Wendernes develops hypergolic rocket engines designed for suborbital research applications.
HTP Monopropellant Thrusters
Hydrogen peroxide monopropellant thrusters for attitude control and trajectory modification.
Thrust: 10-100 N
Specific Impulse: 145-160 seconds (vacuum)
Propellant: High-test peroxide (85-98% Hâ‚‚Oâ‚‚)
Operation: Pulsed or continuous burn capability
WFNA Bipropellant Rocket Engines
White fuming nitric acid engines for higher thrust applications.
Thrust: 500-5000 N
Specific Impulse: 240-260 seconds (vacuum)
Oxidizer: Inhibited white fuming nitric acid (IWFNA)
Fuel: Monomethylhydrazine (MMH) or hydrazine derivatives
Mixture Ratio: Optimized for performance and stability
IWFNA Inhibitor Technology
Use of iodine pentoxide-derived iodic acid as corrosion inhibitor enables:
Standard stainless steel and aluminum alloys instead of exotic materials
Reduced material costs and improved manufacturability
Longer engine service life and improved reliability
Compatibility with standard propellant handling equipment
Boron-Enhanced Research
Development of boron-enhanced propellant formulations for increased volumetric energy density. Current work focuses on understanding technical limitations through controlled ground testing.