초록 ▼

An aircraft, such as a missile, has control surfaces that have segments that are hinged together. The control surfaces deploy from a closed position, for example with the segments folded against a fuselage, so as to allow for launching from a launch tube. Once the aircraft is launched the control su

An aircraft, such as a missile, has control surfaces that have segments that are hinged together. The control surfaces deploy from a closed position, for example with the segments folded against a fuselage, so as to allow for launching from a launch tube. Once the aircraft is launched the control surfaces deploy from the closed position to an open position, with the segments opening up farther from the body or fuselage. In the open position or deployed state the segments may be substantially planar. Locks of the control surfaces may be used to lock the segments in place in the open position. The locks may include hollow sleeves that slide over the control surface segments. The sleeves and the segments may include a protrusions and depressions that engage each other to hold the segments in the open configuration.

대표청구항 ▼

1. An aircraft comprising: a fuselage; anda control surface that deploys from a stowed state in which the control surface is wrapped around the fuselage;wherein the control surface includes: control surface segments that are hingedly coupled together; andlocks to hold the control surface segments in

1. An aircraft comprising: a fuselage; anda control surface that deploys from a stowed state in which the control surface is wrapped around the fuselage;wherein the control surface includes: control surface segments that are hingedly coupled together; andlocks to hold the control surface segments in a deployed state of the control surface; andwherein the locks are hollow sleeves that slide along control surface segments, and that cover hinged couplings between the control surface segments, when the control surface is in the deployed state. 2. The aircraft of claim 1, wherein the control surface is a canard or a wing. 3. The aircraft of claim 1, wherein the control surface is a tail fin. 4. The aircraft of claim 1, wherein the aircraft is a missile. 5. The aircraft of claim 1, wherein the control surface segments have depressions therein that receive inward-protruding parts of the locks, to secure the locks from sliding relative to the control surface segments, when the control surface is in the deployed state. 6. The aircraft of claim 5, wherein the inward-protruding parts include spring fingers. 7. The aircraft of claim 6, wherein the spring fingers have free ends that point toward the fuselage. 8. The aircraft of claim 6, wherein the spring fingers have free ends that point away the fuselage. 9. The aircraft of claim 1, wherein the control surface segments consist of three control surface segments. 10. The aircraft of claim 1, wherein the control surface is substantially planar when in the deployed state. 11. An aircraft comprising: a fuselage; anda control surface that deploys from a stowed state in which the control surface is wrapped around the fuselage;wherein the control surface includes: control surface segments that are hingedly coupled together; andlocks to hold the control surface segments in a deployed state of the control surface; andwherein the control surface segments each have a smaller chord at a proximal end closest to the fuselage, than at a distal end distal from the fuselage. 12. The aircraft of claim 11, wherein the control surface segments have a substantially parallelogram shape. 13. The aircraft of claim 11, wherein the locks are sleeves have non-uniform width that corresponds to chord variations in the control surface. 14. The aircraft of claim 13, wherein the sleeves make an interference fit with the control surface segments to prevent bending at the hinged couplings between the control surface segments, when the control surface is in the deployed state. 15. The aircraft of claim 1, wherein the locks each include a lock mechanism that secures the locks relative to the control surface segments, to hold the control surface segments in the deployed state. 16. The aircraft of claim 15, wherein the lock mechanism includes protrusion on one of the locks or the control surface segments, that engages a recess on the other of the locks or the control surface segments. 17. The aircraft of claim 1, wherein the control surface is in a recess in the fuselage when in the stowed state. 18. A method of aircraft flight, the method comprising: launching an aircraft from a launcher, with control surfaces of the aircraft in a stowed state, along a fuselage of the aircraft;spinning the aircraft during and/or after the launching; andafter the launching, deploying the control surfaces, wherein the deploying includes:control surface segments of each of the control surfaces opening up to deployed state by pivoting on hinged connections between the segments of each control surface, and/or by pivoting on hinged connections between the control surfaces and the fuselage; and sliding locks of the control surfaces in place over the hinged connections between the segments, to maintain the control surfaces in the deployed state. 19. The method of claim 18, wherein the sliding the locks includes sliding sleeves that enclose the control surface segments.