Unmanned aerial vehicle provided with detachable motor arms
The unmanned aerial vehicle (UAV) includes detachable motor arms. In this way, the UAV may be conveniently stored and transported, rapidly assembled in the field, and repaired in the event of a crash. The motor arms are also configured to separate from the fuselage in the event of a crash. An example unmanned aerial vehicle comprises: a fuselage and two motor arms. Each motor arm is detachably secured to the fuselage by two mechanical connectors and comprises a tube having a rotary wing propulsion system on each end and an electrical connector, positioned between the two rotary wing propulsion systems, configured to conductively interface with an electrical connector in an underside of the fuselage. The two mechanical connectors detachably securing each motor arm to the fuselage are configured to facilitate the separation of that motor arm from the fuselage during a crash.
1. An unmanned aerial vehicle comprising:
a fuselage, a first motor arm and a second motor arm detachably secured to the fuselage, each motor arm is detachably secured to the fuselage by two mechanical connectors and comprises a tube having a rotary wing propulsion system on each end and an electrical connector, positioned between the two rotary wing propulsion systems, configured to conductively interface with an electrical connector in an underside of the fuselage, the two mechanical connectors detachably securing each motor arm to the fuselage are configured to facilitate the separation of that motor arm from the fuselage during a crash;
wherein each mechanical connector is a discrete component that comprises two breakaway pegs extending from a first side and a mounting clamp on a bottom end.
2. The unmanned aerial vehicle of claim 1 , wherein the breakaway pegs of each mechanical connector are secured within cooperating sockets located in a side of the fuselage.
3. The unmanned aerial vehicle of claim 1 , wherein the mounting clamp of each mechanical connector is configured to secure about the tube of a motor arm.
4. The unmanned aerial vehicle of claim 3 , wherein the mounting clamp of each mechanical connector comprises two curved branches configured to resiliently deform when secured about the tube of a motor arm.
5. The unmanned aerial vehicle of claim 1 , wherein the electrical connector of each motor arm includes registration sockets configured to receive registration pins extending from the underside of the fuselage.
6. The unmanned aerial vehicle of claim 1 , wherein the electrical connector of each motor arm includes release ramps, positioned about electrical contacts, configured to interface with cooperating release ramps, positioned about electrical contacts, of the cooperating electrical connector in the underside of the fuselage.
7. An unmanned aerial vehicle comprising:
a fuselage, a first motor arm and a second motor arm detachably secured to the fuselage, each motor arm is detachably secured to the fuselage by two mechanical connectors and comprises a tube having a rotary wing propulsion system on each end and an electrical connector, positioned between the two rotary wing propulsion systems, configured to conductively interface with an electrical connector in an underside of the fuselage, the two mechanical connectors detachably securing each motor arm to the fuselage are configured to facilitate the separation of that motor arm from the fuselage during a crash;
wherein each mechanical connector is a discrete component that comprises a body portion having two flexible arms, each flexible arm includes a breakaway peg that extends from a distal end.
8. The unmanned aerial vehicle of claim 7 , wherein the breakaway peg on each flexible arm is secured within a cooperating socket in a side of the fuselage.
9. The unmanned aerial vehicle of claim 8 , wherein at least one breakaway peg of each mechanical connector includes a lip configured to engage with the cooperating socket in the fuselage.
10. The unmanned aerial vehicle of claim 7 , wherein the body portion of each mechanical connector is configured to fit about, and support, the tube of a motor arm.
11. The unmanned aerial vehicle of claim 7 , wherein the electrical connector of each motor arm includes registration sockets configured to receive registration pins extending from the underside of the fuselage.
12. The unmanned aerial vehicle of claim 7 , wherein the electrical connector of each motor arm includes release ramps, positioned about electrical contacts, configured to interface with cooperating release ramps, positioned about electrical contacts, of the cooperating electrical connector in the underside of the fuselage.
13. The unmanned aerial vehicle of claim 7 , wherein each mechanical connector further comprises a leg that extends from the body portion.