Recent Progress in Aerospace Mechanisms for Reusable Launch Vehicles: A Review

Baolin Tian; Jiaxing Liu; Xuecong Yang; Jia Guo; Haitao Yu; Hongjian Zhang; Fan Yang; Chunhui Gu; Yuhong Shi; Haibo Gao; Dong Li; Zongquan Deng

doi:10.1016/j.eng.2026.02.030

Engineering ›› :202602030 DOI: 10.1016/j.eng.2026.02.030

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Recent Progress in Aerospace Mechanisms for Reusable Launch Vehicles: A Review

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Abstract

Reusable launch vehicles (RLVs) are essential for achieving low-cost, frequent, and sustainable space access, making space travel more affordable and providing new opportunities for large-scale commercial space exploration. Aerospace mechanisms, which are regarded as fundamental technology for multifunctional launch vehicles, can provide structural support, facilitate power distributions, enable propulsion and maneuvering, and guarantee the proper deployment and operation of launch vehicle components. In this paper, the current state-of-the-art developments of key aerospace mechanisms for RLVs are reviewed, including connection-separation mechanisms, controllable recovery mechanisms, and attitude control mechanisms, along with the corresponding thermal protection techniques. Furthermore, considering the technological challenges associated with the aerospace mechanisms of RLVs, future potential trends and directions for multifunctional long-term on-orbit tasks, smart materials and actuation, extraterrestrial recovery for round-trip flights, software for aerospace mechanism design and virtual validation, and intelligent health monitoring and management are identified.

Keywords

Reusable launch vehicle / Aerospace mechanism / Recovery technique / Separation and thrust mechanisms / Landing gears

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Baolin Tian, Jiaxing Liu, Xuecong Yang, Jia Guo, Haitao Yu, Hongjian Zhang, Fan Yang, Chunhui Gu, Yuhong Shi, Haibo Gao, Dong Li, Zongquan Deng. Recent Progress in Aerospace Mechanisms for Reusable Launch Vehicles: A Review. Engineering 202602030 DOI:10.1016/j.eng.2026.02.030

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References

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[1]	Wang C, Wang X, Zhang H, Zhang X, Wang J, Ji B. Development and research of reusable launch vehicles. Aerospace Techno 2018;(9):18-26. Chinese.

[2]	Yang K, Qu J. 2023 review of foreign reusable launch vehicle development. Space International. 2024;(4):34-9. Chinese.

[3]	Cui N, Wu R, Wei C, Xu D, Zhang L. Development and key technologies of vertical takeoff vertical landing reusable launch vehicle. Astronaut Syst Eng Technol 2018; 2(2):27-42. Chinese.

[4]	Schneider A, Desmariaux J, Klevanski J, Schröder S, Witte L. Deployment dynamics analysis of CALLISTO’s approach and landing system. CEAS Space J 2023; 15(2):343-56.

[5]	Tang H, Zhang D, Gan Z. Control system for vertical take-off and landing vehicle’s adaptive landing based on multi-sensor data fusion. Sensors 2020; 20(16):4411.

[6]	Seriani S. A new mechanism for soft landing in robotic space exploration. Robotics 2019; 8(4):103.

[7]	Maeda T, Ozaki T, Hara S, Matsui S. Touchdown dynamics of planetary lander with translation-rotation motion conversion mechanism. J Spacecr Rockets 2017; 54(4):973-80.

[8]	Xu D, Zhang Z, Wu K, Li HB, Lin JF, Zhang XD, et al. Recent progress on development trend and key technologies of vertical take-off vertical landing reusable launch vehicle. Chin Sci Bull 2016; 61(32):3453-63. Chinese.

[9]	Zhong Z, Zhang H, Zhou J, Huang Y. Review of non-pyrotechnic connection and separation technology of spacecraft. Manned spacefl 2019; 25(1):128-42. Chinese.

[10]	Zhang H, Yu B, Wu H, Zhang Z, Wang C. Research on technology development of launch vehicle mechanism. Missiles Space Veh 2023; 398(6):1-9. Chinese.

[11]	Feng S, Ma Z, Wu Y, Luan Y, Wang Y. Survey and review on key technologies of reusable launch vehicle abroad. Missiles Space Veh 2014; 335(5):84-8. Chinese.

[12]	Yue H, Yang Y, Lu Y, Yang F, Wu J, Ruan Q, et al. Research progress of space non-pyrotechnic low-shock connection and separation technology (SNLT): a review. Chin J Aeronauti 2022; 35(11):113-54.

[13]	Cebrian AS, Halter B, Gerngross T.RUAG's approach to develop a modular low shock separation and jettison system. In:Proceedings of the 8th European Conference for Aeronautics and Space Sciences (EUCASS); 2019 Jun 1-4; Madrid, Spain. Brussels: European Research Council; 2019. p. 1-12.

[14]	Kim D, Jeong D, Lee Y, Lee Y. Study on the performance evaluation of the explosive bolt that has been natural aging. J Korean Soc Propulsion Eng 2017; 3(21):84-90.

[15]	Wang G, Zhang H, Wu H. Development and outlook of non-pyrotechnic separation mechanism for launch vehicle. J Astronaut 2023; 44(3):334-47. Chinese.

[16]	Lee J, Hwang DH, Jang JK, Kim DJ, Lee YJ, Lee JR, et al. Pyroshock prediction of ridge-cut explosive bolts using hydrocodes. Shock Vib 2016; 2016(1):1218767.

[17]	Li X, Man J, Wu Q, Luo Y, Yang J. A validation test method for release reliability of pyrotechnic separation nut. Spacecr Eng 2014; 23(4):120-4. Chinese.

[18]	Lee J, Han J. Separation and release devices for aeronautical and astronautical systems: a review. Int J Aeronaut Space Sci 2025; 26(1):131-61.

[19]	Bi X, Chen B, Wu H, Wang L, Jiang L, Wang B, et al. Design, analysis and optimization of linear bundled separation device for launch vehicle. J Mech Eng 2019; 55(14):60-8. Chinese.

[20]	Apollo11Space. How did the saturn v stages separate? [Internet]. Washington, DC: NASA; 2022 [cited 2025 May 17]. Available from: https://apollo11space.com/how-did-the-saturn-v-stages-separate/.

[21]	Yasunaga Y, Fukushima Y, Nakamura T, Fujita T.Separation jettison test of Japanese H-II rocket satellite fairing. In: Proceedings of the 28th Aerospace Sciences Meeting; 1990 Jan 8-11; Reno, NV, USA. Reston: AIAA; 1990. p. 720.

[22]	Zhang Y, Wu H, Zhang H, Yu B, Wang C, Yue C. Analysis of the technological development path of SpaceX’s launch vehicle mechanisms and its implications. J Astronaut 2025; 46(3):631-40. Chinese.

[23]	Rocket Lab. Advanced lightband user's manual [Internet]. Los Angeles: Rocket Lab; 2024 [cited 2025 May 18]. Available from: www.rocketlabusa.com/space-systems/separation-systems/.

[24]	Yang B, Xiao L, Gai Y. Research progress on non-pyrotechnic unlocking device of clamp-band separation for satellite and rocket. Mach Des Manuf 2018;(9 Suppl):178-80,184. Chinese.

[25]

Gall KR, Lake MS, Harvey J, Ricca E.Development of a shockless thermally actuated release nut using elastic memory composite material. In: Proceedings of the 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; 2003 Apr 7-10; Norfolk, Virginia. Reston: AIAA; 2003. p. 1582.

[26]	Peffer A, Denoyer K, Fosness E, Sciulli D. Development and transition of low-shock spacecraft release devices. In: Proceedings of the 2000 IEEE Aerospace Conference. Proceedings (Cat. No.00TH8484); 2000 Mar 25; Big Sky, MT, USA. Piscataway: IEEE; 2000 p. 277-84.

[27]	Yang F, Yue H, Zhang Y, Peng J, Deng Z. Research on a low-impact unlocking trigger device of heavy load based on shape memory alloy fiber. Adv Mech Eng 2017; 9(10):1-14.

[28]	Varghese PL. Investigation of energy transfer in the ignition mechanism of a nasa standard initiator. Report. Washington, DC: NASA; 1988.

[29]	Hwang D, Han J, Lee J, Lee Y, Kim D. A mathematical model for the separation behavior of a split type low-shock separation bolt. Acta Astronaut 2019; 164:393-406.

[30]	Elchert K.Space shuttle solid rocket booster separation system. In: Proceedings of the Guidance and Control Conference; 1982 Aug 9-11; San Diego, CA, USA. Reston: AIAA; 1982. p. 1556.

[31]	Bos M, Nienkemper R, Meiboom F. Development of the nosecone separation system for the Ariane-5 booster recovery system. In: Proceedings of the 13th Aerodynamic Decelerator Systems Technology Conference; 1995 May 15-18; Clearwater Beach, FL, USA. Reston: AIAA; 1995. p. 1592.

[32]	Ming A, Yang Y, Zhang Y, Lu C. Launch vehicle non-pyrotechnic cold gas thrust separation system. Aerosp Chin 2022;(11):20-4. Chinese.

[33]	Gai Y, Liang X, Yang S, Wang R. Research progress of non-pyrotechnic clamp-band separation technology. Mach Des Manuf 2018;(5 Suppl):136-9. Chinese.

[34]	Sauder J, Gebara C, Reddy NH, García-Mora CJ. A framework for small satellite deployable structures and how to deploy them reliably. Commun Eng 2024; 3:72.

[35]	Hwang H, Kim B, Choi J. A compact non-explosive separation device for high preload and low shock. Int J Precis Eng Manuf 2014; 15(1):83-8.

[36]	Cai F, Meng X. Non-pyrotechnic device for joining and separating. Spacecr Recovery Remote Sens 2005; 26(4):50-5. Chinese.

[37]	Pan X, Zhang Y, Lu Y, Yang F, Yue H. A reusable SMA actuated non-explosive lock-release mechanism for space application. Int J Smart Nano Mater 2020; 11(1):65-77.

[38]	Yoo YI, Jeong JW, Lim JH, Kim KW, Hwang DS, Lee JJ. Development of a non-explosive release actuator using shape memory alloy wire. Rev Sci Instrum 2013; 84(1):015005.

[39]	Buckley S, Fosness E, Gammill W. Deployment and release devices efforts at the air force research laboratory space vehicles directorate. In: Proceedings of the AIAA Space 2001 Conference and Exposition; 2001 Aug 28-30; Albuquerque, NM, USA. Reston: AIAA; 2001. p. 4601.

[40]	Zhao X, Zhao C, Li J, Guan Y, Chen S, Zhang L. Research on design, simulation, and experiment of separation mechanism for micro-nano satellites. Appl Sci 2022; 12(12):5997.

[41]	Hwang D, Han J, Lee J, Lee Y, Kim D. Performance optimization of a split-type low-shock separation bolt. J Spacecr Rockets 2021; 58(1):232-9.

[42]	Yu B, Xiang S, Yan L, Yang Y, Liang Y. Study on separation characteristics of pyrotechnic separation pushing rod. J Ordnance Equip Eng 2020; 41(12):57-62. Chinese.

[43]	Xing X, Zhang P, Zhao Z. Simulation and experimental study on pyrotechnic separator. J Ordnance Equip Eng 2022; 43(4):19-24. Chinese.

[44]	Konno KE, Catalano DA, Krivanek TM. Evaluation of separation mechanism design for the Orion/Ares launch vehicle. In: Proceedings of the 35th Aerospace Mechanisms Symposium; 2008 May 7-9; Huntsville, AL, USA. Washington, DC: NASA; 2008. p. 20080023306.

[45]	Shang L, Wang A, Wang K, He Z. Application of locking/unlocking device based on liquid metal in space deployable mechanism. Manned spacefl 2017; 23(4):572-6. Chinese.

[46]	Exolaunch. Carbonix user manual [Internet]. Berlin: Exolaunch; 2024 [cited 2025 May 18]. Available from: https://exolaunch.com/carbonix.html#2.

[47]	Chen Z, Ning L, Wang P. The development of launch vehicle booster recovery technology. Astronaut Syst Eng Technol 2021; 5(5):66-74. Chinese.

[48]	Astorg J, Barreau F, de Kluiver C. The Ariane 5 solid rocket booster recovery-a technical and managerial challenge. In: Proceedings of the 13th Aerodynamic Decelerator Systems Technology Conference; 1995 May 15-18; Clearwater Beach, FL, USA. Reston: AIAA; 1995. p. 1532.

[49]

Zhang M, Yonemoto K, Fujikawa T.Detailed design and system components of the helicopter recovery system for winged rocket WIRES#015. In:Proceedings of the 15th Asia-Pacific International Symposium on Aerospace Technology, APISAT 2024; 2024 Oct 28-30; Adelaide, Australia. Canberra: Engineers Australia; 2024. p. 1843-51.

[50]	Song Z, Huang B, Wang X, Zhang H. Status and challenges of reusable launch vehicle recovery technology. J Deep Space Explor 2022; 9(5):457-69.

[51]	Zhang X, Yan N, Hao Y, Zhang Z, Liu B. Design of measurement and control scheme for aerial recovery of launch vehicle sub-stage. In: Proceedings of the Ninth Symposium on Novel Photoelectronic Detection Technology and Applications; 2022 Nov 2-4; Hefei, China. Bellingham: SPIE; 2023. p. 126173P.

[52]	Filatyev AS, Buzuluk V, Yanova O, Ryabukha N, Petrov A. Advanced aviation technology for reusable launch vehicle improvement. Acta Astronaut 2014; 100:11-21.

[53]	Zimpfer D, Hattis P, Ruppert J, Gavert D. Space shuttle GN&C development history and evolution. In: Proceedings of the AIAA SPACE 2011 Conference & Exposition; 2011 Sep 27-29; Long Beach, CA, USA. Reston: AIAA; 2011. p. 7244.

[54]	Yang Q, Lin Q, Wu X. Latest developments in russian reusable rockets. Aerospace China 2022;(06):53-7. Chinese.

[55]	Xu K, Xu F, Wu D. A technical review of landing gear mechanisms for space launch vehicles. Aerosp China. 2023;(10):18-24. Chinese.

[56]	Blue Origin. New shepard [Internet]. City of Kent: Blue Origin; 2025 [cited 2025 May 18]. Available from: https://www.blueorigin.com/new-shepard.

[57]	Thies C. Investigation of the landing dynamics of a reusable launch vehicle and derivation of dimension loading for the landing leg. CEAS Space J 2022; 14(3):565-76.

[58]	Wu H, Song B, Su H, Zhang Q. Analysis and research on the design characteristics of the Falcon 9 launch vehicle structural subsystem. Aerospace Technology. 2017;(9):1-4,59. Chinese.

[59]	Song Z, Huang B, Wang X, Zhang H, Wang C, Zhuang F. Development of reusable space launch vehicles and their key technologies. Sci Technol Foresight 2022; 1(1):62-74.

[60]	Li Y, Zhang H, Song Z, Zhang L, Wang C, Ma H. Configuration optimization and design of vertical landing mechanisms of reusable launch vehicles. J Deep Space Explor 2022; 9(5):470-6.

[61]	Zhang H, Zhang L, Wang C, Yu B, Zhang D, Xiao Y, et al. inventors; Beijing Aerospace Systems Engineering Research Institute, assignee. A highly lightweight landing buffer mechanism for reusable launch vehicles. Chinese patent CN114111462A. 2023 July 14.

[62]	Krziwanie F, Rotärmel W, Vicenzino SG, Schneider A. Development of the landing leg structure for CALLISTO. J Evol Sp Activities 2024; 2:168.

[63]	Rickmers P, Dumont E, Kottmeier S, Redondo Gutierrez JL, Bussler L, Kottmeier S, et al. The CALLISTO and ReFEx flight experiments at DLR-challenges and opportunities of a wholistic approach. Acta Astronaut 2024; 225:417-33.

[64]	Peng X, Zheng L, Wang Y. inventors; Starry Sky Aerospace Technology Group Co., Ltd., Beijing Starry Sky Technology Co., Ltd, assignees. A launch vehicle stage recovery and landing mechanism. Chinese patent. CN111361766A. 2020 Jul 3.

[65]	cnBeta.China's reusable rocket first: private Hyperbola-2 landing mechanism completes ground deployment test [Internet]. Redmond: MSN; 2021 [cited 2025 May 18]. Available from: https://www.cnbeta.com.tw/articles/tech/1174743.htm.

[66]	Zhang M, Xu D, Yue S, Tao H. Design and dynamic analysis of landing gear system in vertical takeoff and vertical landing reusable launch vehicle. Proc Inst Mech Eng Part G J Aerosp Eng 2019; 233(10):3700-13.

[67]	Xu D, Sun X, Ou Y, Sheng Y, Wu J, Lin J. inventors; Shanghai Institute of Aerospace System Engineering, assignee. An externally mounted electric retractable landing gear mechanism. Chinese patent CN105438502B. 2017 May 31.

[68]	Krammer A, Blecha L, Lichtenberger M. Fin actuation, thrust vector control and landing leg mechanisms design for the retalt vtvl launcher. CEAS Space J 2022; 14(3):577-91.

[69]	Marwege A, Gülhan A, Klevanski J, Hantz C, Karl S, Laureti M, et al. RETALT: review of technologies and overview of design changes. CEAS Space J 2022; 14(3):433-45.

[70]	Blue Origin. New glenn [Internet]. City of Kent: Blue Origin; 2025 [cited 2025 Mar 11]. Available from: https://www.blueorigin.com/new-glenn.

[71]	Yu H, Tian B, Yan Z, Gao H, Zhang H, Wu H, et al. Watt linkage-based legged deployable landing mechanism for reusable launch vehicle: principle, prototype design, and experimental validation. Engineering 2023; 20:120-33.

[72]	Yu H, Gao H, Tian B, Liu Z, Li N, Ding L, et al. inventors; Harbin Institute of Technology, assignee. A pneumatic-driven reusable rocket landing support mechanism. Chinese patent CN109178351A. 2019 Jan 11.

[73]	Gao H, Yu H, Tian B, Ding L, Li N, Liu Z, et al. inventors; Harbin Institute of Technology, assignee. An electrically retractable and deployable support mechanism for a reusable rocket prototype. Chinese patent CN109455320A. 2019 Mar 12.

[74]	Giagkozoglou Vincenzino S, Rotärmel W, Petkov I, Elsäßer H, Dumont E, Witte L, et al.Reusable structures for CALLISTO. In: Proceedings of the 8th European Conference for Aeronautics and Space Sciences (EUCASS); 2019 Jul 1-4; Madrid, Spain. Brussels: European Research Council; 2019. p. 1-12.

[75]	Tian B, Yu H, Yan Z, Zhang H. Design and simulation of a locking mechanism applied to landing support system. Astronaut Syst Eng Technol 2019; 3(6):46-51. Chinese.

[76]	Nie X, Yang N, Nie H, Zhang M. Design and simulation analysis of the development locking mechanism of vertical take-off and landing vehicle. Mach Des Manuf Eng 2020; 19(8):61-6. Chinese.

[77]	Wang C, Zhang H, Zhang L, Wang J, Zhang X, Yu B, et al. inventors; Beijing Institute of Aerospace System Engineering, assignee. A reusable rocket landing leg collapsible energy-absorbing bidirectional buffer. Chinese patent CN112027119A. 2020 Dec 4.

[78]	Ma H, Zhao S, Jiao Z.Study of a hydro-pneumatic buffer with a variable damper for launch vehicle landing legs. In: Proceedings of the 8th European Conference for Aeronautics and Space Sciences (EUCASS); 2019 Jun 1-4; Madrid, Spain. Brussels: European Research Council; 2019. p. 1-11.

[79]	Yue S, Nie H, Zhang M, Huang M, Xu D. Optimization and performance analysis of oleo-honeycomb damper used in vertical landing reusable launch vehicle. J Aerosp Eng 2018; 31(2):04018002.

[80]	Nie H, Yue S, Zhang M, Jiang R, Wu X, Zhang Q. inventors; Nanjing University of Aeronautics and Astronautics, assignee. Reusable launch vehicle buffer landing leg and its buffering method. Chinese patent CN103935525A. 2014 Jul 23.

[81]	Wang C, Chen J, Li X, Chen H, Nie H, Lin F. Design, dynamic analysis, and experiments of MRF dampers for lunar landers. Adv Space Res 2021; 68(7):3012-25.

[82]	Wang A, Nie H, Liu G. Semi-active control of lunar lander soft landing based on magnetorheological shock strut. Chin Mech Eng 2009; 20(22):2659-62, 2693. Chinese.

[83]	Hu Z, Zhang X, Song Z, Tian J, Zhang L, Chen X, et al. A rocket vertical landing recovery mechanism based on a ground arresting scheme. J Deep Space Explor 2022; 9(5):477-82. Chinese.

[84]	Huang H inventor; Huang H assignee. Reusable ground capture and recovery device and rocket-to-ground controllable recovery method. Chinese patent CN109911253A. 2019 June 21.

[85]	Ma H, Zhang H, Wang C, Zhu Z, Yu B, Xie Y, et al. inventors; Beijing Institute of Aerospace System Engineering, assignee. A hanging rope mechanism for vertical recovery launch vehicles. Chinese patent CN117128817A. 2023 Nov 28.

[86]	Song X, Zhang H, Sun Z. inventors; Beijing Institute of Technology, assignee. A rocket recovery cable system. Chinese patent CN114655474A. 2022 June 24.

[87]	Wang C, Zhang X, Tian J, Xiao Y, Song Z, Yang F, et al. inventors; Beijing Institute of Aerospace System Engineering, assignee. A drag rudder and tether recovery integrated mechanism, and recovery method. Chinese patent CN115523806A. 2022 Dec 27.

[88]	Wang H, Xiang D, Zhang H, Cui S, Li J, Wu H. A novel cable-net buffer device for recovering reusable launch vehicle: design, dynamic modeling, and performance analysis. Proc Inst Mech Eng C 2024; 238(13):6391-404.

[89]	Zhang H, Zhao Z, Ren G, Hu P, Yang Y, Pan Z, et al. Arresting-cable system for robust terminal landing of reusable rockets. J Spacecr Rockets 2021; 58(2):425-43.

[90]	Zhang H, Zhang C, Song X. Design and analysis of buffer device of cable system for reusable rocket recovery and landing. J Astronaut 2022; 43(9):1152-62. Chinese.

[91]	Zhang H, Song X, Sun Z. inventors; Beijing Institute of Technology, assignee. A universal rocket recovery cable system based on cam profile design. Chinese patent CN114572429A. 2022 Jun 3.

[92]

Space.com. SpaceX catches giant Starship booster with 'Chopsticks' on historic flight 5 rocket launch and landing (video) [Internet]. New York City: Space.com; 2024 Oct 13 [cited 2025 May 22]. Available from: https://www.space.com/spacex-starship-flight-5-launch-super-heavy-booster-catch-success-video.

[93]	COSMOLEAP. The general consumption guide for Mechagodzilla-an analysis of the starship recovery system [Internet]. BeiJing: COSMOLEAP; 2024 Oct 17 [cited 2025 May 22]. Available from: https://www.cosmoleap.cn/news_detail/c-_detailId%3D1856247362848673792.html.

[94]

Born To Engineer.SpaceX Starship Flight 5: revolutionary “Chopsticks” booster catch marks new era in spaceflight [Internet].London: Born To Engineer; 2024 [cited 2025 May 22]. Available from: https://www.borntoengineer.com/spacex-starship-flight-5-revolutionary-chopsticks-booster-catch-marks-new-era-in-spaceflight.

[95]	Shi Y, Xiao Y, Xu W. The technology of CZ-2F escape vehicle’s maximum velocity head simulated flight test. J Astronaut 2004; 25(5):484-7. Chinese.

[96]	Pruzan D, Mendenhall M, Rose W, Schuster D. Grid fin stabilization of the orion launch abort vehicle. In: Proceedings of the 29th AIAA Applied Aerodynamics Conference; 2011 Jun 27-30; Honolulu, HI, USA. Reston: AIAA; 2011. p. 3018.

[97]	Wang C, Yuan W, Guo Y, Zhang H, Wang X, Shi Y. Experimental study of kinetic characteristics for gid fin transmission mechanism of reusable launch vehicle. Acta Scientiarum Naturalium Universitatis 2018; 54(6):1137-46. Chinese.

[98]	Guo J, Yu B, Ma H, Wang C, Xie J. Analysis of super heavy-starship transport system mechanism. Missiles Space Veh 2024; 402(3):29-37. Chinese.

[99]	Wang C, Yang J, Cui Z, Wu H. Research on application of grid fin mechanism on launch vehicle falling area control. Missiles Space Veh 2023; 394(3):12-9. Chinese.

[100]

A major improvement: what changed on Starship 25 & booster 9? [Internet]. Online: Ringwatchers; 2023 Nov 25 [cited 2025 May 20]. Available from: https://ringwatchers.com/article/s25-b9-updates.

[101]

Zhang Y, Zuo G, Xu Y, Du R, Zhao F, Qu F. Numerical simulation on aerodynamic characteristics of new type control surface of starship. Acta Aeronaut Astronaut Sinica 2021; 42(2):624058-624058. Chinese.

[102]

Sagliano M, Heidecker A, Hern á ndez JM, Schlotterer M, Woicke S, et al. Onboard guidance for reusable rockets:aerodynamic descent and powered landing. In: Proceedings of the AIAA Scitech 2021 Forum; 2021 Jan 11-15, 19-21; VIRTUAL EVENT. Reston: AIAA; 2021. p. 862.

[103]

Charbonnier D, Vos J, Marwege A, Hantz C. Computational fluid dynamics investigations of aerodynamic control surfaces of a vertical landing configuration. CEAS Space J 2022; 14(3):517-32.

[104]

Herberhold M, Bussler L, Sippel M, Wilken J. Comparison of SpaceX’s Starship with winged heavy-lift launcher options for europe. CEAS Space J 2025; 18:121-44.

[105]

Dresia K, Jentzsch S, Waxenegger-Wilfing G, Dos Santos Hahn R, Deeken J, Oschwald M, et al. Multidisciplinary design optimization of reusable launch vehicles for different propellants and objectives. J Spacecr Rockets 2021; 58(4):1017-29.

[106]

Ma H, Wu H, Zhang H, Cao X, Jiang L, Le C. Research on type synthesis of the launch vehicle engine nozzle morphing mechanism. Astronaut Syst Eng Technol 2023; 7(4):41-50. Chinese.

[107]

Kim H, Yang S, Choi J. Analysis of orbit injection performance of KSLV-II by weight reduction. J Korean Soc Propulsion Eng 2018; 22(5):141-51.

[108]

Farì S, Seelbinder D, Theil S, Simplicio P, Bennani S. Physical modeling and simulation of electro-mechanical actuator-based TVC systems for reusable launch vehicles. Acta Astronaut 2024; 214:790-808.

[109]

Yang S, Gan L, Wang T, Zhu E, Yang L, Chen H. Compound attitude control strategy for reusable launch vehicle based on improved particle swarm optimization algorithm. Aerospace 2024; 11(7):555.

[110]

Bykerk T, Karl S, Laureti M, Ertl M, Ecker T. Retro-propulsion in rocket systems: recent advancements and challenges for the prediction of aerodynamic characteristics and thermal loads. Prog Aerosp Sci 2024; 151:101044.

[111]

Uyanna O, Najafi H. Thermal protection systems for space vehicles: a review on technology development, current challenges and future prospects. Acta Astronaut 2020; 176:341-56.

[112]

Fang G, Wang Z, Li S, Wang B, Meng S. Review of high-temperature oxidation properties for carbon fiber toughened ceramic matrix composites: oxidation mechanisms, oxidation damage experiments and model. Acta Mater Compositae Sinica 2024; 41(9):4518-34. Chinese.

[113]

Mazzaracchio A. Thermal protection system and trajectory optimization for orbital plane change aeroassisted maneuver. J Aerosp Technol Manag 2013; 5(1):49-64.

[114]

Piacquadio S, Pridöhl D, Henkel N, Bergström R, Zamprotta A, Dafnis A, et al. Comprehensive comparison of different integrated thermal protection systems with ablative materials for load-bearing components of reusable launch vehicles. Aerospace 2023; 10(3):319.

[115]

Zhao S, Li J, Zhang C, Zhang W, Lin X, He X, et al. Thermo-structural optimization of integrated thermal protection panels with one-layer and two-layer corrugated cores based on simulated annealing algorithm. Struct Multidiscipl Optim 2015; 51(2):479-94.

[116]

Gogu C, Bapanapalli SK, Haftka RT, Sankar BV. Comparison of materials for an integrated thermal protection system for spacecraft reentry. J Spacecr Rockets 2009; 46(3):501-13.

[117]

Sun X, Huang W, Ou M, Zhang R, Li S. A survey on numerical simulations of drag and heat reduction mechanism in supersonic/hypersonic flows. Chin J Aeronauti 2019; 32(4):771-84.

[118]

Kharati-Koopaee M, Gazor H. Assessment of the aerodisk size on drag reduction and thermal protection of high-Bluntness vehicles at hypersonic speeds. J Aerosp Eng 2017; 30(4):04017008.

[119]

Guo S, Xu J, Qin J, Gu R. Fluid-thermal interaction investigation of spiked blunt bodies at hypersonic flight condition. J Spacecr Rockets 2016; 53(4):629-43.

[120]

Ou M, Yan L, Huang W, Li S, Li L. Detailed parametric investigations on drag and heat flux reduction induced by a combinational spike and opposing jet concept in hypersonic flows. Int J Heat Mass Transf 2018;126(Part A):10-31.

[121]

Wang Z, Sun X, Huang W, Li S, Yan L. Experimental investigation on drag and heat flux reduction in supersonic/hypersonic flows: A survey. Acta Astronaut 2016; 129:95-110.

[122]

NASA.First 3D woven composite for NASA thermal protection systems [Internet]. Washington, DC: NASA; 2016 [cited 2026 Jan 10]. Available from: https://www.nasa.gov/technology/manufacturing-materials-3-d-printing/first-3d-woven-composite-for-nasa-thermal-protection-systems.

[123]

Pichon T, Lacoste M. Barreteau, Glass DE. Integrated thermal protection systems and heat resistant structures. In: Proceedings of the 57th International Astronautical Congress; 2006 Oct 2-6; Valencia, Spain. Reston: AIAA; 2006. p. 1-11.

[124]

Bao W. A review of reusable launch vehicle technology development. Hangkong Xuebao 2023; 44(23):1-26.

[125]

Parsa R. Revolutionizing space travel: inside SpaceX's game-changing Starship heat shield technology [Internet]. Space Time 24; 2026 [12 Jan 2026]. Available from: https://spacetime24.com/game-changing-starship-heat-shield-technology/.

[126]

Milos FS, Gasch M, Prabhu DK. Conformal phenolic impregnated carbon ablator arcjet testing, ablation, and thermal response. J Spacecr Rockets 2015; 52(3):804-12.

[127]

Stewart DA, Leiser DB, Gökçen T, Switzer MR, Skokova KA, Feldman JD. Advanced lighweight TUFROC thermal protection system for space plane applications. Report. Washington, DC: NASA; 2024 Feb. Report No.: NASA/TM-20240002574.