초록 ▼

Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a launch vehicle that has a first end and a second end generally opposite the first end, and is elongated along a vehicle axi

Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a launch vehicle that has a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. The vehicle carries an exposed outwardly facing surface having a first region positioned or positionable to have a first cross-sectional area generally normal to the vehicle axis toward the first end of the vehicle, and a second region positioned or positionable to have a second cross-sectional area generally normal to the vehicle axis toward the second end of the vehicle. The first cross-sectional area is less than the second cross-sectional area. The system can further include a propulsion system carried by the launch vehicle and having at least one nozzle positioned toward the first end of the vehicle to launch the launch vehicle. In a further particular embodiment, the exposed surface can include a deployable flare surface that is positioned toward the forward section of the vehicle and is stowed during an ascent phase of the vehicle. During descent, the deployable flare surface can pivot outwardly to slow the vehicle down for a tail-down landing. Systems is accordance with other embodiments include launch vehicles with fuel tanks shaped to control the motion of the center of gravity of fuel in the tanks as the fuel level in the tank changes.

대표청구항 ▼

1. An aerospace system, comprising: a vertical take-off and landing launch vehicle having a first end and a second end generally opposite the first end, the launch vehicle being elongated along a vehicle axis extending between the first end and the second end;a propulsion system carried by the launc

1. An aerospace system, comprising: a vertical take-off and landing launch vehicle having a first end and a second end generally opposite the first end, the launch vehicle being elongated along a vehicle axis extending between the first end and the second end;a propulsion system carried by the launch vehicle and having at least one nozzle positioned at the first end of the launch vehicle to launch the launch vehicle;a deployable and stowable, outwardly facing surface carried by the launch vehicle, the deployable surface being moveable relative to the launch vehicle between a stowed position and a deployed position, the deployable surface being configured to produce a first vehicle cross-sectional area generally normal to the vehicle axis when stowed and a second vehicle cross-sectional area generally normal to the vehicle axis when deployed, the second cross-sectional area being closer to the second end of the launch vehicle than the first end and being greater than the first cross-sectional area and greater than all vehicle cross sectional areas generally normal to the vehicle axis located between the first end and the second cross-sectional area; anda controller carried by the launch vehicle and configured to stow the deployable surface during vehicle ascent, and to deploy the deployable surface during vehicle descent. 2. The system of claim 1 further comprising a sensor operatively coupled to the controller to provide a signal indicative of a change between vehicle ascent and vehicle descent. 3. The system of claim 1 wherein the deployable surface includes multiple deployable panels, with neighboring panels having different circumferential locations. 4. The system of claim 3 wherein neighboring panels overlap. 5. The system of claim 4 wherein the overlapping panels include multiple outer panels and multiple inner panels, with an individual inner panel positioned between and radially inwardly from two adjacent outer panels. 6. The system of claim 1 wherein the deployable surface is pivotably moveable relative to the launch vehicle. 7. The system of claim 1 wherein the deployable surface is generally aerodynamically sealed. 8. The system of claim 1 wherein the deployable surface has air passages positioned to allow air to flow through the deployable surface. 9. The system of claim 1 wherein the deployable surface includes a vane. 10. The system of claim 1 wherein the deployable surface includes a flare. 11. The system of claim 1 wherein the deployable surface includes multiple elements and wherein the controller is programmed with instructions to move an individual element independently of another individual element. 12. The system of claim 1 wherein the deployable surface is a second deployable surface, and wherein the vehicle includes a first deployable surface positioned toward the first end of the vehicle, and wherein the controller is programmed with instructions to control the motions of the first and second deployable surfaces independently. 13. An aerospace system, comprising: a vertical take-off and landing launch vehicle having a first end and a second end generally opposite the first end, the launch vehicle being elongated along a vehicle axis extending between the first end and the second end;at least one outwardly facing, exposed surface carried by the launch vehicle, the exposed surface having a first region that is positioned or positionable to produce a first exposed surface area per unit length along the vehicle axis toward the first end of the vehicle, the exposed surface having a second region positioned or positionable to produce a second exposed surface area per unit length along the vehicle axis toward the second end of the vehicle, the second surface area per unit length being greater than the first surface area per unit length, and greater than any exposed surface area per unit length located between the first end and the second exposed surface area per unit length;wherein the second region is movable relative to the launch vehicle axis between a stowed position and a deployed position, and wherein the second region of the exposed surface is configured to produce the second surface area per unit length when in the deployed position, wherein the second region is in the stowed position during an ascent stage and in the deployed position during a decent stage of the launch vehicle's flight; anda propulsion system carried by the launch vehicle and having at least one nozzle positioned at the first end of the launch vehicle to launch the launch vehicle. 14. The system of claim 13 wherein the first exposed surface area per unit length is the largest exposed surface area per unit length of the exposed surface toward the first end of the vehicle, and the second exposed surface area per unit length is the largest exposed surface area per unit length of the exposed surface toward the second end of the vehicle. 15. The system of claim 13 further comprising a sensor operatively coupled to the controller to provide a signal indicative of a change between vehicle ascent and vehicle descent. 16. The system of claim 13 wherein the second region includes multiple deployable panels, with neighboring panels having different circumferential locations. 17. The system of claim 16 wherein neighboring panels overlap. 18. The system of claim 17 wherein the overlapping panels include multiple outer panels and multiple inner panels, with an individual inner panel positioned between and radially inwardly from two adjacent outer panels. 19. The system of claim 13 wherein the second region is pivotably moveable relative to the launch vehicle. 20. The system of claim 13 wherein the second region is generally aerodynamically sealed. 21. The system of claim 13 wherein the second region has air passages positioned to allow air to flow through the deployable surface. 22. The system of claim 13 wherein the second region includes a vane. 23. The system of claim 13 wherein the second region includes a flare. 24. The system of claim 13 wherein the second region includes multiple elements and wherein the controller is programmed with instructions to move an individual element independently of another individual element. 25. The system of claim 13 wherein the second region includes a second deployable surface, and wherein the vehicle includes a first deployable surface positioned toward the first end of the vehicle, and wherein the controller is programmed with instructions to control the motions of the first and second deployable surfaces independently.