JPH07323898A - Infrared ray radiation reducing device for airplane - Google Patents

Abstract

PURPOSE:To reduce radiation of infrared rays due to engine exhaust of an airplane. CONSTITUTION:When a pilot switch 1 is operated, coolant from a pressure accumulator 3 is injected to engine exhaust of an airplane from an injection nozzle 5, and a temperature of the engine exhaust is lowered, and consequently, radiation of infrared rays is reduced. On the other hand, a swirl is generated in the flow of the engine exhaust, so that the engine exhaust is mixed with low temperature air around the airplane body so as to be diffused, and the temperature of the engine exhaust is lowered, and as a result, radiation of the infrared rays is reduced.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft infrared radiation reducing apparatus for reducing infrared rays due to exhaust from an engine of an aircraft.

[0002]

2. Description of the Related Art In recent years, the development of aircraft and flying vehicles that detect infrared rays to detect and eliminate threats has been remarkable. In particular, an aircraft equipped with a jet engine has a weak point that is found by an aircraft or a flying body having a device for detecting infrared rays because the engine exhaust has a high temperature.

On the other hand, in the latest aircraft, the amount of infrared radiation is reduced by adopting a two-dimensional nozzle, shielding high temperature parts, etc., but this is not sufficient.

Further, in flight of an aircraft, the engine output is squeezed to lower the exhaust temperature, the aircraft is evaded in a cloud where infrared transmission is poor, and a high temperature dummy is dropped to disturb the threat. However, there are problems that the performance of the aircraft is deteriorated, the weather conditions that can be used are limited, and the number of dummies that can be mounted is limited. It was

The present invention has been made in view of the above, and it is an object of the present invention to provide an infrared ray emission reducing device for an aircraft, which effectively reduces infrared rays due to engine exhaust.

[0006]

The infrared radiation reducing apparatus for an aircraft according to the present invention has the following means. (1) A coolant supply source, a coolant injection nozzle for the engine exhaust, and a coolant control means provided in a line connecting the coolant supply source and the injection nozzle are provided. (2) A vortex generator provided in a flow path of the engine exhaust to generate a vortex in the flow of the engine exhaust. (3) In the infrared radiation reducing device for an aircraft according to (2), a thrust deflection nozzle controlled by a first control device to change a direction of engine exhaust, and a vortex generation signal received from the first control device. It is characterized in that a second control device for controlling the device is provided.

[0007]

In the present invention (1), the coolant is supplied from the coolant supply source to the coolant injection nozzle by the cooling control means and is injected into the engine exhaust. This cools the engine exhaust to a lower temperature and reduces infrared radiation.

In the present invention (2), a vortex is generated in the engine exhaust flow by the vortex generator. Due to the vortices generated in the flow of the engine exhaust, the engine exhaust is mixed with the low temperature air around the airframe and diffused, the temperature of the engine exhaust is rapidly lowered, and infrared radiation is reduced.

According to the present invention (3), in addition to the operation of the present invention (2), the vortex generator is controlled according to the position of the thrust deflection nozzle that changes the direction of engine exhaust, and the engine from the thrust deflection nozzle is controlled. The vortex generator is controlled in accordance with the direction in which the exhaust gas is ejected to effectively generate a vortex in the engine exhaust gas and to effectively reduce infrared radiation.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described with reference to FIG.

Reference numerals 1 and 3 are a pilot switch and a pressure accumulator, respectively, which are provided inside the body of the aircraft. A refrigerant such as liquid nitrogen is contained in the pressure accumulator 3, and the pressure accumulator 3 is
It is connected via piping 6 to a plurality of injection nozzles 5 that open to an engine exhaust portion 4 of a jet engine or the like. The refrigerant control valve 2 provided in the pipe 6 is connected to the pilot switch 1, controlled by the pilot switch 1, and opened / closed by turning on / off the pilot switch.

In this embodiment, when the pilot turns on the pilot switch 1, the refrigerant control valve 2 is opened, and the refrigerant in the pressure accumulator 3 is injected from the injection nozzle 5 into the engine exhaust in the engine exhaust section. This cools the hot engine exhaust, lowering its temperature and reducing infrared emissions.

When infrared radiation is not required, the pilot can turn off the pilot switch 1 and close the cooling control valve 2 to save the amount of refrigerant consumed.

A second embodiment of the present invention will be described with reference to FIGS.
Explained by. In FIG. 2, reference numeral 11 is a pilot switch provided inside the body of the aircraft. 16, 16
Is a thrust deflection nozzle that is provided in an engine exhaust portion such as a jet engine at the rear of the aircraft body, and the rear portion of the thrust deflection nozzle is arranged in pair so as to project rearward from the aircraft body. By rotating the rear end 16 about a horizontal axis at the front end so as to move the rear end in the vertical direction, the direction of engine exhaust can be changed to change the direction of thrust.

As shown in FIGS. 2 and 3, a plurality of plates 15 and 15 are arranged in the engine exhaust portion of the airframe at a distance from each other across the engine exhaust flow.
The left and right vortex generators are composed of a plurality of plates 15a.
Is capable of rotating from a position parallel to the flow of engine exhaust to a position angled to that flow. Vortex generator 1
5 is disposed immediately upstream of each thrust deflection nozzle 16 and is provided so as to be paired with the upper surface and the lower surface of the engine exhaust portion of the machine body. Therefore, as shown in FIG. 2, in this embodiment having two thrust deflection nozzles 16 on the left and right, four vortex generators 15 are provided on the top, bottom, left and right.

Reference numerals 13 and 13 are first control devices for operating the left and right thrust deflection nozzles 16 and 16, and 12 is a second switch to which signals from the pilot switch 11 and the first control devices 13 and 13 are input. A control device, and the control device 12
Outputs the signal to the actuators 14, 14 for operating the vortex generators 15, 15.

In this embodiment, when it is not necessary to reduce the infrared radiation, the pilot switch 11 is turned off, and a plurality of plates 15a of the vortex generator 15 are connected to the exhaust gas of the engine as shown in the upper portion of FIG. Make it parallel to the flow. Therefore, the engine exhaust 1 ejected from the thrust deflection nozzle 16
No vortex is generated in the flow of 7.

When reduction of infrared radiation is required,
The pilot turns on the pilot switch 11 (P _{1 in} FIG. 3) and the signal is input to the second control device 12, whereby the thrust deflection nozzle 16 is operated.
The signal of the position of the thrust deflection nozzle 16 is input from the control device 13 of FIG. 2 to the second control device 12 (P _{2 in} FIG. 3). In the second controller 12, the vortex generator 15 to be operated is determined based on the signal from the first controller 13 (P _{3 in} FIG. ₃ ), and the signal is output to the actuators 14, 1
4 (P _{4 in} FIG. 3).

Therefore, the plate 15a of the vortex generator 15 which is determined to be activated by the second controller 12 is as shown in FIG.
As shown in the lower part of FIG. 1, a vortex 18 is generated in the engine exhaust flow at an angled position with respect to the engine exhaust flow. Since the engine exhaust 17 in which the vortex 18 is generated is ejected from the thrust deflection nozzle 16, mixing and diffusion with the surrounding low temperature air is promoted, and the temperature of the engine exhaust abruptly decreases to cause infrared rays. Radiation can be reduced. Also, as described above, the vortex generator 15 to be operated is operated.
Is determined by the position of the thrust deflection nozzle 16, so that any or all of the left and right vortex generators 15 and the upper and lower vortex generators 15 can be operated appropriately according to the deflection direction of the thrust deflection nozzle 16, and it is effective during engine exhaust. The vortex 18 can be generated in

Further, in this embodiment, takeoff and landing, ascent and descent,
If you do not need to reduce infrared radiation such as cruising,
By deactivating the vortex generator 15, it is possible to prevent an increase in resistance due to a vortex and prevent a decrease in fuel consumption.

[0021]

As described above, according to the present invention, the refrigerant is injected to the engine exhaust, or vortices are generated in the flow of the engine exhaust to mix and diffuse with the air around the airframe to be discharged outside the airframe. The temperature of the generated engine exhaust can be rapidly lowered, which can effectively reduce infrared radiation from the aircraft.

[Brief description of drawings]

FIG. 1 is an explanatory diagram of a first embodiment of the present invention.

FIG. 2 is a perspective view of a second embodiment of the present invention.

FIG. 3 is a plan view of a main part of the main part of the second embodiment.

FIG. 4 is a flowchart of control in the second embodiment.

[Explanation of symbols]

 1 Pilot Switch 2 Refrigerant Control Valve 3 Accumulator 4 Engine Exhaust Section 5 Injection Nozzle 6 Piping 11 Pilot Switch 12 Second Control Device 13 First Control Device 14 Actuator 15 Vortex Generator 15a Vortex Generator Plate 16 Thrust Deflection Nozzle 17 Engine Exhaust 18 Vortex

Claims (3)

[Claims] 1. An aircraft comprising: a coolant supply source; a coolant injection nozzle for ejecting the engine exhaust gas; and a coolant control means provided in a line connecting the coolant supply source and the injection nozzle. Infrared radiation reduction device. 2. An infrared radiation reducing apparatus for an aircraft, comprising: a vortex generator provided in a flow path of engine exhaust to generate a vortex in a flow of engine exhaust. 3. A thrust deflection nozzle controlled by a first controller to change the direction of engine exhaust, and the first controller.
The infrared radiation reducing device for an aircraft according to claim 2, further comprising a second control device that controls the vortex generator by receiving a signal from the control device.