Abstract: One embodiment is an electric drive system including a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto via a swashplate; a gear box associated with the plurality of redundant motors; a cyclic actuation system for controlling an individual pitch of the rotor blades connected to the swashplate; and at least one structural element for retaining the redundant motors, the gear box, and the cyclic actuation system together as a single integrated unit.

Abstract: One embodiment is an electric drive system for an aircraft including a motor, a gear box associated with the motor, and a cooling fan for drawing air into the unit across an electronic component to cool the electronic component and for expelling air into an oil cooler for cooling oil contained therein. The electric drive system further includes an oil distribution system for distributing oil cooled by the oil cooler to at least one motor and at least one gearbox, the distributed oil being used to cool the motor and the gearbox, a reservoir for collecting the distributed oil after it has been used to cool the motor and the gearbox, and at least one structural element for retaining the motor, gearbox, the cooling fan, the oil distribution system, and the reservoir together as a unit.

Abstract: One embodiment is an electric drive system for an aircraft comprising a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto; a gear box associated with the plurality of redundant motors; a collective actuator for controlling a collective pitch of the rotor blades connected to the rotor shaft; and at least one structural element for retaining the redundant motors, the gear box, and the collective actuator together as a single integrated unit.

Abstract: One embodiment is an electric drive system including a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto via a swashplate; a gear box associated with the plurality of redundant motors; a cyclic actuation system for controlling an individual pitch of the rotor blades connected to the swashplate; and at least one structural element for retaining the redundant motors, the gear box, and the cyclic actuation system together as a single integrated unit.

Abstract: One embodiment is an electric drive system for an aircraft comprising a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto; a gear box associated with the plurality of redundant motors; a collective actuator for controlling a collective pitch of the rotor blades connected to the rotor shaft; and at least one structural element for retaining the redundant motors, the gear box, and the collective actuator together as a single integrated unit.

Abstract: One embodiment is an electric drive system for an aircraft including a motor, a gear box associated with the motor, and a cooling fan for drawing air into the unit across an electronic component to cool the electronic component and for expelling air into an oil cooler for cooling oil contained therein. The electric drive system further includes an oil distribution system for distributing oil cooled by the oil cooler to at least one motor and at least one gearbox, the distributed oil being used to cool the motor and the gearbox, a reservoir for collecting the distributed oil after it has been used to cool the motor and the gearbox, and at least one structural element for retaining the motor, gearbox, the cooling fan, the oil distribution system, and the reservoir together as a unit.

Abstract: Various implementations directed to a cabin thermal management system are provided. In one implementation, an aircraft may include a passenger cabin configured to transport one or more passengers. The aircraft may also include a battery pack configured to power one or more electronic components of the aircraft. The aircraft may further include a cabin thermal management system configured to regulate a cabin temperature of the passenger cabin by transferring thermal energy from the battery pack to the passenger cabin.

Abstract: Various implementations directed to a ground support equipment unit for use with electric aircraft are provided. In one implementation, a ground support equipment (GSE) unit may include a GSE thermal loop coupled to one or more channels of a battery pack onboard an aircraft, where the GSE thermal loop is configured to allow fluid from the one or more channels to circulate therein. The GSE unit may also include a GSE thermal system coupled to the GSE thermal loop, where the GSE thermal system is configured to regulate a battery temperature of the battery pack.

Abstract: A method of alarm data communication involves protecting a premise with an alarm sensor, sensing an exception, text messaging a responsible user's text-messaging device a text message indicative of such exception and, in the absence of an effective cancel instruction, propagating a signal to a central alarm monitoring station indicative of such exception or otherwise expediting dispatch of authorities to the premise in response to such exception. Another aspect of this method involves that, notwithstanding the absence of an effective cancel instruction, there instead might be the issuance of an effective verify instruction, which propagates to the central alarm monitoring station as indicative of not only the exception but also that such exception is verified.