Airframe
Disclosed here are unmanned aerial vehicle embodiments including some embodiments having a fuselage, tail, and wings including example embodiments with an adaptable payload section, alternatively or additionally, modular flight surfaces including tail, wings and motor, alternatively or additionally the vehicle configured for short landings with reversible thrust, alternatively or additionally, the unmanned aerial vehicle configured with direct connection to moveable flight control surfaces.
1. An unmanned aerial vehicle, comprising:
a fuselage;
a rigid frame yoke member extending transversely within the fuselage and having first and second distal ends, a top portion, front portion, aft portion, and bottom portion;
a tail member receptacle affixed to the aft portion of the transverse rigid frame yoke member;
a first wing rib attached to the first distal end, and a second wing rib attached to the second distal end, wherein the first and second wing rib each include a wing attachment assembly; and
a payload assembly, attached to the front portion of the transverse rigid frame yoke member, the payload assembly having a pair of U-shaped structures spaced along a width of the unmanned aerial vehicle and including a payload receptacle mounted in the payload assembly.
2. The unmanned aerial vehicle of claim 1 , wherein each wing attachment assembly comprises a sliding assembly.
3. The unmanned aerial vehicle of claim 1 , wherein each wing attachment assembly includes a quick connect assembly to mount free wing attachments.
4. The unmanned aerial vehicle of claim 1 , further comprising:
a first wing attachment detachably connected to the first distal end; and
a second wing attachment detachably connected to the second distal end.
5. The unmanned aerial vehicle of claim 1 , wherein the U-shaped payload structures, mounted to the transverse rigid frame yoke member, includes a motor mount for a detachable electric motor.
6. The unmanned aerial vehicle of claim 1 , wherein the payload assembly includes a cargo supporting bracket that spans a width of the payload assembly.
7. The unmanned aerial vehicle of claim 1 , further comprises a removable battery pack, removably affixed to the payload assembly.
8. The unmanned aerial vehicle of claim 1 , wherein the tail member receptacle is detachably connected to a tail boom assembly.
9. The unmanned aerial vehicle of claim 8 , the tail boom assembly comprising:
two fixed flight surfaces connected by a fulcrum, and two movable flight control surfaces mounted on the two fixed flight surfaces;
at least two servo motors mounted in the fulcrum and each attached to a paddle; and
wherein the paddle is directly mounted to the movable flight control surfaces.
10. The unmanned aerial vehicle of claim 8 , wherein the tail member receptacle detachable connection comprises a snap assembly.
11. The unmanned aerial vehicle of claim 8 , wherein the tail member receptacle includes a magnetic connector, configured to magnetically attach to the tail boom assembly.
12. The unmanned aerial vehicle of claim 8 , wherein the tail member receptacle includes two holes, configured to mate with two resilient tabs on the tail boom.
13. The unmanned aerial vehicle of claim 1 , further comprising:
a motor mount assembly affixed to a front of the payload assembly; and
an electric motor detachably fixed to the motor mount assembly, wherein the electric motor includes a propeller assembly.
14. The unmanned aerial vehicle of claim 13 , wherein the detachable electric motor is detachably attached to the motor mount assembly by a snap connector.
15. The unmanned aerial vehicle of claim 13 , further comprising:
an onboard computer with a processor and a memory attached to the transverse rigid frame yoke member, the computer in communication with the electric motor;
a radio antenna affixed to the transverse rigid frame yoke member, the radio antenna in communication with the onboard computer configured to receive instruction from a wireless control station; and
wherein the electric motor is configured to spin in two rotational directions, and wherein the onboard computer is configured to command the electric motor to reverse spin after receiving data from the wireless controller station via the radio antenna.