초록 ▼

A man-portable unmanned aerial system launcher (UAS) launcher includes a rail assembly having an internal track and a carriage assembly having a base configured to translate within the internal track. The carriage assembly also includes a cradle configured to support a UAS and a bracket configured t

A man-portable unmanned aerial system launcher (UAS) launcher includes a rail assembly having an internal track and a carriage assembly having a base configured to translate within the internal track. The carriage assembly also includes a cradle configured to support a UAS and a bracket configured to support the cradle above the base. The UAS launcher includes a launch control system configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal. The UAS launcher also includes one or more elastic members configured to engage the carriage assembly and the rail assembly. Once the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members. Release of the carriage assembly enables force generated by strain of the elastic members to propel the carriage assembly toward a launch position.

대표청구항 ▼

1. An unmanned aerial system (UAS) launcher, comprising: a rail assembly extending from a first end to a second end and including one or more launch rails, wherein the rail assembly includes an internal track;a carriage assembly including: a base configured to translate within the internal track of

1. An unmanned aerial system (UAS) launcher, comprising: a rail assembly extending from a first end to a second end and including one or more launch rails, wherein the rail assembly includes an internal track;a carriage assembly including: a base configured to translate within the internal track of the rail assembly between a launch-ready position adjacent the first end of the rail assembly and a launch position adjacent the second end of the rail assembly;a cradle configured to support a UAS; anda bracket configured to support the cradle above the base;a launch control system secured to the rail assembly and configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal directing the launch control system to release the carriage assembly; andone or more elastic members having a first end to-configured to engage the carriage assembly and a second end configured to engage the rail assembly, wherein after the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members, and wherein the release of the carriage assembly by the launch control system enables force generated by strain of the one or more elastic members to propel the carriage assembly toward the launch position,wherein the UAS launcher has a first configuration wherein the carriage assembly is translated to the launch-ready position and the one or more elastic members are uncoupled from the carriage assembly, and a second configuration wherein the one or more elastic members are coupled to engage the carriage assembly and the rail assembly when the carriage assembly is secured in the launch-ready position. 2. The UAS launcher of claim 1, wherein the rail assembly, the carriage assembly, the launch control system, and the one or more elastic members comprise a man-portable device weighing not more than 25 pounds (11.4 kilograms). 3. The UAS launcher of claim 1, wherein the rail assembly includes two or more launch rails, and wherein the two or more launch rails are joined by a clamp configured to engage external surfaces of the two or more launch rails. 4. The UAS launcher of claim 1, wherein each of the one or more launch rails includes a section of an extruded material. 5. The UAS launcher of claim 1, wherein the rail assembly is generally enclosed on a bottom side and on first and second lateral sides extending from the bottom side, and is partially enclosed on a top side, wherein the top side defines a slot configured to permit the bracket to extend therethrough between the base and the cradle of the carriage assembly as the assembly translates within the internal track. 6. The UAS launcher of claim 5, wherein the plurality of rolling members include lower-facing rolling members configured to rotatably engage a first internal face of the bottom side of the rail assembly and side-facing rolling members configured to rotatably engage second internal faces of lateral sides of the rail assembly as the carriage assembly translates within the internal track of the rail assembly. 7. The UAS launcher of claim 6, further comprising upper-facing rolling members configured to rotatably engage a third internal face of the top side of the rail assembly as the carriage assembly translates within the internal track of the rail assembly. 8. The UAS launcher of claim 1, wherein the rail assembly includes at least one first stop adjacent the first end of the rail assembly and at least second stop adjacent the second end of the rail assembly to restrict movement of the carriage assembly between the launch-ready position and the launch position within the internal track. 9. The UAS launcher of claim 8, further comprising a first shock absorber configured to decelerate the carriage assembly as the carriage assembly reaches the launch-ready position. 10. The UAS launcher of claim 8, further comprising a second shock absorber configured to decelerate the carriage assembly as the carriage assembly reaches the launch position. 11. The UAS launcher of claim 1, wherein the base of the carriage assembly includes a plurality of rolling members configured to rotatably engage the internal track of the rail assembly in orthogonal directions. 12. The UAS launcher of claim 1, wherein the launch control system includes a carriage release mechanism configured to release the carriage assembly in response to receiving the launch signal. 13. The UAS launcher of claim 12, wherein the launch control system is configured to receive the launch signal in the form of a mechanical signal presented by application of a mechanical force. 14. The UAS launcher of claim 12, wherein the carriage release mechanism includes an electromechanical release mechanism and the launch signal includes an electrical launch signal. 15. The UAS launcher of claim 14, wherein the electromechanical release mechanism includes a solenoid. 16. The UAS launcher of claim 14, wherein the electromechanical release mechanism is configured to receive the electrical launch signal via a wired connection. 17. The UAS launcher of claim 16, wherein the wired connection includes an Ethernet connection configured to receive the electrical launch signal via an Ethernet. 18. The UAS launcher of claim 14, wherein the electromechanical release mechanism is configured to receive the electrical launch signal via a wireless connection. 19. The UAS launcher of claim 18, wherein the wireless connection includes an Internet-Protocol enabled receiver configured to receive the electrical launch signal via a wireless Internet connection. 20. The UAS launcher of claim 12, further comprising one or more safety mechanisms configured to prevent an unintended launch. 21. The UAS launcher of claim 20, wherein the one or more safety mechanisms includes a launch rail safety pin configured to be received into at least one of the rail assemblies such that the launch rail safety pin blocks the carriage assembly from translating relative to the rail assembly when the carriage release mechanism releases the carriage assembly until the launch rail safety pin is removed from the at least one of the rail assemblies. 22. The UAS launcher of claim 20, wherein the one or more safety mechanisms includes a carriage release safety mechanism that includes a carriage release safety pin configured to be received into the carriage release assembly to prevent the carriage release assembly from releasing the carriage assembly in response to receiving the launch signal until the carriage release safety pin is removed from the carriage assembly. 23. The UAS launcher of claim 1, wherein the carriage assembly includes at least one first bracket configured to engage the first end of the one or more elastic members and the rail assembly includes at least one second bracket adjacent the second end of the rail system to engage the second end of the one or more elastic members. 24. The UAS launcher of claim 1, further comprising a vertical support assembly configured to be coupled to the rail assembly adjacent to the second end of the rail assembly, wherein the vertical support assembly is configured to support the second end of the rail assembly at a height above a surface. 25. The UAS launcher of claim 24, wherein the vertical support assembly includes one or more struts configured to engage an external surface of the rail assembly. 26. The UAS launcher of claim 24, wherein the one or more struts are rotatably mounted to the external surface of the rail assembly, enabling the one more struts to be rotated between a stowed position and a deployed position. 27. The UAS launcher of claim 24, wherein the vertical support assembly is configured to be adjusted to enable adjustment of the height at which the vertical support assembly supports the second end of the rail assembly above the surface. 28. The UAS launcher of claim 1, further comprising an anchor assembly configured to be coupled to the rail assembly adjacent to the first end of the rail assembly. 29. The UAS launcher of claim 28, wherein the anchor assembly is configured to receive an anchor to secure the rail assembly to a surface. 30. The UAS launcher of claim 1, further comprising a rotatable mounting system including: a mount configured to engage a surface; anda coupling secured to the mount and configured to rotatably engage the rail assembly, wherein the rail assembly may be rotated relative to the surface. 31. The UAS launcher of claim 30, wherein the mount includes a tripod. 32. The UAS launcher of claim 30, wherein the rotatable mounting system further comprises a wind vane configured to be secured to the rail assembly adjacent to the first end, wherein the wind vane is configured to be driven downwind by a prevailing wind and to cause the first end of the rail assembly to face in a downwind direction thereby causing the second end of the rail assembly to face in an upwind direction, wherein the second end of the rail assembly automatically rotates to face the second end of the rail assembly into the prevailing wind. 33. The UAS launcher of claim 30, wherein the rotatable mounting system comprises a second man-portable device weighing not more than 25 pounds (11.4 kilograms). 34. The UAS launcher of claim 1, further comprising a UAS control system configured to selectively activate one or more systems of the UAS. 35. The UAS launcher of claim 34, wherein the start control system and the launch control system are configured to be activated by a common control device. 36. An unmanned aerial system (UAS) launcher, comprising: a rail assembly extending from a first end to a second end and including one or more launch rails;a carriage assembly configured to support a UAS and to translate the UAS along the rail assembly between a launch-ready position adjacent the first end of the rail assembly and a launch position adjacent the second end of the rail assembly;one or more elastic members having a first end to-configured to engage the carriage assembly and a second end configured to engage the rail assembly, wherein once the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members;a launch control system secured to the rail assembly and configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal directing the launch control system to release the carriage assembly, and wherein the release of the carriage assembly by the launch control system enables force generated by strain of the one or more elastic members to propel the carriage assembly toward the launch position; anda rotatable mounting system including:a mount configured to engage a surface;a coupling secured to the mount and configured to rotatably engage the rail assembly, wherein the rail assembly may be rotated relative to the surface; anda wind vane configured to be secured to the rail assembly adjacent to the first end, wherein the wind vane is configured to be driven downwind by a prevailing wind and to cause the first end of the rail assembly to face in a downwind direction thereby causing the second end of the rail assembly to face in an upwind direction,wherein the rail assembly automatically rotates to face the second end of the rail assembly into the prevailing wind. 37. The UAS launcher of claim 36, wherein the carriage assembly is configured to be translated to the launch-ready position before the one or more elastic members are coupled to engage the carriage assembly and the rail assembly, and wherein the one or more elastic members are coupled to engage the carriage assembly and the rail assembly after the carriage assembly is secured in the launch-ready position. 38. The UAS launcher of claim 36, wherein the mount includes a tripod. 39. The UAS launcher of claim 36, wherein the UAS launcher is a man-portable device weighing not more than 50 pounds (22.7 kilograms). 40. The UAS launcher of claim 36, wherein the rail assembly includes an internal track configured to enable a portion of the carriage assembly to translate within the internal track. 41. The UAS launcher of claim 36, wherein the launch control system includes an electromechanical release mechanism configured to receive the launch signal as an electrical signal. 42. The UAS launcher of claim 41, wherein the electromechanical release mechanism is configured to receive the electrical signal from at least one of a wired connection and a wireless connection.