초록 ▼

Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to co

Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

대표청구항 ▼

1. An aerospace system, comprising: a space launch vehicle having an upper end, a lower end, a vehicle axis extending between the upper and lower ends, and one or more rocket nozzles positioned toward the lower end, wherein the launch vehicle is configured to implement a routine that includes: direc

1. An aerospace system, comprising: a space launch vehicle having an upper end, a lower end, a vehicle axis extending between the upper and lower ends, and one or more rocket nozzles positioned toward the lower end, wherein the launch vehicle is configured to implement a routine that includes: directing thrust from at least one of the one or more rocket nozzles to lift the launch vehicle during launch, the upper end being above the lower end during launch;subsequent to launch, descending and landing with the lower end below the upper end; andduring descent, shifting a center of pressure of the launch vehicle from a first position below a center of gravity of the vehicle to a second position above the center of gravity by moving a control surface, wherein the control surface includes a translating element, and wherein shifting the center of pressure of the vehicle includes moving the translating element between a lower position toward the lower end of the vehicle and an upper position toward the upper end of the vehicle. 2. The aerospace system of claim 1 wherein the routine further includes directing thrust from the one or more rocket nozzles to decelerate the launch vehicle during decent. 3. The aerospace system of claim 1 wherein the control surface describes a first cross-sectional area generally normal to the vehicle axis toward the upper end of the launch vehicle during descent, the launch vehicle having a second cross-sectional area generally normal to the vehicle axis toward the lower end of the launch vehicle during descent, the second cross-sectional area being less than the first cross-sectional area. 4. The aerospace system of claim 1 wherein the control surface includes an outwardly facing, exposed surface that describes a first cross-sectional area generally normal to the vehicle axis toward the upper end of the launch vehicle during descent, the launch vehicle having a second cross-sectional area generally normal to the vehicle axis toward the lower end of the launch vehicle during descent, the second cross-sectional area being less than the first cross-sectional area. 5. The aerospace system of claim 1 wherein shifting the center of pressure of the vehicle includes moving the control surface from a stowed position to a deployed position. 6. The aerospace system of claim 1 wherein the routine further comprises directing thrust from the one or more rocket nozzles during landing. 7. The aerospace system of claim 1 wherein the control surface is tapered outwardly in a direction toward the upper end. 8. The aerospace system of claim 1 wherein the control surface includes a vane. 9. The aerospace system of claim 1 wherein the launch vehicle further comprises one or more fins positioned toward the lower end and separate from the control surface. 10. The aerospace system of claim 1 wherein the launch vehicle further comprises one or more control fins positioned toward the lower end and separate from the control surface, and wherein the routine further includes controlling a direction of the launch vehicle during descent via the one or more control fins. 11. The aerospace system of claim 1 wherein the launch vehicle further comprises one or more control fins positioned toward the lower end and separate from the control surface, wherein the routine further includes controlling a direction of the launch vehicle during descent by pivoting the one or more control fins about a corresponding pivot axis extending outwardly from the vehicle axis. 12. The aerospace system of claim 1 wherein the launch vehicle further comprises one or more bidirectional control fins positioned toward the lower end and separate from the control surface, wherein the routine further includes controlling a direction of the launch vehicle during ascent via at least one of the one or more bidirectional control fins, and controlling a direction of the launch vehicle during descent via at least one of the one or more bidirectional control fins. 13. The aerospace system of claim 1 wherein the launch vehicle further comprises one or more bidirectional control fins positioned toward the lower end and separate from the control surface, wherein the routine further includes controlling a direction of the launch vehicle during ascent by pivoting at least one of the one or more of the bidirectional control fins about a corresponding pivot axis extending outwardly from the vehicle axis, and controlling a direction of the launch vehicle during descent by pivoting the at least one of the one or more bidirectional control fins about the corresponding pivot axis. 14. A system for providing access to space, the system comprising: a space launch vehicle, wherein the space launch vehicle includes one or more rocket engines; anda controller carried by the space launch vehicle, the controller being programmed with instructions that, when executed:direct thrust from a lower end of the launch vehicle to lift the launch vehicle during ascent, the launch vehicle having an upper end positioned above the lower end during ascent;shift a center of pressure of the launch vehicle from a first position below a center of gravity of the launch vehicle to a second position above the center of gravity by moving at least one of a plurality of control surfaces from a stowed position to a deployed position after launch, wherein the upper end of the vehicle is positioned above the lower end during descent, wherein the plurality of control surfaces are positioned toward the upper end, and wherein each of the control surfaces includes a plurality of air passages positioned to allow air to flow through the control surfaces during descent; anddirect thrust from the lower end of the launch vehicle to decelerate the launch vehicle during descent. 15. The system of claim 14 wherein the at least one control surface is moved from the stowed position to the deployed position during descent. 16. The system of claim 14 wherein the center of gravity is positioned between the plurality of control surfaces and the rocket engines. 17. The system of claim 14 wherein the plurality of control surfaces are positioned above the center of gravity during descent. 18. The system of claim 14 wherein the center of pressure is aft of the center of gravity during vehicle ascent, and wherein the center of pressure is aft of the center of gravity during vehicle descent. 19. The system of claim 14 wherein moving the at least one control surface from the stowed position to the deployed position includes pivoting the control surface relative to the launch vehicle. 20. The system of claim 14 wherein moving the at least one control surface from the stowed position to the deployed position includes pivoting the control surface outwardly relative to the launch vehicle. 21. The system of claim 14 wherein moving the at least one control surface from the stowed position to the deployed position includes moving a fin. 22. The system of claim 14 wherein moving the at least one control surface from the stowed position to the deployed position includes deploying a flare surface. 23. The system of claim 14 wherein moving the at least one control surface from the stowed position to the deployed position includes deploying two individual elements, and wherein the controller is further programmed with instructions that, when executed move the individual elements at different rates, by different amounts, or both at different rates and by different amounts to control a direction of the launch vehicle during descent. 24. The system of claim 14 wherein the controller is further programmed with instructions that, when executed, control a direction of the launch vehicle on descent via the at least one control surface. 25. The system of claim 14 wherein the controller is further programmed with instructions that, when executed, control a direction of the launch vehicle on descent via a fin that is different than the at least one control surface. 26. The system of claim 14 wherein the at least one control surface is a first control surface, and wherein the controller is further programmed with instructions that, when executed, control a direction of the launch vehicle on descent via a second control surface that is different than the first control surface, wherein the first control surface is positioned above the center of gravity on descent, and wherein the second control surface is positioned below the center of gravity on descent. 27. The system of claim 14 wherein the controller is further programmed with instructions that, when executed, control a direction of the launch vehicle on ascent and on descent via a bidirectional control fin that is different than the at least one control surface. 28. The system of claim 14 wherein the at least one control surface is a first control surface, and wherein the controller is further programmed with instructions that, when executed, control a direction of the launch vehicle on ascent and on descent via a second control surface that is different than the first control surface, wherein the first control surface is positioned above the center of gravity on descent, and wherein the second control surface is positioned below the center of gravity on descent. 29. A method for operating a space launch vehicle, the method comprising: directing thrust from a nozzle of a launch vehicle to lift the launch vehicle, the launch vehicle having 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, directing the launch vehicle to descend and land with the lower end below the upper end; andshifting a center of pressure of the launch vehicle from a first position to a second position via an exposed surface, wherein the first position is located between a center of gravity of the vehicle and the lower end, wherein the second position is located between the center of gravity and the upper end, and wherein the exposed surface is carried toward the upper end, the exposed surface defining a first cross-sectional area generally normal to the vehicle axis toward the upper end during descent, the vehicle having a second cross-sectional area generally normal to the vehicle axis toward the lower end during descent, the second cross-sectional area being less than the first cross-sectional area, wherein the exposed surface includes a translating element that is movable between a lower position toward the lower end of the vehicle and an upper position toward the upper end of the vehicle, and wherein shifting the center of pressure includes translating the element from the lower position to the upper position. 30. The method of claim 29 wherein the exposed surface includes a deployable element, and wherein shifting the center of pressure includes moving the deployable element from a stowed position to a deployed position. 31. The method of claim 29 wherein the exposed surface includes a deployable element, and wherein shifting the center of pressure includes moving the deployable element from a stowed position to a deployed position while the upper end remains above the lower end. 32. The method of claim 29, further comprising directing thrust from the nozzle to decelerate the launch vehicle as the launch vehicle descends with the upper end above the lower end. 33. The method of claim 29, further comprising controlling the vehicle during descent by movement of one or more fins positioned toward the lower end and separate from the exposed surface. 34. An aerospace system comprising: a vertical take-off and landing space launch vehicle having a forward end and an aft end;a rocket propulsion system carried by the launch vehicle and having at least one exhaust nozzle positioned toward the aft end, wherein the rocket propulsion system provides thrust when the launch vehicle is flying in an ascent orientation in which the forward end leads the aft end, and when the launch vehicle is flying in a descent orientation in which the aft end leads the forward end;a plurality of deployable control surfaces carried by the launch vehicle and moveable between stowed positions and deployed positions, each of the deployable control surfaces having a plurality of air passages configured to allow air to flow through the deployable control surfaces; anda controller configured to move at least one of the deployable control surfaces from the stowed position to the deployed position, the controller further configured to move the at least one deployable control surface to steer the launch vehicle in the descent orientation. 35. The aerospace system of claim 34 wherein the plurality of deployable control surfaces are positioned against an underlying surface of the launch vehicle when the plurality of deployable control surfaces are in the stowed positions, and wherein the plurality of deployable control surfaces extend outwardly from the launch vehicle when the plurality of deployable control surfaces are in the deployed positions. 36. The aerospace system of claim 34 wherein the launch vehicle includes a cylindrical body portion between the forward end and the aft end, wherein the plurality of deployable control surfaces are positioned against the cylindrical body portion when the plurality of deployable control surfaces are in the stowed positions, and wherein the plurality of deployable control surfaces extend outwardly from the launch vehicle when the plurality of deployable control surfaces are in the deployed positions. 37. The aerospace system of claim 34, wherein each of the deployable control surfaces is configured to move independently to steer the launch vehicle in the descent orientation. 38. The aerospace system of claim 34, wherein the plurality of deployable control surfaces are configured to move in concert to steer the launch vehicle in the descent orientation. 39. The aerospace system of claim 34 wherein the at least one deployable control surface is pivotably moveable relative to the launch vehicle when the at least one deployable control surface is in the deployed position. 40. The aerospace system of claim 34 wherein the plurality of deployable control surfaces are configured to produce a first launch vehicle cross-sectional area generally normal to a longitudinal axis of the launch vehicle when the deployable control surfaces are in the stowed position, and wherein the deployable control surfaces are further configured to produce a second launch vehicle cross-sectional area generally normal to the longitudinal axis when the deployable control surfaces are in the deployed position, the second cross-sectional area being greater than the first cross-sectional area and greater than all vehicle cross-sectional areas generally normal to the longitudinal axis located between the forward end and the aft end. 41. The aerospace system of claim 34 wherein the rocket propulsion system is configured to turn off prior to deployment of the at least one deployable control surface, and wherein the rocket propulsion system is further configured to restart after deployment of the at least one deployable control surface. 42. The aerospace system of claim 34, further comprising one or more control fins separate from the plurality of deployable control surfaces, wherein the controller is further configured to move the one or more control fins to control a direction of the launch vehicle during descent. 43. The system of claim 34, further comprising one or more bidirectional control fins separate from the plurality of deployable control surfaces, wherein the controller is configured to move the one or more bidirectional control fins to control a direction of the launch vehicle during ascent, and wherein the controller is further configured to move the one or more bidirectional control fins to control a direction of the launch vehicle during descent.