CN203228928U - Aircraft wing - Google Patents

Abstract

The utility model provides an aircraft wing which has high lifting capacity in an effective protected area, is simple in structure and further can be used for improving the endurance and the bearing capacity of an aircraft. The aircraft wing comprises a wing body, wherein a bottom flap is arranged below the wing body, the front edge of the bottom flap is connected with the front edge of the wing body to form a whole body through a C-shaped front end plate, a gap is reserved between the bottom flap and the wing body, and the width of the cross section of the bottom flap is 20%-90% of that of the cross section of the wing body. The aircraft wing provided by the utility model enables the aircraft to produce a greater lift force in the flying process so as to ensure that the wing can obtain a better stress effect at the same speed in the case of the same body projected area. Further, the aircraft can fly farther in the case of same energy consumption.

Description

airplane wing

technical field

The utility model relates to the improvement of the structure of the wing of an aircraft, in particular to make the lift of the wing larger under the condition that the projection area is consistent.

Background technique

For the purpose of maximizing the lift of the wing within the effective projected area, in the prior art, some wings of different lengths and widths are installed on the leading edge and the trailing edge of the wing, some of which can be deflected downward, and some can be tilted toward The front stretches out, and some can slide back, etc., which are part of the wing. Simply put, flaps increase lift by changing the camber of the airfoil, increasing the wing area, and maintaining laminar flow. Two types of flaps are common, the Fuller flap and the Kruger flap. Fuller flaps (trailing edge flaps) are movable airfoils installed on the trailing edge of the wing, and are usually attached to the lower surface of the wing. When in use, the flap retreats along the slide rail installed on the lower wing surface, and simultaneously deflects downward. Kruger flaps (leading edge flaps) are located on the leading edge of the wing. Its shape corresponds to a part of the leading edge of the wing. When in use, the Kruger flap is extended forward and downward by using the hydraulic actuator, which not only changes the airfoil shape, but also increases the wing area, and the effect of increasing the lift is also better.

Above-mentioned two kinds of flaps have a high utilization rate in modern aircraft, and aircrafts with these two kinds of flaps are widely used in military and civil fields. However, these two flaps require a more complex motion control system to drive them to adjust their attitude; they have complex structures and high requirements for movable connections; and they consume high energy consumption during operation. For example, we have seen a number of utility model creations around improving the aerodynamic performance of wings made by Airbus Operations Ltd., Airbus UK Ltd. and Airbus Operations Co., Ltd. in recent years (201080061029.0-aircraft wing, 2007800067899. X-plane wing, 201080014161.6-wing-shaped wing with increased lift flap, etc.).

At the same time, we also see that with the continuous expansion of the use and function of aircraft, new requirements are put forward for the endurance of aircraft and the miniaturization of models (such as drones and model aircraft used for military reconnaissance and civil aerial photography). This requires the most concise design to improve the endurance of the aircraft, maintain a stable attitude, reduce the volume, and increase the carrying capacity.

Utility model content

Aiming at the above problems, the utility model provides an aircraft wing with high lifting capacity and simple structure within the effective projected area, which can further improve endurance and bearing capacity.

The technical scheme of the utility model: comprising a wing body, a bottom flap is provided below the wing body, and the front edge of the bottom flap is connected with the front edge of the wing body through a C-shaped front end plate , there is a gap between the bottom flap and the wing body, and the cross-sectional width of the bottom flap is 20-90% of the cross-sectional width of the wing body.

The height of the gap is 0.1-5 times of the thickness of the wing body.

An arc-shaped bulge is arranged above the wing body, and the ridge line of the bulge is in front of the top surface of the wing body and correspondingly arranged above the centerline of the cross-section of the bottom flap.

The height of the raised ridge line is 1.1-2.5 times the height of the wing body.

Holes are provided on the bottom skirt.

The hole is an oblique hole towards the rear of the wing body.

The utility model is provided with a bottom flap under the wing, so that the wing body forms a brand-new airfoil (different from previous biplanes, and also different from the front and rear edge flaps of existing monoplanes), According to the principle of aerodynamics, the gap between the bottom flap and the body of the utility model will form a negative pressure during the flight process, so that the entire wing can obtain an upward and forward lift force; During the flight, the generated lift is greater, that is, under the same projected area of the body, at the same speed, the wing can obtain a better force effect. In turn, the aircraft can fly farther under the same energy consumption.

Description of drawings

Fig. 1 is the structural representation of wing of the utility model,

Fig. 2 is A-A sectional view among Fig. 1,

Fig. 3 is B-B sectional view among Fig. 1,

Fig. 4 is the structural representation of the optimized embodiment of wing of the present utility model,

Fig. 5 is the reference diagram of the application state when the wing of the utility model is used in combination with the leading edge flap,

Fig. 6 is a working principle diagram one of the present utility model,

Fig. 7 is the working principle figure two of the present utility model,

Fig. 8 is the working principle figure three of the present utility model,

In the figure, 1 is the body, 10 is the front panel, 2 is the trailing edge flap, 3 is the gap, 30 is the opening of the gap, 4 is the bottom flap, 40 is the hole, 400 is the oblique hole, 5 is the bulge, 6 is the front Edge flap;

The dotted line in the figure indicates the air flow path, the double-dashed line indicates the air flow path in the gap, and the solid arrow indicates the force direction.

Detailed ways

The utility model is shown in Fig. 1-5,: comprise wing body 1, be provided with bottom flap 4 below described wing body 1, the leading edge of described bottom flap 4 and the front edge of described wing body 1 The edge is connected as a whole by a C-shaped front end plate 10, and there is a gap 3 between the bottom flap 4 and the wing body 1, and the cross-sectional width of the bottom flap 4 is 20 times the cross-sectional width of the wing body 1. -90%.

The height of the gap 3 is 0.1-5 times of the thickness of the wing body 1 .

The top of the wing body 1 is provided with an arc-shaped bulge 5 , the ridge line of the ridge 5 is in front of the top surface of the wing body 1 , and is correspondingly arranged above the centerline of the cross section of the bottom flap 4 . The effect of the bulge 5 is to adjust the air velocity above and below, and the radian of the bulge 5 is properly selected to further stabilize the attitude of the flight.

The height of the ridge line of the ridge 5 is 1.1-2.5 times the height (thickness) of the wing body 1. Also for the purpose of stabilizing the flight attitude, setting the raised position is to ensure that the wing can always get enough lift.

A hole 40 is provided on the bottom flap 4 .

The hole 40 is an oblique hole 400 facing the rear of the wing body 1 .

The utility model does not exclude the common use with the trailing edge flap 2 and/or the leading edge flap 6 of the wing. It can further optimize the aerodynamic performance of the aircraft.

The working principle of the present utility model is shown in Figures 6, 7, and 8. We found that when the model is used to fly under the drive of the catapult (speed 20-50km/h), as shown in Figures 6, 7, the front airflow When it reaches the tip of the wing, it flows separately from the top and bottom. At the leading edge of the wing (i.e. the dotted line), it is obvious that the flow velocity below is greater than the flow velocity above, and at this time the upper pressure is strong, and the pressure direction is downward; when the airflow enters the opening 30 of the gap, it is just the opposite, and the flow velocity of the airflow below is much higher. is smaller than the upper side, so the direction of the pressure F is obliquely upward, providing lift.

Combined with the situation of high-speed flight (for example, the speed is greater than 300 kilometers), in view of the fact that the utility model does not have the conditions to conduct wind tunnel tests at present, theoretically, if the through hole 4 is added under the bottom flap 4, it should be able to ensure that the opening 3 The adaptation relationship between the negative pressure of the airfoil and the overall structural strength of the wing, and at the same time, a certain loop airflow can be formed inside the gap 3 (as shown by the double-dot dash line in the figure), and the loop airflow can also effectively promote airflow in the wing body. The bottom surface of 1 forms a certain lift effect. The through hole 40 is further improved to an inclined hole 400 facing the rear of the wing body 1, which can be used as a "negative pressure air supply port" for the gap 3 to form a loop airflow in the gap 3 while avoiding the formation of wind resistance.

Claims (6)

1. aircraft wing, comprise wing-body, it is characterized in that, below described wing-body, be provided with the smaller or inner piece on the right side of a Chinese garment which buttons on the right, the leading edge of the described smaller or inner piece on the right side of a Chinese garment which buttons on the right and the leading edge of described wing-body are connected as a single entity by the front end-plate of C shape, leave the space between the described smaller or inner piece on the right side of a Chinese garment which buttons on the right and the described wing-body, the cross-sectional width of the described smaller or inner piece on the right side of a Chinese garment which buttons on the right is the 20-90% of wing-body cross-sectional width.

2. aircraft wing according to claim 1 is characterized in that, the height in described space is 0.1-5 times of wing-body thickness.

3. aircraft wing according to claim 1 is characterized in that, the top of described wing-body is provided with the protuberance of arc, and the place ahead, the correspondence that the ridge line of described protuberance is in the wing-body end face is arranged on the position of smaller or inner piece on the right side of a Chinese garment which buttons on the right cross-section center line top.

4. aircraft wing according to claim 3 is characterized in that, the height of the ridge line of described protuberance is 1.1-2.5 times of wing-body height.

5. according to arbitrary described aircraft wing among the claim 1-4, it is characterized in that, be provided with the hole at the described smaller or inner piece on the right side of a Chinese garment which buttons on the right.

6. according to arbitrary described aircraft wing in the claim 5, it is characterized in that described hole is the inclined hole towards the wing-body rear.

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