Kestrel (rocket engine)
|Country of origin||United States|
|Application||upper stage boost|
|Propellant||LOX / RP-1|
|Thrust (vac.)||6,900 pounds-force (31 kN)|
|Chamber pressure||135 pounds per square inch (930 kPa)|
|Isp (vac.)||317 seconds (3.11 km/s)|
|Dry weight||52 kilograms (115 lb)|
Kestrel is ablatively cooled in the chamber and throat and radiatively cooled in the nozzle, which is fabricated from a high strength niobium alloy. As a metal, niobium is highly resistant to cracking compared to carbon-carbon. According to SpaceX, an impact from orbital debris or during stage separation might dent the metal but have no meaningful effect on engine performance. Helium pressurant efficiency is substantially increased via a titanium heat exchanger on the ablative/niobium boundary.
Thrust vector control is provided by electro-mechanical actuators on the engine dome for pitch and yaw. Roll control (and attitude control during coast phases) is provided by helium cold gas thrusters.
A TEA-TEB pyrophoric ignition system is used to provide multiple restart capability on the upper stage. In a multi-manifested mission, this design would allow for drop off at different altitudes and inclinations.
Enhancements to the design of the original Kestrel engine were planned, called the Kestrel 2.
The engine design was still pressure-fed, and was supposed to fly on a newly designed second stage that used Aluminium-lithium alloy 2195, rather than the 2014 Aluminum used in the Falcon 1 second stage. Engine changes were to include tighter tolerances to improve consistency, higher Isp, and lighter weight. The Kestrel 2 did not remain in active development after the Falcon 1 was replaced by the much larger Falcon 9 v1.0 which used an improved Merlin 1C for its upper stage.
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