Meggitt Aerospace Limited

Dunlop Gmbh

Other

Dunlop Aerospace Limited

Richard John Miller

David Alexander Bailey

Ross John Marshall

Nicholas Charles Griffin

Graham Carrier

Ian Leonard Stimson

Upgrading existing aircraft braking systems to accommodate replacement of existing brake units employing sintered friction materials with brake units employing carbon-carbon composite friction materials is often desirable. However, when upgrading the braking systems it is necessary to ensure that the integrity of the existing airframe is not compromised by the use of the new brake assemblies employing the carbon-carbon composite friction materials. Consequently, the present invention replaces existing pressure control valves of existing braking systems with an electronic control unit () coupled to a pressure control servovalve (), thereby ensuring proper application of hydraulic pressure to brake assemblies (). An advantage of this invention is that the pressure profile of the hydraulic fluid is controllable and hence the integrity of the airframe is maintained.

Hydraulic fluid control apparatus

In the field of avionics, it is difficult to justify initiation of new aircraft programmes for replacement of small numbers of niche aircraft. Instead, in many cases, retrofitting existing aircraft is preferred for economic reasons. In this respect, upgrading existing braking systems to accommodate replacement of existing brake units employing sintered friction materials with brake units employing carbon-carbon composite friction materials is desirable. However, when upgrading the braking systems it is necessary to ensure that the integrity of the existing airframe is not compromised by the use of the new brake assemblies employing the carbon-carbon composite friction materials. Consequently, the present invention replaces existing pressure control valves of existing braking systems with an electronic control unit () coupled to a pressure control servovalve () thereby ensuring proper application of hydraulic pressure to brake assemblies (). An advantage of this invention is that the pressure profile of the hydraulic fluid is controllable and hence the integrity of the airframe is maintained.

A method for charging an aircraft braking system for use includes monitoring actuations of an aircraft braking system to identify where generating usage and non-wear generating usage of the aircraft braking system, and charging the aircraft braking system for use based on the identified usage of the aircraft braking system. An apparatus for monitoring usage of aircraft brakes and charging the aircraft brakes for usage includes at least one sensor for sensing a brake output parameter when the aircraft brakes are actuated and providing signals indicative of values of the sensed brake output parameter. The apparatus further includes a processing system for processing the signals and determining whether an actuation of the aircraft brakes is a wear generating usage or a non-wear generating usage and operating a pricing scheme based on actuation of the aircraft brakes and the associated usage.

Brake condition monitoring

A system and method for monitoring the usage of brake members of an aircraft braking system. The system makes a separate record of each brake actuation in which there is relative movement of the brake member's facing friction surfaces which causes wear, determines the types of brake usage and operates a pricing/payment scheme to charge for brake usage.

A device for producing a two dimensional image includes means for generating coherent light, and means for directing light received from the means for generating coherent light to a plurality of electrically addressable spatial light modulators (EASLM). The device includes means for diffracting the light, wherein the light is simultaneously diffracted by the plurality of EASLM, and means for displaying the two dimensional image. The device further includes means for directing the diffracted light to the means for displaying the two dimensional image, wherein a frame rate of each of the plurality of EASLM is greater than a frame rate of the two dimensional image produced at the means for displaying the two dimensional image.

Image projection device and method

A system and method for monitoring the applications of carbon-carbon brakes of an aircraft to determine brake condition and operate a brake maintenance program or charge a brake system user. The system and method includes monitoring each actuation of the brakes and making a separate record of each actuation of the brakes in which there is relative movement of the facing friction surfaces that cause wear, and from that separate record determining brake usage. The monitoring may include measuring changes and processing the signals to distinguish between those which fall below and those which are above a threshold value. The method and system may comprise sensing a plurality of braking parameters having values dependent upon the wear in the system and different faults of the system, and identifying and recording wear and faults based on combinations of values of the parameters.

System and method for monitoring the applications of the brakes, e.g. of an aircraft to determine brake condition and operate a brake maintenance programme or charge a brake system user. It is desirable to have accurate information for determining the condition and predicting the life of carbon-carbon brake discs. This is important for safety as well as commercial reasons. The number of landings of an aircraft is often used as a determinant for such as lifetime warranties for brake discs and recommended maintenance periods. However, at least for carbon disc brakes, this may not be entirely accurate. For example such brake discs also wear during taxiing. The system and method herein includes monitoring each actuation of the brakes and making a separate record of each actuation of the brakes in which there is relative movement of the facing friction surfaces that cause wear, and from that separate record determining brake usage. The monitoring may include measuring changes and processing the signals to distinguish between those which fall below and those which are above a threshold value. Herein there is also described, a method and apparatus for monitoring a braking system comprising sensing a plurality of braking parameters having values dependent upon wear in the system and different faults of the system, and identifying and recording wear and faults based on combinations of values of said parameters.

An aircraft braking system for a main undercarriage or undercarriages incorporates at least two brakes, which may be carbon type brakes, and a control unit for selectively disabling at least one brake during taxiing only, the control unit being arranged to ensure that the disabling of the brake or brakes does not affect the directional stability of the aircraft when the braking system is operated.

Aircraft braking systems

A system for guarding against the leakage of fluid from a hydraulic system, particularly an aircraft braking system, which employs a flow control valve under the control of an electronic processor. The electronic processor integrates with respect to time a function of the input signal to the flow control valve and the pressure of the output of fluid, compares the value of the integrated function with a predetermined value, and effects closure of the control valve if the comparison indicates a substantial fluid loss.

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Coventry, United Kingdom

Richard John Miller