Systems and methods to launch aircraft

Systems and methods to launch an aircraft are disclosed. In one embodiment, a system to launch an aircraft comprises a launch arm comprising at least one load cell, an aircraft coupled to the launch arm, and a release mechanism in communication with the at least one load cell, wherein the release mechanism releases the aircraft when the at least one load cell indicates that a load on the launch arm is below a predetermined threshold. Other embodiments may be described.

BACKGROUND

The subject matter described herein relates to systems and methods to launch aircraft.

Aircraft, particularly smaller autonomous and semi-autonomous aircraft such as surveillance drones, blimps, and quad rotors, may be launched from ground-based launch platforms. Weather conditions and wind may complicate launch operations for such aircraft.

SUMMARY

In one embodiment, a system to launch an aircraft comprises a launch arm comprising at least one load cell, an aircraft coupled to the launch arm, and a release mechanism in communication with the at least one load cell, wherein the release mechanism releases the aircraft when the at least one load cell indicates that a load on the launch arm is below a predetermined threshold.

In another embodiment, an aircraft comprises a fuselage, a thrust generator, one or more control surfaces, a flight control system, wherein the flight control system receives feedback from at least one load cell on a launch arm and adjusts the thrust generator and the one or more control surfaces on the aircraft and a release mechanism to release the aircraft from the launch arm when a load measured by the at least one load cell on the launch arm falls below a predetermined threshold.

In another embodiment, a method to launch an aircraft comprises coupling an aircraft to a launch arm comprising at least one load cell, pivoting the launch arm between a first position in which the launch arm is stowed and a second position in which the launch arm is deployed, adjusting a thrust generator and one or more control surfaces on the aircraft; and releasing the aircraft from the launch arm when the at least one load cell indicates that a load on the launch arm is below a predetermined minimum.

DETAILED DESCRIPTION

Systems and methods to launch an aircraft are described herein. Specific details of certain embodiments are set forth in the following description and the associated figures to provide a thorough understanding of such embodiments. One skilled in the art will understand, however, that alternate embodiments may be practiced without several of the details described in the following description.

The invention may be described herein in terms of functional and/or logical block components and various processing steps. For the sake of brevity, conventional techniques related to data transmission, signaling, network control, and other functional aspects of the systems (and the individual operating components of the systems) may not be described in detail herein. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent example functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical embodiment.

The following description may refer to components or features being “connected” or “coupled” or “bonded” together. As used herein, unless expressly stated otherwise, “connected” means that one component/feature is in direct physical contact with another component/feature. Likewise, unless expressly stated otherwise, “coupled” or “bonded” means that one component/feature is directly or indirectly joined to (or directly or indirectly communicates with) another component/feature, and not necessarily directly physically connected. Thus, although the figures may depict example arrangements of elements, additional intervening elements, devices, features, or components may be present in an actual embodiment.

FIG. 1is a schematic illustration of system to launch an aircraft, according to embodiments. Referring first toFIG. 1, in some embodiments a system100comprises a launch arm110coupled to an aircraft130. Launch arm110comprises at least one load cell120capable of measuring a load on the launch arm110. In some embodiments the load cell120generates load data in three dimensions, as indicated by the (x,y,z) axis depicted inFIG. 1.

In some embodiments aircraft130may comprise a thrust generator132, e.g., a propeller or other engine, and one or more control surfaces134to generate a thrust vector for the aircraft. Aircraft130may further comprise a release mechanism136to release the aircraft130from the launch arm110.

In some embodiments aircraft130comprises an onboard flight control system140, which in turn may comprise one or more processor(s)142, and an input/output interface144. The onboard flight control system140may be communicatively coupled to a remote flight control system160via a suitable communication link. Remote flight control system may comprise an I/O interface162, one or more processors164and a display or other input/output mechanism166.

By way of example, in some embodiments aircraft130may be embodied as a blimp, an airplane, a quad rotor device, an unmanned aerial vehicle, or other aerial vehicle which may be controlled via the remote flight control system160operated automatically or by an operator interfacing with a display or other input/output mechanism166.

In some embodiments components of the system100cooperate to implement a method to launch the aircraft only when conditions are safe for a launch.FIG. 2is a flowchart illustrating operations in a method launch an aircraft, according to embodiments, whileFIGS. 3A-3Eillustrate the system in various stages of operation.

Referring toFIG. 2, at operation210an aircraft is coupled to the launch arm. Referring toFIG. 3A, in some embodiments the launch arm110and the aircraft130may be coupled to a mobile vehicle such as a trailer105. When the aircraft is not in use the launch arm110and the aircraft may be stowed in the trailer105(FIG. 3B).

At operation215the launch arm110may be pivoted using rotatable101from a first position in which the launch arm is stowed, as depicted inFIG. 3A, to a second position in which the launch arm is deployed, as depicted inFIG. 3C. In some embodiments the launch arm110may comprise a head112which rotates and/or gimbals with respect to the launch arm110to allow the aircraft to rotate and to pitch or yaw on the launch arm110(FIG. 3D).

At operation220the load cell120is monitored to assess the load on the launch arm110. By way of example, in some embodiments the onboard flight control system140receives load data from the load cell120. In embodiments in which the aircraft130operates autonomously the one or more processor(s)142may evaluate the data on the aircraft130to determine a load on the launch arm110. By contrast, in embodiments in which the aircraft130is controlled remotely the load data may be transmitted from the onboard flight control system140to a remote flight control system160. The load data may be evaluated automatically by the processor(s)164or may be presented on a display or other input/output mechanism166, e.g. a user interface, for evaluation by an operator.

At operation225the thrust generator132and one or more control surfaces134of the aircraft130may be adjusted to adjust the thrust vector of the aircraft. By way of example, in some embodiments the thrust vector may be adjusted to compensate for gravity, loads generated by wind blowing the aircraft130, and/or other environmental factors. In embodiments in which the aircraft130operates autonomously the one or more processors142may adjust the thrust generator132and the control surfaces134. By contrast, in embodiments in which the aircraft130is controlled remotely the thrust generator132and the control surfaces134may be controlled by the remote flight control system160, either automatically or by an operator.

If, at operation230, load data received from the load cell120indicates that the load on the launch arm exceeds a predetermined threshold then control passes back to operation220and the load data is monitored while the thrust is adjusted (operation225). By contrast, if at operation230the load drops below a predetermined threshold then control passes to operation235and the release mechanism136is activated to release the aircraft130from the launch arm110(FIG. 3E).

In some embodiments the threshold for the load may be set at a level which indicates that the aircraft130can safely take off from the launch arm110. By way of example, the load threshold may be set such that the aircraft130is released when the thrust vector substantially cancels out the load from gravity, wind conditions, and/or other environmental conditions operating on the aircraft. In other embodiments the threshold may be set such that the aircraft130is not released until the thrust vector provides upward lift for the aircraft130.

While the release mechanism136had been described as being a component of the aircraft130, in alternate embodiments the release mechanism136may be a component of the launch arm110.