Aerial vehicle with deployable components
An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one precondition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one precondition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one precondition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.
1. A method of deploying an unmanned aerial vehicle (UAV), the method comprising:
detecting at least one precondition of the UAV in a compact arrangement;
activating a gearbox connected to at least one wing upon the detection of the at least one precondition;
transitioning the at least one wing to from the compact arrangement to a deployed configuration using the gearbox; and
attaining a stable flight condition in the deployed configuration.
2. The method of claim 1 , wherein the at least one precondition comprises at least one of the following: velocity, acceleration, and leveling.
3. The method of claim 1 , further comprising adjusting a wing sweep angle with a transition of the at least one wing.
4. The method of claim 1 , further comprising expanding a length of the at least one wing upon after attaining the stable flight condition.
5. The method of claim 1 , further comprising deploying at least one additional component of the UAV after detection of the precondition.
6. The method of claim 5 , wherein the deployed at least one additional component is a telescoping boom.
7. The method of claim 6 , further comprising deploying an antenna associated with the telescoping boom.
8. The method of claim 5 , wherein deploying the at least one additional component further comprises deploying at least one stabilizer.
9. The method of claim 1 , further comprising detecting a launch.
10. The method of claim 9 , wherein detecting the launch comprises detecting the launch from at least one of: an aircraft and a tube-integrated system.
11. The method of claim 1 , further comprising maintaining roll control during the deployment of the at least one wing.
12. The method of claim 1 , wherein detecting the at least one precondition comprises detecting the at least one precondition associated with a distance travelled.
13. The method of claim 1 , further comprising adjusting a wingspan of the at least one wing in the deployed configuration.
14. The method of claim 13 , further comprising:
completing a mission; and
terminating the mission.
15. The method of claim 13 , further comprising activating a belt system for the adjustment of the wingspan.
16. The method of claim 13 , wherein adjusting the wingspan of the UAV further comprises at least one of the following: extending and retracting an outer section of the at least one wing and exposing an inner section of the at least one wing.
17. The method of claim 14 , further comprising detecting at least one additional precondition.
18. The method of claim 14 , further comprising actuating at least one control surface on the at least one wing.
19. The method of claim 18 , wherein attaining the stable flight condition comprises actuating at least one stabilizer of the UAV.
20. The method of claim 19 , further comprising operating the UAV with an on-board flight controller.