Patent Application
20190382112
Aircraft are increasingly utilizing electrically powered devices and motors that increase demands on power storage and generating devices. Increased amounts of electric power can be obtained by increasing the size of power generating devices. However, the peak demands for power generation are often at idle or takeoff conditions. Accordingly, a power generating device sized to meet peak demand requirements may be oversized for most operating conditions including for example aircraft cruise conditions. Additionally, while battery power can be utilized to supplement operation during peak conditions, batteries maintain a fixed weight regardless of the amount of power remaining. Aircraft and engine manufactures continue to seek improvements to aircraft operation to improve performance and propulsive efficiencies.
Aircraft and engine manufactures continue to seek improvements to aircraft operation to improve performance and propulsion efficiencies.
A method of operating an aircraft according to an exemplary embodiment of this disclosure includes among other possible things, communicating power from a storage device within an unmoved aerial vehicle (UAV) to an aircraft; controlling a propulsive device within the UAV with a control system of the aircraft to provide propulsive thrust to the aircraft; and detaching the UAV including the storage device and the propulsion device from the aircraft responsive to the energy within the storage device being below a predefined threshold.
In a further embodiment of the foregoing method of operating an aircraft, the storage device comprises a battery and communicating power comprises communicating electric energy to at least one system of the aircraft from the battery within the UAV.
In a further embodiment of any of the foregoing methods of operating an aircraft, controlling the propulsive device provides a propulsive thrust during takeoff operation of the aircraft.
In a further embodiment of any of the foregoing methods of operating an aircraft, controlling the propulsive device to provide a propulsive thrust until the storage device is below the predefined threshold is included.
In a further embodiment of any of the foregoing methods of operating an aircraft, guiding the UAV to away from the aircraft to a predefined location for retrieval is included.
In a further embodiment of any of the foregoing methods of operating an aircraft, the UAV includes control surfaces and a controller to autonomously guide the UAV away from the aircraft and to the predefined location.
In a further embodiment of any of the foregoing methods of operating an aircraft, guiding the UAV away from the aircraft in a non-powered condition is included.
In a further embodiment of any of the foregoing methods of operating an aircraft, the propulsion device comprises an electric motor driving propeller blades. The electric motor draws power from the storage device.
In a further embodiment of any of the foregoing methods of operating an aircraft, moving the propeller blades to a retracted position when not providing propulsive thrust is included.
In a further embodiment of any of the foregoing methods of operating an aircraft, the propulsion device comprises a gas turbine engine and the UAV includes fuel storage for powering the gas turbine engine.
An unmanned aerial vehicle (UAV) for supplying power to another aircraft, the UAV, according to an exemplary embodiment of this disclosure includes, among other things, a power supply communicating power to an aircraft; a motor generating a propulsive thrust; at least one control surface for controlling a direction of the vehicle independent of the main aircraft; and a controller governing operation of the motor and the control surface, wherein the controller is configured to operate the motor responsive to commands from the aircraft to provide propulsive thrust to the aircraft.
In a further embodiment of the foregoing UAV for supplying power to another aircraft the power supply provides electric power to at least one system of the aircraft.
In another embodiment of any of the foregoing UAV for supplying power to another aircraft, a mount enabling separation of the UAV from the aircraft such that the UAV may be separated from the aircraft in response to the power supply being depleted below a predefined threshold is included.
In another embodiment of any of the foregoing UAV for supplying power to another aircraft, the motor of the UAV provides propulsive thrust to the aircraft during takeoff operations.
In another embodiment of any of the foregoing UAV for supplying power to another aircraft, the motor of the UAV provides propulsive thrust until the power supply is depleted below a predefined threshold.
In another embodiment of any of the foregoing UAV for supplying power to another aircraft, the motor comprises an electric motor driving a propeller.
In another embodiment of any of the foregoing UAV for supplying power to another aircraft, the propellers are movable to a stowed position.
In another embodiment of any of the foregoing UAV for supplying power to another aircraft, hinges are attached to the propellers to enable movement from the stowed position to a deployed position. An end stop limiting outward radial movement about the hinges in the deployed position is included.
In another embodiment of any of the foregoing UAV for supplying power to another aircraft, the motor comprises a gas turbine engine.
Although the different examples have the specific components shown in the illustrations, embodiments of this invention are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another one of the examples.
These and other features disclosed herein can be best understood from the following specification and drawings, the following of which is a brief description.
A battery maintains a constant volume and weight once discharged and no longer capable of providing electric energy. Unlike fuel that is burned to produce power and therefore once used no longer contributes to the load on the aircraft, the battery is a constant load on the aircraft regardless of the level of energy. The example UAV 24 is detachable from the aircraft 10 once the battery 28 is no longer providing energy to the aircraft 10. In this example embodiment, two (2) UAVs 24 are mounted to the aircraft structure 18. In this example, the UAVs 24 are mounted on the wings of the aircraft 10 outboard of the aircraft engines 14. In this disclosed example, the aircraft engines 14 are gas turbine engines. However, the example engines 14 may be of any other type of engine.
The UAVs 24 include the power storage device that in this example is a battery 28. It should be appreciated that the battery 28 may be a single battery or a group of batteries or other power cell configuration that produces an electric output. The battery 28 is coupled through electrical conduits 22 to the aircraft system 12. The aircraft system 12 may be any system that utilizes electric energy including control, environmental control and/or propulsion systems. Moreover, the UAVs 24 may provide electric power that is used prior to power from any additional on board power storage systems schematically indicated at 46.
The disclosed UAVs 24 include a motor 30 that drives propeller blades 26. The motor 30 and propeller blades 26 are controllable by the aircraft controller 16 while coupled to the aircraft 10. The aircraft controller 16 controls operation of the UAV motor 30 to provide additional propulsive thrust for high thrust demand aircraft operation such as during a takeoff operation. The motor 30 of the UAV 24 may also be utilized to assist in aircraft operation to reduce the load on the aircraft engines 14 to conserve onboard energy stores such as fuel. Moreover, the power provided by the UAV battery 28 can be utilized in other situations where use of on board aircraft energy stores is the least efficient such as for example while idling or taxing on the ground.
The example motor 30 is driven by power supplied by the battery 28 of each corresponding UAV 24. Accordingly, the battery 28 provides electric energy to the aircraft 10 and also to power the motor 30 to provide additional propulsive thrust.
Referring to
Once the UAVs 24 are detached from the aircraft 10, they will move away from the aircraft 10 to reduce the load on the aircraft 10. The UAVs 24 may then guide themselves back to a retrieval location schematically shown at 32. At the retrieval location, the UAVs 24 may be recharged for remounting to an aircraft 10.
The UAVs 24 may proceed away from the aircraft 10 in a powered condition using power from the battery 28 to provide power to drive the motor 30. If the motor 30 is driven, the charge level of the battery 28 that triggers detachment of the UAV 24 from the aircraft 10 will account for the power required to propel the UAV 24 back to the retrieval location 32.
In another example embodiment, the UAV 24 may glide to the retrieval location 32 in an unpowered condition. Gliding the UAV 24 back to the retrieval location enables a longer duration of power supplied to the aircraft 10.
Referring to
The blades 38 are connected by way of a hinges 48 to enable movement from the stowed position to the deployed position as shown in
Referring to
Accordingly, the disclosed UAV provides auxiliary battery power to an aircraft to meet increased demands and reduce loads on primary systems during pre-flight, ground idle, takeoff, climb and other high or inefficient power demand conditions while also providing additional propulsive thrust during takeoff that may than be detached from the aircraft and recovered for recharging and reuse.
Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this disclosure. For that reason, the following claims should be studied to determine the scope and content of this disclosure.
