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25 pages, 10751 KiB

Open AccessArticle

The Dvaraka Initiative: Mars’s First Permanent Human Settlement Capable of Self-Sustenance

by Arvind Mukundan, Akash Patel, Bharadwaj Shastri, Heeral Bhatt, Alice Phen and Hsiang-Chen Wang

Aerospace 2023, 10(3), 265; https://doi.org/10.3390/aerospace10030265 - 9 Mar 2023

Cited by 8 | Viewed by 3459

Abstract

From the farthest reaches of the universe to our own galaxy, there are many different celestial bodies that, even though they are very different, each have their own way of being beautiful. Earth, the planet with the best location, has been home to [...] Read more.

From the farthest reaches of the universe to our own galaxy, there are many different celestial bodies that, even though they are very different, each have their own way of being beautiful. Earth, the planet with the best location, has been home to people for as long as we can remember. Even though we cannot be more thankful for all that Earth has given us, the human population needs to grow so that Earth is not the only place where people can live. Mars, which is right next to Earth, is the answer to this problem. Mars is the closest planet and might be able to support human life because it is close to Earth and shares many things in common. This paper will talk about how the first settlement on Mars could be planned and consider a 1000-person colony and the best place to settle on Mars, and make suggestions for the settlement’s technical, architectural, social, and economic layout. By putting together assumptions, research, and estimates, the first settlement project proposed in this paper will suggest the best way to colonize, explore, and live on Mars, which is our sister planet. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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15 pages, 3115 KiB

Open AccessArticle

Predefined-Performance-Based Full-Process Control for Ultra-Close and High-Precision Formation Flying

by Xiande Wu, Wenbin Bai, Yaen Xie, Xianliang Zhang and Ting Song

Aerospace 2023, 10(2), 152; https://doi.org/10.3390/aerospace10020152 - 7 Feb 2023

Cited by 1 | Viewed by 1494

Abstract

The prescribed performance robust control method for the leader/follower (L/F) formation is proposed in this paper to solve the problem of spacecraft formation flying (SFF) full-process control (FPC). The objective of FPC is to establish an ultra-close formation with the constraint of collision [...] Read more.

The prescribed performance robust control method for the leader/follower (L/F) formation is proposed in this paper to solve the problem of spacecraft formation flying (SFF) full-process control (FPC). The objective of FPC is to establish an ultra-close formation with the constraint of collision avoidance between two spacecraft, and then to maintain the formation configuration with high-precision accuracy in a period of time. The main contribution of this paper lies in the following three aspects. Firstly, the six-degree-of-freedom (DOF) error dynamics model of SFF is developed to describe the synchronization motion of the L/F system. Secondly, the prescribed performance bound that comprehensively considers transience and transient performance is designed, which is key for the realization of collision avoidance and high-precision accuracy requirements. Finally, combing prescribed performance control and robust control theories, based on the backstepping method, the predefined performance robust controller is designed, and the tracking errors are proven to converge to the predefined performance bounds in the presence of external disturbances by using the predefined performance robust controller. Illustrative simulations are performed to verify the proposed theoretical results. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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19 pages, 4726 KiB

Open AccessArticle

Application of Model-Free Control to the Operation of Post-Capture Combined Spacecraft

by Ting Song, Zixuan Zheng, Yufei Guo and Jianping Yuan

Aerospace 2023, 10(1), 90; https://doi.org/10.3390/aerospace10010090 - 16 Jan 2023

Cited by 2 | Viewed by 1976

Abstract

A model-free control method is applied to the attitude and orbital operation of the post-capture combined spacecraft, which consists of a space robot and debris. The main contribution of this paper lies in the following three aspects. Firstly, the discrete dynamic linearization method [...] Read more.

A model-free control method is applied to the attitude and orbital operation of the post-capture combined spacecraft, which consists of a space robot and debris. The main contribution of this paper lies in the following three aspects. Firstly, the discrete dynamic linearization method of the motion equation for a post-capture combined spacecraft is proposed, and then, the standardized expression form of multiple input and multiple output system for the attitude and orbital dynamics motions of post-capture combined spacecraft are presented. Secondly, the data mapping model of the post-capture combined spacecraft is defined, and based on this, an initial value online optimization method for the data mapping model is provided, which is key for the convergence of model-free control. Finally, a test system based on the ground-based three-axis spacecraft simulator is built to simulate the attitude and orbital operation of post-capture combined spacecraft, and the experimental system is implemented to verify the validation of the model-free control method proposed in this paper. The results show that the model-free control has a good control effect on the attitude and orbit of the post-capture combined spacecraft, even if the configuration of the spacecraft is time-varying. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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30 pages, 2131 KiB

Open AccessArticle

Low-Energy Transfer Design of Heliocentric Formation Using Lunar Swingby on the Example of LISA

by Jia Yang, Zhong Zhang, Fanghua Jiang and Junfeng Li

Aerospace 2023, 10(1), 18; https://doi.org/10.3390/aerospace10010018 - 25 Dec 2022

Cited by 3 | Viewed by 2069

Abstract

Space-based gravitational wave (GW) detection at low frequencies is of great scientific significance and has received extensive attention in recent years. This work designs and optimizes the low-energy transfer of the heliocentric formation of GW detectors, which starts from a geosynchronous transfer orbit [...] Read more.

Space-based gravitational wave (GW) detection at low frequencies is of great scientific significance and has received extensive attention in recent years. This work designs and optimizes the low-energy transfer of the heliocentric formation of GW detectors, which starts from a geosynchronous transfer orbit and targets an Earth-like orbit. Based on the example of the Laser Interferometer Space Antenna (LISA), the transfer is first designed in two-body dynamical models and then refined in simplified high-fidelity dynamical models that only consider the major orbital perturbations evaluated here. The main contributions of this work are to present an adaptive model continuation technique and to exploit the lunar swingby technique to reduce the problem-solving difficulty and velocity increment of orbital transfer, respectively. The adaptive model continuation technique fully reveals the effect of perturbations and rapidly iterates the solutions to the simplified models. The simulation results show that the lunar swingby does reduce the energy needed to escape the Earth’s sphere of influence. It is found that the gravitation of the Earth–Moon system has a significant contribution to reducing the velocity increment. The solution of low-energy transfer in the simplified models is that the duration is 360.6615 days and the total velocity increment is 0.8468 km/s. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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19 pages, 2646 KiB

Open AccessArticle

Geometric Optimization of Blunt Bodies with Aerodisk and Opposing Jet for Wave Drag and Heat Reduction

by Muhammad Hamza, Saima Bukhat Khan and Adnan Maqsood

Aerospace 2022, 9(12), 800; https://doi.org/10.3390/aerospace9120800 - 6 Dec 2022

Cited by 1 | Viewed by 2270

Abstract

The use of passive, active, or hybrid flow control techniques is often investigated to reduce the acoustic signature, wave drag, and aerodynamic heating associated with the supersonic flow regime. This research explores passive and hybrid flow control techniques to achieve an optimal reduction [...] Read more.

The use of passive, active, or hybrid flow control techniques is often investigated to reduce the acoustic signature, wave drag, and aerodynamic heating associated with the supersonic flow regime. This research explores passive and hybrid flow control techniques to achieve an optimal reduction in wave drag and aerodynamic heating on a blunt body using an aerodisk. While passive techniques use one or two aerospikes, hybrid techniques employ opposing jets and aerospikes. Numerical analysis is performed using Reynolds-Averaged Navier–Stokes (RANS) equations to analyze the bodies’ flow field. The statistical technique, Design of Experiments (DOE), is combined with Response Surface Method (RSM) to find the optimal configuration for four cases by generating design space. Two cases were considered for the optimization: single aerospike with and without opposing jet and double aerospike with and without opposing jet. Variables used for the design of the aerodisks were spike length and diameter, while the response variables were wave drag and normalized heat flux. The current study has established an optimum relationship between spike length and aerospike diameter located in front of the main blunt body for both single and double aerospikes. The study’s results suggest that a double aerodisk configuration is more beneficial for reducing drag and heat flux at supersonic speed than a single aerodisk. By incorporating an opposing jet at a pressure ratio of 0.8 from the frontal aerodisk to the spiked blunt body, it can reduce drag and heat flux by 86% and 95%, respectively. Finally, numerical verification is performed for statistically optimized designs. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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20 pages, 11105 KiB

Open AccessArticle

Comparison of Two Folded Methods of Solar Sails

by Laohu Yuan, Rui Song, Feng Wang, Jianzheng Wei and Jiafu Liu

Aerospace 2022, 9(12), 746; https://doi.org/10.3390/aerospace9120746 - 23 Nov 2022

Cited by 2 | Viewed by 1842

Abstract

The solar sails can be deployed by jointed truss or by inflated support tube. The deployed process and final deployed state of the solar sails is closely related to the design of the deployed mechanism. Therefore, the design of the deployed mechanism is [...] Read more.

The solar sails can be deployed by jointed truss or by inflated support tube. The deployed process and final deployed state of the solar sails is closely related to the design of the deployed mechanism. Therefore, the design of the deployed mechanism is very important for this new type of spacecraft. In this paper, we study the problem of the inflatable deployment of the solar sail; we utilized MSC.Patran to build the Z-folded and the Z+ curly-folded finite element models. LS-DYNA was used to simulate the dynamic characteristics of the above two solar sails under different conditions, and the results were analyzed. The results show that in the model that adopted the Z-folded method, the deployed process is relatively stable, and the effect of deployment is good, which is more suitable for practical application. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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15 pages, 1250 KiB

Open AccessArticle

Mixed-Sensitivity Control for Drag-Free Spacecraft Based on State Space

by Yuan Liu and Changwu Jiang

Aerospace 2022, 9(11), 708; https://doi.org/10.3390/aerospace9110708 - 12 Nov 2022

Cited by 1 | Viewed by 1605

Abstract

This paper investigates a mixed-sensitivity control method for a class of drag-free spacecraft-needed frequency-separation control, which overcomes the coupled problem of a multiple-in multiple-out (MIMO) system with multiple sensitive-axes and disturbances of actuators. Firstly, the relative dynamics equation is established based on the [...] Read more.

This paper investigates a mixed-sensitivity control method for a class of drag-free spacecraft-needed frequency-separation control, which overcomes the coupled problem of a multiple-in multiple-out (MIMO) system with multiple sensitive-axes and disturbances of actuators. Firstly, the relative dynamics equation is established based on the character of displacement error, which is separated by that test-mass (TMs) tracking ideal orbit with high-frequency displacement and cavity of spacecraft tracking TMs with low-frequency displacement. Secondly, the feedback gain matrix is obtained by the LMI/SDP, which is devised by a general system containing a weight function. Finally, the simulation results demonstrate the performance of the proposed method. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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21 pages, 8355 KiB

Open AccessArticle

Design and Analysis of a Compression and Separation Device for Multi-Satellite Deployment

by Yong Zhao, Qingguang Zhao, Fei Yang, Honghao Yue, Xiaoze Yang and Huaiyu Li

Aerospace 2022, 9(8), 446; https://doi.org/10.3390/aerospace9080446 - 14 Aug 2022

Cited by 4 | Viewed by 2189

Abstract

The launch method of one arrow with multiple satellites can greatly shorten the time for constellation networking and improve the deployment efficiency. A new compression and separation device with a four-bar perimeter arrangement is proposed for multi-satellite compaction and in-orbit release. A compression [...] Read more.

The launch method of one arrow with multiple satellites can greatly shorten the time for constellation networking and improve the deployment efficiency. A new compression and separation device with a four-bar perimeter arrangement is proposed for multi-satellite compaction and in-orbit release. A compression device with gap elimination is designed to implement the reliable compaction of stacked flat satellites. An electromagnetic separation device is proposed to achieve the fast, low-interference release of multi-satellites. The dynamic model with flexible guide bars is established. The separation characteristics of multiple satellites are analyzed by the kinematic simulation. The prototype is developed, and the related experiment is implemented. The results show that the four-guide-bar-edge arrangement scheme with a gap elimination device achieves reliable locking and fast separation under a vibration environment. The dynamic separation characteristics of satellites are investigated by the air floatation experiments. The results show that a stable separation speed and low disturbance angular velocity are achieved under 10% spring error. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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25 pages, 3258 KiB

Open AccessArticle

Modular Self-Reconfigurable Satellite Inverse Kinematic Solution Method Based on Improved Differential Evolutionary Algorithm

by Gangxuan Hu, Guohui Zhang, Yanyan Li, Xun Wang, Jiping An, Zhibin Zhang and Xinhong Li

Aerospace 2022, 9(8), 434; https://doi.org/10.3390/aerospace9080434 - 6 Aug 2022

Cited by 1 | Viewed by 1521

Abstract

The modular self-reconfigurable satellites (MSRSs) are a new type of satellite that can transform configuration in orbit autonomously. The inverse kinematics of MSRS is difficult to solve by conventional methods due to the hyper-redundant degrees of freedom. In this paper, the kinematic model [...] Read more.

The modular self-reconfigurable satellites (MSRSs) are a new type of satellite that can transform configuration in orbit autonomously. The inverse kinematics of MSRS is difficult to solve by conventional methods due to the hyper-redundant degrees of freedom. In this paper, the kinematic model of the MSRS is established, and the inverse kinematic of the MSRS is transformed into an optimal solution problem with minimum pose error and minimum energy consumption. In order to find the inverse kinematic exact solution, the refractive opposition-based learning and Cauchy mutation perturbation improved differential evolutionary algorithm (RCDE) is proposed. The performance of the algorithm was examined using benchmark functions, and it was demonstrated that the accuracy and convergence speed of the algorithm were significantly improved. Three typical cases are designed, and the results demonstrate that the optimization method is effective in solving the MSRS inverse kinematics problem. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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Review

Jump to: Research

27 pages, 4548 KiB

Open AccessReview

Review of On-Orbit Robotic Arm Active Debris Capture Removal Methods

by Wei Zhang, Feng Li, Junlin Li and Qinkun Cheng

Aerospace 2023, 10(1), 13; https://doi.org/10.3390/aerospace10010013 - 23 Dec 2022

Cited by 24 | Viewed by 6884

Abstract

Space is the driving force of the world’s sustainable development, and ensuring the sustainability of human activity in space is also necessary. Robotic arm active debris capture removal (RA-ADCR) is a noteworthy technology for containing the dramatic increase in space debris and maintaining [...] Read more.

Space is the driving force of the world’s sustainable development, and ensuring the sustainability of human activity in space is also necessary. Robotic arm active debris capture removal (RA-ADCR) is a noteworthy technology for containing the dramatic increase in space debris and maintaining orbital safety. This review divides the RA-ADCR technology progress history into three periods and presents the status of related research. Two major development trends are summarized and subdivided through the analysis and collation of research achievements over the past three years. Taking the treatment of parameter uncertainties as the entry point, researchers would like to improve the discrimination accuracy and scope to reduce uncertainties. On the other hand, researchers accept such uncertainties and would like to offset and avoid the impact of uncertainties by extending the error margins. Subsequently, the challenges of RA-ADCR are analyzed in line with the task execution flow, which mainly focuses on the conflict between on-satellite computing power and the performance of task execution. In addition, feasible solutions for the current phase are discussed. Finally, future outlooks are evaluated and discussed. Full article

(This article belongs to the Special Issue Emerging Space Missions and Technologies)

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