The law enforcement standoff inspection drone capability (L-SID) integrates Various technology to enable a capability implemented at the squad car level to allow the first-to-scene the ability to remotely pre-screen the scene for threat, before an on-foot approach. This is accomplished with an officer launched and controlled and specially configure small unmanned aircraft system (UAS). The LAS is integrated with a specially configured one-hand drone controller, a wearable see through heads-up-display glasses, microphone that's linked to the UAS's onboard loudspeaker, and a special processing that enables looking through a vehicle of building tinted windows during enforcement event. The system operates on a private ad-hoc network, implements IEEE 802.1 1 g/n WPA 3 standards, and provides continuous live steamed scene data throughout the enforcement event. All data and video collected is transmitted in real-time to headquarters.

A device for emergency disconnection of a high voltage electrical connection between a power source and a high voltage component of an electric aircraft in response to a crash. The device includes a controller, where the controller is configured to receive a sensor datum from a sensor of device, to determine a crash element between and initiate a disconnection protocol as a function of the crash element.

In an aspect, a system for fixed-pitch lift configured for use in an electric aircraft includes a plurality of flight components mechanically coupled thereto, each configured to provide lift to the electric aircraft. The electric aircraft also includes a first pusher mechanically coupled to a first owing of the electric aircraft, wherein the first pusher is configured to provide forward flight to the electric aircraft, a second pusher mechanically coupled to a second wing of the electric aircraft, wherein the second pusher is configured to provide forward flight to the electric aircraft as well, a sensor that is configured to detect vertical lift and forward flight from a pilot control and generate a command datum, as a function of the pilot control, a flight controller which may include a computing device configured to receive the command datum and direct the electric aircraft, as a function of the command datum.

Systems and methods relate to electric propulsor fault detection. An exemplary system includes at least a first inverter configured to accept a direct current and produce an alternating current, a first propulsor, a first motor operatively connected with the first propulsor and powered by the alternating current, and at least a noise monitoring circuit electrically connected with the direct current and configured to detect electromagnetic noise and disengage the at least an inverter as a function of the electromagnetic noise.

A drone docking ports (DDP) mounted on a pole top in close proximity to an accident scene with an openable and closable enclosure, a docking plate having integrated battery wired or wireless recharging pads, and a control module (CM) is disclosed. The CM is adapted to autonomously control all functions of the DDP including actuation of the enclosure and relay of video, audio, and flight control information between the CM and a central monitoring center and/or emergency personnel. A drone with a top and bottom profile design allowing numerous drones to be stacked upon one another and store in the DDP. When the DDP enclosure is in an open position, a drone or stack of drones may initiate a flight from the DDP and to re-dock the drone or stack of drones when the flight is completed, the enclosure may be closed to protect the drone or stack of drones.

Modified magnetic levitation system for flying vehicle Modified magnetic levitation system for flying vehicle includes a propeller system (11, 12, 13), an axial levitation system (101, 102), radial levitation system (part of 201), rotary propulsion system (part of 201) and passive magnetic bearing system (301). An axial levitation system includes plurality of halbach array pairs connected on rotor and special short circuited coil windings connected on stator. A propulsion mechanism (part of 201) is provided for rotating rotor along the centre axis. Radial levitation and propulsion system (201) includes halbach arrays (53) located at outer circumference of rotor and interweaved active and passive coil windings (43) located at inner circumference of stator. Passive magnetic bearing system (301) includes parts of rotor and stator around centre axis of the system. Passive magnetic bearing (PMB) is utilized to levitate rotor at rest, below lift-off speed, and start and end condition of rotations.

An unmanned aerial vehicle (“UAV”) having an envelope and a drone body capable of delivering packages is disclosed. Methods for utilizing UAVs to deliver packages and systems for housing UAVs are also disclosed. In one aspect, a UAV includes a dual cavity envelope having an ellipsoid shape with a first internal cavity and a second internal cavity, the first internal cavity configured to hold a lighter than air gas, the second internal cavity configured to hold a heated gas, and a drone body attached to and located below the dual cavity vertical envelope.

A system and method for a recharging station including an elevated landing pad, a rechargeable component coupled to the elevated landing pad, a power delivery unit configured to deliver power from a power supply unit or power storage unit to the recharging component, and a support component coupled to the bottom of the elevated landing pad.

A vertical take-off and landing (VTOL) aircraft (10) includes a fuselage and first and second forward wings (20, 22), each wing (20, 22) having a fixed leading edge and a trailing control surface (50) which is pivotal about a generally horizontal pivot axis. The aircraft (10) includes first and second electric motors (60) each having rotors (70), the electric rotors (70) being pivotal with the trailing control surface (50) between a first position in which each rotor (70) has a generally vertical axis of rotation, and a second position in which each rotor (70) has a generally horizontal axis of rotation, a control system (90) is configured to selectively operate the first electric motor (60) and the second electric motor (60) at different rotational speeds to generate a turning moment to pivot the control surface (50) about the pivot axis (33).

An electric aircraft charging connector, including a set of pins, a sensor, a controller, and a locking mechanism. The set of pins may include an AC pin, the AC pin configured to supply AC power to a charging port and/or a DC pin, the DC pin configured to supply DC power to the charging port. The sensor can detect power flow from the pins to the charging port. The controller is communicatively connected to the sensor and configured to receive a signal from the sensor and send a locking signal to a locking mechanism. The locking mechanism is communicatively connected to the controller, having an engaged state wherein the charging connector is mechanically coupled to the charging port and a disengaged state wherein the charging connector is mechanically uncoupled form the charging port, the locking mechanism configured to receive a locking signal from the controller and enter the engaged state.