原始名称记载: Hamilton Sundstrand Corporation

An apparatus includes a generator including an input shaft, a jet engine including a low pressure spool, and a multi-speed transmission mechanically coupling the low pressure spool to the input shaft. The apparatus further includes a transmission controller configured to disengage an electrical load from the generator, while the electrical load is disengaged from the generator, perform a shifting operation of the multi-speed transmission, and after performing the shifting operation, reengage the electrical load to the generator.

A fuel system includes a system inlet and a system outlet. The fuel system also includes a metering valve with a metering valve inlet fluidically connected to the system inlet, and a metering valve outlet fluidically connected to the metering valve inlet. A pressure regulating valve includes an inlet fluidically connected to the metering valve outlet, and an outlet fluidically connected to the system outlet. A spool of the pressure regulating valve is configured to fluidically open and close the inlet to the outlet. The pressure regulating valve also includes a control chamber on a control side of the spool. A pilot valve includes a return port fluidically connected to the system outlet, and a supply port fluidically connected to a line fluidically connecting the metering valve outlet to the inlet of the pressure regulating valve. The pilot valve also includes a signal port fluidically connected to the control chamber.

A fluid system includes a reference pressure source, a first valve, and a second valve. The first valve includes a housing with a first damping port fluidically connected to the reference pressure source and a second damping port fluidically connected to the reference pressure source. The first valve also includes a spool moveable within the housing. The spool includes a damping window formed on the spool. The damping window fluidically connects the first damping port to the second damping port. The second valve is fluidically connected to at least one of the first damping port and the second damping port.

An apparatus may include a solid-state power controller (SSPCs), a pulse generator, a feedback detector, and a microcontroller. The SSPC may be configured to output power from a power source to an aircraft electrical load. The pulse generator may be configured to generate a pulse through the SSPC. The pulse feedback detector may be configured to detect a response pulse from the generated pulse reflected from the aircraft electrical load, wherein the pulse feedback detector may be operably coupled to a power output of the SSPC. The microcontroller may be configured to trip the SSPC when the response pulse detected by a corresponding pulse feedback detector operably coupled to the SSPC is determined to be abnormal.

A motor includes a housing. The motor includes a stator with a plurality of slots disposed axially along an axis of rotation of a rotor, the stator having a first end and a second end, wherein the first end and second end are separated along the axis of rotation of the rotor. The motor includes stator windings disposed on the plurality of slots, the stator windings comprising a core set of windings, a first set of end turns proximate to the first end, and a second set of end turns proximate to the second end. The motor includes a cooling sleeve surrounding the stator windings, the cooling sleeve having a first opening proximate to the first end of the stator, and a second opening proximate to the second end of the stator and a thermally conductive dissipation cap thermally connected to the cooling sleeve.

A first electrical machine is configured to act as an electrical motor in a first mode and an electrical generator in a second mode. Each first electrical machine is associated with a high-pressure spool of a turbine engine. A first controller is configured to control a load level of the first electrical machine responsive to a first load level control signal. A second electrical machine is configured to act as an electrical motor in the first mode and as an electrical generator in the second mode. The second electrical machine is associated with a low-pressure spool of the turbine engine. A second controller is configured to control a load level of the second electrical machine responsive to a second load level control signal. A third controller is configured to generate the first load level control signal and the second load level control signal responsive to temperatures of the first electrical machine, the first controller, the second electrical machine, and the second controller.

A method includes receiving, by an electronic device via a data bus, status information associated with a set of circuit breakers (CBs) of the aircraft. The status information includes an identifier and current state of each among the set. The method includes obtaining a database including on aircraft test procedure (OATP) CB tables in a second data format and including the CB identifier and an expected state of each CB among the set. The method includes translating the status information from a first data format to the second data format, thereby generating a translated current state of each CB among the set. The method includes, for each respective CB among the set, determining whether the translated current state and the expected state conflict and in response to identifying a conflict between the expected state and the translated current state, generating a command to change the current state.