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Design and Sizing of a Payload Fairing for a Small-Satellite Launch Vehicle
The goal of this thesis is to size the fairing of a small-satellite (150kg) launch vehicle for the aerodynamic and thermal design loads encountered during the mission, and to design the fairing separation system.
Background: This thesis is carried out within 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 developing the load-carrying structures of the launcher.
Motivation: The ALTAIR launcher will require a fairing to protect the payload against aerodynamic, thermal, and vibro-acoustic loads during the atmospheric phase of the mission. Once the launch vehicle exits the dense atmosphere, these loads become insignificant and the fairing is jettisoned. To minimize the aerodynamic drag, the fairing of the ALTAIR launch vehicle will comprise a cylindrical base section transitioning into an aerodynamically optimized ogive nosecone. Due to requirements on mass reduction of the upper stage strucutres, a composite sandwich construction will be used for the payload fairing.
Background: This thesis is carried out within 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 developing the load-carrying structures of the launcher.
Motivation: The ALTAIR launcher will require a fairing to protect the payload against aerodynamic, thermal, and vibro-acoustic loads during the atmospheric phase of the mission. Once the launch vehicle exits the dense atmosphere, these loads become insignificant and the fairing is jettisoned. To minimize the aerodynamic drag, the fairing of the ALTAIR launch vehicle will comprise a cylindrical base section transitioning into an aerodynamically optimized ogive nosecone. Due to requirements on mass reduction of the upper stage strucutres, a composite sandwich construction will be used for the payload fairing.
The goal of this thesis is to size the fairing of the ALTAIR launch vehicle for the design loads (aerodynamic and thermal) encountered during the mission, including the design of the fairing separation system. The major tasks are:
- Literature research on payload fairing design
- Sizing of the fairing structure for the governing aerodynamic and thermal loads using FEA
- Optimization of the laminate layup for further weight reduction of the fairing
- Conceptual design of the separation system enabling fairing separation into two half shells
- Detailed design and sizing (FEA) of the fairing separation system
The goal of this thesis is to size the fairing of the ALTAIR launch vehicle for the design loads (aerodynamic and thermal) encountered during the mission, including the design of the fairing separation system. The major tasks are: - Literature research on payload fairing design - Sizing of the fairing structure for the governing aerodynamic and thermal loads using FEA - Optimization of the laminate layup for further weight reduction of the fairing - Conceptual design of the separation system enabling fairing separation into two half shells - Detailed design and sizing (FEA) of the fairing separation system
Christoph Karl
CMASLab - ETH Zürich
Tannenstrasse 3, CLA E 32.2
8092 Zurich
Tel: +41 44 632 0840
Email: karlc@ethz.ch
Christoph Karl CMASLab - ETH Zürich Tannenstrasse 3, CLA E 32.2 8092 Zurich Tel: +41 44 632 0840 Email: karlc@ethz.ch
Thesis Proposal_Design and Optimization of a Payload Fairing for a Small-Satellite Launch Vehicle.pdf
