CN205157156U

CN205157156U - Wind tunnel test strutting arrangement

Info

Publication number: CN205157156U
Application number: CN201520845344.2U
Authority: CN
Inventors: 赵霞; 宗宁; 黎军; 韩江旭; 王孜孜; 王宵
Original assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC; AVIC Shenyang Aerodynamics Research Institute
Current assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC; AVIC Shenyang Aerodynamics Research Institute
Priority date: 2015-10-28
Filing date: 2015-10-28
Publication date: 2016-04-13
Anticipated expiration: 2025-10-28

Abstract

The utility model provides a wind tunnel test strutting arrangement for provide the support to the model aircraft in the wind -tunnel, wind tunnel test strutting arrangement include one set up in tumbler disc and two generals of wind -tunnel lower wall the aircraft nose of model aircraft connect respectively in the upper wall of wind -tunnel and the last bracing cable of lower wall and lower bracing cable, the last fixed welding of tumbler disc has the identical bracing piece of two root structure, two upper end of the support bar pass through the ball bearing respectively with the wing tip rotates and connects about the model aircraft, two spinal branch vaulting poles are followed the model aircraft about the wing tip to the extension is drawn in in to the tumbler disc direction, the bracing piece has an upper strut pole and a lower part bracing piece, the upper strut pole with contained angle between the bracing piece of lower part is the 120 -165 degree. The utility model provides a wind tunnel test strutting arrangement mixes the characteristics that have bracing cable braced system and rigid braced system, has had the little and supporting stable's of aerodynamical interference advantage concurrently.

Description

Wind tunnel test supporting device

Technical Field

The utility model relates to an aircraft wind tunnel test equipment, especially a wind tunnel test strutting arrangement for among aircraft wind tunnel test process.

Background

When an airplane needs to perform a wind tunnel test without leaving a wind tunnel model supporting system, a model bracket is usually adopted to fix the whole airplane model in a wind tunnel test section. The support system can interfere with the flow around the model. How to reduce or correct the problem of support interference is an important content of experimental aerodynamic research, and the accuracy of wind tunnel experimental data can be effectively improved.

SUMMERY OF THE UTILITY MODEL

The to-be-solved technical problem of the utility model is to provide an experimental strutting arrangement of wind tunnel, it can be used to provide stable support to aircraft model in the aircraft wind tunnel is experimental, has the advantage that the pneumatic interference of opening a line braced system is little simultaneously concurrently.

In order to solve the technical problem, the utility model provides a wind tunnel test supporting device for providing support for an airplane model in a wind tunnel, the wind tunnel test supporting device comprises a rotating disc arranged on the lower wall of the wind tunnel and two upper and lower lines which connect the nose of the airplane model to the upper and lower walls of the wind tunnel respectively, two supporting rods with the same structure are fixedly welded on the rotating disc, and the upper ends of the two supporting rods are respectively connected with the left and right wingtips of the airplane model in a rotating manner through ball bearings; the two support rods are folded and extended from the left wingtip and the right wingtip of the airplane model to the direction of the rotating disc; the bracing piece has an upper portion bracing piece and a lower part bracing piece, the upper portion bracing piece with the contained angle between the lower part bracing piece is 120 supplyes 165 degrees.

Preferably, the upper tension line and the lower tension line are respectively connected with an upper tension line wheel and a lower tension line wheel which are fixed on the upper wall and the lower wall of the wind tunnel.

The utility model provides a wind-tunnel test strutting arrangement has mixed the characteristics of opening a line braced system and hard formula braced system, has adopted hard formula bearing structure in the wing tip position that opening a line braced system is difficult to connect, and has kept opening a line at the aircraft nose position and has supported to pneumatic interference is little and support stable advantage has concurrently.

Drawings

The drawings are only intended to illustrate and explain the present invention and do not limit the scope of the invention. Wherein,

fig. 1 is a schematic structural diagram of a wind tunnel test support device according to an embodiment of the present invention.

Detailed Description

In order to clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.

The airplane model is small in size, the tail and the wings are very thin on the whole, supporting points are not easy to set, and the wind tunnel test supporting device is not easy to swing in a wind tunnel test due to poor structural setting, so that the test precision is influenced. To the above problem, the utility model provides an experimental strutting arrangement of wind-tunnel, as shown in FIG. 1, wherein it is shown according to the utility model discloses a concrete embodiment's experimental strutting arrangement of wind-tunnel 1's schematic structure diagram, this strutting arrangement are arranged in the wind-tunnel to provide the support to aircraft model 10.

Referring to fig. 1, the wind tunnel test supporting device 1 in this embodiment includes a rotating disc 11 disposed on the lower wall of the wind tunnel, and two upper tension lines 12 and two lower tension lines 13 which connect the nose of the airplane model 10 to the upper wall and the lower wall of the wind tunnel respectively, two supporting rods 14 with the same structure are fixedly welded on the rotating disc 11, and the upper ends of the two supporting rods 14 are rotatably connected to the left wingtip and the right wingtip of the airplane model 10 through ball bearings 16 respectively.

Wherein, the upper tension line 12 and the lower tension line 13 respectively control the pitch angle of the airplane model 10 through an upper tension line wheel 17 and a lower tension line wheel 18 which are fixed on the upper wall and the lower wall of the wind tunnel.

It can be seen from the figure that the utility model discloses a wind tunnel test strutting arrangement 1 is the bearing structure who mixes the characteristics of opening line braced system and hard braced system, is exactly at the position that opening line braced system is difficult to connect, for example the wing tip position has adopted hard braced structure, and has kept opening the line at the aircraft nose position and has supported to have had the advantage that opening the line supports that pneumatic disturbance is little concurrently to and hard braced system stability is good, the mature advantage of technique.

In an actual airplane wind tunnel test, the lengths of the tension lines 12 and 13 can be adjusted through the matching action of the tension line wheels 17 and 18, so that the nose can perform vertical pitching motion by taking the ball bearings 16 which are rotatably connected with the left wingtip and the right wingtip of the airplane model 10 as supporting points, and the aerodynamic characteristics of the airplane model 10 at different pitching angles can be measured. When the aerodynamic characteristics of the airplane model 10 at different yaw angles need to be measured, the rotating disc 11 can be rotated to drive the two support rods 14 to enable the airplane model 10 to deflect left and right. Obviously, because the support rod 14 and the airplane model 10 are hard-supported, the airplane model 10 can be conveniently driven to deflect during the rotation of the rotating disc 11, and the stability of support and rotation is obviously superior to that of tension line support.

In addition, when the rotating disc 11 rotates, the tension of the tension wire wheels 17 and 18 can be loosened, and the lengths of the tension wire wheels 12 and 13 can be adjusted, so that the machine head deflects. This is especially different for the current bracing system of bracing wire, current bracing wire support system is in order to adjust the deflection angle of aircraft model, need set up a carousel of connecting each bracing wire respectively in the upper wall and the lower wall of wind-tunnel, two upper and lower carousels cooperate and rotate and just can adjust the deflection angle of aircraft model, and still need readjust the length of each bracing wire after the adjustment to ensure that the state of aircraft model accords with the experimental requirement, the amount of labour is very big, adjustment work is tedious, the parameter is many, easily lead to the mistake to rework.

And the utility model discloses an among the wind tunnel test strutting arrangement 1, only need set up a rotating disc 11 on the lower wall of wind-tunnel for support two spinal branch vaulting poles 14 just can, structural great simplification has been carried out, need not set up two rotating discs like in the current line braced system of opening, moreover, the fixed point (the position that the line wheel is located) of opening the line and the wind-tunnel at aircraft nose position also need not remove along with the deflection of aircraft model. That is to say, in the wind tunnel test supporting device 1 of the utility model, the bracing wire 12 and the lower bracing wire 13 are respectively connected and are being fixed in bracing wire wheel 17, 18 on wind tunnel upper wall and lower wall, and the position of bracing wire wheel 17, 18 is fixed relatively to the wind tunnel, need not fix it on slewing mechanism along with the rotation of aircraft model's deflection, consequently, the utility model discloses a bracing wire 12, 13 and the operating system who is connected with it, for example bracing wire wheel 17, 18 etc. can need not to consider parameters such as weight, maneuverability, on the contrary because its fixed connection's attribute, can set up multiple complicated joint measurement device on it. Furthermore, due to the fact that the tensile wires 12 and 13 and the control systems connected with the tensile wires, such as the tensile wire wheels 17 and 18, are not movably arranged, the adjustment of the lengths of the tensile wires 12 and 13 is very convenient, after the airplane model is adjusted and deflected, the state of the airplane model can be determined only by adjusting the lengths of the two tensile wires 12 and 13, the workload is greatly reduced, the labor is saved to a certain extent, the efficiency is improved, and the problems of repeated reworking, measurement, calculation and the like caused by complicated adjustment steps are avoided.

In addition, compare in current opening wire braced system, the utility model discloses an experimental strutting arrangement 1 of wind-tunnel still has an obvious advantage, that is to say, because the utility model discloses an opening wire 12, 13 need not link together with rotating disc 11 and rotate, opening wire wheel 17, 18 need not fixed connection on rotating disc 11, consequently, rotating disc 11's size need not to consider opening wire 12, 13's fixed position problem, this is also very important in the actual work, because the size of wind tunnel is limited after all, if can reduce the interference that just can the minimize air current of bearing structure's in the wind-tunnel as far as possible size.

The utility model discloses in, because the size of carousel 11 is irrelevant with the fixed mounting position of zhang xian 12, 13, also need not to consider the fixed problem of zhang xian wire wheel 17, 18 promptly, consequently, carousel 11 can reduce its area as far as possible under the sufficient condition of intensity. As can be seen from fig. 1, the area of the rotating disk 11 is significantly smaller than the projected area of the airplane model 10, and the diameter thereof is also significantly smaller than the distance between the two wingtips, so that, in one embodiment, the two support rods 14 can be drawn and extended from the left and right wingtips of the airplane model toward the rotating disk 11, thereby achieving the purpose of reducing the area of the rotating disk 11. In another embodiment, the supporting rod 14 has an upper supporting rod 141 and a lower supporting rod 142, and in order to balance the contradiction between the area reduction and the supporting stability, the included angle between the upper supporting rod 141 and the lower supporting rod 142 is preferably 120 degrees and 165 degrees.

The above description is only exemplary of the present invention, and is not intended to limit the scope of the present invention. Any equivalent changes, modifications and combinations that may be made by those skilled in the art without departing from the spirit and principles of the invention should be considered within the scope of the invention.

Claims

1. A wind tunnel test supporting device is used for supporting an airplane model in a wind tunnel and is characterized by comprising a rotating disc arranged on the lower wall of the wind tunnel and two upper tensile lines and two lower tensile lines which respectively connect the nose of the airplane model to the upper wall and the lower wall of the wind tunnel, wherein two supporting rods with the same structure are fixedly welded on the rotating disc, and the upper ends of the two supporting rods are respectively and rotatably connected with the left wingtip and the right wingtip of the airplane model through ball bearings; the two support rods are folded and extended from the left wingtip and the right wingtip of the airplane model to the direction of the rotating disc; the bracing piece has an upper portion bracing piece and a lower part bracing piece, the upper portion bracing piece with the contained angle between the lower part bracing piece is 120 supplyes 165 degrees.

2. The wind tunnel test support device of claim 1, wherein the upper tension line and the lower tension line are respectively connected with an upper tension line wheel and a lower tension line wheel fixed on the upper wall and the lower wall of the wind tunnel.