Modular and dynamically reconfigurable flying systems encompassing flying vehicle modules
A flying surface may comprise a plurality of interconnectable flying vehicles configured for mid-flight reconfiguration of the flying surface. Each flying vehicle may be entirely self-sufficient, including an onboard thrust unit, an onboard controller, an onboard power unit, and connectors configured to engage corresponding connectors of other flying vehicles to form a flying surface. The flying vehicles may additionally be configured for self-control, thereby enabling a distributed control model for a flying surface that does not require significant, centralized processing power and corresponding power storage. The flying surfaces may dynamically reconfigure mid-flight by attaching or detaching flying vehicles so as to enable a wide variety of in-flight maneuvers.
1. A flying vehicle comprising:
a frame defining one or more sidewalls, wherein the frame has an open upper end and an open lower end;
a thrust unit secured within the frame and configured to provide lift for the flying vehicle;
a power unit in connection with the thrust unit;
a controller configured to transmit control signals to the thrust unit; and
a plurality of connectors positioned around an exterior surface of the frame, wherein the connectors are configured to engage external connectors of at least one adjacent flying vehicle, wherein the one or more connectors are configured to form a dynamically adjustable joint when engaged with external connectors of at least one adjacent flying vehicle, wherein the dynamically adjustable joint has a dynamically controllable rigidity adapted to be dynamically changed during flight so that the dynamically controllable rigidity has a first rigidity value during a first time interval while the flying vehicle is in flight and a second rigidity value during a second time interval while the flying vehicle is in flight, wherein said first value is different from said second value.
2. The flying vehicle of claim 1 , further comprising a communication module configured to transmit status data to one or more additional flying vehicles.
3. The flying vehicle of claim 1 , wherein the communication module is configured for wireless data transmission.
4. The flying vehicle of claim 1 , wherein the controller is further configured to receive a master control signal from one of an additional flying vehicle prior to transmitting control signals to the thrust module.
5. The flying vehicle of claim 4 , wherein the controller is configured to generate a control signal based at least in part on a distributed control configuration for a plurality of flying vehicles.
6. The flying vehicle of claim 1 , wherein the controller is further configured to:
generate master control signals for one or more additional flying vehicles; and
transmit the master control signals to the one or more additional flying vehicles.
7. The flying vehicle of claim 1 , further comprising an onboard power unit.
8. The flying vehicle of claim 1 , wherein the flying vehicle comprises a power receiver configured to receive wireless power transmission from a power generation unit.
9. The flying vehicle of claim 8 , wherein the power receiver is embodied as one or more antennae positioned within the thrust unit.
10. The flying vehicle of claim 1 , wherein each of the plurality of connectors are hermaphrodite connectors.
11. The flying vehicle of claim 1 , wherein the one or more connectors are configured to form an adjustable joint when engaged with external connectors of at least one adjacent flying vehicle, wherein the adjustable joint is configurable between a rigid configuration and a flexible configuration.
12. The flying vehicle of claim 1 , wherein the thrust unit comprises an electric motor and propeller.
13. The flying vehicle of claim 1 , further comprising one or more proximity sensors positioned on the frame, wherein the one or more proximity sensors are configured to detect an adjacent flying vehicle.
14. The flying vehicle of claim 1 , wherein the thrust unit is reversible to selectably provide thrust in one of two opposing directions.
15. The flying vehicle of claim 1 , further comprising one or more control surfaces configured to provide attitude adjustment to the flying vehicle.