ECAPS delivers state of the art HPGP rocket engines and monopropellant LMP-103S, as well as design, development, qualification, integration, manufacturing and production of space propulsion systems specially tailored and tested to meet specific customer needs. In addition we deliver launch services - world wide fuelling services for satellites using LMP-103S.
The 1 N HPGP thruster is the base line for several new European and US missions. The up-scaled versions for 5 N and 22 N are under development in order to form a suite applicable for satellite propulsion systems. HPGP (High Performance Green Propellant) is a smart alternative to traditional propulsion. With a high specific impulse and density, it enables better performance and reduces mission costs.
Monopropellant LMP-103S
The novel ADN-based monopropellant LMP-103S is low toxic, environmentally benign and provides increased performance compared with Hydrazine. The specific impulse is 6 % higher and propellant density is 24 % higher, resulting in a 30 % increase in density-specific impulse.
- LMP-103S is long term compatible with most construction materials used in Hydrazine COTS components and propulsion systems.
- LMP-103S propellant is transport classified according to UN Class 1.4S, allowing air transportation in passenger and cargo carriers.
- SCAPE-suits are not required while handling monopropellant LMP-103S.
- LMP103-S is long-term storable and, unlike Hydrazine, not sensitive to contact with air and humidity.
1 N HPGP Rocket Engine
The 1N HPGP Rocket Engine has been designed for attitude and orbit control of small spacecraft. It is designed for operation in steady-state and pulse mode. The HPGP engine is aimed to replace hydrazine thrusters in conventional blow-down monopropellant propulsion systems with significant density impulse improvement. The engine has been demonstrated during the PRISMA mission and is the baseline thruster for several new European and US missions.
5 N HPGP Rocket Engine
The 5N HPGP Rocket Engine is based on the 1N HPGP thruster, it is however designed for attitude, trajectory and orbit control of small to medium size spacecraft. It is also designed for operation in steady-state and pulse mode. The engine is aimed to replace hydrazine thrusters in conventional monopropellant propulsion systems with significant density impulse improvement.
22 N HPGP Rocket Engine
The 22 N HPGP Rocket Engine has been designed for attitude and orbit control of spacecraft. It is designed for operation in steady-state and pulse mode. The HPGP engine is aimed to replace hydrazine thrusters in conventional monopropellant propulsion systems with significant density impulse improvement.
The 22 N HPGP Rocket Engine development models X-1 and -2 has been successfully test fired, thus verifying the feasibility to scale the HPGP technology to higher thrust levels.
The thruster is equipped with a Moog Inc. single seat propellant flow control valve. The high temperature resistant catalyst is developed and manufactured by ECAPS. The reactor heater and thermocouples are redundant. The thrust chamber is made of refractory metal.
