Hs Marston Aerospace Limited

Other

Hamilton Sundstrand Corporation

David Russell Scott

Berwyn Pollard

Sean L Cameron

William E Rhoden

Peter L Jalbert

Rudolph Thomas Beaupre

Brian C Scott

Stuart Anthony Astley

Nigel Philip Clark

Patrick James Jones

Berwyn Owain Pollard

A valve is provided and includes a bypass block defining a bypass flowpath fluidly communicable with main flowpaths, a member disposable within the bypass block to occupy and move between first and second positions, the member being configured to permit fluid flow through the bypass flowpath when occupying the first position and to block a portion of the bypass flowpath to thereby prevent fluid flow through the bypass flowpath when occupying the second position and an elastic element. The elastic element is coupled to the member and configured to bias the member in a biasing direction toward the second position responsive to a temperature of fluid flowing along the main flowpaths.

Valve and valve system responsive to fluid temperature

A valve includes an outer structure. The valve includes a hollow shaft that includes holes formed therein, the shaft disposed within the outer structure and translatable from a first position to a second position. A memory metal alloy (MMA) spring is coupled to the shaft and the outer structure, the MMA spring expanding and moving the shaft from the first position to the second position in response to a temperature of a fluid. A valve head is coupled to the shaft and adapted to be biased within the outer structure, the valve head closing a bypass inlet in the first position and allowing fluid to enter the bypass inlet in the second position, and transferring fluid from the bypass inlet into the hollow shaft so that the fluid can exit the valve via an outlet. A pressure relief mechanism may be included.

Bypass valve with a hollow shaft and a memory metal alloy spring

A system for managing thermal transfer in an aircraft includes a fuel stabilization unit, a fuel-air heat exchanger, and a turbine. The fuel-air heat exchanger is located downstream from the fuel stabilization unit. The fuel-air heat exchanger places deoxygenized fuel in a heat exchange relationship with compressor bleed air to produce heated deoxygenized fuel and cooled bleed air. The turbine is operationally connected to the engine compressor and receives cooled bleed air from the fuel-air heat exchanger.

Small engine cooled cooling air system

A laminated heat exchanger includes at least one heat exchange layer that includes a plurality of side members that define a frame having an interior portion. A plurality of heat exchange members extend between at least two of the plurality of side members across the interior portion. The plurality of heat exchange members are linked by a ligament member to form a heat exchange member chain.

Laminated heat exchanger

A heat exchanger apparatus is disposed within a first pathway along which a first fluid flows. The heat exchanger apparatus includes a component disposed in the first pathway and the component includes heat transfer surfaces. Each heat transfer surface includes a central body, an outer body surrounding the central body and intermediate bodies extending between the central body and the outer body. The heat transfer surfaces are arranged together such that the central bodies, the outer bodies and the intermediate bodies of each heat transfer surface form at least one or more second pathways along which a second fluid flows and such that the outer bodies of each heat transfer surface form a component surface disposed to contact the first and second fluids.

Heat exhanger apparatus including heat transfer surfaces

A surface cooler includes a base plate, and at least one fin element extending from the base plate. The at least one fin element includes an outer surface portion that is configured and disposed to be in direct contact with a first fluid and an inner surface portion that is configured and disposed to be in direct contact with a second fluid. The at least one fin element defines a primary heat exchange member that is configured and disposed to facilitate an exchange of heat between the first and second fluids.

Surface cooler having channeled fins

A surface cooler is provided and includes an oil layer, through which oil flows, a separating plate disposed in heat transfer communication with the oil and fins extending into an air flow pathway and being disposed in heat transfer communication with the separating plate, the fins being arranged with varied configurations at each of two or more sections sequentially defined along a predominant direction of air flow along the air flow pathway.

Three phase fin surface cooler

A surface cooler is provided and includes an oil layer through which oil flows, fins extending into an air flow pathway and being disposed at a first side of the oil layer in heat transfer communication with the oil, an acoustic lining to reduce noise present in or transmitted by the air flow pathway, which is disposed at a second side of the oil layer opposite the first side and noise transfer tubes extending through the oil layer to transfer the noise present in or transmitted by the air flow pathway to the acoustic lining.

Surface cooler with noise reduction

Apparatus and methods for performing satellite proximity operations such as inspection, recovery and life extension of a target satellite through operation of a &ldquo;Satellite Inspection Recovery and Extension&rdquo; (&ldquo;SIRE&rdquo;) spacecraft which can be operated in the following modes (teleoperated, automatic, and autonomous). The SIRE concept further consists of those methods and techniques used to perform certain (on-orbit) operations including, but not limited to, the inspection, servicing, recovery, and lifetime extension of satellites, spacecraft, space systems, space platforms, and other vehicles and objects in space, collectively defined as &ldquo;target satellites&rdquo;. The three basic types of SIRE proximity missions are defined as &ldquo;Lifetime Extension&rdquo;, &ldquo;Recovery&rdquo;, and &ldquo;Utility&rdquo;. A remote cockpit system is provided to permit human control of the SIRE spacecraft during proximity operations.

Growing community of inventors

Walsall, United Kingdom

David Russell Scott