Hypergolic rocket engines use hypergolic propellants, which are substances that ignite spontaneously upon contact with each other.
Hypergolic rocket engines are known for their simplicity and reliability, as they eliminate the need for an external ignition source. They are commonly used in spacecraft for various applications, including orbit insertion, attitude control, and orbital maneuvers. The specific details of the engine’s performance depend on the choice of hypergolic propellants and the design of the engine components.
The thrust equation for a turbojet engine using control volume analysis is expressed as:
where,
- is the thrust force,
- ṁe is the mass flow rate of exhaust gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle exit in meters per second (m/s).
- ṁ0 is the mass flow rate of inlet gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle Inlet in meters per second (m/s).
- is the Pressure at the nozzle exit in pascals (Pa).
- is the Pressure at the nozzle inlet in pascals (Pa).
- is the Area of the nozzle exit in square meters (m²).