Rotating release launching system
The present disclosure provides rolling release launching system that is operative to receive and retain a drone or other payload in a protected launcher. The launcher helps to reduce the drag of the payload and to protect the payload from environmental factors. The payload is launched when a rotating door opens to expose the payload in a bay area. The rotating door may be parallel or concentric to a longitudinal axis of the body portion of the device. The payload may be launched using a biasing and fastening mechanism, which may include detachably coupling bracket, to induce an angular moment and releasing force on the payload during launch.
1. A configurable payload deployment system, the system comprising:
a launcher comprising a detachable coupling mechanism configured to:
retain a configurable payload in a first orientation, and
release the configurable payload at a second orientation; and
a rotating door enclosing an interior of the launcher, the rotating door operative to rotate between a closed arrangement and an open arrangement, the rotating door configured to:
secure at least a portion of the interior of the launcher in the closed arrangement,
generate angular momentum as the rotating door transitions from the closed arrangement to the open arrangement,
transfer, via the detachable coupling mechanism, the generated angular momentum as the rotating door rotates to the open arrangement, and
expose the portion of the interior of the launcher in the open arrangement.
2. The system of claim 1 , wherein the rotating door is configured to enable a rolling release of the configurable payload at least in part by a transfer of the generated angular momentum.
3. The system of claim 1 , wherein the configurable payload performs a rolling release from the launcher to prevent at least one expandable component of the configurable payload from contacting the launcher, and wherein the door returns to the closed arrangement after the release of the configurable payload.
4. The system of claim 1 , wherein the launcher further comprises a nose cone disposed at a forward end of the launcher to reduce drag of the system.
5. The system of claim 3 , wherein the expandable components of the configurable payload comprises at least one wing section.
6. The system of claim 3 , wherein the expandable components of the configurable payload comprise at least one stabilizer.
7. The system of claim 2 , wherein payload is exposed to an external environment as the rotating door transitions from the closed arrangement to the open arrangement.
8. The system of claim 2 , wherein the closed arrangement of the rotating door prevents exposure of the configurable payload to an external environment.
9. The system of claim 1 , wherein the rotating door is controlled by a drive mechanism on the launcher.
10. The system of claim 9 , wherein the mechanism assists the rotating door portion generating the angular momentum.
11. The system of claim 3 , wherein the rotation of the door from the closed arrangement to the open arrangement does not interfere with the rolling release of the payload.
12. The system of claim 3 , wherein the rotating door is configured to return to the closed arrangement after the release the configurable payload.
13. The system of claim 2 , wherein the angular momentum applied to the configurable payload corresponds to an axis of rotation of the rotating door as the door transitions from the closed arrangement to the open arrangement.
14. The system of claim 1 , wherein the rotating door is configured to rotate about a longitudinal axis of the launcher.
15. The system of claim 3 , wherein the configurable payload comprises one or more of:
a drone,
a sensor,
a buoy,
a munition,
a device, or
an object suitable for deployment from within the launcher.
16. The system of claim 1 , wherein the configurable payload detachably connects to the rotating door via the detachable coupling mechanism.
17. The system of claim 1 , wherein the detachable coupling mechanism biases.
18. The system of claim 1 , wherein the detachable coupling mechanism biases the configurable payload in a desirable alignment upon release.
19. The system of claim 1 , wherein the detachable coupling mechanism positions the configurable payload to be in the first orientation within the launcher when the rotating door is in the closed arrangement and in the second orientation within is in the open arrangement.
20. The system of claim 16 , wherein the detachable connection applies an opposing force equal to a gravitational force acting on the configurable payload when the rotating door is in the closed arrangement to secure the payload in the launcher.