Oblique Cold Launch Technology of Mars Ascent Vehicle

doi:10.12382/bgxb.2024.0957

Abstract

Abstract:

The launch of Mars Ascent Vehicle (MAV) is the key technology to realize China's 2030 Mars Sample Return.To study the oblique cold launch technology of MAV,based on the theory of interior ballistics of catapults,a parallel recoilless interior ballistic scheme is designed to meet the launch conditions of Mars.Based on the discrete element method,a discrete element model of Mars soil is established.Additionally,a rigid-flexible coupling dynamics model of the launcher system is constructed.Finally,based on the launch dynamics theory,the entire launch process of the MAV under different working conditions is simulated and analyzed.The results show that the internal ballistics scheme obtained can meet the launch requirements.The recoilless design plays an important role in ensuring the stability of the launch vehicle.Discretization of soil helps to characterize the dynamic behavior of Martian soil.The larger the ground inclination angle,the worse the stability and launch accuracy.Among the four directions at the same inclination angle,the stability of the launch facing uphill is the worst.The “virtual leg” phenomenon can reduce launch stability and may even cause the launch device to topple,leading to launch failure.

Key words: Mars launch, oblique cold launch, interior ballistics design, discrete element, launch dynamics

CLC Number:

TJ768.2

LIU Gentong, JIANG Yi, CAI Yunlong. Oblique Cold Launch Technology of Mars Ascent Vehicle[J]. Acta Armamentarii, 2025, 46(8): 240957-.

Figures/Tables 38

References 30

[1]	JONES A. Achieving mars sample return on a single Ares V launch[D]. Huntsville,AL,US: The University of Alabama in Huntsville, 2010.
[2]	马永丽, 李沐阳, 马子皓, 等. 火星上的气固流态化模拟实验[J]. 化工进展, 2024, 43(8):4203-4209. doi: 10.16085/j.issn.1000-6613.2023-1147
	MA Y L, LI M Y, MA Z H, et al. Experiment of simulation study on gas-solid fluidization on Martian environments[J]. Chemical Industry and Engineering Progress, 2024, 43(8):4203-4209. (in Chinese) doi: 10.16085/j.issn.1000-6613.2023-1147
[3]	赵健楠, 赵源, 张诗琪, 等. 火星水资源探测、开采及原位利用研究进展[J]. 华中科技大学学报(自然科学版), 2024, 52(8):29-40.
	ZHAO J N, ZHAO Y, ZHANG S Q, et al. Research progress on exploration,exploitation,and in-situ utilization of Martian water resources[J]. Journal of Huazhong University of Science and Technology (Natural Science Edition), 2024, 52(8):29-40. (in Chinese)
[4]	时蓬, 范全林, 汤惟玮. 关于2030年前火星采样返回科学任务的展望[J]. 空间科学学报, 2020, 40(3):301-304.
	SHI P, FAN Q L, TANG W W. Prospects of mars sample return science mission before 2030[J]. Chinese Journal of Space Science, 2020, 40(3):301-304. (in Chinese)
[5]	张胜, 唐晓峰, 刘可平, 等. 火星上升器发射技术综述[J]. 空天防御, 2023, 6(3):66-76.
	ZHANG S, TANG X F, LIU K P, et al. Review on research status of mars ascent vehicle's launching technology[J]. Air and Space Defense, 2023, 6(3):66-76. (in Chinese)
[6]	ROSS D, RUSSELL J, SUTTER B. Mars ascent vehicle(MAV):designing for high heritage and low risk[C]// Proceedings of 2012 IEEE Aerospace Conference. Big Sky,MT,US: IEEE, 2012:1-6.
[7]	SENGUPTA A, PAUKEN M, KENNETT A, et al. Systems engineering and support systems technology considerations of a Mars ascent vehicle[C]// Proceedings of 2012 IEEE Aerospace Conference. Big Sky,MT,US: IEEE, 2012:3028-3038.
[8]	SHOTWELL R, BENITO J, KARP A, et al.Drivers, developments and options under consideration for a Mars ascent vehicle[C]// Proceedings of 2016 IEEE Aerospace Conference. Big Sky,MT,US: IEEE, 2016:1-14.
[9]	LANDIS G A, OLESON S R, PACKARD T W, et al. Design study of a Mars ascent vehicle for sample return using in-situ generated propellant[C]// Proceedings of the 10th Symposium on Space Re-source Utilization. Grapevine,TX,US: AIAA, 2017:0424.
[10]	YAGHOUBI D, MA P. Integrated design results for the MSR DAC-0.0 Mars ascent vehicle[C]// Proceedings of 2021 IEEE Aerospace Conference(50100). Big Sky,MT,US: IEEE, 2021:1-17.
[11]	谭大成. 弹射内弹道学[M]. 北京: 北京理工大学出版社, 2015.
	TAN D C. Interior ballistics of catapults[M]. Beijing: Beijing Institute of Technology Press, 2015. (in Chinese)
[12]	VANDAELE A C, AOKI S, BAUDUIN S, et al. Composition and chemistry of the Martian atmosphere as observed by Mars express and exomars trace gas orbiter[J]. Space Science Reviews, 2024, 220(7):75-112.
[13]	常勇强, 曹子栋, 赵振兴, 等. 多组分气体热物性参数的计算方法[J]. 动力工程学报, 2010, 30(10):772-776.
	CHANG Y Q, CAO Z D, ZHAO Z X, et al. Calculation method for thermal properties of multi-component gas[J]. Journal of Chinese Society of Power Engineering, 2010, 30(10):772-776. (in Chinese)
[14]	孙冠文, 崔寒茵, 李超, 等. 火星大气频散声速剖面建模方法及其对声传播路径的影响[J]. 物理学报, 2022, 71(24):271-283.
	SUN G W, CUI H Y, LI C, et al. Methods of modelling dispersive sound speed profiles of Martian atmosphere and their effects on sound propagation paths[J]. Acta Physica Sinica, 2022, 71(24):271-283. (in Chinese)
[15]	黄飞, 吕俊明, 程晓丽, 等. 火星进入器高空稀薄气动特性[J]. 航空学报, 2017, 38(5):15-21.
	HUANG F, LÜ J M, CHENG X L, et al. Aerodynamics of Mars entry vehicles under hypersonic rarefied condition[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(5):15-21. (in Chinese)
[16]	庞春桥, 陶钢, 李召, 等. 轻型无后坐力炮的动不平衡冲量特性[J]. 兵工学报, 2020, 41(12):2424-2431. doi: 10.3969/j.issn.1000-1093.2020.12.007
	PANG C Q, TAO G, LI Z, et al. Dynamic unbalance impulse charecteristics of a light recoilless rifle[J]. Acta Armamentarii, 2020, 41(12):2424-2431. (in Chinese) doi: 10.3969/j.issn.1000-1093.2020.12.007
[17]	贾乐凡, 史宏斌, 沙宝林. 翻转条件下固体火箭发动机药柱-衬层界面力学响应[J]. 推进技术, 2022, 43(12):390-396.
	JIA L F, SHI H B, SHA B L. Dynamic response of solid rocket motor grain-liner interface under flip condition[J]. Journal of Propulsion Technology, 2022, 43(12):390-396. (in Chinese)
[18]	程李东, 姜毅, 张曼曼, 等. 水压式垂直发射装置内弹道建模与分析[J]. 哈尔滨工程大学学报, 2022, 43(2):221-227.
	CHENG L D, JIANG Y, ZHANG M M, et al. Modeling and analyzing the interior trajectory of hydraulic submersible vertical missile launchers[J]. Journal of Harbin Engineering University, 2022, 43(2):221-227. (in Chinese)
[19]	廖欢欢, 张海波, 熊勇, 等. 高低压室发射弹丸内弹道仿真与试验研究[J]. 弹道学报, 2022, 34(4):45-51. doi: 10.12115/j.issn.1004-499X(2022)04-007
	LIAO H H, ZHANG H B, XIONG Y, et al. Simulation and experimental study on interior ballistics of projectiles launched with high-low pressure chamber[J]. Journal of Ballistics, 2022, 34(4):45-51. (in Chinese)
[20]	杨磊, 涂冬媚, 朱启银, 等. 考虑变温幅值影响的颗粒循环热固结离散元法试验研究[J]. 岩土力学, 2022, 43(增刊1):591-600.
	YANG L, TU D M, ZHU Q Y, et al. Experimental research on discrete element method of particle cyclic thermal consolidation considering the influence of variable temperature amplitude[J]. Rock and Soil Mechanics, 2022, 43(S1):591-600. (in Chinese)
[21]	肖万港, 周云波, 傅耀宇, 等. 土壤对军用越野车辆机动性能影响分析[J]. 兵工学报, 2024, 45(1):288-298. doi: 10.12382/bgxb.2022.0528
	XIAO W G, ZHOU Y B, FU Y Y, et al. Analysis of the influence of soil on the maneuverability of military off-road vehicles[J]. Acta Armamentarii, 2024, 45(1):288-298. (in Chinese) doi: 10.12382/bgxb.2022.0528
[22]	欧阳自远, 肖福根. 火星及其环境[J]. 航天器环境工程, 2012, 29(6):591-601.
	OUYANG Z Y, XIAO F G. Mars and its environment[J]. Spacecraft Environment Engineering, 2012, 29(6):591-601. (in Chinese)
[23]	刘汉生, 王江, 赵健楠, 等. 典型模拟火星土壤研究进展[J]. 载人航天, 2020, 26(3):389-402.
	LIU H S, WANG J, ZHAO J N, et al. Research progress of typical Martian soil simulants[J]. Manned Spaceflight, 2020, 26(3):389-402. (in Chinese)
[24]	王庚祥, 马道林, 刘洋, 等. 多体系统碰撞动力学中接触力模型的研究进展[J]. 力学学报, 2022, 54(12):3239-3266.
	WANG G X, MA D L, LIU Y, et al, Research progress of contact force models in the collision mechanics of multibody system[J]. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(12):3239-3266. (in Chinese)
[25]	吴宝广. 星球着陆器钻采及着陆条件下高紧实度模拟星壤整备及其性能研究[D]. 长春: 吉林大学, 2017.
	WU B G. The preparation and performance analysis of high compactness simulated planet soil under the condition of planetary lander equipment's drilling samples and landing[D]. Changchun: Jilin University, 2017. (in Chinese)
[26]	ASH R L, EMERY J, CRANE B, et al. Mechanical properties of icy Mars regolith simulant:assessment of a potential ISRU feedstock[C]// Proceedings of the 8th Symposium on Space Resource Utilization. San Diego,CA,US: AIAA, 2016.
[27]	NASA Engineering Management Council. Structural design and test factors of safety for space-flight hardware:NASA-STD-5001[S]. Washington,D.C.,US: NASA, 2014.
[28]	张震东, 马大为, 仲健林, 等. 某型导弹冷发射装备场坪适应性研究[J]. 兵工学报, 2020, 41(2):280-290. doi: 10.3969/j.issn.1000-1093.2020.02.009
	ZHANG Z D, MA D W, ZHONG J L, et al. Research on adaptability of a cold launching system of missile to launching site[J]. Acta Armamentarii, 2020, 41(2):280-290. (in Chinese) doi: 10.3969/j.issn.1000-1093.2020.02.009
[29]	付国华, 张礼学, 翟杰勇, 等. 一种基于多元感知的电动调平装置“虚腿”判定方法[J]. 桂林电子科技大学学报, 2022, 42(3):181-186.
	FU G H, ZHANG L X, ZHAI J Y, et al. A judgment method of “Virtual leg” of electric leveling device based on multiple perception[J]. Journal of Guilin University of Electronic Technology, 2022, 42(3):181-186. (in Chinese)
[30]	王武, 付小强, 卢青山, 等. 某型火箭炮运弹车自动调平控制系统的设计与实现[J]. 兵工学报, 2022, 43(增刊1):82-87.
	WANG W, FU X Q, LU Q S, et al. Design and implementation of automatic leveling control system for a rocket launcher ammunition supply vehicle[J]. Acta Armamentarii, 2022, 43(S1):82-87. (in Chinese) doi: 10.12382/bgxb.2022.A022

气体名称	质量分数/%
二氧化碳	95.10
氮气	2.59
氩气	1.94
氧气	0.16
一氧化碳	0.06
其他气体	0.15

气体名称	质量分数/%
二氧化碳	95.10
氮气	2.59
氩气	1.94
氧气	0.16
一氧化碳	0.06
其他气体	0.15

参数	数值
重力加速度/(m·s^-2)	3.72
大气压强/Pa	6.36×10²
平均分子量	43.34
大气密度/(kg·m^-3)	0.02
大气比热比	1.3364
平均温度/K	210

参数	数值
重力加速度/(m·s^-2)	3.72
大气压强/Pa	6.36×10²
平均分子量	43.34
大气密度/(kg·m^-3)	0.02
大气比热比	1.3364
平均温度/K	210

参数	数值
弹射质量/kg	300
离筒速度/(m·s^-1)	8
最大发射加速度/(m·s^-2)	25
发射装置质量/kg	800
导轨摩擦系数	0.1
上升器直径/m	0.248
上升器长度/m	1.974
弹射行程/m	2.000
发射倾角/(°)	50