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• W2313877091 abstract "New missions have been presented recently, showing a renewed interest in atmospheric reentry. Demonstrators are proposed in the frame of the European framework for a manned exploration of Mars, the so-called Aurora program, aiming at performing scientific and technology measurements in hypervelocity configurations (Earth entry vehicles). Sample return calls for demonstration of feasibility of a direct capture in a planetary atmosphere (MSR, Aurora). Alternatively, reentry remains one critical phase for the mastering of reusable launchers; demonstrators are proposed to address the technology acquisition and validation for that purpose, such as the French Pre-X initiative. All these missions are faced with the technological challenge of high accuracy navigation. These missions show a wide diversity in the conditions navigation will be operated, and confirm the interest of versatile, well-mastered navigation solutions with guaranteed performances. Past studies have permitted to identify satellite-based radio-navigation as a key enabling technology for Earth reentry. Satellite based navigation offers constant and reliable performance to support vehicle system design. The present paper addresses specifically the applicability of INS-GPS based navigation solution to these types of reentry missions. A key aspect of all reentry vehicles is the presence of a black-out phase, implying the need for an inertial navigation system (INS) as the core of the navigation function. With respect to this inertial pure navigation, the interest of satellite-based navigation is examined. Compared performance is presented that illustrate the prominent role of GPS to eliminate divergence and maintain entry conditions. Pure INS navigation appears highly dependant on mission definition and future RLV missions, demonstrators, or mission for exploration and sample return may feature very long stay in 0-g conditions with no possibility for accurate alignment of the INS system. The critical technologies and feasibility issues are reviewed in a second part of the paper, and key design features proposed to solve for them. A new line of product is emerging from past and on-going studies for GPS navigation of launchers, orbiters and reentry vehicles, combining compacity with high performance in a fully integrated configuration. This evolution of navigation products from single technology to diversified functional chains with decentralized intelligence is a true opportunity for making affordable reentry demonstrators in the short term. Paper concludes on maturity and short term availability in support to mission planning needs. Acronyms ARD Atmospheric Reentry Demonstrator C/No Signal to Noise Ratio DOF Degrees Of Freedom GNC Guidance, Navigation and Control IMU Inertial Measurement Unit INS Inertial Navigation System ISS International Space Station LEO Low Earth Orbit MSR Mars Sample Return RF Radio Frequency SPARC Small Payload Return Capsule TRP Technological Research Program TTFF Time To First Fix 54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law 29 September 3 October 2003, Bremen, Germany IAC-03-V.3.07 Copyright © 2003 by the International Astronautical Federation. All rights reserved." @default.
• W2313877091 created "2016-06-24" @default.
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• W2313877091 date "2003-09-29" @default.
• W2313877091 modified "2023-09-25" @default.
• W2313877091 title "Inertial and Blended INS/GPS Navigation Solutions For Atmospheric Reentry" @default.
• W2313877091 doi "https://doi.org/10.2514/6.iac-03-v.3.07" @default.
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