The embodiments are directed to an interface mount between a vehicle steering/control device and a mobile computer protective case. The interface mount has two sides. One side of the interface mount is attached to the vehicle steering/control device. The other side of the interface mount is attached to an AMPS hole pattern plate.

An aircraft and a control yoke for operating the aircraft. The control yoke includes a base, a handle for manual operation of the aircraft, and a graphical communication device centered at the base for receiving a command from an operator and autonomously operating the aircraft according to the received command.

This document details a series of inventions relating to the design and optimization of hybrid-to-electric aircraft. In particular, a system and method is presented to improve the effectiveness of mixed aerodynamic control surfaces which are actuated by a novel electromechanical actuator which allows the system to be tolerant to actuator faults and jams. In addition, innovations relating to integration and quick swap of large energy storage units such as batteries are disclosed, and further, an algorithm which may be used to optimize numerous aspects of the regional hybrid-to-electric aircraft known as Total Cost Door to Door or TCD2D.

An apparatus for controlling the pitch of an aircraft. The apparatus includes a horizontal control column extending from a control wheel horizontally towards a front wall of a cockpit. A pitch output link is connected to a downstream pitch control mechanism to transfer a force applied at the pitch output link to the downstream pitch control mechanism. A transfer assembly is connected to the horizontal control column and to the pitch output link. The transfer assembly translates a horizontal force applied to the horizontal control column to the pitch output link to provide the force applied to the downstream pitch control mechanism.

A method for turning an aerial vehicle such as a drone-type vehicle is provided, according to one embodiment. The method provides for receiving a turning input and detecting a current momentum of the aerial vehicle. The method provides for converting the turning input into a yaw command and calculating a change in yaw associated with the turning input. The method provides for calculating a roll command based on the current momentum of the aerial vehicle and based on the change in yaw associated with the turning input. Further, the method provides for executing the yaw command and the roll command in synchrony, wherein the executing the yaw command and the roll command in synchrony causes the aerial vehicle to perform a turn.

A system and method for detecting yoke interference for an aircraft having an auto pitch trim function is provided. The system includes a source of elevator load data, a source of aircraft speed data, and a processing system. The processing system is coupled to receive the elevator load data, the aircraft speed data, and initial condition center-of-gravity (CG) data that is representative of at least an estimated initial position of the CG of the aircraft. The processing system is configured to process at least the speed data and the initial condition CG data to: (i) determine an expected elevator load on the elevator flight control surface, (ii) determine if the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, and (iii) when the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, generate a disconnect signal that will disable the auto pitch trim function.

To provide an aerial vehicle that can realize ease of operation during driving. An aerial vehicle according to the present technology includes: a vehicle body extending in a front-rear direction; a saddle section provided on an upper side of the vehicle body; a grip section provided on the front side of the saddle section in the vehicle body; and a rotary wing section which is provided in the vehicle body and which generates lift and/or thrust with respect to the vehicle body; wherein an operation section for performing operations pertaining to actions relating to ascent and/or propulsion of the vehicle body is provided in the grip section.

To provide an aerial vehicle that can improve the driving feel and riding comfort of a rider. An aerial vehicle according to the present technology includes: a vehicle body extending in the front-rear direction; a saddle section provided on an upper side of the vehicle body; a motive power section provided on an underside of the vehicle body, at a position below the saddle section; and a rotary wing section which is provided at at least one of the front and rear of the motive power section, and which rotates by using the motive power section as a motive power source.

An aircraft having a frame assembly that supports a compressor having an outer shell that defines front and rear nozzle ports with rotatable nozzles for selectable vertical or horizontal thrust. The inner shell and the outer shell define an intake gap therebetween such as an annulus. A first fan unit within the inner shell and is configured to exhaust air through the front nozzle ports. A second fan unit within the outer shell intakes air through the intake gap and exhausts air through the rear nozzle ports. The fan units are preferably connected to one another via a drive shaft that is surrounded by a streamlining tube. The fan units each include a plurality of fans having stators therebetween. The stators have a plurality of stator arms with a wing structure pivotally attached to the trailing edge for angling air flow from a front to a rear fan.

A control system for operating an air vehicle for urban air mobility (UAM) is arranged such that when a steering operation for a steering wheel and a stroke operation for an accelerator pedal and a brake pedal are performed for operating the air vehicle for UAM, haptic feedback providing notification of any operational limitations is provided to a driver, so that operation stability and convenience of the driver are secured and stable steering, acceleration, and deceleration of the air vehicle are performed.