Heat management system for aircraft

Claim 2

A heat management system for an aircraft having an engine, a main fuel tank for storage and supply of fuel for said engine, a first fuel line through which fuel is supplied from said main fuel tank to said engine for consumption therein, and a main fuel pump for pumping said fuel from said main fuel tank to said engine through said first fuel line, comprising: a. a cooling loop thermally interfacing the fuel flow through said first fuel line for extracting heat from the fuel contained in said main fuel tank by circulation of a refrigerant through said loop, said loop including a condenser near said first fuel line intermediate said main fuel pump and said engine, said condenser thermally interfacing the fuel flow through said first fuel line, an evaporator near said main fuel tank and thermally interfacing the fuel contained therein, and a thermal expansion valve and compressor intermediate said condenser and evaporator for circulating said refrigerant through said loop; b. a second fuel line interconnecting said main fuel tank with said first fuel line at a point intermediate said condenser and said engine, for recirculating to said main fuel tank fuel flowing through said first fuel line in excess of momentaneous engine consumption requirements; and c. a first control valve for controlling the flow of fuel through said second fuel line.

Claim 3

The heat management system as recited in claim 1, further comprising: d. means for monitoring the fuel flow rate in each said fuel line, said means providing an output signal characteristic of the fuel flow rate in each said line; e. temperature sensing means for monitoring the temperature of the fuel at a plurality of predetermined points within the said heat management system, said temperature sensing means providing a plurality of output signals characteristic of the temperatures at said plurality of points; and f. means, responsive to said output signals, for controlling the fuel flow through each said fuel flow line whereby the fuel flow rate to said engine is positively controlled and the temperature of the fuel flowing to said engine is maintained below a predetermined maximum level.

Claim 4

The heat management system as recited in claim 1, further comprising, a heat exchanger for exchanging heat from a heat producing system of said aircraft with said fuel, said heat exchanger disposed near said first fuel line intermediate said main fuel pump and the point of connection of said second fuel line, said heat exchanger thermally interfacing the fuel flow through said first fuel line.

Claim 5

The heat management system as recited in claim 1, further comprising, a heat exchanger for exchanging heat from a heat producing system of said aircraft with the fuel flowing through said second fuel line, said heat exchanger disposed near said second fuel line intermediate said main fuel tank and the point of connection of said first fuel line and said second fuel line and thermally interfacing the fuel flow through said second fuel line.

Claim 6

A heat management system for an aircraft having an engine, a main fuel tank for storage and supply of fuel for said engine, a first fuel line through which fuel is supplied from said main fuel tank to said engine for consumption therein, and a main fuel pump for pumping said fuel from said main fuel tank to said engine through said first fuel line, comprising: a. a reserve tank for containing cooled fuel; b. a cooling loop, thermally interfacing the fuel flow through said first fuel line, for extracting heat from the fuel contained in said reserve tank by circulation of a refrigerant through said loop, said loop including a condenser near said first fuel line intermediate said main fuel pump and said engine, said condenser thermally interfacing the fuel flow through said first fuel line, an evaporator near said reserve tank and thermally interfacing the fuel contained therein, and a thermal expansion valve and compressor intermediate said condenser and evaporator for circulating said refrigerant through said loop; c. a second fuel line interconnecting said main fuel tank with said first fuel line at a point intermediate said condenser and said engine, for recirculating to said main fuel tank fuel flowing through said fuel line in excess of momentaneous engine consumption requirements; and d. a first control valve for controlling the flow of fuel through said second fuel line.

Claim 7

A heat management system for an aircraft having an engine, a main fuel tank for storage and supply of fuel for said engine, a first fuel line through which fuel is supplied from said main fuel tank to said engine for consumption therein, and a main fuel pump for pumping said fuel from said main fuel tank to said engine through said first fuel line, comprising: a. a reserve tank for containing cooled fuel; b. a cooling loop, thermally interfacing the fuel flow through said first fuel line, for extracting heat from the fuel contained in said reserve tank by circulation of a refrigerant through said loop, said loop including a condenser near said first fuel line intermediate said main fuel pump and said engine, said condenser thermally interfacing the fuel flow through said first fuel line, an evaporator near said reserve tank and thermally interfacing the fuel contained therein, and a thermal expansion valve and compressor intermediate said condenser and evaporator for circulating said refrigerant through said loop; c. a second fuel line interconnecting said main fuel tank with said first fuel line at a point intermediate said condenser and said engine, for recirculating to said main fuel tank fuel flowing through said fuel line in excess of momentaneous engine consumption requirements; and d. a first control valve for controlling the flow of fuel through said second fuel line.

Claim 8

The heat management system as recited in claim 5, further comprising, a second cooling loop, thermally interfacing the fuel flow through said first fuel line, for extracting heat from the fuel contained in said main tank by circulation of a refrigerant through said second loop, said second loop connected to said condenser near said first fuel line and including a second evaporator near said main tank and thermally interfacing the fuel contained therein, and a second thermal expansion valve and second compressor intermediate said condenser and second evaporator for circulating said refrigerant through said loop.

Claim 9

The heat management system as recited in claim 5, further comprising, a first heat exchanger for exchanging heat from a heat producing system of said aircraft with the fuel flowing through said first fuel line, said first heat exchanger disposed near said first fuel line intermediate said main fuel pump and the point of connection of said first fuel line and said second fuel line and thermally interfacing the fuel flow through said first fuel line.

Claim 10

The heat management system as recited in claim 5, further comprising, a second heat exchanger for exchanging heat from a heat producing system of said aircraft with the fuel flowing through said second fuel line, said second heat exchanger disposed near said second fuel line intermediate said main fuel tank and the point of connection of said first fuel line and said second fuel line and thermally interfacing the fuel flow through said second fuel line.

Claim 11

The heat management system as recited in claim 5, further comprising, a third fuel line, interconnecting said reserve tank and said first fuel line at a point intermediate said main fuel pump and said condenser, a second control valve in said third fuel line for controlling the flow of fuel therethrough, and a reserve fuel pump for selectively pumping fuel from said reserve tank into said first fuel line for mixing therein of cooled fuel from said reserve tank with that from said main fuel tank.

Claim 12

The heat management system as recited in claim 9, further comprising, a third control valve in said first fuel line intermediate said main fuel pump and the point of connection of said second fuel line with said first fuel line, a third fuel line interconnecting said reserve fuel tank and said first fuel line at a point intermediate said main fuel pump and said third control valve, and a fourth control valve for controlling fuel flow through said third fuel line from said main fuel tank to said reserve fuel tank.

Claim 13

The heat management system as recited in claim 5, further comprising means, connected to said reserve tank, for cooling the fuel contained therein by controllably evaporating a portion of said fuel contained in said reserve tank.

Claim 14

The heat management system as recited in claim 11 wherein said means for cooling said fuel includes a vacuum system and control valve operatively connected to said reserve tank.

Claim 15

The heat management system as recited in claim 5, further comprising: e. means for monitoring the fuel flow rate in each said fuel line, said means providing an output signal characteristic of the fuel flow rate in each said line; f. temperature sensing means for monitoring the temperature of the fuel at a plurality of predetermined points within the said heat management system, said temperature sensing means providing a plurality of output signals characteristic of the temperatures at said plurality of points; and g. means, responsive to said output signals, for controlling the fuel flow through each said fuel flow line whereby the fuel flow rate to said engine is positively controlled and the temperature of the fuel flowing to said engine is maintained below a predetermined maximum level.