Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods
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.
1. An airborne vehicle comprising:
a first end portion;
a second end portion;
one or more aerodynamic control surfaces, wherein the aerodynamic control surfaces are configured to facilitate aerodynamic control of the vehicle when the vehicle is flying in a first orientation in which the first end portion leads the second end portion, and when the vehicle is flying in a second orientation in which the second end portion leads the first end portion, wherein each of the aerodynamic control surfaces has a low or non-swept forward edge and a highly-swept aft edge when the vehicle is in the first orientation, wherein the forward edge extends from a root portion of the control surface to a tip portion of the control surface and has a sweep angle of from about 85 degrees to about 90 degrees, and wherein the aft edge extends from the root portion to the tip portion and has a sweep angle of from about 15 degrees to about 40 degrees; and
one or more rocket engine exhaust nozzles positioned toward the second end portion, wherein the forward edge portions of the bidirectional control surfaces face generally away from the second end portion and the aft 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 back and forth about a corresponding pivot axis, and wherein the pivot axis is positioned between a maximum thickness of the root portion and the first edge portion.
2. The airborne vehicle of claim 1 wherein the airborne vehicle is a rocket.
3. The airborne vehicle of claim 1 wherein the airborne vehicle is a rocket and wherein the one or more aerodynamic control surfaces are positioned toward the second end portion of the rocket.
4. The airborne vehicle of claim 1 wherein the airborne vehicle is a rocket and wherein the one or more aerodynamic control surfaces are movably positioned toward the second end portion of the rocket.
5. A rocket for transporting at least one of humans and cargo into space, the rocket comprising:
a first end portion;
a second end portion;
a deployable aerodynamic surface positioned toward the first end portion;
a plurality of bidirectional control surfaces, wherein each of the bidirectional control surface 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, and
a second edge portion extending between the root portion and the tip portion, wherein the first edge portion leads the second edge portion when the rocket is flying in a first orientation in which the first end portion leads the second end portion and the deployable aerodynamic surface is stowed, and wherein the second edge portion leads the first edge portion when the rocket is flying in a second orientation in which the second end portion leads the first end portion and the deployable aerodynamic surface is deployed; and
one or more engine 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 back and forth about a corresponding pivot axis, and wherein the pivot axis is positioned between a maximum thickness of the root portion and the first edge portion.
6. The rocket of claim 5 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.
7. The rocket of claim 5 wherein the bidirectional control surfaces are positioned closer to the second end portion than the first end portion, and wherein the one or more engine exhaust nozzles are positioned proximate the second end portion.
8. The rocket of claim 5 , wherein the bidirectional control surfaces are configured to pivot back and forth about individual pivot axes to aerodynamically control the rocket when the rocket is flying in the first orientation and when the rocket is flying in the second orientation.
9. The rocket of claim 5 , wherein each of the bidirectional control surfaces has a symmetrical diamond-shaped cross-section.
10. The rocket of claim 5 , 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.
11. The rocket of claim 5 , further comprising:
a payload module positioned toward the first end portion; and
a booster module positioned toward the second end portion, wherein the plurality of bidirectional control surfaces are attached to the booster module.
12. The rocket of claim 5 wherein the bidirectional control surfaces are positioned closer to the second end portion than the first end portion.