CN105366031A - Winglet device with adjustable angle - Google Patents

Abstract

A winglet device with adjustable inclination, comprising a wingtip support (1), an insert (2), a connecting rod (3) and a compression spring (4); the wingtip support (1) and the wing There are two or more grooves on one side of the wingtip support (1), and a non-revolving insert groove and a blind hole are respectively provided at both ends of each groove; the insert (2 ) is consistent with the shape of the insert groove, and is set in the insert groove. There is a circle of adjustment grooves distributed along the circumference on the outer end surface of the insert (2), and each adjustment groove together forms a Centrally symmetrical figure; one end of the connecting rod (3) is provided with a ring of protrusions matched with the adjustment groove, and the protrusion is set in the adjustment groove, and the connecting rod (3) is connected with the winglet; the compression spring ( 4) One end is installed in the blind hole, and the other end is pressed against the other end surface of the connecting rod (3) to axially compress the connecting rod (3). many.

Description

An adjustable winglet device

technical field

The invention relates to a winglet device, which belongs to the field of aviation vehicle design.

Background technique

Winglets are used for subsonic aircraft, mainly including civil aviation passenger aircraft, military transport aircraft, aerial refueling aircraft, early warning aircraft and unmanned aerial vehicles. In the subsonic aircraft in the world today, some winglets are set up to improve the flow of the airflow in the span of the wing, reduce the induced drag of the wing, reduce fuel consumption, and improve economic performance.

But not all subsonic aircraft use winglets. The first is the cost issue. The installation of winglets increases the design and manufacturing costs, and the installation of winglets on passenger aircraft will cost hundreds of thousands of dollars. Secondly, the aircraft performs various tasks, and the winglets can only exert their advantages to the greatest extent during the cruise process, that is to say, the fuel-saving effect of the winglets is the best only during long-distance flights; again, the winglets The winglets are located at both ends of the wing, which are very easy to be damaged due to collisions, and the reliability is not high. Since it is difficult to disassemble, the maintenance after damage is also troublesome, and the maintainability is poor. Therefore, when designing a subsonic aircraft, it is necessary to consider comprehensively to decide whether to arrange winglets.

Therefore, how to make the winglet easy to disassemble and maintain and adapt to the diversity of tasks is the key point. If these problems can be solved, the application of winglets will be more extensive.

The patent "a detachable and adjustable winglet device" (Application No.: 201310692469.1) discloses a winglet device, which uses intubation tubes and slots to adjust the angle of the winglets, and uses metal buckles to adjust the angle of the winglets. Secure the winglets through the cannula. However, this device has few adjustable angles and takes up a lot of space. The metal buckle chain will move in the air, and it is easy to disconnect and fall off, which affects flight safety.

Contents of the invention

The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art and provide a winglet device with multiple adjustable angles, small occupied space and high reliability.

The technical scheme adopted in the present invention is:

A winglet device with adjustable inclination, comprising: a wingtip support, an insert, a connecting rod and a compression spring;

The wing tip support is connected with the wing tip, which is a semi-cylindrical body, and one end of the semi-cylindrical body shrinks to form a semi-conical shape; there are two or more grooves on the cylindrical surface of the semi-cylindrical body, and two opposite grooves of each groove The end faces are respectively provided with a non-revolving insert groove and a blind hole; the shape of the insert is consistent with the shape of the insert groove, and it is set in the insert groove. There is a circle along the circumference of the insert on the outer end surface. Distributed adjustment grooves, each adjustment groove together form a symmetrical figure along the center of the circumference; one end of the connecting rod is provided with a circle of protrusions that match the adjustment grooves, and the protrusions are sleeved in the adjustment grooves, and the connecting rod It is connected with the winglet; one end of the compression spring is installed in the blind hole, and the other end is pressed against the other end surface of the connecting rod to axially compress the connecting rod.

The number of the embedded block grooves is 16 or more.

The groove of the slug is in interference fit with the slug.

The adjustment groove and the protrusion are clearance fit.

The insert groove is in the shape of a rectangular parallelepiped with rounded sides.

The advantage of the present invention compared with prior art is:

1) The present invention makes the inclination angle of the winglet adjustable by changing the angle at which the adjustment groove on the insert block and the protrusion on the connecting rod are nested. The optimal inclination angle of the winglet can be determined through flight tests at different inclination angles; and the socket structure occupies less space, is lighter in weight, and can realize stepless adjustment of the angle, that is, the angle interval is smaller and the adjustable angle is more ;

2) The present invention utilizes the connecting rod to connect the winglet, and the connecting rod is in the groove of the wingtip support, so it takes up less volume and is lighter in weight, which is very important for aerostructures; secondly, due to its small size, less air resistance;

3) The present invention uses a compression spring to limit the front and rear movement of the winglet. The compression spring has a large compression force, is not easy to disengage, and has high reliability; there is no gap between the compression spring and the connecting rod, and the limiting ability is stronger;

4) In the present invention, the winglet and the wing are not integrated, and there are few parts, so it is easy to disassemble. Therefore, when the winglet is damaged, the winglet can be replaced directly and quickly, and the replacement and maintenance are more convenient;

5) In the present invention, the wingtip support is a streamlined design with low air resistance.

Description of drawings

Fig. 1 is the structural representation of device of the present invention;

Fig. 2 is the first axonometric view of the wingtip support of the present invention;

Fig. 3 is the second axonometric view of the wingtip support of the present invention;

Fig. 4 is the schematic diagram of block of the present invention;

Fig. 5 is the schematic diagram of connecting rod of the present invention;

Fig. 6 is the schematic diagram of compression spring of the present invention;

Fig. 7 is a partial schematic view of the groove part of the present invention.

detailed description

As shown in FIG. 1 and FIG. 7 , the present invention provides a winglet device with an adjustable inclination angle, which includes: a wingtip support 1 , an insert 2 , a connecting rod 3 and a compression spring 4 .

As shown in Fig. 2 and Fig. 3, the wingtip support 1 is connected with the wing tip, and is a semi-cylindrical body, and one end of the semi-cylindrical body shrinks in a semi-conical shape to reduce air resistance; There are two grooves, a non-revolving insert groove and a blind hole are opened at both ends of each groove. In this embodiment, the insert groove is in the shape of a cuboid with rounded sides. As shown in FIG. 4 , the shape of the insert 2 is consistent with the shape of the insert groove, and is set in the insert groove and has an interference fit with it. There is a through hole in the center of the insert 2, the purpose of setting the through hole is to reduce weight; there is a circle of adjustment grooves evenly distributed along the through hole on one side of the insert 2, the number of adjustment grooves should be 16 or more , to give full play to the role of adjusting the angle. In this embodiment, the adjusting groove is a concave hole, and the shape of each adjusting groove is consistent, and they together form a symmetrical figure along the center of the circle;

As shown in Figure 5, the connecting rod 3 is provided with a circular hole, which can reduce the weight and also reduce the area of the processing surface; one end surface of the connecting rod 3 is provided with a circle of protrusions evenly distributed along the circumference, Corresponding to the adjustment groove on the insert 2, the protrusion is sleeved in the adjustment groove, and there is a clearance fit between the two, and the connecting rod 3 is connected with the winglet.

The design of the adjustment groove and protrusion is to limit the rotation of the connecting rod 3 on the one hand, and to realize stepless angle adjustment, that is, a smaller angle adjustment interval. During installation, the angle of inclination of the winglet connected to the connecting rod 3 is changed by changing the angle at which the adjustment groove and the protrusion are nested. The inclination angle of the winglet is adjustable, and the optimal inclination angle of the winglet can be determined through flight tests at different inclination angles.

As shown in Figure 6, it is a compression spring 4. One end of the compression spring 4 is installed in the blind hole, and the other end is pressed against the other end surface of the connecting rod 3, and the connecting rod 3 is axially compressed, and its function is to limit the connecting rod. 3 axial movement.

Considering that the acceleration of the aircraft along its own axis direction is generally less than the acceleration of gravity, there are two hold-down springs in total. Considering the safety margin, the hold-down force of hold-down spring 4 should be at least multiplied by an acceleration of gravity by the mass of the winglet. That is, F≥mg.

The method of installation and use of the device described in the invention is as follows:

When in use, first install the insert 2 in the insert groove of the wingtip support 1, then install the compression spring 4 in the round hole of the wingtip support 1, then press the spring tightly, and insert the connecting rod 3 into the Go into the insert block 2, release the spring so that it presses the connecting rod 3.

The inclination position of the connecting rod 3 is adjusted, and the optimal inclination angle of the winglet is determined through flight tests at different inclination angles.

The present invention is described more specifically below by several examples:

Example 1: Adjust the inclination angle of the winglet to achieve the best aerodynamic effect

The winglet device of the present invention can adjust the inclination angle of the winglet, and through flight tests under different inclination angles, the test data results are analyzed to determine the optimal inclination angle of the winglet to obtain the optimal aerodynamic effect.

Example 2, quick and easy replacement of damaged winglets

The winglet device of the present invention is convenient to use and maintain. If the winglet of the aircraft is damaged, it does not need to be repaired like the current winglet, but can be disassembled and replaced immediately, saving a lot of valuable maintenance time. At the same time, the damaged winglet can be brought back to the maintenance area for maintenance and treatment without having to be discarded, which saves a lot of cost.

The description of the present invention in the above description and description is only illustrative and non-limitative, and various changes and modifications can be made to the above-mentioned embodiments without departing from the present invention as defined in the appended claims. , and/or fixes.

Parts not described in detail in the present invention belong to the well-known technology of those skilled in the art.

Claims (6)

1. a winglet device for tilt adjustable, is characterized in that, comprising: wingtip bearing (1), abaculus (2), pipe link (3) and holddown spring (4);

Wingtip bearing (1) is connected with wing wingtip, and a side of wingtip bearing (1) has two and with upper groove, and the end face that two of each groove are relative is respectively equipped with abaculus groove and a blind hole of a non-revolved body shape; The profile of abaculus (2) is consistent with the shape of abaculus groove, is enclosed within abaculus groove, the outer face of abaculus (2) has the circumferential adjusting grooves of a circle, and each adjusting grooves forms along the centrosymmetric figure of this circle center jointly; One end of pipe link (3) is provided with the projection that a circle matches with adjusting grooves, and projection is enclosed within adjusting grooves, and pipe link (3) is connected with winglet; One end of holddown spring (4) is contained in blind hole, and the other end withstands on another end face of pipe link (3), axial compression pipe link (3).

2. a winglet device for tilt adjustable as claimed in claim 1, is characterized in that, the quantity of described abaculus groove be 16 and more than.

3. a winglet device for tilt adjustable as claimed in claim 1 or 2, is characterized in that, described wingtip bearing (1) is semicylinder, and one end of semicylinder is shunk in semi-conical.

4. a winglet device for tilt adjustable as claimed in claim 1 or 2, is characterized in that, described abaculus groove and abaculus (2) interference fit.

5. a winglet device for tilt adjustable as claimed in claim 1 or 2, is characterized in that, described adjusting grooves and projection are free-running fit.

6. a winglet device for tilt adjustable as claimed in claim 1 or 2, is characterized in that, described abaculus groove is the rectangular shape that side is rounded down.