-space morphing vehicles (NMVs) with a large range of parameter uncertainty and external disturbance. For this purpose, a novel linear/nonlinear active disturbance rejection switching control method for the longitudinal dynamical model [...] Read more.
This paper is concerned with the problems of robust switching control for near-space morphing vehicles (NMVs) with a large range of parameter uncertainty and external disturbance. For this purpose, a novel linear/nonlinear active disturbance rejection switching control method for the longitudinal dynamical model of NMVs based on the type-2 fuzzy logic system is proposed. Both linear active disturbance rejection control (LADRC) and nonlinear active disturbance rejection control (NLADRC) were designed for the velocity and altitude subsystems of NMVs. Then, the stability analysis of the cascade closed-loop and switching control systems were carried out. Furthermore, a switching control strategy based on the interval type-2 fuzzy logic system was developed, and the change rules of aerodynamic parameters with Mach number and angle of attack were examined. Finally, the experimental results validated the superior switching performance of the proposed control strategy. Full article
(This article belongs to the Special Issue Intelligence Sense, Optimization, and Control in Space Vehicles)
►▼ Show Figures

Figure 1

22 pages, 6686 KiB  
Article
Numerical Analysis of the Kinematic Accuracy of the Hermetic Harmonic Drive in Space Vehicles
by Jacek Pacana, Dominika Siwiec and Andrzej Pacana
Appl. Sci. 2023, 13(3), 1694; https://doi.org/10.3390/app13031694 - 29 Jan 2023
Cited by 2 | Viewed by 1743
Abstract
The unfriendly-for-humans environment of space causes automatic or remotely controlled vehicles and devices to be used for its research. In robot and manipulator control systems, and also in mechanisms adjusting antennas and photovoltaic panels, the hermetic harmonic drive can be used. A special [...] Read more.
The unfriendly-for-humans environment of space causes automatic or remotely controlled vehicles and devices to be used for its research. In robot and manipulator control systems, and also in mechanisms adjusting antennas and photovoltaic panels, the hermetic harmonic drive can be used. A special advantage of this type of gear is the ability to transfer power to an isolated space separated by physical barriers from external influences. Therefore, the purpose was to design gears that will allow achieving the highest kinematic precision for control systems by simultaneously maintaining their hermetics. The article presented an analysis of the kinematic accuracy of harmonic hermetic drives powered by four different types of wave generators. The generators used differed in construction but also caused other deformations of the flexspline. The calculation of angular displacement was prepared in the computer program Abaqus. The simulations were performed on virtual models of a complete harmonic hermetic drive using the finite element method (FEM). The results from the analysis allow the most favorable solution to be applied to the Mars rover drive or spacecraft control system. It was determined for which of the wave generators the kinematic accuracy is the highest and how high the backlash exists for the reversing rotation. Finally, the proposed design will allow one to increase the accuracy of the working movements and control of space vehicles while ensuring a minimal influence of the external ambient. Full article
(This article belongs to the Special Issue Intelligence Sense, Optimization, and Control in Space Vehicles)
►▼ Show Figures

Figure 1

19 pages, 14013 KiB  
Article
New Construction Solutions of Gear Using in Space Vehicle Control Systems
by Jacek Pacana, Dominika Siwiec and Andrzej Pacana
Appl. Sci. 2022, 12(23), 12285; https://doi.org/10.3390/app122312285 - 1 Dec 2022
Cited by 5 | Viewed by 1530
Abstract
Outer space presents construction challenges that are completely different from the terrestrial environment. They should be characterized by high resilience and indefinite durability because there is no possibility of repair during exploitation. There are drives in spacecraft control systems that are necessary to [...] Read more.
Outer space presents construction challenges that are completely different from the terrestrial environment. They should be characterized by high resilience and indefinite durability because there is no possibility of repair during exploitation. There are drives in spacecraft control systems that are necessary to move solar panels, robotic arms, and manipulators, and also to position antennas. In these devices, they have applications where harmonic drives are characterized by high kinematic accuracy but relatively low mechanical strength. The analysis presented in this study is aimed at modifying the shape of the harmonic drive to increase its durability and reliability. In this study, the most vulnerable damage element of the harmonic drive is the flexspline. The calculation was carried out using the finite element method (FEM) in the computer program ABAQUS. A standardized shape was tested as a basic model, and several other design solutions were proposed. For each of them, the mechanical strength was determined, which allowed the selection of the most preferred shape for the flexspline of the harmonic drive. The specific environmental requirements of the expectations for sand for gear used in spacecraft control systems were included in the analysis. The selected construction solutions of the flexspline allow for longer work and transfer of greater loads by the harmonic driver than the solutions currently used. The choice of harmonic driver design shape allows for failure-free and maintenance-free work in space vehicle control systems. Full article
(This article belongs to the Special Issue Intelligence Sense, Optimization, and Control in Space Vehicles)
►▼ Show Figures

Figure 1

21 pages, 3860 KiB  
Article
Adaptive Sliding Mode Control via Backstepping for an Air-Breathing Hypersonic Vehicle Using a Double Power Reaching Law
by Shutong Huang, Ju Jiang and Ouxun Li
Appl. Sci. 2022, 12(13), 6341; https://doi.org/10.3390/app12136341 - 22 Jun 2022
Cited by 2 | Viewed by 1251
Abstract
This paper presents a backstepping-based adaptive sliding mode control scheme using a new double power reaching law for an air-breathing hypersonic vehicle (AHV) with uncertainties. A novel double power reaching law is proposed to speed up the state stabilization. A backstepping control scheme [...] Read more.
This paper presents a backstepping-based adaptive sliding mode control scheme using a new double power reaching law for an air-breathing hypersonic vehicle (AHV) with uncertainties. A novel double power reaching law is proposed to speed up the state stabilization. A backstepping control scheme is proposed for a class of high-order nonlinear system with uncertainties. Then, a novel sliding mode controller using the new double power reaching law is developed to maintain the high tracking performance of the AHV. In order to further attenuate the influence of uncertainties, new adaptive laws are employed. Lastly, simulation studies show that the novel double power reaching law can guarantee that the state of the system converges to zero equilibrium in fixed time, and the controller proposed can effectively reduce the influence of uncertainties on the AHV and achieve good tracking performance. Full article
(This article belongs to the Special Issue Intelligence Sense, Optimization, and Control in Space Vehicles)
►▼ Show Figures

Figure 1

18 pages, 1157 KiB  
Article
Semi-Analytical Planetary Landing Guidance with Constraint Equations Using Model Predictive Control
by Xinyuan Miao, Lin Cheng, Yu Song, Junfeng Li and Shengping Gong
Appl. Sci. 2022, 12(12), 6166; https://doi.org/10.3390/app12126166 - 17 Jun 2022
Cited by 1 | Viewed by 1250
Abstract
With the deepening of planetary exploration, rapid decision making and descent trajectory planning capabilities are needed to cope with uncertain environmental disturbances and possible faults during planetary landings. In this article, a novel decoupling method is adopted, and the analytical three-dimensional constraint equations [...] Read more.
With the deepening of planetary exploration, rapid decision making and descent trajectory planning capabilities are needed to cope with uncertain environmental disturbances and possible faults during planetary landings. In this article, a novel decoupling method is adopted, and the analytical three-dimensional constraint equations are derived and solved, ensuring real-time guidance computation. The three-dimensional motion modes and thrust profiles are analyzed and determined based on Pontryagin’s minimum principle, and a supporting semi-analytical reachability judgment method is presented, which can also be used to determine controllability. The algorithm is embedded in the model predictive control (MPC) framework, and several techniques are adopted to enhance stability and robustness, including thrust averaging, thrust correction after ignition, thrust reservation, and open-loop terminal guidance. Numerical simulations demonstrate that the proposed algorithm can guarantee real-time trajectory generation and meanwhile maintain considerable optimality. In addition, the MPC simulation shows that the algorithm can maintain a good accuracy under external disturbances. Full article
(This article belongs to the Special Issue Intelligence Sense, Optimization, and Control in Space Vehicles)
►▼ Show Figures

Figure 1

16 pages, 3811 KiB  
Article
Switching Neural Network Control for Underactuated Spacecraft Formation Reconfiguration in Elliptic Orbits
by Jinlong Yu, Zhi Li, Lu Jia and Yasheng Zhang
Appl. Sci. 2022, 12(12), 5792; https://doi.org/10.3390/app12125792 - 7 Jun 2022
Cited by 4 | Viewed by 1252
Abstract
A switching neural network control scheme, consisting of the adaptive neural network controller and sliding mode controller, is proposed for underactuated formation reconfiguration in elliptic orbits with the loss of either the radial or in-track thrust. By using the inherent coupling of system [...] Read more.
A switching neural network control scheme, consisting of the adaptive neural network controller and sliding mode controller, is proposed for underactuated formation reconfiguration in elliptic orbits with the loss of either the radial or in-track thrust. By using the inherent coupling of system states, the switching neural network technique is then adopted to estimate the unmatched disturbances and design the underactuated controller to achieve underactuated formation reconfiguration with high precision. The adaptive neural network controller works in the active region, and the disturbances composed of linearization errors and external perturbations are approximated by radial basis function neural networks. The adaptive sliding mode controller works outside the active region, and the upper bound of the approximation errors is estimated by the adaptation law. The stability of the closed-loop control system is proved via the Lyapunov-based approach. The numerical simulation results have demonstrated the rapid, high-precision and robust performance of the proposed controller compared with the linear sliding mode controller. Full article
(This article belongs to the Special Issue Intelligence Sense, Optimization, and Control in Space Vehicles)
►▼ Show Figures

Figure 1

22 pages, 7137 KiB  
Article
Free Final-Time Fuel-Optimal Powered Landing Guidance Algorithm Combing Lossless Convex Optimization with Deep Neural Network Predictor
by Wenbo Li and Shengping Gong
Appl. Sci. 2022, 12(7), 3383; https://doi.org/10.3390/app12073383 - 26 Mar 2022
Cited by 9 | Viewed by 2023
Abstract
The real-time guidance algorithm is the key technology of the powered landing. Given the lack of real-time performance of the convex optimization algorithm with free final time, a lossless convex optimization (LCvx) algorithm based on the deep neural network (DNN) predictor is proposed. [...] Read more.
The real-time guidance algorithm is the key technology of the powered landing. Given the lack of real-time performance of the convex optimization algorithm with free final time, a lossless convex optimization (LCvx) algorithm based on the deep neural network (DNN) predictor is proposed. Firstly, the DNN predictor is built to map the optimal final time. Then, the LCvx algorithm is used to solve the problem of fuel-optimal powered landing with the given final time. The optimality and real-time performance of the proposed algorithm are verified by numerical examples. Finally, a closed-loop simulation framework is constructed, and the accuracy of landing under various disturbances is verified. The proposed method does not need complex iterative operations compared with the traditional algorithm with free final time. Therefore, the computational efficiency can be improved by an order of magnitude. Full article
(This article belongs to the Special Issue Intelligence Sense, Optimization, and Control in Space Vehicles)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-7
Back to TopTop