Abstract: A combined hover and forward thrust control assembly for a dual-mode aircraft includes a support structure attached to an aircraft frame of an aircraft having at least a vertical thrust propulsor and at least a forward thrust propulsor a throttle lever rotatably mounted to the support structure, wherein rotating the throttle lever in a first direction increases power to at least a vertical thrust propulsor and rotating the throttle lever in a second direction decreases power to at least a vertical thrust propulsor and a linear thrust control mounted on the throttle lever, wherein movement of the linear thrust control in a first direction increases forward thrust of at least a forward thrust propulsor, and movement of the linear thrust control in a second direction decreases forward thrust of the forward thrust propulsor.

Abstract: A hover and thrust control assembly for dual-mode aircraft including a plurality of flight components mechanically coupled to an aircraft includes a support structure attached to an aircraft frame of an aircraft having a control stick coupled to the support structure. The control stick may include a length and radius and configured to be manipulated along a plurality of axes, wherein the manipulation of the control stick produces an electronic signal, wherein the control stick is further configured to be manipulated rotationally about the length of the control stick. A first interface device disposed on the control stick may be configured to receive an interaction and adjust a lift of the dual-mode aircraft as a function of the interaction. A second interface device may be configured to receive an interaction and adjust the lift of the dual-mode aircraft as a function of the interaction.

Abstract: A combined hover and forward thrust control assembly for a dual-mode aircraft includes a support structure attached to an aircraft frame of an aircraft having at least a vertical thrust propulsor and at least a forward thrust propulsor a throttle lever rotatably mounted to the support structure, wherein rotating the throttle lever in a first direction increases power to at least a vertical thrust propulsor and rotating the throttle lever in a second direction decreases power to at least a vertical thrust propulsor and a linear thrust control mounted on the throttle lever, wherein movement of the linear thrust control in a first direction increases forward thrust of at least a forward thrust propulsor, and movement of the linear thrust control in a second direction decreases forward thrust of the forward thrust propulsor.

Abstract: A three-dimensional directional control assembly for a dual-mode aircraft, wherein the aircraft is capable of vertical and forward thrust. The assembly comprising a support structure, wherein the support structure is coupled to a dual-mode aircraft. The assembly further comprises a control stick coupled to support structure, wherein the control stick having a length and radius is configured to be manipulated along a plurality of axes, wherein the manipulation of the control stick produces an electronic signal. The assembly further comprises a first interface device disposed on the control stick configured to receive an interaction and enable a thrust element to spin as a function of the interaction. The assembly further comprises a second interface device, wherein the second interface is configured to receive an interaction and disable the thrust element as a function of the interaction.

Abstract: A broadband ultrasonic transducer device (UTD) is disclosed that utilizes a plurality of narrow-band piezo electric elements grouped into single-frequency sub-arrays to provide a relatively simple, highly-reliable deterrent unit (DU) capable of emitting ultrasonic energy over a wide coverage area and at a sound pressure level that meets or exceeds other DU approaches. In an embodiment, the broadband UTD includes a housing portion configured to couple to a plurality of piezo sub-array plates. Each piezo sub-array plate includes a plurality of pockets or cavities to receive respective narrow-band (e.g., 1-3 kHz) piezo electro transducer elements with characteristics, e.g., geometries and material composition, that cause each to emit ultrasonic energy at a particular resonant frequency. A controller of the UTD implements a control scheme to emit ultrasonic energy in a plurality of output modes including a white noise node and a single-frequency mode for deterrence applications.

Abstract: A three-dimensional directional control assembly for a dual-mode aircraft, wherein the aircraft is capable of vertical and forward thrust. The assembly comprising a support structure, wherein the support structure is coupled to a dual-mode aircraft. The assembly further comprises a control stick coupled to support structure, wherein the control stick having a length and radius is configured to be manipulated along a plurality of axes, wherein the manipulation of the control stick produces an electronic signal. The assembly further comprises a first interface device disposed on the control stick configured to receive an interaction and enable a thrust element to spin as a function of the interaction. The assembly further comprises a second interface device, wherein the second interface is configured to receive an interaction and disable the thrust element as a function of the interaction.

Abstract: A combined hover and forward thrust control assembly for a dual-mode aircraft includes a support structure attached to an aircraft frame of an aircraft having at least a vertical thrust propulsor and at least a forward thrust propulsor a throttle lever rotatably mounted to the support structure, wherein rotating the throttle lever in a first direction increases power to at least a vertical thrust propulsor and rotating the throttle lever in a second direction decreases power to at least a vertical thrust propulsor and a linear thrust control mounted on the throttle lever, wherein movement of the linear thrust control in a first direction increases forward thrust of at least a forward thrust propulsor, and movement of the linear thrust control in a second direction decreases forward thrust of the forward thrust propulsor.

Abstract: A broadband ultrasonic transducer device (UTD) is disclosed that utilizes a plurality of narrow-band piezo electric elements grouped into single-frequency sub-arrays to provide a relatively simple, highly-reliable deterrent unit (DU) capable of emitting ultrasonic energy over a wide coverage area and at a sound pressure level that meets or exceeds other DU approaches. In an embodiment, the broadband UTD includes a housing portion configured to couple to a plurality of piezo sub-array plates. Each piezo sub-array plate includes a plurality of pockets or cavities to receive respective narrow-band (e.g., 1-3 kHz) piezo electro transducer elements with characteristics, e.g., geometries and material composition, that cause each to emit ultrasonic energy at a particular resonant frequency. A controller of the UTD implements a control scheme to emit ultrasonic energy in a plurality of output modes including a white noise node and a single-frequency mode for deterrence applications.