JP2713664B2 - Cold air generator for supersonic vehicles - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a low-temperature air generator for a supersonic flying object, a supersonic flying object such as an unmanned or manned supersonic aircraft, or the like.

[0002]

2. Description of the Related Art FIG. 2 shows a conventional example. In this example, a ramjet engine is used as a propulsion device of the supersonic flying object 1 to fly a long distance. The ramjet engine has a combustor 2, an exhaust nozzle 3 connected to a rear portion of the combustor 2,
A fuel pump 4, a fuel control device 5 connected to the fuel pump 4, a fuel pipe 6 connected to the fuel control device 5, a fuel nozzle 7 attached to the fuel pipe 6, and opening into an air intake duct 9 described later; It comprises a ramjet ignition device 8. These are combined with an air intake duct 9 and a fuel tank 10 containing liquid fuel to form a propulsion device.
Located at the rear. When the flying object 1 is accelerated to a supersonic speed by an auxiliary solid rocket or the like, air starts to flow into the air intake duct 9 from the front in a vigorous manner. At that time, the fuel pump 4 sucks the liquid fuel from the fuel tank 10, sends the liquid fuel to the fuel nozzle 7 attached to the air intake duct 9 through the fuel control device 5 and the fuel pipe 6, and sprays it into the airflow. When the fuel is ignited, the high-temperature gas generated in the combustor 2 is ejected backward at a high speed through the exhaust nozzle 3 to generate a forward thrust, and thereafter the ramjet ignition device 8 is stopped. Even works as a ramjet engine. Here, reference numeral 11 denotes an engine electronic control unit mounted inside the flying object 1 behind the fuel tank 10, and calculates a target value of a fuel flow rate flowing through the fuel nozzle 7 and a fuel adjustment valve opening of the fuel control unit 5. And a function of determining the operation start timing of the ramjet ignition device 8.

[0003] When flying at supersonic speed, the outer surface of the flying object 1 is aerodynamically heated, and this heat is transmitted to the inside of the flying object. Also,
A part of the heat generated in the combustor 2 is transmitted through the wall of the combustor 2 to the compartment containing the engine electronic control unit 11. Further, the engine electronic control unit 11 is self-heated by the heat generated from the internal circuit. For this reason, when the flight time is long, such as a flying object propelled by a ramjet engine, the engine electronic control unit 11 having low heat resistance malfunctions or is damaged. When other electronic devices are mounted, they are the same as the engine electronic control device. Therefore, it is necessary to cool the electronic device. When this is performed by the conventional technique, the following method can be adopted.

[0004] In the example shown in Fig. 2, the surface of the engine electronic control unit 11 is formed as a double wall, and a system is employed in which liquid fuel flows between the walls to directly cool the engine.

[0005] As another method, an air intake duct 9 is provided.
There is a system in which the air extracted from is cooled by a refrigerator (cooler) to generate low-temperature air and blown to electronic devices such as the engine electronic control unit 11.

There is also a system in which a high-pressure gas such as a nitrogen gas or a carbon dioxide gas or a liquefied gas thereof is jetted little by little to generate a low-temperature gas and blow it to electronic equipment such as the engine electronic control unit 11.

[0007]

An electronic device for preventing aerodynamic heating, heat transfer from the combustor 2 and heating of the electronic device due to self-heating of the electronic device itself when the flying object 1 flies at a supersonic speed for a long distance. In the above-described conventional method using direct cooling with the fuel, explosion-proof and double-walled electronic devices are caused, which leads to an increase in weight. Also, piping and wiring become complicated, and maintenance becomes difficult. It should be noted that the cooling efficiency is likely to be non-uniform because the entire surface of the device cannot be double-walled due to wiring reasons.

In addition, the above-mentioned conventional system using a refrigerator has a complicated structure, which leads to a narrower space for storing equipment and an increase in weight. Furthermore, the above-mentioned conventional method using a high-pressure gas or a liquefied gas requires a heavy high-pressure vessel to be mounted. In the case of a long range, it is difficult to employ a high pressure vessel, especially since it becomes large and heavy.

An object of the present invention is to provide a low-temperature air generator for a supersonic flying vehicle capable of solving the above problems.

[0010]

According to the present invention, there is provided a low-temperature air generating device for a supersonic flying object, comprising a ram air turbine for driving auxiliary equipment and using a liquid fuel for propulsion. A heat exchanger is provided for cooling the working air of the ram air turbine using liquid fuel as a cooling fluid.

[0011]

[Function] In the ram air turbine for driving auxiliary equipment,
The temperature of the working air, which has a high pressure, decreases because the working air drives the turbine to perform work. However, the working air exchanges heat with the liquid fuel in the heat exchanger, and the temperature further decreases. This low-temperature air cools electronic devices mounted on the flying object and keeps the temperature within an allowable range to prevent malfunction and destruction thereof.

Further, the temperature of the liquid fuel rises due to heat exchange with the working air, so that the liquid fuel is easily evaporated and combustion is promoted.

[0013]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described with reference to FIG. Reference numeral 1 denotes a supersonic flying object having a ramjet engine similar to that shown in FIG. 2, and includes a combustor 2, an exhaust nozzle 3, a fuel pump 4, a fuel control device 5, a fuel pipe 6,
Combustion nozzle 7, ramjet ignition device 8, fuel tank 1
0 and the engine electronic control unit 11 have the same configuration as in FIG. 2, and the description thereof will be omitted.

Inside the air intake duct 9 which is provided around the rear part of the body of the flying object 1 and opens forward and is connected to the combustor 2 of the ramjet engine, the air intake duct 9 and the air intake duct 9 fly inside. A diverter 12 for air intake is provided between the body 1 and the body, and a part of the air taken in the diverter 12 is extracted and a ram air turbine for driving the fuel pump 4 is provided. 13 is supplied to the ram
The air turbine 13 is driven. The air that has exited the ram air turbine 13 is supplied from the fuel pump 4 to a heat exchanger 14 that uses liquid fuel as a cooling-side fluid to the fuel control device 5, and the air exit side of the heat exchanger 14. Is connected to an air pipe 15 leading to the engine electronic control unit 11.

The operation of the ramjet engine in the present embodiment is substantially the same as that of the conventional flying object shown in FIG. 2, but the pressure and temperature are higher than the surrounding atmosphere by the amount corresponding to the flying speed in the diverter 12. High-pressure air is used as ram air turbine 1 for driving fuel pump 4 as working air.
3 to drive the ram air turbine 13. The air that has worked in the ram air turbine 13 is reduced in pressure and temperature, and then guided to the heat exchanger 14, where it exchanges heat with the liquid fuel sent from the fuel pump 4, and further by the liquid fuel. After being cooled, it is blown through the air pipe 15 to the engine electronic control unit 14 to cool it. The air that has been cooled in this way is discharged to the outside through gaps or the like appropriately provided on the outer surface of the flying object 1.

As described above, in this embodiment, the engine electronic control unit 14 is cooled by the low-temperature air and maintained at a temperature within an allowable range, thereby preventing malfunction and destruction of the engine electronic control unit 14. Can be prevented.

Further, the liquid fuel exchanges heat with the air by the heat exchanger 14 to increase the temperature, so that the liquid fuel is easily evaporated and the combustion in the combustor 2 is promoted.

In the above embodiment, the heat exchanger 14 is provided on the downstream side of the ram air turbine 13. However, the heat exchanger 14 may be provided on the upstream side of the ram air turbine 13. Further, the working air exiting the ram air turbine 13 for driving the fuel pump is introduced into the heat exchanger 14, but when the generator is driven by the ram air turbine, the working air is You may make it introduce | transduce into a heat exchanger. Further, the working air of the ram air turbine may be extracted from the air intake duct 9 in FIG. Further, in the above-described embodiment, the liquid fuel that has exited the fuel pump 4 is supplied to the heat exchanger 14, but if the pressure loss is small, the liquid fuel is supplied to the heat exchanger. And heat pump 4 from the heat exchanger 14
It is also possible to supply liquid fuel to the apparatus.

Although the above embodiment relates to a low-temperature air generator for a flying object flying at supersonic speed, the present invention is also applicable to a low-temperature air generator for unmanned or manned aircraft flying at supersonic speed. Needless to say, we can do it.

[0020]

In a supersonic flying vehicle that uses liquid fuel for propulsion, it is common that auxiliary equipment such as a fuel pump is driven by a ram air turbine. The working air, whose temperature is lowered by the work, is further subjected to heat exchange with liquid fuel to lower its temperature to become low-temperature air. Therefore, this low-temperature air can be used for cooling electronic devices and the like. As described above, according to the present invention, with a simple configuration in which a heat exchanger and its piping are simply added to a conventional apparatus, it is possible to cool and effectively utilize air that has been conventionally wasted to the outside.

Further, the liquid fuel exchanges heat with the working air of the ram air turbine and the temperature thereof rises, so that the liquid fuel tends to evaporate and the combustion is promoted.

[Brief description of the drawings]

FIG. 1 is a side sectional view of one embodiment of the present invention.

FIG. 2 is a side sectional view of a conventional supersonic flying object.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Flying object 2 Combustor 3 Exhaust nozzle 4 Fuel pump 5 Fuel control device 6 Fuel pipe 7 Fuel nozzle 8 Ram jet igniter 9 Air intake duct 10 Fuel tank 11 Engine electronic control device 12 Divertor 13 Ram air turbine 14 Heat Exchanger 15 Air piping

Claims (1)

(57) [Claims] 1. A supersonic vehicle having a ram air turbine for driving auxiliary equipment and using liquid fuel for propulsion,
A low-temperature air generator for a supersonic flying object, comprising a heat exchanger for cooling the working air of the ram air turbine using the liquid fuel as a cooling fluid.