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Design of a Multi-Payload Adapter for a Small-Satellite Launch Vehicle
The main objective of this thesis is to design a multi-payload adapter-dispenser system for a small-satellite launch vehicle, which enables the concurrent launch of multiple smaller payloads in addition to one primary spacecraft.
Background: This thesis is carried out in the framework of the European ALTAIR project (Air Launch space Transportation using an Automated aircraft and an Innovative Rocket), which aims to demonstrate the economic and technical viability of a novel launch system for the access to space of small satellites (150 kg). The ALTAIR system comprises an innovative launch vehicle designed around advanced composite structures, which is air-launched from an automated carrier aircraft. As part of this multidisciplinary project, ETH is responsible for the load-carrying structures of the launcher.
Motivation: The ALTAIR launch vehicle is designed for a nominal payload of 150 kg at a sun-synchronous orbit (SSO) of 800 km. To transport the satellite safely into orbit, the uppermost stage of the rocket comprises a conical payload adapter, which - at the current stage - enables the accommodation of one primary satellite. For lighter satellites, in order to exploit the full performance capabilities of the launch vehicle and to increase its mission flexibility, a multi-payload adapter is to be developed, which allows the concurrent launch and orbit insertion of multiple smaller satellites such as CubeSats.
Background: This thesis is carried out in the framework of the European ALTAIR project (Air Launch space Transportation using an Automated aircraft and an Innovative Rocket), which aims to demonstrate the economic and technical viability of a novel launch system for the access to space of small satellites (150 kg). The ALTAIR system comprises an innovative launch vehicle designed around advanced composite structures, which is air-launched from an automated carrier aircraft. As part of this multidisciplinary project, ETH is responsible for the load-carrying structures of the launcher.
Motivation: The ALTAIR launch vehicle is designed for a nominal payload of 150 kg at a sun-synchronous orbit (SSO) of 800 km. To transport the satellite safely into orbit, the uppermost stage of the rocket comprises a conical payload adapter, which - at the current stage - enables the accommodation of one primary satellite. For lighter satellites, in order to exploit the full performance capabilities of the launch vehicle and to increase its mission flexibility, a multi-payload adapter is to be developed, which allows the concurrent launch and orbit insertion of multiple smaller satellites such as CubeSats.
The goal of this thesis is to design a multi-payload adapter-dispenser system for the ALTAIR launch vehicle, which enables the concurrent launch of multiple smaller payloads. The major tasks are:
- Literature research on multi-payload adapters of existing launch vehicles
- Conceptual design of the payload adapter consideration lightweight requirements, payload arrangement, and a modular design allowing to -
- Detailed design (CAD) the payload adapter subsystems and sizing of the load-carrying structures using FEM.
The goal of this thesis is to design a multi-payload adapter-dispenser system for the ALTAIR launch vehicle, which enables the concurrent launch of multiple smaller payloads. The major tasks are: - Literature research on multi-payload adapters of existing launch vehicles - Conceptual design of the payload adapter consideration lightweight requirements, payload arrangement, and a modular design allowing to - - Detailed design (CAD) the payload adapter subsystems and sizing of the load-carrying structures using FEM.
Christoph Karl
ETH Zurich - CMASLab
Tannenstrasse 3 - CLA E 32.2
8092 Zurich, Switzerland
Tel: +41 44 632 0840
Email: karlc@ethz.ch
Christoph Karl ETH Zurich - CMASLab Tannenstrasse 3 - CLA E 32.2 8092 Zurich, Switzerland