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Aerospace
Special Issues
Dynamics, Guidance and Control of Aerospace Vehicles
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Dynamics, Guidance and Control of Aerospace Vehicles

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: 15 August 2024 | Viewed by 2678

Special Issue Editors

Prof. Dr. Wanchun Chen

E-Mail Website
Guest Editor
School of Astronautics, Beihang University, 37 Xueyuan Road, Haidian District, Beijing 100191, China
Interests: flight dynamics, guidance and control; integrated design; analysis of aerospace vehicle
Dr. Wenbin Yu

E-Mail Website
Co-Guest Editor
School of Astronautics, Beihang University, 37 Xueyuan Road, Haidian District, Beijing 100191, China
Interests: applied mathematics; flight dynamics, guidance and control
Dr. Zhongyuan Chen

E-Mail Website
Co-Guest Editor
School of Astronautics, Beihang University, 37 Xueyuan Road, Haidian District, Beijing 100191, China
Interests: cooperative guidance; formation control; integrated navigation; hardware-in-the-loop simulation

Special Issue Information

Dear Colleagues,

Today, aerospace vehicles have a wide range of applications, including in satellites, probes, landers, hypersonic glide vehicles, missiles, etc. On the other hand, requirements for the guidance and control systems of aerospace vehicles are increasing. Firstly, aerospace vehicles must satisfy multiple terminal and process constraints to achieve specific objectives. Secondly, the current trend of multifunctional space vehicles highlights the need for the cooperative control/guidance of multiple vehicles to enable them to perform certain tasks that used to be conducted by a single conventional aerospace vehicle, or to achieve multiple goals at once. Thirdly, the strong nonlinearity of some dynamics will impede the analysis of dynamic systems and the design of guidance and control strategies for aerospace vehicles.

This Special Issue aims to feature original research papers, as well as comprehensive state-of-the-art surveys, on recent scientific discoveries and technological advancements in the dynamics, guidance and control of aerospace vehicles. Topics include, but are not limited to: 

  • Analytical dynamic models;
  • Aerospace vehicle dynamics;
  • Trajectory planning;
  • Entry guidance;
  • Multi-constraint guidance;
  • Cooperative guidance;
  • The dynamics and control of formation flying;
  • Trajectory optimization.

We look forward to receiving your submissions, and invite you to contact us if you have any questions.

Prof. Dr. Wanchun Chen
Dr. Wenbin Yu
Dr. Zhongyuan Chen
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. Aerospace is an international peer-reviewed open access monthly 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

  • analytical dynamic models
  • aerospace vehicle dynamics
  • trajectory planning
  • entry guidance
  • multi-constraint guidance
  • cooperative guidance
  • dynamics and control of formation flying
  • trajectory optimization
  • optimal control of aerospace vehicles

Published Papers (4 papers)

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Research

23 pages, 3190 KiB  
Article
Rapid and Near-Analytical Planning Method for Entry Trajectory under Time and Full-State Constraints
by Wenjie Xia, Peichen Wang, Xunliang Yan, Bei Hong and Xinguo Li
Aerospace 2024, 11(7), 580; https://doi.org/10.3390/aerospace11070580 - 16 Jul 2024
Viewed by 309
Abstract
A rapid trajectory-planning method based on an analytical predictor–corrector design of drag acceleration profile and a bank-reversal logic based on double-stage adaptive adjustment is proposed to solve the entry issue under time and full-state constraints. First, an analytical predictor–corrector algorithm is used to [...] Read more.
A rapid trajectory-planning method based on an analytical predictor–corrector design of drag acceleration profile and a bank-reversal logic based on double-stage adaptive adjustment is proposed to solve the entry issue under time and full-state constraints. First, an analytical predictor–corrector algorithm is used to design the profile parameters to satisfy the terminal of altitude, velocity, range, time, and flight-path angle constraints. Subsequently, an adaptive lateral planning algorithm based on heading adjustment and maintenance is proposed to achieve the flight stage adaptive division and determination of the bank-reversal point, thereby satisfying the terminal position and heading angle constraints. Concurrently, a rapid quantification method is proposed for the adjustable capacity boundary of the terminal heading angle. On this basis, a range-and-time correction strategy is designed to achieve high precision and the rapid generation of a three-degree-of-freedom entry trajectory under large-scale lateral maneuvering. The simulation results demonstrated that compared with the existing methods, the proposed method can adaptively divide flight stages, ensuring better multitask applicability and higher computational efficiency. Full article
(This article belongs to the Special Issue Dynamics, Guidance and Control of Aerospace Vehicles)
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22 pages, 4248 KiB  
Article
Deep Reinforcement Learning-Based Differential Game Guidance Law against Maneuvering Evaders
by Axing Xi and Yuanli Cai
Aerospace 2024, 11(7), 558; https://doi.org/10.3390/aerospace11070558 - 6 Jul 2024
Viewed by 389
Abstract
To achieve the intelligent interception of different types of maneuvering evaders, based on deep reinforcement learning, a novel intelligent differential game guidance law is proposed in the continuous action domain. Different from traditional guidance laws, the proposed guidance law can avoid tedious manual [...] Read more.
To achieve the intelligent interception of different types of maneuvering evaders, based on deep reinforcement learning, a novel intelligent differential game guidance law is proposed in the continuous action domain. Different from traditional guidance laws, the proposed guidance law can avoid tedious manual settings and save cost efforts. First, the interception problem is transformed into the pursuit–evasion game problem, which is solved by zero-sum differential game theory. Next, the Nash equilibrium strategy is obtained through the Markov game process. To implement the proposed intelligent differential game guidance law, an actor–critic neural network based on deep deterministic policy gradient is constructed to calculate the saddle point of the differential game guidance problem. Then, a reward function is designed, which includes the tradeoffs among guidance accuracy, energy consumption, and interception time. Finally, compared with traditional methods, the interception accuracy of the proposed intelligent differential game guidance law is 99.2%, energy consumption is reduced by 47%, and simulation time is shortened by 1.58 s. All results reveal that the proposed intelligent differential game guidance law has better intelligent decision-making ability. Full article
(This article belongs to the Special Issue Dynamics, Guidance and Control of Aerospace Vehicles)
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22 pages, 3795 KiB  
Article
Data-Driven-Method-Based Guidance Law for Impact Time and Angle Constraints
by Wenjie Cao, Jia Huang and Sijiang Chang
Aerospace 2024, 11(7), 540; https://doi.org/10.3390/aerospace11070540 - 1 Jul 2024
Viewed by 379
Abstract
To increase the hit efficiency and lethality of a flight vehicle, it is necessary to consider the vehicle’s guidance law concerning both impact time and angle constraints. In this study, a novel and straightforward impact time and angle control guidance law that is [...] Read more.
To increase the hit efficiency and lethality of a flight vehicle, it is necessary to consider the vehicle’s guidance law concerning both impact time and angle constraints. In this study, a novel and straightforward impact time and angle control guidance law that is independent of time-to-go and small angle approximations is proposed with two stages using a data-driven method and proportional navigation guidance. First, a proportional navigation guidance-based impact angle control guidance law is designed for the second stage. Second, from various initial conditions on the impact angle control guidance simulation with various initial conditions, the input and output datasets are obtained to build a mapping network. Using the neural network technique, a mapping network model that can output the ideal flight path angle in flight is constructed for impact time control in the first stage. The proposed impact time and angle control guidance law reduces to the proportional navigation guidance law when the flight path angle error converges to zero. The simulation results show that the proposed guidance law delivers excellent performance under various conditions (including cooperative attack) and features better acceleration performance and less control energy than does the comparative impact time and angle control guidance law. The results of this research are expected to supplement those exploring various paradigms to solve the impact time and angle control guidance problem, as concluded in the current literature. Full article
(This article belongs to the Special Issue Dynamics, Guidance and Control of Aerospace Vehicles)
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32 pages, 32908 KiB  
Article
An Analytical Reentry Solution Based Online Time-Coordinated A* Path Planning Method for Hypersonic Gliding Vehicles Considering No-Fly-Zone Constraint
by Zihan Xie, Changzhu Wei, Naigang Cui and Yingzi Guan
Aerospace 2024, 11(6), 499; https://doi.org/10.3390/aerospace11060499 - 20 Jun 2024
Viewed by 462
Abstract
To meet the time-coordinated requirement of hypersonic gliding vehicles to reach a single target simultaneously in the presence of no-fly-zone constraints, this paper proposes a time-coordinated A* path planning method considering multiple constraints. The path planning method is designed based on an analytical [...] Read more.
To meet the time-coordinated requirement of hypersonic gliding vehicles to reach a single target simultaneously in the presence of no-fly-zone constraints, this paper proposes a time-coordinated A* path planning method considering multiple constraints. The path planning method is designed based on an analytical steady gliding path model and the framework of the A* algorithm. Firstly, an analytical steady gliding path model is designed based on a quadratic function-type altitude-velocity profile. It can derive the control commands explicitly according to the desired terminal altitude and velocity, thus establishing a mapping between the terminal states and the control commands. Secondly, the node extension method of the A* algorithm is improved based on the mapping. Taking the terminal states as new design variables, a feasible path-node set is produced by a one-step integration using the control commands derived according to different terminal states. This node extension method ensures the feasibility of the path nodes while satisfying terminal constraints. Next, the path evaluation function of the A* algorithm is modified by introducing a heuristic switching term to select the most proper node as a waypoint, aiming to minimize the arrival time deviation. Meanwhile, introducing the penalty items into the path evaluation function satisfies the no-fly-zone constraints, process constraints, and control variable constraints. Finally, an online time-coordinated method is proposed to determine a commonly desired arrival time for several hypersonic gliding vehicles. It eliminates the need to specify the arrival time in advance and improves the capability to deal with sudden threats, increasing the path planning method’s online application capability. The proposed method can achieve online time-coordinated multi-constraint path planning for several hypersonic gliding vehicles, whose effectiveness and superiority are verified by simulations. Full article
(This article belongs to the Special Issue Dynamics, Guidance and Control of Aerospace Vehicles)
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Planned Papers

The below list represents only planned manuscripts. Some of these manuscripts have not been received by the Editorial Office yet. Papers submitted to MDPI journals are subject to peer-review.

Title: Long-term perturbed orbit propagation method based on node correction and incremental iteration
Author: Dong
Highlights: (1) A numerical computation method is proposed for iterative computation using integral increments (2) Analyzes the influencing factors when using the method for orbit propagation calculations (3) Designed a computational scheme for long-term orbits based on node corrections (4) Experimental evidence that the proposed method can increase the computational speed by tens of times

Title: Research on Honeycomb Structure for Pyroshock Isolation at Spacecraft-Rocket Interface
Authors: Xixiong Wang; Zhibo Gao; Dong Cheng; Xuchen Deng; Tao Yu; Zhaoye Qin; Fulei Chu
Affiliation: School of Electromechanical and Automotive Engineering, Yantai University, Yantai 264005, China
Abstract: Honeycomb is a splendid kind of structure for aerospace engineering with the advantage of light weight, good shock absorption and good structural stability. This article aims to provide methods to isolate Pyroshock based on honeycomb structure and guarantee the safety of such equipment against high-frequency shock response. According to stress wave theory, an equation for stress wave transmittance of honeycomb structure is derived considering the effect of cell wall length and thickness, where desirable honeycomb parameters are obtained. The complexity of transfer path of the honeycomb structure is exploited to build the spacecraft-rocket interface, which could increase the impedance of the stress wave dramatically. Both finite element analysis and experiments are carried out to validate the shock isolation strategies. The influence of parameters such as cell wall length and thickness of stainless steel honeycomb on the isolation performance is analyzed. It is revealed that the honeycomb structure has the significant effect on Pyroshock isolation performance when the wall length of the honeycomb cell is 8 mm and the thickness of the cell is 0.1 mm.

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