Bell Helicopter Textron Inc.

Textron Innovations Inc.

Gary Scott Froman

Ernst C Schellhase

Joseph Wendelsdorf

Keith Hale

Mark Paul Eisenhauer

Roger Jacques Michel Aubert

Richard Dean Miller

Daniel R Tippett

Donavan Drewes

John Peter Pappas

An electrical bonding test device, including a test system circuit configured to generate a current pulse for ground bonding testing of subject units, a first test system connector configured to provide an electrical connection between a first unit connector shell of a first unit of the subject units and the test system circuit and to pass the current pulse to the first unit connector shell during the ground bonding testing, and a second test system connector configured to provide an electrical connection between a second unit connector shell of a second unit of the subject units and a first node of the test system circuit. The test system circuit is further configured to provide an indication indicating whether a bonding path through the subject units is a conductive path having a resistance below a resistance threshold.

Handheld electrical bonding test system

In one embodiment, an aircraft electronics system includes a hardware processor, a charge collection circuit to collect charge; a switching circuit controlled by the hardware processor to discharge the charge collected on the charge collection circuit through a bonding circuit formed from a chassis and a bonding surface; and a voltage measurement circuit to measure a voltage difference between measurement terminals across the chassis and the bonding surface.

Integrated capacitive discharge electrical bonding assurance system

In one embodiment, a system may comprise an electro-thermal heating element and a controller. The electro-thermal heating element may be configured to heat a structure, and the controller may be configured to: identify a target temperature for the structure; identify a target rate of temperature change for the structure; identify a target voltage for heating the structure at the target rate of temperature change; and apply the target voltage to the electro-thermal heating element.

Anti-ice system for thermally fragile materials

A test system for testing a sensor system includes a high-impedance resistor for forming a voltage divider with any corrosion or foreign substance that might be present between a signal conductor and a ground conductor. While a voltage is applied across the voltage divider, the voltage can be measured across the high-impedance resistor for determining whether an undesirable amount of conductance exists between the signal wire and ground. The test system also includes switching means for switching between any number of signal wires of a system undergoing testing.

System and method for detecting sensor leakage

An ice protection system for a structure has at least one electro-thermal heating element carried by the structure and a controller for selectively controlling the operation of each heating element. The controller operates each heating element according to a selected duty cycle defined by a pattern of time intervals, the controller selecting the duty cycle at least partially in response to measurements of ambient conditions about the structure.

Anti-icing system for radomes

A transducer test system for testing accelerometers or velocity transducers includes a signal conditioner and a shaker that can be used in a field environment, for example by an avionics technician at an aircraft. A test transducer and a reference transducer, which is a known-good version of the test transducer, are mounted onto the shaker and electrically connected to the signal conditioner. The technician shakes the two transducers simultaneously by manually shaking the shaker. The signal conditioner receives and compares the signals output from the test and reference transducer in order to determine the operating condition of the test transducer.

System and method for testing of transducers

An ice management system is configured for an aircraft having at least one rotor (), each rotor having a plurality of blades. The system has an alternating current (AC) electrical power supply for supplying AC power (), the AC power supply being adapted to be carried by the aircraft remote from the rotor (). A converter converts the AC power to direct-current (DC) power. At least one ice protection device is carried by the rotor and operated using the DC power.

Ice management system for rotary-wing aircraft

An ice management system is configured for an aircraft having at least one rotor, each rotor having a plurality of blades. The system has an electrical power supply adapted to be carried by the aircraft remote from the rotor, and at least one heater is carried by the rotor for heating at least a portion of the rotor. A solid-state control relay is carried by the rotor and conductively coupled between the power supply and each heater for selectively controlling the flow of electrical power from the power supply to each heater. In addition, the system may incorporate a solid-state feed relay carried by the aircraft remote from the rotor and conductively coupled between the power supply and the control relay for selectively controlling the flow of electrical power to the control relay.

Ice management system for tiltrotor aircraft

A bearing monitor has a bearing sensor to monitor frequencies emitted by a bearing in a rotating component. The bearing sensor has an output to a processor. The processor is attached to the rotating component to process the output from the bearing sensor to a digital or logical signal, which may include determining if the output indicates that the bearing requires service.

Collective head bearing monitor

A redundant ice management system and method to de-ice and anti-ice an aircraft member (,) is provided. The system comprising a primary ice management sub-system (,) for providing thermal ice management to the aircraft member and a secondary ice management sub-system (,) for providing back-up thermal ice management to the aircraft member (,) in the event of a failure by the primary ice management sub-system (,). The system provides primary and secondary de-ice and anti-ice capabilities to the aircraft member (,) before and during airborne operation.

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Ft. Worth, TX, United States of America

Gary Scott Froman