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Lakshmi Narayana Phaneendra Peri, Antonella Ingenito and Paolo Teofilatto
The goal of this paper is to investigate the aerodynamic and aerothermodynamic behavior of the Schiaparelli capsule after the deployment of a supersonic disk-gap-band (DGB) parachute during its re-entry phase into the Martian atmosphere. The novelty of t...
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Jacopo Guadagnini, Gabriele De Zaiacomo and Michèle Lavagna
This paper focuses on the mission analysis of the return trajectory of a Vertical Landing Reusable Launch Vehicle, both for Return-to-Launch-Site (RTLS) and DownRange Landing (DRL) recovery strategies. The main objective is to assess the mission performa...
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Kun Zhang, Jianyao Yao, Wenxiang Zhu, Zhifu Cao, Teng Li and Jianqiang Xin
The thermal protection system (TPS) represents one of the most critical subsystems for vehicle re-entry. However, due to uncertainties in thermal loads, material properties, and manufacturing deviations, the thermal response of the TPS exhibits significa...
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Francesco Salmaso, Mirko Trisolini and Camilla Colombo
The continuously growing number of objects orbiting around the Earth is expected to be accompanied by an increasing frequency of objects re-entering the Earth?s atmosphere. Many of these re-entries will be uncontrolled, making their prediction challengin...
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Alice De Oliveira and Michèle Lavagna
This paper introduces a Reusable Launch Vehicle (RLV) descent dynamics simulator coupled with closed-loop guidance and control (G&C) integration. The studied vehicle?s first-stage booster, evolving in the terrestrial atmosphere, is steered by a Thrus...
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Mingjie Li, Chijun Zhou, Lei Shao, Humin Lei and Changxin Luo
The method proposed can be used for accurate trajectory generation of a re-entry glide vehicle in the flight range domain with distributed grid points. It also provides ideas for trajectory generation based on the guidance mechanism.
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Stefano Piacquadio, Dominik Pridöhl, Nils Henkel, Rasmus Bergström, Alessandro Zamprotta, Athanasios Dafnis and Kai-Uwe Schröder
Economic viability of small launch vehicles, i.e., microlaunchers, is impaired by several factors, one of which is a higher dry to wet mass ratio as compared to conventional size launchers. Although reusability may reduce launch cost, it can drive dry an...
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Panneerselvam Balaraman, Vijayaraj Stephen Joseph Raj and Veloorillom Madhavan Sreehari
High-speed aerospace applications, such as re-entry vehicles, mostly involve thin-walled structural components with a high strength-to-weight ratio and high-temperature resistant. The present novel work comprises the structural and thermal analysis of re...
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Egidio D?Amato, Immacolata Notaro, Giulia Panico, Luciano Blasi, Massimiliano Mattei and Alessia Nocerino
In the last decade, the increasing use of NanoSats and CubeSats has made the re-entry capsule an emerging research field needing updates in configuration and technology. In particular, the door to advancements in terms of efficiency and re-usability has ...
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Xiaobin Wang, Peng Jiang, Yujian Tang, Pengfei Cheng and Weixu Zhang
Predicting the surface morphology of materials during steady-state ablation is important in rocket motor nozzles and the heat shields of vehicles performing atmospheric re-entry. When designing ablative materials, a high number of calculations is require...
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