Project Description PDF Stampa E-mail

asdThe preliminary study aims to investigate all aspects configured, building and operating the project IRENE before their actual design. The study serves to freeze the configuration, outline weight, size and performance of the capsule, to analyze key subsystems, to define a mission profile and to choose the launchers. The capsule should have the following features:Massa al lancio dell’ordine di 100 –120 kg.

• launch mass of about 120 kg.
• Structure made from composite materials.
• Thermal Protection System (TPS) which allows the reusability of the capsule.
• Operative life in LEO about 1 week
• Production time applicant not more than 12 months.
Launchers • Compatible Shtil-2, or other commercial launchers (e.g. VEGA)
• LEO orbits, all inclinations.
• Modular Design approach
• Propulsion system for attitude control and orbital.
• 3-axis stabilization.
• Aiming inertial, star or nadir pointing
• High autonomy board. 

 

Specifically, the study of system is aimed to develop the following topics:

1.Mission Analysis
2.Configuration
3.Aerodynamics and aero-thermodynamic
4.Structure and Attitude Control
5.TPS
6.Power, avionics and onboard electronics
7.Landing/Splashdown impact analysis

 In the design of space vehicles, the need for a thermal protection system was established in all applications where a spacecraft is exposed in certain phases of the mission, a streamlined environment that subjects it to thermal and mechanical stress tending compromise the integrity of structures and equipment as also the payload. To describe the phenomenology characteristic of these stresses is useful to refer to the phase of re-entry.

 On the way back into the atmosphere, the vehicle loses kinetic energy that is converted into heat and transferred to the gas surrounding the vehicle. The fluid tends to aerodynamic heating by convection, conduction and radiation through the viscous boundary layer surrounding the vehicle, giving rise to the so-called "aerodynamic heating.

 Faced with the problem of choosing a specific TPS for a re-entry vehicle is part of the first type of materials chosen and their mode of operation according to the following mechanisms:

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• The absorption of heat incident on the surface of the material by raising its temperature;
• The rejection of the incident heat through the issuance of the radiative surface of the material;
• Change of phase and / or degradation of chemical reactions that absorb much of the heat incident and that, as an additional mechanism for heat rejection, may reject heat through diffusion of fluid mass that tends to act as a coolant.
 

Very often the heat shield is characterized by one or more main materials that resist heat input through one of the mechanisms just mentioned, and a secondary material that acts as an insulator between the outer surface of the protection, more stressed, and the very structure and own the vehicle.

So will be studied the thermal protection systems to be adopted on the capsule.

 For the scaling found for the capsule's heat shield will make use of innovative materials, combined with alternative methods to decrease the heat flows, such as obtaining a high ballistic parameter (area / mass) through the use of technologies aerodynamic deployable

  Flight Profile

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