Xinyu Jiang¹, Chongrui Du¹, Yamin Wang², Honghua Dai^1,*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.33, No.4, pp. 1-1, 2025, DOI:10.32604/icces.2025.011552

Abstract Persistent high-resolution observation of the solar corona is essential for advancing human’s understanding of critical solar phenomena, including coronal heating, solar wind acceleration, and the initiation of coronal mass ejections that significantly impact space weather. This study proposes a novel space-based solar corona observation mission concept, which uses a tethered solar sail spacecraft to create a sustained artificial total solar eclipse near the Sun-Earth L2 point. By positioning a probe at the end of Earth’s umbra cone and leveraging Earth as a natural occulter, the mission enables uninterrupted observations of the innermost solar corona. To… More >

Zhiguang Zhang, Caisheng Wei, Guanhua Huang, Zeyang Yin^*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.33, No.3, pp. 1-1, 2025, DOI:10.32604/icces.2025.010967

Abstract An optimal predictive control method for spacecraft rendezvous based on Koopman operator is proposed for the the libration point rendezvous problem of Earth-moon system. Firstly, the relative motion dynamics model between the chaser and the target spacecraft in the Earth-moon system is established. Secondly, considering the influence of nonlinearity on spacecraft rendezvous control, a global linearization method of nonlinear rendezvous system driven by Koopman operator is proposed. In this method, the Koopman linearization operator is approximated by the extended dynamic mode decomposition (EDMD) method on the finite dimension. Subsequently, based on the linearization model of… More >

Chuxin Wang, Qi Wu, Zenong Fang, Chang Liu, Guoguang Li, Ye Wang, Hongxing Zhang^*, Jianyin Miao

Frontiers in Heat and Mass Transfer, Vol.23, No.4, pp. 1261-1280, 2025, DOI:10.32604/fhmt.2025.066473 - 29 August 2025

Abstract With the development of space-based remote sensing and deep space exploration technology, higher standards for temperature stability and uniformity of payloads have been proposed to spacecraft thermal control systems. As an efficient two-phase heat transfer device with active temperature control capabilities, the loop heat pipe (LHP) can be widely applied in spacecraft thermal control systems to achieve reliable temperature control under various operating modes and complex space thermal environments. This paper analyzes the fundamental theories of thermal switch-controlled, reservoir temperature-controlled, and bypass valve-controlled LHPs. The focus is on the theories and methods of achieving high-precision… More >

Xue Wang^1,2, Weizhou Zhu^1,2, Zhao Cui^2,3, Xingguang Qian^2,3, Jinke Yang^1,2, Jianjun Jia^1,2,*, Yikun Wang^2,3,*

CMES-Computer Modeling in Engineering & Sciences, Vol.140, No.1, pp. 325-337, 2024, DOI:10.32604/cmes.2024.048804 - 16 April 2024

Abstract The gravitational wave spacecraft is a complex multi-input multi-output dynamic system. The gravitational wave detection mission requires the spacecraft to achieve single spacecraft with two laser links and high-precision control. Establishing one spacecraft with two laser links, compared to one spacecraft with a single laser link, requires an upgraded decoupling algorithm for the link establishment. The decoupling algorithm we designed reassigns the degrees of freedom and forces in the control loop to ensure sufficient degrees of freedom for optical axis control. In addressing the distinct dynamic characteristics of different degrees of freedom, a transfer function More >

Hongqian Zhao^1,2, Honghua Dai^1,2,*, Xiaokui Yue^1,2

The International Conference on Computational & Experimental Engineering and Sciences, Vol.25, No.4, pp. 1-1, 2023, DOI:10.32604/icces.2023.09294

Abstract Detumbling is a crucial first step for on-orbit service and space debris removal. Plume is an efficient medium for failed spacecraft detumbling which can avoid direct contact to ensure the safety of the spacecraft. However, traditional molecular plume may lead to an unaffordable fuel consumption. This paper proposes a novel detumbling strategy by using plasma plume with the popularization of Hall effect thrusters on spacecraft. To overcome the difficulty of real-time calculation in traditional models, a fully analytical plasma plume model is established which can improve the autonomy of the chaser[1]. An optimal detumbling guidance… More >

Wei Cong, Yong Zhao^*, Bingxiao Du^*, Senlin Huo, Xianqi Chen

CMES-Computer Modeling in Engineering & Sciences, Vol.136, No.1, pp. 621-654, 2023, DOI:10.32604/cmes.2023.025143 - 05 January 2023

Abstract The spacecraft equipment layout optimization design (SELOD) problems with complicated performance constraints and diversity are studied in this paper. The previous literature uses the gradient-based algorithm to obtain optimized non-overlap layout schemes from randomly initialized cases effectively. However, these local optimal solutions are too difficult to jump out of their current relative geometry relationships, significantly limiting their further improvement in performance indicators. Therefore, considering the geometric diversity of layout schemes is put forward to alleviate this limitation. First, similarity measures, including modified cosine similarity and gaussian kernel function similarity, are introduced into the layout optimization More >

Sha Wang^1,2, Chenglong He¹, Baichun Gong^2,*, Xin Ding², Yanhua Yuan³

CMES-Computer Modeling in Engineering & Sciences, Vol.134, No.1, pp. 121-134, 2023, DOI:10.32604/cmes.2022.017470 - 24 August 2022

Abstract As to solve the collaborative relative navigation problem for near-circular orbiting small satellites in close-range under GNSS denied environment, a novel consensus constrained relative navigation algorithm based on the lever arm effect of the sensor offset from the spacecraft center of mass is proposed. Firstly, the orbital propagation model for the relative motion of multi-spacecraft is established based on Hill-Clohessy-Wiltshire dynamics and the line-of-sight measurement under sensor offset condition is modeled in Local Vertical Local Horizontal frame. Secondly, the consensus constraint model for the relative orbit state is constructed by introducing the geometry constraint between More >

Danhe Chen^1,*, A. A. Baranov², Chuangge Wang¹, M. O. Karatunov³, N. Yu. Makarov³

CMES-Computer Modeling in Engineering & Sciences, Vol.127, No.3, pp. 977-991, 2021, DOI:10.32604/cmes.2021.014662 - 24 May 2021

Abstract As the number of space objects (SO) increases, collision avoidance problem in the rendezvous tasks or re-constellation of satellites with SO has been paid more attention, and the dangerous area of a possible collision should be derived. In this paper, a maneuvering method is proposed for avoiding collision with a space debris object in the phasing orbit of the initial optimal solution. Accordingly, based on the plane of eccentricity vector components, relevant dangerous area which is bounded by two parallel lines is formulated. The axises of eccentricity vector system pass through the end of eccentricity… More >

Gen Xu, Danhe Chen, Xiang Zhang, Wenhe Liao^*

CMES-Computer Modeling in Engineering & Sciences, Vol.125, No.2, pp. 865-878, 2020, DOI:10.32604/cmes.2020.012844 - 12 October 2020

Abstract For the on-orbit flight missions, the model of orbit prediction is critical for the tasks with high accuracy requirement and limited computing resources of spacecraft. The precession-nutation model, as the main part of extended orbit prediction, affects the efficiency and accuracy of on-board operation. In this paper, the previous research about the conversion between the Geocentric Celestial Reference System and International Terrestrial Reference System is briefly summarized, and a practical concise precession-nutation model is proposed for coordinate transformation computation based on Celestial Intermediate Pole (CIP). The idea that simplifying the CIP-based model with interpolation method… More >

Baichun Gong¹, Chenglong He^{2, *}, Degang Zhang¹

CMES-Computer Modeling in Engineering & Sciences, Vol.122, No.1, pp. 207-219, 2020, DOI:10.32604/cmes.2020.08616 - 01 January 2020

Abstract Aimed at the problem of final translation of space rendezvous for the applications such as docking, inspection and tracking, optimal straight-line guidance algorithm based on pulse/continuous low-thrust in the context of Clohessy-Wiltshire dynamics is proposed. Two modes of guidance strategy: varying-speed and fixed-speed approaching scheme for V-bar and R-bar approach by using constant/finite low-thrust propulsion respectively are studied, and the corresponding fuel-optimal conditions are obtained. Numerical simulation is conducted to verify and test the proposed algorithms. The results show that there is generally no different between the fuel consumptions by using the two different approaching More >