System and method for hypersonic payload separation

1. An apparatus comprising:

a body having at least one pitch control system and a mounting system, the mounting system configured to couple to a payload;

a rocket engine coupled to the body and configured to accelerate the body to a hypersonic speed; and

a control system configured to release the payload while the body moves at the hypersonic speed by commanding the at least one pitch control system to adjust an angle of attack of the body to a negative angle of attack and commanding the mounting system to release the payload while the body is moving at the hypersonic speed and at the negative angle of attack.

2. The apparatus of claim 1 , wherein the at least one pitch control system comprises one or more one aerodynamic control surfaces, one or more orientation thrusters of a reaction control system, or a combination thereof.

3. The apparatus of claim 2 , further comprising at least one wing coupled to the body, wherein the body is reusable, and wherein the payload comprises an upper stage rocket.

4. The apparatus of claim 1 , further comprising one or more actuators coupled to the body, the one or more actuators configured to exert a force on the payload to move the payload relative to the body.

5. The apparatus of claim 4 , wherein the one or more actuators are hydraulically activated.

6. The apparatus of claim 1 , further comprising:

landing gear coupled to a first side of the body, wherein the body is configured to take-off vertically and land horizontally; and

an aerothermal coating associated with at least a portion of the first side, wherein the payload is mounted to a second side of the body opposite the first side.

7. The apparatus of claim 1 , wherein the angle of attack is relative to an airflow associated with the body.

8. The apparatus of claim 1 , wherein the negative angle of attack generates positive air pressure between the body and the payload, and wherein the body generates more negative lift than the payload.

9. The apparatus of claim 1 , wherein the rocket engine is configured to be active during release of the payload.

10. The apparatus of claim 1 , wherein the rocket engine is configured to be inactive during release of the payload.

11. The apparatus of claim 10 , further comprising one or more orientation thrusters configured to rotate and stabilize the body prior to release of the payload, during release, after release, or a combination thereof.

12. A system comprising:

a booster and an upper stage rocket, the booster comprising:

a body having at least one pitch control system and a mounting system, the mounting system configured to couple to the upper stage rocket;

a rocket engine coupled to the body and configured to accelerate the body to a hypersonic speed; and

a control system configured to release the upper stage rocket while the body moves at the hypersonic speed by commanding the at least one pitch control system to adjust an angle of attack of the body to a negative angle of attack and commanding the mounting system to release the upper stage rocket while the body is moving at the hypersonic speed and at the negative angle of attack; and

the upper stage rocket comprising:

a frame coupled to the mounting system of the booster;

an upper stage propulsion system; and

an upper stage controller configured to activate the upper stage propulsion system after release of the upper stage rocket.

13. The system of claim 12 , wherein the booster further comprises an aerothermal coating disposed on an underbelly of the body, and wherein the mounting system is coupled to a top side of the body opposite the underbelly.

14. The system of claim 12 , wherein the booster is configured to be reusable, wherein the booster is configured to take-off vertically and land horizontally, wherein the upper stage controller is configured to activate the upper stage propulsion system in response to determining that a distance from the booster to the upper stage rocket is greater than or equal to a threshold separation distance, and wherein the upper stage rocket is configured to deploy a payload.

15. The system of claim 12 , wherein the booster further comprises a plurality of actuators configured to exert a force on the upper stage rocket during release.

16. The system of claim 12 , wherein at least one of the booster and the upper stage rocket include a reaction control system and one or more orientation thrusters.

17. A method comprising:

during hypersonic flight of a booster, sending a first control command to a flight control system of the booster to adjust at least one pitch control system of the booster to orient a body of the booster at a negative angle of attack; and

while the body is oriented at the negative angle of attack, sending a second control command to a mounting system of the booster to release a payload mounted to the body of the booster.

18. The method of claim 17 , wherein the body is moving between about Mach 5 and about Mach 10 during release of the payload, and wherein a dynamic pressure associated with the body is between about zero pounds per square foot (psf) and about 25 psf during release of the payload.

19. The method of claim 17 , wherein, at the negative angle of attack, the booster generates more negative lift than the payload, and wherein the negative angle of attack causes a positive air pressure to develop between the body and the payload.

20. The method of claim 17 , wherein the mounting system couples the payload to an upper surface of the booster, wherein the booster is configured to avoid contacting the payload after release, and wherein the booster is configured to be at least about 100 feet from the payload within about five seconds of release.