Abstract: The present disclosure provides an aircraft thermal management system. The aircraft thermal management system includes a first hydraulic system for circulating a first hydraulic fluid, a second hydraulic system for circulating a second hydraulic fluid, and a third hydraulic system for circulating a third hydraulic fluid. The aircraft thermal management system also includes a controller configured to: (i) determine a temperature of the first hydraulic fluid, a temperature of the second hydraulic fluid, and a temperature of the third hydraulic fluid, and (ii) based on the determined temperature of the first hydraulic fluid, utilize the second hydraulic fluid and/or the third hydraulic fluid to modify an operational temperature of the first hydraulic fluid.

Abstract: The present disclosure provides an aircraft thermal management system. The aircraft thermal management system includes a first hydraulic system for circulating a first hydraulic fluid, a second hydraulic system for circulating a second hydraulic fluid, and a third hydraulic system for circulating a third hydraulic fluid. The aircraft thermal management system also includes a controller configured to: (i) determine a temperature of the first hydraulic fluid, a temperature of the second hydraulic fluid, and a temperature of the third hydraulic fluid, and (ii) based on the determined temperature of the first hydraulic fluid, utilize the second hydraulic fluid and/or the third hydraulic fluid to modify an operational temperature of the first hydraulic fluid.

Abstract: A thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature and a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature. The thermal management system also includes a sealed heat transfer device coupled between the first hydraulic system and the second hydraulic system. The sealed heat transfer device is not in flow communication with either of the first hydraulic system and the second hydraulic system. The sealed heat transfer device is configured to transfer heat from the second hydraulic fluid to the first hydraulic fluid.

Abstract: An aircraft hydraulic thermal management system utilizes fuel to cool hydraulic fluid by means of a heat exchanger. A hydraulic pump includes a case drain flow of hydraulic fluid at a first temperature to drive a hydraulic motor; the hydraulic motor circulates hydraulic fluid to a reservoir at a second temperature. The heat exchanger is positioned remotely of the fuel tank, and has first and second channels positioned in thermal communication to transfer heat from the hydraulic fluid to the fuel. The hydraulic motor is mechanically coupled to the fuel pump; the hydraulic motor, driven by case drain flow through the first channel, thus operates the fuel pump to move fuel through the second channel. The thermal management system is configured to assure that a) the hydraulic pump circulates hydraulic fluid to the reservoir at the second temperature, and b) the second temperature is always lower than the first temperature.

Abstract: A thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature and a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature. The thermal management system also includes a sealed heat transfer device coupled between the first hydraulic system and the second hydraulic system. The sealed heat transfer device is not in flow communication with either of the first hydraulic system and the second hydraulic system. The sealed heat transfer device is configured to transfer heat from the second hydraulic fluid to the first hydraulic fluid.

Abstract: A thermal management system is provided. The thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature, a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature, and a heat exchanger coupling the first hydraulic system to the second hydraulic system, wherein the heat exchanger is configured to exchange heat between the first hydraulic fluid and the second hydraulic fluid.

Abstract: A thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature and a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature. The thermal management system also includes a sealed heat transfer device coupled between the first hydraulic system and the second hydraulic system. The sealed heat transfer device is not in flow communication with either of the first hydraulic system and the second hydraulic system. The sealed heat transfer device is configured to transfer heat from the second hydraulic fluid to the first hydraulic fluid.

Abstract: An aircraft hydraulic thermal management system utilizes fuel to cool hydraulic fluid by means of a heat exchanger. A hydraulic pump includes a case drain flow of hydraulic fluid at a first temperature to drive a hydraulic motor; the hydraulic motor circulates hydraulic fluid to a reservoir at a second temperature. The heat exchanger is positioned remotely of the fuel tank, and has first and second channels positioned in thermal communication to transfer heat from the hydraulic fluid to the fuel. The hydraulic motor is mechanically coupled to the fuel pump; the hydraulic motor, driven by case drain flow through the first channel, thus operates the fuel pump to move fuel through the second channel. The thermal management system is configured to assure that a) the hydraulic pump circulates hydraulic fluid to the reservoir at the second temperature, and b) the second temperature is always lower than the first temperature.

Abstract: There is provided in an embodiment a hydraulic fluid heat dissipation control assembly for an aircraft hydraulic system. The hydraulic fluid heat dissipation control assembly has one or more heat exchangers. The hydraulic fluid heat dissipation control assembly further has at least one flow control element coupled to the one or more heat exchangers to control flow and heat dissipation of a hydraulic fluid. There is also provided a method of controlling heat dissipation of a hydraulic fluid in an aircraft hydraulic system using the hydraulic fluid heat dissipation control assembly disclosed herein.

Abstract: A thermal management system is provided. The thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature, a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature, and a heat exchanger coupling the first hydraulic system to the second hydraulic system, wherein the heat exchanger is configured to exchange heat between the first hydraulic fluid and the second hydraulic fluid.

Abstract: A thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature and a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature. The thermal management system also includes a sealed heat transfer device coupled between the first hydraulic system and the second hydraulic system. The sealed heat transfer device is not in flow communication with either of the first hydraulic system and the second hydraulic system. The sealed heat transfer device is configured to transfer heat from the second hydraulic fluid to the first hydraulic fluid.

Abstract: A knife assembly and chipping knife therefor. The knife assembly includes a knife, and employs an upper clamping member and a lower clamping member for clamping the knife therebetween. The knife has an elongate axis and two spaced apart cutting edges parallel to the elongate axis and defining a first reference plane. The knife is further defined by a plane of reflective symmetry that is perpendicular to the first reference plane and which contains the elongate axis. The knife has a front side and a back side spaced from the front side. The front and back sides terminate in the cutting edges. A deflector ridge projects from the front side and reaches a point of greatest maximum projection of the knife from the first reference plane, the point lying in the plane of reflective symmetry.

Abstract: A conical chipper/canter head. The head includes, at least, one or more chipping knives. Each chipping knife provides at least one pair of linear cutting edges including a face cutting edge and a chip cutting edge angled with respect to each other. The face cutting edge defines a planar, face cutting surface of revolution of the cutting head, and the chip cutting edge defines a conical, chip cutting surface of revolution of the cutting head. The face and chip cutting edges of the same chipping knife lie in substantially the same plane. A cutting head may include a plurality of facing knives and corresponding clamping members in addition to one or more chipping knives. The facing knives and corresponding clamping members are adapted so that each of the facing knives is removable from the cutting head without removing any other facing knives.

Abstract: A drum flaker and knife therefor. A drum flaker comprises a drum for turning about an axis of revolution, a plurality of knife assemblies mounted to the drum, and a plurality of knives for mounting in the knife assemblies. The knives each have an elongate axis and comprise, on a first cutting side of the knife, at least two sets of cutting edges. The cutting edges of one of the sets alternate with and are radially offset from corresponding and respective cutting edges of the other of the sets.

Abstract: A conical chipper/canter head. The head includes, at least, one or more chipping knives. Each chipping knife provides at least one pair of linear cutting edges including a face cutting edge and a chip cutting edge angled with respect to each other. The face cutting edge defines a planar, face cutting surface of revolution of the cutting head, and the chip cutting edge defines a conical, chip cutting surface of revolution of the cutting head. The face and chip cutting edges of the same chipping knife lie in substantially the same plane. A cutting head may include a plurality of facing knives and corresponding clamping members in addition to one or more chipping knives. The facing knives and corresponding clamping members are adapted so that each of the facing knives is removable from the cutting head without removing any other facing knives.

Abstract: A knife assembly and chipping knife therefor. The knife assembly includes a knife, and employs an upper clamping member and a lower clamping member for clamping the knife therebetween. The knife has an elongate axis and two spaced apart cutting edges parallel to the elongate axis and defining a first reference plane. The knife is further defined by a plane of reflective symmetry that is perpendicular to the first reference plane and which contains the elongate axis. The knife has a front side and a back side spaced from the front side. The front and back sides terminate in the cutting edges. A deflector ridge projects from the front side and reaches a point of greatest maximum projection of the knife from the first reference plane, the point lying in the plane of reflective symmetry.