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Vehicles with bidirectional 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

Vehicles with bidirectional 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.

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1. A rocket comprising: a first end portion;a second end portion;one or more bidirectional aerodynamic control surfaces, wherein each of the one or more aerodynamic control surfaces spans between a root portion and a distal tip portion; anda control system configured to pivot each of the one or more

1. A rocket comprising: a first end portion;a second end portion;one or more bidirectional aerodynamic control surfaces, wherein each of the one or more aerodynamic control surfaces spans between a root portion and a distal tip portion; anda control system configured to pivot each of the one or more aerodynamic control surfaces about a pivot axis extending from the root portion toward the tip portion to steer the rocket when the rocket is flying in a first orientation in which the first end portion leads the second end portion, and to steer the rocket when the rocket is flying in a second orientation in which the second end portion leads the first end portion. 2. The rocket of claim 1, wherein the rocket includes one or more engines and associated exhaust nozzles positioned toward the second end portion of the rocket, and wherein the one or more aerodynamic control surfaces are positioned toward the second end portion of the rocket. 3. The rocket of claim 1 wherein each of the one or more aerodynamic control surfaces has a low-sweep or non-swept forward edge and a highly swept aft edge when the rocket is in the first orientation. 4. The rocket of claim 1, wherein the rocket includes one or more engines and associated exhaust nozzles positioned toward the second end portion of the rocket, and wherein each of the one or more aerodynamic control surfaces is positioned toward the second end portion of the rocket and includes a forward edge positioned away from the second end portion and an aft edge positioned toward the second end portion, wherein the forward edge has a first sweep angle and the aft edge has a second sweep angle that is greater than the first sweep angle. 5. The rocket of claim 1, wherein the pivot axis is spaced apart from a first edge portion of the control surface and a second edge portion of the control surface. 6. The rocket of claim 5, wherein the pivot axis is positioned between a midpoint of the root portion and the first edge portion. 7. The rocket of claim 1, wherein the first orientation is an ascent orientation, and wherein the second orientation is a descent orientation. 8. The rocket of claim 1 wherein each of the one or more aerodynamic control surfaces exhibits a first lift slope when the rocket is flying in the first orientation, and wherein each of the one or more aerodynamic control surfaces exhibits a second lift slope that is different from the first lift slope when the rocket is flying in the second orientation. 9. The rocket of claim 1, further comprising: a payload module positioned toward the first end portion; anda booster module positioned toward the second end portion, wherein each of the one or more aerodynamic control surfaces is movably attached to the booster module. 10. A rocket for transporting at least one of humans and cargo into space, the rocket comprising: a first end portion;a second end portion; anda plurality of movable bidirectional control surfaces that steer the rocket when the rocket is flying in a first orientation in which the first end portion leads the second end portion, and when the rocket is flying in a second orientation in which the second end portion leads the first end portion, wherein each of the bidirectional control surfaces includes: a root portion;a distal tip portion spaced apart from the root portion;a first edge portion extending between the root portion and the tip portion; anda second edge portion extending between the root portion and the tip portion, wherein a chord extends between the first edge portion and the second edge portion;wherein the first edge portion leads the second edge portion when the rocket is flying in the first orientation. 11. The rocket of claim 10 wherein each of the bidirectional control surfaces exhibits a first lift slope when the rocket is flying in the first orientation, and wherein each of the bidirectional control surfaces exhibits a second lift slope that is more gradual than the first lift slope when the rocket is flying in the second orientation. 12. The rocket of claim 10 wherein the bidirectional control surfaces are positioned closer to the second end portion than the first end portion, and wherein the rocket further comprises one or more rocket exhaust nozzles positioned proximate the second end portion. 13. The rocket of claim 10, wherein the bidirectional control surfaces are configured to pivot about individual axes to steer the rocket when the rocket is flying in the first orientation and when the rocket is flying in the second orientation. 14. The rocket of claim 10, wherein each of the bidirectional control surfaces has a diamond-shaped cross-section. 15. The rocket of claim 10, further comprising one or more rocket exhaust nozzles positioned toward the second end portion, wherein the first edge portions of the bidirectional control surfaces face generally away from the second end portion and the second edge portions of the bidirectional control surfaces face generally away from the first end portion, wherein each of the bidirectional control surfaces is configured to rotate about a corresponding pivot axis, and wherein the pivot axis is positioned between a midpoint of the root portion and the first edge portion. 16. The rocket of claim 10, further comprising one or more rocket exhaust nozzles positioned toward the second end portion, wherein the first edge portions of the bidirectional control surfaces face generally away from the second end portion and the second edge portions of the bidirectional control surfaces face generally away from the first end portion, and wherein the first edge portions have a first sweep angle and the second edge portions have a second sweep angle that is greater than the first sweep angle. 17. The rocket of claim 10, further comprising: a payload module positioned toward the first end portion; anda booster module positioned toward the second end portion, wherein the plurality of bidirectional control surfaces are attached to the booster module. 18. The rocket of claim 10, further comprising one or more rocket exhaust nozzles positioned toward the second end portion, wherein the first edge portions of the bidirectional control surfaces face generally away from the second end portion and the second edge portions of the bidirectional control surfaces face generally away from the first end portion, and wherein the first edge portions have a first sweep angle and the second edge portions have a second sweep angle that is different from the first sweep angle. 19. The rocket of claim 10 wherein each bidirectional control surface further includes a pivot axis positioned between a midpoint of the root portion and the first edge portion, and wherein each of the bidirectional control surfaces is configured to rotate back and forth about its corresponding pivot axis to steer the rocket when the rocket is flying in the first orientation and when the rocket is flying in the second orientation. 20. The rocket of claim 10 wherein the second edge portion leads the first edge portion when the rocket is flying in the second orientation. 21. A space launch vehicle having a nose portion spaced apart from a tail portion, the vehicle comprising: a rocket exhaust nozzle;a plurality of fins extending outwardly from the vehicle, each of the plurality of fins having a first edge portion closer to the nose portion than the tail portion, a second edge portion closer to the tail portion than the nose portion, and an axis extending between the first and second edge portions; anda control system configured to pivot each fin about each fin's respective axis to provide active aerodynamic control of the vehicle when the vehicle is in nose-first airflow and when the vehicle is in tail-first airflow. 22. The space launch vehicle of claim 21, wherein when the vehicle is in nose-first airflow, the vehicle is in an ascent orientation, and wherein when the vehicle is in tail-first airflow, the vehicle is in a descent orientation. 23. The space launch vehicle of claim 21, further comprising: a payload module positioned toward the nose portion; anda propulsion module positioned toward the tail portion, wherein the plurality of fins is attached to the propulsion module. 24. The space launch vehicle of claim 21, wherein the rocket exhaust nozzle is positioned proximate the tail portion. 25. The space launch vehicle of claim 21, wherein each of the plurality of fins exhibits a first lift slope when the vehicle is in nose-first airflow, and wherein each of the plurality of fins exhibits a second lift slope that is different from the first lift slope when the vehicle is in tail-first airflow. 26. The space launch vehicle of claim 21, wherein the control system has one or more circuits configured to pivot each of the plurality of fins independently with respect to each other.