Abstract: Systems and methods are disclosed for providing flexible, scalable, and controllable electrical power to an aircraft. In some embodiments, a modular power unit comprises a container containing a power generation unit, a control system, a conditioning system, and an environmental control system. The power generation unit produces a generated power. The control system provides control signals to the power generation unit and controls at least one parameter of the generated power. The conditioning system receives and conditions the generated power and provides an output power to the power bus of the aircraft. The environmental control system provides a temperature regulating fluid to the power generation unit.

Abstract: A hybrid interchangeable battery evaluation tool (HIBET) is provided. HIBET determines an amount of electrical energy and an amount of jet fuel necessary for a hybrid electric aircraft to complete a flight based on a range of the flight, a payload of the hybrid electric aircraft, an indication of a battery mass limitation of the hybrid electric aircraft, and an optimization of an energy split between the electrical energy and the jet fuel. HIBET causes an indication of the amount of electrical energy to be displayed in a graphical user interface and/or to be otherwise outputted.

Abstract: In some examples, a shock absorption bracket includes one or more damping pads coupled to a facing surface of an absorption leg. The absorption leg is attached to a support leg and defines an internal corner with the support leg. The support leg is configured to attach to an equipment cabinet. The shock absorption bracket may be configured to define a gap between the damping pads and one or more support surfaces of the equipment cabinet. The shock absorption bracket may be configured to attach to a rear section of an equipment cabinet having an equipment access in a front section of the equipment cabinet.

Abstract: In some examples, a shock absorption bracket includes one or more damping pads coupled to a facing surface of an absorption leg. The absorption leg is attached to a support leg and defines an internal corner with the support leg. The support leg is configured to attach to an equipment cabinet. The shock absorption bracket may be configured to define a gap between the damping pads and one or more support surfaces of the equipment cabinet. The shock absorption bracket may be configured to attach to a rear section of an equipment cabinet having an equipment access in a front section of the equipment cabinet.

Abstract: Electrical voltage detection circuit and methods for determining the presence or absence of voltage in electrical equipment. An isolated power supply provides power to one or more voltage detection devices configured to detect voltage on one or more busses of electrical equipment. A switch is configured to provide supply voltage from the isolated power supply to the one or more busses of electrical equipment when the switch is closed. The voltage detection devices may determine if the one or more busses of electrical equipment are de-energized by detecting the voltage on the busses when the switch is open. The integrity of the electrical equipment may be verified by detecting, with the voltage detection devices, the voltage on the busses when the switch is closed, where the expected voltage readings are based on voltages being provided to one or more busses by the isolated power supply.

Abstract: A hybrid interchangeable battery evaluation tool (HIBET) is provided. HIBET determines an amount of electrical energy and an amount of jet fuel necessary for a hybrid electric aircraft to complete a flight based on a range of the flight, a payload of the hybrid electric aircraft, an indication of a battery mass limitation of the hybrid electric aircraft, and an optimization of an energy split between the electrical energy and the jet fuel. HIBET causes an indication of the amount of electrical energy to be displayed in a graphical user interface and/or to be otherwise outputted.

Abstract: Systems and methods are disclosed for providing flexible, scalable, and controllable electrical power to an aircraft. In some embodiments, a modular power unit comprises a container containing a power generation unit, a control system, a conditioning system, and an environmental control system. The power generation unit produces a generated power. The control system provides control signals to the power generation unit and controls at least one parameter of the generated power. The conditioning system receives and conditions the generated power and provides an output power to the power bus of the aircraft. The environmental control system provides a temperature regulating fluid to the power generation unit.

Abstract: Electrical voltage detection circuit and methods for determining the presence or absence of voltage in electrical equipment. An isolated power supply provides power to one or more voltage detection devices configured to detect voltage on one or more busses of electrical equipment. A switch is configured to provide supply voltage from the isolated power supply to the one or more busses of electrical equipment when the switch is closed. The voltage detection devices may determine if the one or more busses of electrical equipment are de-energized by detecting the voltage on the busses when the switch is open. The integrity of the electrical equipment may be verified by detecting, with the voltage detection devices, the voltage on the busses when the switch is closed, where the expected voltage readings are based on voltages being provided to one or more busses by the isolated power supply.