Launch vehicles with ring-shaped external elements, and associated systems and methods

Patent metadata

Field	Value
Publication number	US-10266282-B2
Application number	US-201615342501-A
Country	US
Kind code	B2
Filing date	Nov 3, 2016
Priority date	Mar 15, 2013
Publication date	Apr 23, 2019
Grant date	Apr 23, 2019

Abstract

Launch vehicles with ring-shaped external elements, and associated systems and methods. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent.

First claim

We claim:

1. A method for operating an aerospace system, comprising:
directing thrust from a nozzle of a launch vehicle to lift the launch vehicle, the launch vehicle having a first end, a second end, and a vehicle axis extending between the first and second ends, the second end being above the first end during launch;
subsequent to launch, directing the launch vehicle to descend and land with the first end below the second end; and
during vehicle descent, allowing air to pass along an external surface of the vehicle, inwardly from an annular element fixedly attached to the launch vehicle, in a direction away from the first end of the launch vehicle.

2. The method of claim 1 wherein lifting the launch vehicle includes lifting the launch vehicle while the annular element is positioned between the first and second ends of the vehicle.

3. The method of claim 1 wherein the launch vehicle has a first stage positioned along the vehicle axis and a second stage positioned along the vehicle axis and joined to the first stage at a predefined separation location and wherein directing thrust includes directing the launch vehicle upwardly with the first and second stages connected, and the annular element having a first position relative to a first overall length of the launch vehicle, and wherein the method further comprises:
separating the first and second stages and, and wherein directing the launch vehicle to descend includes directing the first stage, downwardly with the annular element having a second position relative to a second overall length of the launch vehicle, the second position being different than the first position.

4. The method of claim 1 wherein the annular element has a first edge surface facing toward the first end and a second edge surface facing toward the second end, the second edge surface being blunter than the first edge surface, and wherein the method further comprises:
positioning the first edge surface to be a leading edge surface during descent.

5. The method of claim 1 wherein the annular element has a first edge surface facing a first direction along the vehicle axis and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction, and wherein the method further comprises:
shielding the first edge surface from external flow during vehicle ascent; and
exposing the first edge surface to external flow during vehicle descent.

6. The method of claim 5 wherein the system includes a first stage and a second stage that is separable from the first stage, and wherein:
shielding the first edge includes shielding the first edge with the second stage; and
exposing the first edge by separating the first stage from the second stage.

7. A method for operating an aerospace system, comprising:
directing thrust from a first nozzle of a launch vehicle to lift the launch vehicle, the launch vehicle having a first stage carrying a first nozzle, a second stage carrying a second nozzle, an upper end, a lower end, and a vehicle axis extending between the upper and lower ends, the upper end being above the lower end during launch;
subsequent to launch, activating the second nozzle to separate the first and second stages; and
directing exhaust from the second nozzle through an annular element while the annular element is fixedly carried by the first stage.

8. The method of claim 7 , further comprising directing the first stage to land with the first nozzle facing downwardly.

9. The method of claim 8 , further comprising allowing air to pass through the annular element during descent, in a direction away from the first nozzle.

10. The method of claim 7 wherein separating the first and second stages includes separating the first and second stages without using a mechanical actuator to push at least one of the first and second stages away from the other.

11. The method of claim 7 wherein directing exhaust from the second nozzle includes directing at least a portion of the exhaust to impinge on a close-out surface of the first stage facing toward the second nozzle.

12. The method of claim 11 wherein directing exhaust from the second nozzle includes directing at least a portion of the exhaust through a gap between the annular element and an external, outwardly-facing surface of the first stage.

13. The method of 7 wherein the second stage carries a crew, and wherein activating the second nozzle includes activating the second nozzle as part of a crew escape procedure.

14. An aerospace system, comprising:
a controller, programmed with instructions that, when executed:
direct thrust from a nozzle of a launch vehicle to lift the launch vehicle, the launch vehicle having a first end, a second end, and a vehicle axis extending between the first and second ends, the second end being above the first end during launch;
subsequent to launch, direct the launch vehicle to descend and land with the first end below the second end; and
during vehicle descent, allow air to pass along an external surface of the vehicle, inwardly from an annular element fixedly attached to the launch vehicle, in a direction away from the first end of the launch vehicle.

15. The system of claim 14 wherein the controller is programmed with instructions then, when executed, direct a second stage of the launch vehicle to separate from a first stage of the launch vehicle, with the annular element fixedly attached to the first stage.

Assignees

• Blue Origin Llc

Inventors

• Featherstone Mark
• Sanders John Michael
• Ramsey Roger E
• Wetzel Eric David

Classifications

• B64G1/002 Primary

  Launch systems · CPC title

• B64G1/402

  Propellant tanks; Feeding propellants · CPC title

• B64G1/645

  Separators · CPC title

• B64G1/623

  Retarding devices, e.g. retrorockets · CPC title

• B64G1/2229

  characterised by the deployment actuating mechanism (inflating B64G1/2227) · CPC title