Reusable upper stage rocket with aerospike engine
Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.
1. A vehicle comprising:
a rocket body extending from a forward end to an aft end and defining a longitudinal axis; and
a heat shield at the aft end of the rocket body, the heat shield configured to spherically cap the aft end of the rocket body and dissipate heat encountered upon reentry of the rocket body into the atmosphere, the heat shield comprising a plurality of scarfed nozzles arranged radially around the longitudinal axis of the rocket body,
wherein at least an inboard portion of each scarfed nozzle defines at least a portion of an aerospike contour, and
wherein at least a portion of a thruster module of a plurality of thruster modules is inset into a respective scarfed nozzle of the plurality of scarfed nozzles, the plurality of scarfed nozzles configured to direct exhaust ejected from the plurality of thruster modules along at least the inboard portions of the scarfed nozzles defining portions of the aerospike contour.
2. The vehicle of claim 1 , further comprising an engine located at the aft end of the rocket body, the engine configured to pump propellant to the plurality of thruster modules.
3. The vehicle of claim 1 , further comprising secondary fluid injectors configured to eject fluid that joins with the exhaust ejected from the plurality of thruster modules.
4. The vehicle of claim 3 , wherein the secondary fluid injectors are arranged radially within the heat shield.
5. The vehicle of claim 4 , wherein the plurality of thruster modules are configured to eject exhaust and the secondary fluid injectors are configured to eject fluid to form an exhaust plume that is similar in geometry to the exhaust plume from a full-length plug nozzle.
6. The vehicle of claim 1 , wherein the heat shield is actively cooled.
7. The vehicle of claim 1 , wherein the heat shield comprises a cooling circuit configured to dissipate heat encountered during reentry of the rocket body.
8. The vehicle of claim 1 , wherein the heat shield comprises a semi-spherical surface, and wherein the plurality of scarfed nozzles are embedded radially around the semi-spherical surface of the heat shield.
9. The vehicle of claim 1 , wherein the heat shield comprises a surface configured to cap the aft end of the rocket body, and wherein the plurality of scarfed nozzles are embedded around the surface of the heat shield.
10. The vehicle of claim 9 , wherein inboard surfaces of the plurality of scarfed nozzles collectively define the aerospike contour, and wherein the plurality of scarfed nozzles are configured to direct exhaust along the aerospike contour.
11. A multi-stage vehicle comprising:
a lower stage configured to launch the vehicle; and
an upper stage configured to separate from the lower stage, the upper stage comprising:
a rocket body extending from a forward end to an aft end and defining a longitudinal axis, and
a heat shield at the aft end of the rocket body, the heat shield comprising a surface configured to cap the aft end of the rocket body and dissipate heat encountered upon reentry of the upper stage into the atmosphere, the heat shield comprising a plurality of scarfed nozzles arranged radially around the surface of the heat shield,
wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour, and
wherein at least a portion of a thruster module of a plurality of thruster modules is inset into a respective scarfed nozzle of the plurality of scarfed nozzles, the plurality of scarfed nozzles configured to direct exhaust ejected from the plurality of thruster modules along the aerospike contour collectively defined by inboard surfaces of the plurality of scarfed nozzles.
12. The multi-stage vehicle of claim 11 , further comprising an engine located at the aft end of the rocket body, the engine configured to pump propellant to the plurality of thruster modules.
13. The multi-stage vehicle of claim 11 , wherein the upper stage further comprises secondary fluid injectors configured to eject fluid that joins with the exhaust ejected by the plurality of thruster modules.
14. The multi-stage vehicle of claim 13 , wherein the secondary fluid injectors are arranged radially within the heat shield.
15. The multi-stage vehicle of claim 13 , wherein the plurality of thruster modules are configured to eject exhaust and the secondary fluid injectors are configured to eject fluid to form an exhaust plume that is similar in geometry to the exhaust plume from a full-length plug nozzle.
16. The multi-stage vehicle of claim 11 , wherein the heat shield is actively cooled.
17. The multi-stage vehicle of claim 11 , wherein the heat shield comprises a cooling circuit configured to dissipate heat encountered during reentry of the upper stage.
18. The multi-stage vehicle of claim 11 , wherein the surface comprises a semi-spherical surface, and wherein the plurality of scarfed nozzles are embedded radially around the semi-spherical surface of the heat shield.
19. A method comprising:
launching a multi-stage vehicle, the vehicle comprising:
a lower stage configured to launch the vehicle; and
an upper stage configured to separate from the lower stage, the upper stage comprising:
a rocket body extending from a forward end to an aft end and defining a longitudinal axis; and
a heat shield at the aft end of the rocket body, the heat shield comprising a surface configured to cap the aft end of the rocket body and dissipate heat encountered upon reentry of the upper stage into the atmosphere, the heat shield comprising a plurality of scarfed nozzles arranged radially around the surface of the heat shield,
wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour, and
wherein at least a portion of a thruster module of a plurality of thruster modules is inset into a respective scarfed nozzle of the plurality of scarfed nozzles, the plurality of scarfed nozzles configured to direct exhaust ejected from the plurality of thruster modules along the aerospike contour collectively defined by inboard surfaces of the plurality of scarfed nozzles.
20. The method of claim 19 , further comprising:
descending the upper stage in an aft-end down orientation after separation from the lower stage; and
ejecting the exhaust from the plurality of thruster modules to slow descent of the upper stage.
21. The method of claim 20 , further comprising ejecting fluid from secondary fluid injectors, the fluid from the secondary fluid injectors joining with the exhaust ejected from the plurality of thruster modules.
22. The method of claim 20 , further comprising actively cooling the heat shield during descent of the upper stage.
23. The method of claim 19 , further comprising landing the upper stage vertically.
24. The method of claim 19 , wherein the surface comprises a semi-spherical surface, and wherein the plurality of scarfed nozzles are embedded radially around the semi-spherical surface of the heat shield.