Sundstrand Corporation

Hamilton Sundstrand Corporation

Jeffrey D Nelson

John F Scanlon

Hayden M Reeve

Thomas S Latos

Gary E Dickes

A power unit connected to a power distribution bus operates in one of several modes to either store excess electrical energy from the power distribution or supply electrical energy to the power distribution bus to account for a detected demand/need. The power unit includes turbomachinery having components connected via a shaft, a generator connected to convert rotational energy associated with the turbomachinery to electrical energy for distribution on the bus, and a motor connected to convert electrical energy distributed by the bus to motive energy used to accelerate the turbomachinery components. A power controller monitors the voltage on the distribution bus. In response to excess voltage on the distribution bus, the power controller connects the motor to the bus to cause the excess electrical energy to be converted to motive energy that is used to accelerate the turbomachinery. In response to a voltage shortage on the distribution bus, the power controller connects the generator to the bus to convert rotational energy stored by the turbomachinery to electrical energy that is supplied to the bus.

Integrated power unit as energy storage device for electrical power system

An aircraft is provided that includes one or more engines, an air-driven generator, and a start-circuit for operably connecting an electrical output of the air driven generator for starting one or more of the engines while the aircraft is in flight. Various embodiments also provide apparatus for cross-ship electric starting of multiple engines while the aircraft is in flight or on the ground using: an electrical output of a generator attached to another engine; on-board batteries; an on board auxiliary power unit; or power received from a ground source. A single start-converter is utilized to supply power to AC starter-motors for electric starting of the aircraft's engines. In some embodiments, the engine is soft-started with the air driven generator, by controlling blade pitch in an air driven turbine driving the air driven generator, without the use of the start converter.

Aircraft electrical system providing emergency power and electric

Ballscrew actuators are well known for use as a primary flight control actuator for operating a flight control surface. The operation of the ballscrew actuator is critical to the success of an aircraft mission; however, when the actuator is subject to ballistic fire, a projectile hit which is not totally destructive can still render the actuator inoperable. Increasing the potential for operability of the ballscrew actuator after a projectile hit which is not totally destructive will increase the number of successful returns from aircraft missions. The ballistic tolerant dual load path ballscrew actuator has a selectively-driven ballnut and a ballscrew drivingly connected to the ballnut. The ballscrew has an outer tubular member with an external helical ball groove providing a primary load path. An inner tubular member fits closely within and is fixed to the outer tubular member to provide a secondary load path upon cracking of the outer tubular member by a projectile passing through the outer tubular member. The inner tubular member is formed of ballistic tolerant composite material to maintain its structural integrity when contacted by a projectile which has passed through and cause cracking of the outer tubular member. In one embodiment, the inner tubular member has an outer energy absorbing layer of a ceramic material. In another embodiment, the inner tubular member is preloaded in tension to prevent propagation of a circumferential crack in the outer tubular member and is constructed of wound fibers providing ballistic tolerance and strength in torsion and tension.

Ballistic tolerant dual load path ballscrew and ballscrew actuator

Ballscrew actuators are well known for use as a primary flight control actuator for operating a flight control surface. The operation of the ballscrew actuator is critical to the success of an aircraft mission; however, when the actuator is subject to ballistic fire a projectile hit which is not totally destructive can still render the actuator inoperable. Increasing the potential for operability of the ballscrew actuator after a projectile hit which is not totally destructive will increase the number of successful returns from aircraft missions. The ballistic tolerant dual load path ballscrew actuator has a selectively driven ballnut and a ballscrew drivingly connected to the ballnut. The ballscrew has an outer tubular member with an external helical ball groove providing a primary load path. An inner tubular member fits closely within and is fixed to the outer tubular member to provide a secondary load path upon cracking of the outer tubular member by a projectile passing through the outer tubular member. The inner tubular member is formed of ballistic tolerant composite material to maintain its structural integrity when contacted by a projectile which has passed through and caused cracking of the outer tubular member.

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Belvidere, IL, United States of America

Jeffrey D Nelson