JP2002193193A - Radiator structure for unmanned helicopter - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide radiator structure that can obtain an engine cooling effect effective in every flying state in an unmanned helicopter flying in all directions changing the flight attitude and hovering. SOLUTION: In this radiator structure for the unmanned helicopter 1 provided with an engine in a body 3 covered with a body cover 2, and a radiator through which cooling water of the engine 4 is circulated, a first radiator 11 is arranged in a body cover opening 2A provided on the upper side of the front part of the body 3, and a first bleeder 13 communicating the inside and outside of the body is provided on the lower side of the front part of the body and in a position below the first radiator 11. A second radiator 15 with the wind receiving face placed almost vertically is provided on the lower side of the front part of the body, and a second bleeder 14 is provided at the body cover 2 behind the engine 4.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a radiator structure for radiating cooling water of an unmanned helicopter equipped with a water-cooled engine.

[0002]

2. Description of the Related Art A conventional radiator of an unmanned helicopter is mounted below a main rotor on the front upper surface of an airframe, and receives wind from the main rotor to radiate cooling water.

[0003]

However, the unmanned helicopter flies in a hovering state or in front-to-back and left-right directions while keeping the direction of the body constant, and the flight direction changes, and the flight attitude changes accordingly. For this reason, the wind direction received by the radiator changes, which affects the heat radiation effect. In particular, in the case of a high-speed forward flight in which the engine output is large and the calorific value is large, or in a reverse flight in which the amount of outside air passing through the radiator arranged forward is small, the radiator may not be able to sufficiently cool the cooling water.

The present invention has been made in consideration of the above-mentioned prior art, and relates to an unmanned helicopter that flies back and forth, right and left by changing a flight attitude, stops in the air, and increases or decreases an engine output according to a flight speed or a mounted weight. It is an object of the present invention to provide a radiator structure that can provide an effective engine cooling effect in all flight conditions.

[0005]

According to the present invention, there is provided a radiator structure for an unmanned helicopter having an engine in a body covered with a body cover and a radiator through which cooling water for the engine circulates. ,
A first radiator is disposed in a body cover opening provided on an upper side of a front part of the fuselage, and a first ventilation port communicating between the inside and the outside of the body at a position below the first radiator at a lower part of the front part of the fuselage. An unmanned helicopter, wherein a second radiator having a substantially vertical wind receiving surface is provided on a lower side of the front part of the fuselage, and a second ventilation port is provided on a body cover behind the engine. Provide a radiator structure.

According to this configuration, the wind of the main rotor is received from above, particularly during hovering or low-speed flight, and the wind is guided into the airframe by communicating with the first radiator on the upper side of the front of the airframe. A sufficient heat radiation effect can be obtained by escaping from the air vent of the first radiator, and the second radiator receives sufficient wind from the vertical wind receiving surface during a high-speed forward flight particularly requiring cooling capacity. A heat radiation effect can be obtained. The wind received by this second radiator
When the second radiator is provided outside the body, the heat of the radiator is radiated to the outside by passing through the radiator as it is. When the second radiator is disposed inside the body (the front end surface of the body), the wind received by the second radiator flows through the inside of the body and is released from the second ventilation port behind the engine. In this case, since the second vent is provided at the rear of the engine, the air flowing from the front end face of the aircraft can be used to ventilate the interior of the aircraft and to further cool around the engine, particularly during high-speed forward flight in a high-power operation state. .

During backward flight, on the contrary, air flows into the airframe through the second vent, and this air passes through the first radiator and escapes to the outside of the airframe, thereby releasing heat from the first radiator. . When the second radiator is arranged in the body (front end surface of the body), the air that has flowed into the body during the reverse flight passes through the second radiator together with the first radiator to cool it.

In a preferred configuration example, the second radiator is provided outside the body.

According to this configuration, since the second radiator is provided outside the body outside the body cover, the outside air is sufficiently circulated in both the forward flight and the reverse flight, and a large heat radiation effect is obtained.

In another preferred configuration example, the second radiator is provided on a front end surface of the fuselage such that a back surface thereof faces the inside of the fuselage.

According to this configuration, since the second radiator is provided in the airframe, the flight resistance is reduced, and the distance between the first and second radiators is shortened. Is simplified. In addition,
The term “inside the body” includes that the radiator is exposed to the front end surface of the body and is attached to the body cover such that the back of the radiator faces the inside of the body.

[0012]

Embodiments of the present invention will be described below with reference to the drawings. FIG. 1 is an overall configuration diagram of an unmanned helicopter according to an embodiment of the present invention, in which the fuselage is cut away, and FIGS. 2, 3 and 4 show the hovering, high-speed forward and reverse, respectively. It is explanatory drawing which shows the flow of wind.

As shown in FIG. 1, an unmanned helicopter 1 has an airframe 3 covered with a body cover (shroud) 2.
A water-cooled engine 4 and a transmission 5 connected to the engine 4 are provided in the body 3. 6 is an exhaust pipe. A main rotor 8 connected to the transmission 5 via a rotor shaft 7 is provided above the body 3. A skid 12 that contacts the ground when landing is provided at the lower part of the body 3. At the rear end of the body 3 is provided a tail rotor 10 that is rotationally driven from a transmission 5 via a belt (or chain) 9.

The upper side of the front of the body 3 (ie, the body 3
An opening 2A is provided in the body cover 2 (a portion facing upward above the axis C passing through the tip), and the first radiator 11 is fitted and mounted in the opening 2A. Therefore, the wind receiving surface 11a of the first radiator 11
It faces upward slightly obliquely downward along the body shape, and receives wind from the main rotor 8.

In this case, the radiator 11 may come out above the surface of the surrounding body cover 2 depending on the state of attachment to the peripheral edge of the opening 2A of the body cover 2, or as shown in FIG. Side (back side). In any case, the radiator 11 is arranged in the opening 2A so that the air passing through the opening 2A also passes through the radiator 11. In the present embodiment, the radiator 11 is provided along the body shape, that is, along the shape of the body cover 2 at a position on the upper side (above the axis C) of the front part of the body.

The body cover 2 that covers the body cover 2 located below the first radiator 11 (ie, the lower side of the body 3 (below the axis C)), and the body cover 2 located below the radiator 11 One vent 13 is provided. A second vent 14A is provided in the body cover 2 on the upper surface side of the body 3 behind the transmission 5 connected to the engine 4. This second vent 1
4A may be provided on both left and right sides of the body 3. Further, the rear of the transmission 5 is left open without closing the body cover 2, and a third vent 14B is formed.

In the present embodiment, the second radiator 1 is mounted on the outside of the body at the lower side of the front of the body 3 (below the axis C).
5 is attached with its wind receiving surface 15a substantially vertical. In the illustrated example, the mounting position of the second radiator 15 is below the front end of the first radiator 11. The second radiator 15 is connected to the first radiator 15 through a communication pipe 16.
Is connected in series with the radiator 11.

Such first and second radiators 1
The flow of air passing through 1, 15 is shown in FIGS. At the time of hovering, as shown in FIG. 2, the wind from the main rotor 8 blows from above to the first radiator 11 as shown by an arrow D, passes through the first radiator 11, and circulates through the airframe as shown by an arrow E. It blows through the lower first vent 13 as shown by the arrow F. In this case, the second radiator 15
Hardly any winds flow through.

As shown in FIG. 3, when the wind from the main rotor 8 is combined with a part of the wind from the front with respect to the fuselage 3, the first radiator 1
1, passes through the airplane, flows through the airframe as indicated by an arrow I, and blows through the second and third vents 14A and 14B behind the engine as indicated by an arrow J. At the time of high-speed forward movement, the wind of the arrow G leans forward (approaches horizontal), and more wind from the front of the aircraft, as indicated by the arrow H,
The air blows onto the second radiator 15 from almost the front, passes through it, and blows through as indicated by the arrow K.

At the time of reverse travel, as shown in FIG. 4, wind flows into the body from the second ventilation port 14A and the third ventilation port 14B as shown by the arrow L, and flows through the body as shown by the arrow M. From the first radiator 11 as shown by the arrow N.
Further, in this case, the wind from behind hits the second radiator 15 as shown by the arrow O, passes through it, and blows forward as shown by the arrow P. In particular, wind from the main rotor 8 is also introduced from the second vent 14A.

FIG. 5 shows the first and second radiators 1
It is a perspective view of 1,15. The first and second radiators 11 and 15 connected in series by the communication pipe 16 communicate with a cooling jacket (not shown) of the engine via a cooling water hose 17, and cooling water is supplied by a water pump (not shown). Circulates like an arrow. By connecting the first and second radiators 11 and 15 in series in this manner, the piping structure is simplified and the radiators 11 and 1 are efficiently connected.
Heat can be released from the cooling water passing through the cooling water 5 to cool it.

The linear three-way valve 3 is provided in the middle of the communication pipe 16.
0, and when the engine output is high, such as during high-speed forward movement in response to the engine output, most of the cooling water flows from the upstream communication pipe 16A to the downstream communication pipe 16B, and when hovering or descending flight When the engine output is low, the opening position control of the linear three-way valve 30 may be performed so as to increase the flow rate of the cooling water from the upstream communication pipe 16A to the cooling water hose 31 for branch return. The cooling water hose 31 with the cooling water hose 17 on the downstream side of the radiator 15 merges and returns to the cooling water jacket of the engine.

FIG. 6 is a front view of the unmanned helicopter according to the present invention. As shown, the second of the above-described example of FIG.
The radiator 15 is provided further below the body cover 2 on the lower side of the fuselage. Instead of this position, second radiators 18 may be provided on the left and right sides on the outside of the fuselage as shown by A in FIG. Alternatively, as shown by B, a second radiator 19 may be provided on the front end face of the fuselage (an embodiment of FIG. 7 described later). In this case, the first radiator 11 and the second radiator 19 may have a continuous and integral structure (an embodiment of FIG. 8 described later). In each case, the second radiators 15, 18, 19 are below the axis C of the tip of the fuselage. 6 is a third vent 14B behind the transmission 5.

FIG. 7 shows another embodiment of the present invention. In this embodiment, the second body cover 2 is provided on the front cover of the body.
The second radiator 19 is attached to the inside of the machine (the front end surface of the machine 3) with the wind receiving surface 19a substantially vertical to the opening 2B. The arrangement of the first radiator 11 and other configurations are the same as those in the example of FIG. 1 described above. Thus, the second radiator 19 is connected to the second opening 2B.
By arranging it inside the body of the section, the piping structure such as the communication pipe 16 and the cooling water hose is simplified, and the flight resistance is reduced.

FIG. 8 shows still another embodiment of the present invention. In this embodiment, the opening 2A extends from the upper surface of the fuselage to the front surface, and the second radiator 20 is provided integrally with the first radiator 11 by being bent in an L-shape at the front end thereof. is there. According to this configuration, the first and second
A communication pipe for communicating the radiators 11 and 20 with each other is not required, and the piping structure is further simplified. The other configuration and operation and effect are the same as those of the embodiment of FIG.

Since the second radiators 19 and 20 are attached to the front end surfaces of the inside of the airframe, the wind flows in the embodiments shown in FIGS. 7 and 8 pass through the second radiators 19 and 20 when the vehicle is moving forward and backward. The flow is the same as the flow shown in FIGS. 2 to 4 except that the flowing air flows through the airframe.

[0027]

As described above, according to the present invention, the first radiator on the upper surface of the front part of the fuselage receives the wind of the main rotor from above, particularly during hovering and low-speed flight, and allows it to escape from the first ventilation port. As a result, a sufficient heat radiation effect can be obtained, and the second radiator receives a wind from the vertical wind receiving surface from the front in order to obtain a sufficient heat radiation effect, particularly during a high-speed forward flight requiring cooling capacity. it can.
By providing the second radiator in this manner, the heat radiation effect is enhanced in all flight conditions, and the engine can be sufficiently cooled to achieve stable flight.

[Brief description of the drawings]

FIG. 1 is an overall configuration diagram of an unmanned helicopter according to an embodiment of the present invention.

FIG. 2 is an explanatory diagram of an air flow at the time of hovering in the embodiment of FIG. 1;

FIG. 3 is an explanatory view of an air flow at the time of high-speed forward movement in the embodiment of FIG. 1;

FIG. 4 is an explanatory diagram of an airflow at the time of reverse travel of the embodiment of FIG. 1;

FIG. 5 is a perspective view of the radiator of FIG. 1;

FIG. 6 is a front view of the unmanned helicopter of FIG. 1;

FIG. 7 is an overall configuration diagram of another embodiment of the present invention.

FIG. 8 is an overall configuration diagram of still another embodiment of the present invention.

[Explanation of symbols]

1: unmanned helicopter, 2: body cover, 2A: opening, 2B: second opening, 3: body, 4: engine, 5:
Transmission, 6: exhaust pipe, 7: rotor shaft, 8:
Main rotor, 9: belt, 10: tail rotor, 1
1: first radiator, 11a: wind receiving surface, 12: skid, 13: first vent, 14A: second vent, 1
4B: third vent, 15: second radiator, 15
a: wind receiving surface, 16: communication pipe, 16A: upstream communication pipe,
16B: downstream communication pipe, 17: cooling water hose, 18: second radiator, 19: second radiator, 19a: wind receiving surface, 20: second radiator, 30: linear three-way valve, 31: cooling water hose.

Claims (3)

[Claims] A radiator structure for an unmanned helicopter having an engine inside a body covered with a body cover and a radiator through which cooling water for the engine circulates, wherein a body cover opening provided on an upper side of a front part of the body is provided with a second cover. A first radiator is provided, a first ventilation port is provided below the first radiator at a lower side of the front of the fuselage and below the first radiator, and a wind receiver is provided at a lower side of the front of the fuselage. 2nd surface almost vertical
A radiator structure for an unmanned helicopter, comprising: a radiator according to claim 1; 2. The radiator structure of an unmanned helicopter according to claim 1, wherein said second radiator is provided outside a body of the vehicle. 3. The radiator structure for an unmanned helicopter according to claim 1, wherein the second radiator is provided on a front end surface of the fuselage such that a back surface faces the inside of the fuselage.