The evolution of fairing structure from Ariane 1 to Ariane 4
Abstract
The Ariane 4 carbon fiber composite sandwich fairing is described. Carbon fiber is preferred to Kevlar because of materials and manufacturing costs, compression strength and Kevlar's sensitivity to humidity before impregnation. The development of fiber technology allows large fiber reinforced structure elements which are used for Ariane-4 fairing structures. The core material is aluminum alloy honeycomb. A 135C curing epoxy resin matrix is used. Weight reduction for an Ariane 1 frame stringer type structure is 300 kg, which enables a payload mass to be increased by 10 kg.
- Publication:
-
In CNES The Future of Launchers in Europe
- Pub Date:
- 1982
- Bibcode:
- 1982cnes.rept..399B
- Keywords:
-
- Ariane Launch Vehicle;
- Carbon Fiber Reinforced Plastics;
- Fairings;
- Structural Design Criteria;
- Honeycomb Cores;
- Kevlar (Trademark);
- Payload Mass Ratio;
- Sandwich Structures;
- Weight Reduction;
- Launch Vehicles and Space Vehicles