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Aerospace Propulsion Products (APP) delivers ignition systems qualified to the highest standards of the space industry. Since the mid-1990s, APP has developed and produced igniters for major European launch vehicles, including Ariane 5, Ariane 6, and Vega. Our systems are designed to ensure safe, reliable, and repeatable engine starts for both solid and liquid rocket propulsion.
Discover the productsMany APP products are pyrogen igniters, which use solid propellant to generate hot gas. These are mainly applied in solid rocket motors, but can also be used in liquid engines. APP has produced the Vulcain II igniters and starters for Ariane 5 since 1995, and since 2001 has developed the igniters for solid rocket motors of Vega, which remain in production today. A different approach is the spark torch igniter, which produces hot gas by burning a fuel such as hydrogen or methane with pure oxygen. The combustion starts with a spark or glow plug. Unlike pyrogen igniters, spark torch igniters allow multiple ignitions and are widely used in rocket engine test facilities. Since 1999, APP has also been responsible for the development and production of the ignition system of the Vinci engine, which powers the upper stage of Ariane 6 and is suitable for future applications such as Vega. Vinci’s ignition system features a unique restart capability, enabling up to four ignitions in space and providing the flexibility needed for complex missions.
Vulcain igniters and starters
The igniters are based on pyrogen technology and contain composite solid propellant grains. The unique compositions of the propellants are based on ammonium nitrate and therefore chlorine free combustion products are obtained.
Vinci ignition system
Ariane 6 is Europe’s next-generation launcher, now in production and entering its launch phase. Its upper stage is powered by the Vinci engine, which can be restarted up to four times to deliver payloads into multiple orbits. The Vinci ignition system uses an independent supply of hydrogen and oxygen with dual glow plugs, ensuring reliable restarts under all mission conditions.
Vega solid rocket motor igniters
The Vega launcher family relies on powerful solid rocket motors to deliver satellites into orbit. Each of these motors needs a precise and reliable ignition system to start the combustion process. APP has developed and produced the igniters for both the original Vega and its successor Vega-C. These igniters provide the vital energy to light the solid propellant and ensure a safe and controlled launch sequence.
New applications for ESA Future Launchers Programme
In the general catalytic igniter concept a catalyst is applied to decompose a propellant, thereby releasing thermal energy. In our current design hydrogen peroxide is decomposed into a high temperature mixture of water vapour and oxygen. This can in turn be used to ignite a mixture of propellants in a thrust chamber. The advantage of the catalytic concept is that no regulated electrical device is needed to ignite the propellants in the igniter. Compared to a spark torch igniter, the ignition electronics and the spark plug can be omitted.
The Direct Spark Ignition principle is based on creating plasma directly in the engine’s combustion chamber at a location favourable for ignition, similar to a gas-turbine engine. If successful, this system would make the use of a traditional torch igniter and feed-system obsolete with potentially massive savings in mass and costs.
The Direct Spark Ignition principle is based on creating plasma directly in the engine’s combustion chamber at a location favourable for ignition, similar to a gas-turbine engine. If successful, this system would make the use of a traditional torch igniter and feed-system obsolete with potentially massive savings in mass and costs.
Parachute Deployment Device
APP has participated in an ESA Technology Research Programme (TRP) for development of a European Parachute Deployment Device (PDD) for ejection of the parachute of a space probe descent system.
A mortar and gas generator have been designed and manufactured. Analysis of the propellant and full PDD performance was performed by TNO and Vorticity. Detailed design, assembly and integration of all the hardware has been performed by APP.
A mortar and gas generator have been designed and manufactured. Analysis of the propellant and full PDD performance was performed by TNO and Vorticity. Detailed design, assembly and integration of all the hardware has been performed by APP.