Development, testing and qualification of a Solid Rocket Motor
EADS / CASSIDIAN GmbH did contract in 2011 a feasibility study to develop a solid rocket motor to be used in an auxiliary take off unit. Maximum thrust was specified up to 20 kN and total impulse had to be kept in a closely defined range as well. Rapid thrust build up was of paramount importance.
WEPA-Technologies in cooperation with an external partner did design the engine including all hardware components according to contract requirements, manufactured prototypes and conducted static tests. A nitrate / polymer composite propellant was used. Compared to state of the art double-base or ammoniumperchlorate based systems, handling procedures can be conducted in a much safer manner. As a consequence legal transport and storage issues are significantly less demanding and air transport can be realized.
During the development process
internal ballistics were modified several times to finally meet the specified parameter.
Production processes of the composite propellant were adapted to assure the procedure meeting the highest quality standards.
The specifications defined by EADS / CASSIDIAN were met and proven during several technical acceptance trials.