Paolo Baiocco - Academia.edu (original) (raw)

Papers by Paolo Baiocco

Acta Astronautica, 2005

Numerous studies have already identified that Fully Reusable Launch Vehicle Two-Stage-To-Orbit co... more Numerous studies have already identified that Fully Reusable Launch Vehicle Two-Stage-To-Orbit concepts (FRLV TSTO) could be one of the best solutions for meeting economical and technical objectives of second-generation RLV. In 2001, CNES initiated and funded system studies aimed at defining the most promising FRLV TSTO configurations in terms of technical and technological challenges and economical effectiveness. EADS-LV leads for this purpose an industrial team composed of EADS-LV, SNECMA Moteurs, DASSAULT Aviation and ONERA. The presented programme is a two-phase study addressing three coupled issues: viable configuration definition, key issues analysis and vehicle architecture design. The first phase has been split into three periods: (1) establishing preliminary but consolidated assumptions and ground rules, (2) systematic computation of the two stages main features for a given payload mass into LEO orbit, (3) preliminary definition of remarkable configurations and associated propulsion systems. The second phase, under development, is mainly focused on the design of a study configuration by figuring out key issues and providing consolidated data (technical and economical performance). This paper intends to present the major investigations of the first phase: • a survey of the overall approach; • the main technical characteristics; • the major recommendations for further steps.

Atmospheric glided re-entry is one of the main key technologies for future space vehicle applicat... more Atmospheric glided re-entry is one of the main key technologies for future space vehicle applications. In this frame Pre-X is the CNES proposal to perform in-flight experimentation mainly on reusable thermal protections, aero-thermo-dynamics and guidance to secure the second generation of re-entry X vehicles. This paper describes the system principles and main aerothermodynamic experiences currently foreseen on board the vehicle. A preliminary in-flight experimentation and measurement plan has been assessed defining the main objectives in terms of reusable Thermal Protection System (TPS) and Aero Thermo Dynamics (ATD) data on the most critical phenomena. This flight aims also to take the opportunity to fly some innovative measurements. A complete system loop has been performed including the operations, ground system assessment, and visibility analysis. The vehicle re-entry point is at 120 km and the mission objectives are fulfilled between Mach 25 and 5. Then the vehicle has to pass...

Acta Astronautica, 2021

Rocket reusability dates as long as rockets. Since the beginning of space age, the possibility to... more Rocket reusability dates as long as rockets. Since the beginning of space age, the possibility to reuse the full vehicle or some stages has been a matter of engineering. But this was directly opposite to mass ratio efficiency, the key for a well-designed rocket. Since as soon as a stage has to be recovered, subsystems to provide this function and additional inert mass are needed. Even if reusable systems are only a small part of the worldwide rockets, they flew operationally since the space shuttle age. However, full reusable vehicles are not yet operational and only partially reusable launch vehicles have been flown until now. The preliminary space shuttle design consisted of two stages both liquid and reusable (booster and orbiter stages). The consolidated design retrieved the orbiter (upper stage, the cargo and propulsion bay) and the solid rocket boosters. On Russian side Energia-Buran only retrieved the upper stage with its cargo bay and the same approach was adapted for the or...

: Atmospheric glided re-entry is one of the main key technologies for future space vehicle applic... more : Atmospheric glided re-entry is one of the main key technologies for future space vehicle applications. In this frame Pre-X is the CNES proposal to perform in-flight experimentation mainly on reusable thermal protections, aero-thermo-dynamics and guidance to secure the second generation of re-entry X vehicles. This paper describes the system principles and main aerothermodynamic experiences currently foreseen on board the vehicle. A preliminary in-flight experimentation and measurement plan has been assessed defining the main objectives in terms of reusable Thermal Protection System (TPS) and Aero Thermo Dynamics (ATD) data on the most critical phenomena. This flight aims also to take the opportunity to fly some innovative measurements. A complete system loop has been performed including the operations, ground system assessment, and visibility analysis. The vehicle re-entry point is at 120 km and the mission objectives are fulfilled between Mach 25 and 5. Then the vehicle has to pa...

56th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law

57th International Astronautical Congress, 2006

Iaf Abstracts 34th Cospar Scientific Assembly, 2002

As it is well recognised, RLV are potentially the future solution for the next generation of spac... more As it is well recognised, RLV are potentially the future solution for the next generation of space transportation system. Since several years, activities are going on in CNES with the support of Industry. This paper is going to present the logic of the activities currently running in the field of ground demonstration, system studies and in-flight experimentation. It will present the overall logic and the link with the preparation of a European preparatory programme for RLV's. At the end it will focus on the in-flight experimentation status with the 1st generation of in- flight experimental vehicle necessary to be part of the European programme.

The number of micro satellites is today similar to that of the geostationary class and is foresee... more The number of micro satellites is today similar to that of the geostationary class and is foreseen to grow. The question is if a launch service dedicated to this class of satellites arises, being essentially a matter of launch cost and type of mission. Most of these satellites are for defence and scientific applications. The accessible part of the current market for Europe is foreseen to consist of about 4-6 satellites per year, but this number could arise if European defence needs increase. In this frame the French space agency (CNES) decided to investigate in deeper detail the interest and the feasibility of a micro launch vehicle with an ambitious cost launch target, of the class of the Ariane 5 microsat platform (ASAP 5). A feasibility study has been performed in order to assess the most interesting launch system which could be available by year 2010. The main system requirements have been settled and a brainstorming has been performed in order to lower subsystem costs and find original solutions. The constraints of the study are to have a launch vehicle mainly built in Europe, whose technological feasibility has already been demonstrated inside or outside Europe. The launch vehicle may integrate a limited number of innovative technologies, which may serve as demonstration for future launchers subsystems.

Space Guidance Control and Tracking, Sep 1, 1993

The following paper concerns the study of the Attitude Control System (ACS) of the Orbital Space ... more The following paper concerns the study of the Attitude Control System (ACS) of the Orbital Space Interferometer (OSI) proposed by Jet Propulsion Laboratory (JPL) of Pasadena, both for NASA's Astrometric Interferometry Mission (AIM) and for phase one of NASA's Towards Other Planetary Systems (TOPS) program.

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2006

Space Guidance, Control, and Tracking, 1993

31st Thermophysics Conference, 1996