Rotary ejection system

Abstract

This disclosure provides a payload deployment system that operates to receive and hold a configurable payload. The payload deployment mechanism helps reduce the drag on the payload and protect the payload from environmental factors. The payload may be released using a hinge mechanism to ensure that the payload does not come into contact with the payload deployment mechanism when the payload is deployed. Vents can be used to equalize the pressure between the external environment and the main body of the payload deployment mechanism. The vents can generate additional forces that help separate the payload from the launcher.

Claims

1. A payload deployment mechanism, The main body and The bay area partially defined by the main body portion, A configurable payload that is operable to be detachably connected to the main body portion of the payload deployment mechanism, A force generation mechanism attached to the payload deployment mechanism, wherein the force generation mechanism is configured to apply force to the configurable payload in order to separate the configurable payload from the payload deployment mechanism, A payload deployment mechanism comprising: a hinge mechanism configured to control the separation of the configurable payload from the payload deployment mechanism, wherein the hinge mechanism is configured to pivot about a pivot point located outside the payload deployment mechanism.

2. The payload deployment mechanism according to claim 1, wherein the payload deployment mechanism is configured to hold the configurable payload by at least one latch assembly comprising at least one biasing mechanism.

3. The payload deployment mechanism according to claim 1, wherein the configurable payload is molded to generate drag and create an additional force to detach the configurable payload from the payload deployment mechanism when it is separated from the payload deployment mechanism.

4. The payload deployment mechanism according to claim 3, wherein the configurable payload includes at least one of the leading edge or side of the configurable payload configured to generate drag.

5. The payload deployment mechanism according to claim 3, wherein the configurable payload is integrated into the payload deployment mechanism without affecting the aerodynamics of the payload deployment mechanism while attached to the payload deployment mechanism.

6. The payload deployment mechanism according to claim 3, wherein the drag generated from the configurable payload causes the configurable payload to separate from the payload deployment mechanism.

7. The payload deployment mechanism according to claim 1, further comprising at least one vent configured to direct an external airflow into the payload deployment mechanism.

8. The payload deployment mechanism according to claim 7, wherein the at least one vent directs the external airflow into the payload deployment mechanism so as to equalize the air and external air pressure when the configurable payload separates from the payload deployment mechanism.

9. The payload deployment mechanism according to claim 1, wherein the hinge mechanism comprises a first hinge component and a second hinge component.

10. The payload deployment mechanism according to claim 9, wherein the first hinge component on the payload deployment mechanism and the second hinge component on the configurable payload are separated to deploy the configurable payload.

11. The payload deployment mechanism according to claim 1, wherein the hinge mechanism is located at the rear end of the configurable payload.

12. The payload deployment mechanism according to claim 1, further comprising a parachute attached to the configurable payload.

13. The payload deployment mechanism according to claim 12, wherein the parachute is disposed within the payload deployment mechanism before deployment.

14. The payload deployment mechanism according to claim 12, wherein the parachute is configured to deploy as a result of the separation of the configurable payload from the payload deployment mechanism.

15. The payload deployment mechanism according to claim 12, wherein the parachute is a stationary line parachute.

16. The payload deployment mechanism according to claim 1, wherein the hinge mechanism is configured to prevent the configurable payload from coming into contact with the payload deployment mechanism after the configurable payload has been separated from the payload deployment mechanism.

17. The payload deployment mechanism according to claim 1, wherein the payload deployment mechanism is incorporated into an aerial transport means.

18. The payload deployment mechanism according to claim 1, wherein the payload deployment mechanism is configured to be connected to the aircraft by a coupling assembly positioned between the payload deployment mechanism and a part of the aircraft.

19. The payload deployment mechanism according to claim 1, wherein the bay region is partially defined by a cavity within the payload deployment mechanism.

20. The configurable payload is drones, Sensors, buoy, munitions, Unmanned aerial transport means, or The payload deployment mechanism according to claim 1, comprising one or more objects suitable for deployment from within the payload deployment mechanism.

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