KR200334568Y1 - Air vehicle with horizontal tailing of back of the body - Google Patents

Abstract

The present invention relates to a plane in which the distance between the main wing and the horizontal wing is close, and even when flying at low speed with the nose lifted, the turbulent wake of the main wing does not affect the horizontal wing. It is designed for the horizontal tail wing that can be placed under the wing and receive the flow of air without passing through the main wing. This design allows the vehicle to stabilize, thereby providing the shape of the vehicle having the effect of achieving stable flight posture maintenance and balance.

Description

Air vehicle with horizontal tailing of back of the body

The present invention relates to an ultra-small plane, and more particularly, having a lower horizontal tail wing that can prevent the tail wing from being degraded by turbulence generated by the main wing even when flying at low speed with a rider. It's about a micro airplane.

Research on Micro Air Vehicles (MAVs) began in the early 1990s at the Lincoln Laboratory at the Massachusetts Institute of Technology (MIT) with the concept of micro systems at RAND, USA.

Subsequently, the military's potential for the use of ultra-small aircraft, which was undertaken by the University's own research at the Georgia Tech Research Institute (GTRI) in 1994, increased active funding from the Defense Advanced Research Projects Agency (DARPA), NASA, and other research institutions. Many studies have been conducted to date.

In Table 1, the definition of a fixed-wing subminiature aircraft (MAV), or miniature airplane, whose wings were fixed to the fuselage, officially announced by DARPA in 1997, is shown in Table 1.

Specifications Micro Aircraft (MAV) Maximum size 6-15 cm Gross weight 10-100 g Payload 1-18 g Total flight time 20 to 60 minutes Cruise speed 30-65 km / h Range 1-10 km shape Fixed wing

Such micro airplanes can be used for various purposes by mounting various payloads such as micro CCD cameras. Especially, the military can scout restricted areas that are not easily accessible to the military, measure biochemical and radioactive contamination, and detect and monitor them. It is evaluated to be of great use for military purposes, such as transmitting information in real time. In addition, traffic or environmental violations can be monitored or detected, and traffic congestion can be identified, air pollution status can be observed, survivors can be identified in disaster areas due to fire or building collapse, pollution levels can be investigated, crop pests can be investigated and crop predictions can be made. It is estimated that it will have great utility value for civilian use such as tracking the movement of wild animals and combating harmful insects, and various studies for practical use are being actively conducted.

As shown in Table 1, the micro airplane requires a much smaller size than the level of a model airplane that is simply a miniature airplane. In other words, micro airplanes are by no means a reduced form of large airplanes, so traditional airplane design methods such as stuffing the shell can no longer be applied to micro airplanes.

As a result of the advances in microtechnology known as micro electromechanic systems (MEMS), microplanes have become more prominent in their technological feasibility and innovative technological solutions for aerodynamics, control, propulsion and power, aviation and communications. The study of must be preceded.

In recent years, the propulsion and power problems for micro airplanes have been solved, and have reached a stage where there is no problem in achieving the purpose of simple flight. However, there remains a problem of how to stabilize the micro airplane, which is a very unstable aircraft in an external situation. In other words, it is of interest to secure stable attitude control and maneuverability of ultra-small aircraft.

In other words, in an extremely small and light aircraft having a small inertia, the flight posture can be easily affected by unstable flow caused by movement such as a gust of wind and a turning of an airplane. Because it can have fatal consequences, it is an important problem to be solved before practical use.

In general, an airplane is a general term for an aircraft flying by using a lift generated on a wing fixed to a fuselage with a propulsion device.

As shown in FIG. 1, the fixed wing type micro airplane is composed of a fuselage 1 and a wing, which are largely main bodies, similar to a general airplane, and in detail, the wings are fixed to the center of gravity of the fuselage. Main wing 150, which serves to support the weight of the fuselage in the air by generating lift by thrust generated by the thrust, and the excrement that is fixed to the rear of the fuselage and controls the flight direction and attitude of the plane in the air and maintains balance It is divided into tail wings.

An aileon 160 is mounted on the trailing edge of the main wing 150, respectively. The left and right aileron 160 is a control surface used to control the flight posture by moving in the opposite direction, the lower aileron is lowered up the right aileron, and the left aileon raised the right aileon is connected to go down. For example, if you lower the left side and raise the right side, the lift on the left side of the main wing increases and the lift on the right side of the main wing decreases, which generates a moment to tilt the plane to the right, and vice versa. It is generated for the flight posture control, the flight direction control, and acts for maintaining the balance.

The tail wing is composed of a horizontal tail wing 120 protruding horizontally in both sides from the rear of the fuselage, and a vertical tail wing 100 protruding vertically upward from the rear of the fuselage. Here, the horizontal tail blade 120 is composed of a fixed front horizontal safety plate 130 and the rear lifter 140, the vertical tail wing 100 is a fixed front vertical safety plate 105 and the rear rudder ( 110).

The lifter 140 is movable up and down, so that the lift of the horizontal tail wing 120 increases when it is lowered, thereby generating a moment to lower the nose, and on the contrary, when the lifter 140 is raised, the horizontal wing 120 of the lifter 140 is raised. Since lift is reduced, it generates a moment to raise the nose, and is also used for flight posture control, flight direction control, balance maintenance, etc., among other things, to control the longitudinal movement of the plane.

The rudder 110 is able to move from side to side, so when it is bent to the right, the left wing (100) is generated on the vertical tail wing 100, which generates a moment to turn the nose to the right. As generating the moment to the left, it is used for the flight attitude control, flight direction control, balance maintenance, etc., with the aileron 160 and the lift rudder, and is used to control the transverse motion of the plane.

In general, the main wing is equipped with a flap or a slat, which is a kind of high lift device, and is used to improve stability and maneuverability during flight. Airplanes or planes equipped with triangular wings are used for a variety of control means, such as the use of an aileon and an elevator ellipse (elvon), which is used for flight direction control, flight attitude control and balance.

As described above, the aileron 160, the elevator 140 and the rudder 110 are generally mounted in the fixed wing type micro airplane basically for flight direction and attitude control and balance maintenance. In addition, they basically play a role of controlling a total of three movements, one by one, thereby maintaining balance by controlling flight direction and attitude in the air. That is, the elevating rudder generates a longitudinal pitching movement to raise or lower the nose of the airplane by rotating the airplane bidirectionally about the horizontal axis (Y axis) passing through the center of gravity through the bending operation up and down. By rotating the plane in both directions about the vertical axis (Y axis) passing through the center of gravity through the bending to the left and right, the yawing movement in the lateral direction to switch the plane flight direction by turning the nose to the left or right, In addition, Aileron generates a lateral rolling motion of tilting the plane left and right by rotating the plane in both directions about the vertical axis (X axis) passing through the center of gravity through the bending operation to be opposite to each other up and down.

However, as in a normal airplane, each control plane does not simply generate a single motion. In other words, the plane operated in three-dimensional space is characterized by not only the movement of the specific direction desired by the operator when the specific control surface is operated, but also the additional movement of the unwanted direction.

For example, as shown in FIG. 1, when steering the rudder 110 of the vertical tail wing 100 to generate a yaw motion for the plane flight direction control during flight, the operation of the rudder is indirect. This will affect the steering in other directions. That is, when the rudder 110 is mounted higher than the center of gravity, the plane has a force to rotate sideways with respect to the vertical axis (Z axis), and the nose is rotated upward with respect to the horizontal axis (Y axis) to lift the nose. There is a slight force to raise. In other words, the force in the direction as indicated by the vector in FIG. 1B acts on the plane.

In a general airplane, in order to solve the above-mentioned control problems, it is possible to freely implement various kinds of motions by appropriately manipulating ailerons, elevators and rudders, and adding and subtracting thrust through a propulsion engine. To make it work. In other words, the balance of lift, gravity, and centrifugal force acting on the plane is harmonized through harmonious maneuvering to solve unfavorable phenomena such as slippage during turning.

As a simple example, in the case of the priority session, the plane is tilted to the right by the aileron, and at the same time, the rudder is bent to the right so that the natural flight direction can be made without slipping.

However, micro airplanes have a problem in that it is not easy to implement various kinds of movements freely through harmony like general airplanes. In other words, as the plane becomes extremely small and there is almost no inertia, if the motion generated by the force generated by the operation of each control surface includes a motion in a direction different from the one to be controlled, the fatal instability of the maneuverability It will act as.

That is, the situation is acting as a threat to the flight direction control, flight attitude control and balance maintenance of the micro airplane.

On the other hand, as shown in Figure 2, a general airplane has a horizontal tail wing is installed at a position slightly higher than the main wing, and thus has a predetermined height difference between the main wing and the horizontal tail wing.

Such a micro airplane according to the prior art, when flying at a low speed with a nose, the influence of the air flow through the main wing affects the tail wing. In other words, the flow of turbulent air passing through the main wing directly affects the horizontal and vertical tail wings, so that the horizontal and vertical tail wings for the purpose of flight posture control and balance maintenance have problems. Will be generated. In particular, very small micro-planes also have a major wing and tail wing so close that their effects are negligible.

In order to solve the problems as described above,

The purpose of the present invention is to be free from the influence of turbulent air flow generated from the main wing even when flying with the nose, and the lower horizontal tail wing can perform the main functions of flight posture control and balance maintenance smoothly. It is to provide a micro airplane equipped with.

1 is a view showing a rudder steering state of a general airplane according to the prior art,

1a is a plan view,

1b is a side view,

1c is a front view,

Figure 2 is an exemplary view schematically showing the air flow during flight in a typical airplane according to the prior art.

Figure 3 is an exemplary view schematically showing the air flow during flight in a micro airplane according to the present invention.

4 is a front view of a micro airplane according to the present invention.

* Description of the symbols for the main parts of the drawings *

1: fuselage

10: main wing

20: horizontal tail wing

25, 45: vertical stabilizer

30, 50: vertical tail wing

35, 55: Rudder

In the micro-aircraft according to the present invention for achieving the above object, in the fixed wing type micro-plane having a main wing fixed to the center of the fuselage and the tail wing fixed to the rear of the fuselage,

The lower vertical tail wing is provided at the lower rear of the fuselage to be symmetrical with respect to the upper vertical tail wing and the center of gravity, and the lower vertical tail wing is characterized by having a horizontal tail wing.

In addition, the horizontal tail wing of the micro airplane according to the present invention is characterized in that it is provided with a lifting plate in the rear of the TT flat stabilizer plate and the horizontal stabilizer plate.

Hereinafter, preferred embodiments of the present invention will be described in more detail with reference to the accompanying drawings.

As shown in Figures 3 and 4, the micro airplane according to the embodiment of the present invention is equipped with a main wing 10 in the center of the fuselage 1, similar to a general airplane, a vertical safety plate on the rear of the fuselage 1 ( 25) and the upper vertical tail wing 30 consisting of the rudder 35 is mounted.

In the upper vertical tail wing 30, the front vertical safety plate 25 is directly fixed to the fuselage 1 to support the rudder 35, and the rudder 35 is disposed at the rear of the vertical safety plate 25. It is fixed to rotate about a hinge axis (not shown) within the angular range, and is used as a control surface for controlling yaw motion of a micro airplane.

In addition, the upper vertical tail wing 30 and the lower vertical tail wing 50 which is mounted on the rear of the body 1 so as to be positioned symmetrically with respect to the center of gravity line is further provided. The lower vertical tail wing 50 is also made of a vertical safety plate 45 and the rudder 55, similar to the upper vertical tail wing 30, the vertical safety plate 45 is fixed directly to the body 1 to the rudder 55 ) And the rudder 55 is fixed to the rear of the vertical safety plate 45 so as to be rotated based on a hinge axis (not shown) within a predetermined angle range and is provided on the upper vertical tail wing 30. Together with the rudder 35, it is used as a control surface for controlling yaw motion of a micro airplane.

And, it is provided with horizontal tail blades 20 which are respectively mounted on both sides of the lower vertical tail blades (50). This horizontal tail wing 20 is made of a horizontal safety plate and a lift rudder like a general airplane, the horizontal safety plate is directly fixed to the side of the lower vertical tail wing 50 to support the elevator, the lift rudder at the rear of the horizontal safety plate It is fixed to rotate about the hinge axis within a predetermined angle range and is used as a control surface for controlling the pitch movement of the micro airplane.

Here, as the horizontal tail wing 20 is mounted on the lower vertical tail wing 50 of the form protruding downward from the fuselage tail, it is mounted at a position lower than the main wing 10, to the main wing 10 during flight Free from the effects of turbulence caused by

Such a micro airplane according to the present invention, as shown in Figure 3, is provided with upper and lower vertical tail wings 30, 50 provided in a vertically symmetrical type, to each of the vertical tail wings 30, 50 The provided rudders 35 and 55 operate at the same time when the plane direction change is required during the flight, and thus only the yaw movement can be generated purely in the micro airplane.

In addition, it is provided with a lower horizontal tail wing 20 mounted on the lower vertical tail wing 50, even when flying at low speed holding the nose upwards, the influence of turbulent air flow generated in the main wing is minimized Therefore, it should not be a problem to perform the main functions of the horizontal wing related to flight posture control and balancing.

In particular, it is very advantageous in the micro airplane that the main wing and the tail wing are very close to each other.

The micro airplane according to the present invention as described above realizes the desired plane flight direction control through accurate yaw movement control in the state of preventing unwanted force from occurring, and at low speed in the state of the nose. Even when flying, the effects of turbulent wakes generated by the main wing on the tail wing including the horizontal wing can be minimized, which provides excellent maneuverability and stability to maintain stable flight posture and balance. To have.

Although the present invention has been illustrated and described in connection with specific embodiments, it is understood that various changes, modifications, and changes can be made without departing from the spirit and scope of the invention as indicated by the appended utility model claims. Anyone with ordinary knowledge in Easily will know.

Claims (2)

In a fixed-wing type plane having a main wing fixed to the center of the fuselage and the body, and an upper vertical tail wing fixed to the rear upper part of the fuselage, The lower rear of the fuselage is further provided with a lower vertical tail wing so as to be vertically symmetrical with respect to the upper vertical tail wing and the center of gravity, and the lower vertical tail wing is a very small plane characterized in that it is provided with a horizontal tail wing The method according to claim 1, The horizontal tail wing is a micro airplane, characterized in that it is provided with a lifting plate in the rear of the horizontal stabilizer plate and the horizontal stabilizer plate