JPH0495600A - Airplane body - Google Patents

Abstract

PURPOSE:To reduce a fuselage leeward separation area and lighten the extent of cross-wind resistance as well as to make the effectiveness of a flap and so on by installing some through holes installed in making the atmosphere flowable through from one side to the other side of the circumference of a fuselage, in an airplane body. CONSTITUTION:Both symmetrical through holes 6 pierced through with piping are installed in a fuselage 1 of aircraft, and with these through holes 6, a uniform air current of energy is made feedable to a leeward separation area at a time when the aircraft receives a cross wind. These holes 6 are good even at a right angle to a longitudinal shaft of an airframe, or may be tilted to some extent. A cover is installed in each port of these holes 6 thereby making them free of opening or closing. With this constitution, when a plane body flies at a skid angle, a uniform air current of energy is fed to the leeward separation area by an air current passing through these holes 6, reducing the extent of the separation area, and thereby a flap, an apron 4 or a tip fin 3 (a vertical tail plane at a main plane end) all come out of the separation area, through which inherent 'effectiveness' is made so as to be brought into full play.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to aircraft bodies such as aircraft and flying objects that fly in the atmosphere.

[Conventional technology] A conventional aircraft will be explained based on FIG.

When an aircraft receives a crosswind during flight or when the nose direction of the aircraft is at an angle with the flight direction, a separation area 11 occurs on the leeward side of the fuselage l due to the influence of the large fuselage 1. When the airflow separates, the flow in that area becomes highly turbulent, and the airflow velocity is not uniform in direction. The average flow velocity also decreases, and in extreme cases, the airflow moves with the aircraft and the airflow velocity relative to the aircraft decreases to zero, in what is called a dead water region.

When the aircraft's control surfaces (flats, ailerons, etc. 4) and stabilizers (vertical tail, tip fins 3, etc.) are located in this separation area, the relative airflow velocity to these is almost zero and the airflow is turbulent. The "effectiveness" of the steering surface and stabilizer plate decreases, and in the worst case, the "effectiveness" disappears.

In particular, in the tip fin type in which the vertical stabilizer is attached to the tip of the main wing 2, the chimp fin 3, which is included in the separation area on the leeward side, has no effect on the directional stability of the aircraft, and has no effect on the aircraft stability. This results in a decline in performance and poses a problem to the aerodynamics of the aircraft.

In addition, in the figure, 5 is a ladder.

[Problem to be solved by the invention]

The above-mentioned conventional aircraft had the following problems to be solved.

(1) Reduced separation area on the leeward side of the fuselage during crosswinds.

(2) Reduction of aerodynamic drag caused by the fuselage during crosswinds.

(3) Decrease in the structural weight of the fuselage.

First, the above item (1), reduction of the peeled area, will be explained with reference to FIG. 4.

Generally, when an aircraft is flying with a sideslip angle (when the nose direction and the flight direction do not match), the leeward side ricochet area 11 of the successor structure occurs. In this area of separation,
Since the airflow is turbulent and the airflow velocity relative to the fuselage is low, the effectiveness of the aerodynamic elements in this area (parts that can generate aerodynamic effects such as flaps and vertical tails) decreases. By opening the left and right through holes 6 and minimizing the size of the separation area formed on the leeward side to form a small separation area 12, the aerodynamic elements can be positioned outside the separation flow and their "effectiveness" can be ensured. Therefore, measures are required to reduce the peeled area.

Next, the above item (2) aerodynamic resistance will be explained with reference to FIG.

, the aerodynamic drag of an object depends, of course, on its shape. Generally, the greater the degree of obstruction of the airflow, the greater the resistance. Conversely, the less the object disturbs the -like airflow, such as by having a through hole, the lower the resistance will be. fuselage 1
Even in the combination of the main wing 2 and the main wing 2, by opening the left and right through holes 6 in the fuselage l, the degree of disturbance of the -like airflow is greatly reduced, and aerodynamic drag is reduced.

Regarding the reduction in structural weight in item (3), it is clear that the weight is reduced by reducing the number of fuselage skins used. In addition, aircraft generally consist of a frame structure that provides strength and a skin panel that adjusts the external shape, but by simply removing this skin panel and making minor modifications, the desired purpose can be achieved. . Since it is thought that there will be no large increase in aerodynamic load by removing the outer skin, there is no need for reinforcement, etc., and in the end,
Structural weight is reduced.

In view of the above requirements, an object of the present invention is to provide an aircraft that reduces the separation area on the lee side of the fuselage, reduces crosswind resistance, improves the effectiveness of flaps, etc., and reduces the weight of the aircraft. It is.

[Means to solve the problem]

As a solution to the above problem, the present invention provides an aircraft body such as an aircraft or a flying object that flies in the atmosphere, which is provided with a through hole provided to allow the atmosphere to flow from one side of the outer circumference of the fuselage to the other side. The purpose of the present invention is to provide an aircraft body characterized by the following characteristics.

[Function] Since the present invention is configured as described above, it has the following function.

That is, since the through holes are provided from one side to the other side of the outer circumference of the fuselage, when the aircraft flies with a sideslip angle, the air and flow passing through the left and right through holes create a uniform airflow in the separation area on the lee side. Energy is supplied to reduce the size of the stripped M region. As a result, the flange, ailerons, or tip fins (vertical tail fins at the tips of the main wings) move outside of the separation area, allowing them to exhibit their original effectiveness. (
Flaps and the like in the 9M range lose their "effectiveness" due to the decrease in airflow velocity at -a. ) Also, the airflow passing through the fuselage reduces the occlusion effect of the fuselage on the uniform airflow, thereby reducing the aerodynamic drag of the fuselage.

〔Example] A first embodiment of the present invention will be described with reference to FIG.

Note that the same reference numerals are given to the same constituent members as in the conventional example, and the explanation thereof will be omitted.

FIG. 1 is a perspective view of the aircraft of this embodiment. In the figure, left and right through holes 6 are provided in the fuselage 1 of the aircraft, through which piping passes. The left and right through holes 6 supply uniform airflow energy to the separation area on the lee when the aircraft receives a crosswind.

The larger the diameter of the left and right through holes 6 is, the more desirable it is from an aerodynamic point of view, but the maximum diameter is restricted from the viewpoint of the structure. The left and right through holes 6 may be perpendicular to the longitudinal axis of the fuselage or may be oblique. A cover is provided at the entrance and exit of the left and right through holes 6, and is configured to be opened and closed freely. However, the lid is not shown.

Next, a second embodiment of the present invention will be described with reference to FIG.

In this embodiment, the left and right through holes 6 using the piping of the first embodiment are
Instead of the left and right through holes 6, the fuselage 1 has a completely open structure.
a. However, when a strength member is required in the left and right through holes 6a, a truss-shaped frame structure 7 as shown in the figure is provided. The left and right through holes 6a having a large opening structure equalize the airflow on the left and right sides of the fuselage 1 when the aircraft takes a sideslip angle, thereby reducing the separation area on the leeward side.

A lid is provided at the entrance/exit part (body side) of the left and right through holes 6a,
It is used with the lid open during flight. Close the lid if the flight conditions are such that opening it would cause problems. However, the lid is not shown.

Next, a third embodiment of the present invention will be described with reference to FIG.

This embodiment is an example of a flying object, and as shown in the figure, left and right through holes 6c are provided in the c-c section of the fuselage 1a in the direction of arrows, as in the case of an aircraft, and the left and right through holes 6c that connect to the left and right sides of the fuselage 1a are provided. Ensure the effectiveness of the wings. However, in the case of a flying object, since the concept of the upper and lower parts of the aircraft is weak, upper and lower through holes 6b are also provided in addition to the left and right through holes 6c. The upper and lower through holes 6b serve to ensure the effectiveness of the dorsal (upper) wing when the flying object flies at a large angle of attack.

In addition, since the length of the fuselage 1a of a flying object is longer than that of an aircraft, the left and right through holes 6c and the upper and lower through holes 6b are not only placed at the positions where they join the front wings 8 or the rear wings 9, but also are located closer to the fuselage than the aircraft. It is also effective to place it near the head.

Alternatively, it may be provided on both the front wing 8 portion and the rear wing 9 portion of the flying vehicle, or it may be provided on only one of them.

As described above, according to the first to third embodiments, the left and right through holes 6, 6a6c and the upper and lower through holes 6b are provided in the fuselage 1 of the aircraft and the fuselage 1a of the flying object. or when flying with a slip angle,
This has the advantage that the separation area on the leeward side becomes smaller, reducing air resistance and improving the effectiveness of aerodynamic elements such as flaps. Furthermore, the large left and right through holes 6a have the advantage of reducing the weight of the machine.

(Effects of the Invention) Since the present invention is configured as described above, it has the following effects.

(1) When an aircraft is flying with a sideslip angle, by reducing the size of the separation area formed on the leeward side of the fuselage, the reduction in the effectiveness of aerodynamic elements such as flaps and tip fins is suppressed; Good aerodynamic characteristics (mainly lateral and directional stability and maneuverability) can be ensured.

(2) The left and right through holes provided in the fuselage create airflow that passes through the fuselage, reducing the aerodynamic drag of the fuselage.

(3) By removing the outer skin of the fuselage, the number of parts in the fuselage is reduced, and the weight of the aircraft can be reduced.

[Brief explanation of drawings]

FIG. 1 is a perspective view of the first embodiment of the present invention, FIG. 2 is a perspective view of the second embodiment of the present invention, and FIG. 3 is a view of the third embodiment of the present invention, where (a) is a side view. Figure 4: (b) is a cross-sectional view taken along the line bb in (a), (c) is a cross-sectional view taken along the line c-c in (a), and Figure 4 shows separation on the leeward side of the fuselage in a typical airplane body cross section. This is an explanatory diagram regarding the area, (a) is a comparison diagram when there is no left and right through hole 6, (b) is a comparison diagram when there is, and FIG. , (a) is when there is no through hole, (b) is when there is a through hole, (c) is when there is a flat plate and there is no through hole, (d) is when there is a flat plate and there is a through hole. FIG. 6 is a diagram of a conventional example, where (a) is an overall perspective view, and (b) is a cross-sectional view passing through the king wing of (a). 1.1a...fuselage, 2...main wing. 3...Tip fin 4...Flap or aileron. 5... Rudder, 6.6a, 6c...
Left and right through holes 6o...Upper and bottom through holes, 7... Frame structure (truss). 8...front wing, 9...rear wing.

Claims (1)

[Claims] An aircraft body, such as an aircraft or a flying object, which flies in the atmosphere, is characterized by having a through hole provided to allow the atmosphere to flow from one side of the outer periphery of the fuselage to the other side.