CN105910792A - Airplane wind tunnel test model installation device - Google Patents

Abstract

The invention discloses an aircraft wind tunnel test model installation device and relates to the technical field of aircraft wind tunnel tests. The aircraft wind tunnel test model installation device includes a pitch adjustment device (1), a sliding mechanism (2) and a model mounting support (4); one end of the pitch adjustment device (1) is connected by a first connecting rod (11) At the top of the test wind tunnel, the other end is connected to the rolling shaft (13) by the second connecting rod (12); the angle between the first connecting rod (11) and the second connecting rod (12) can be adjusted; The sliding mechanism (2) is sleeved on the rolling shaft (13), and the sliding mechanism (2) can rotate around the rolling shaft (13); one end of the model mounting support (4) is connected to the The sliding mechanism (2) is connected, and the other end is connected with the test model (5). The beneficial effect of the invention is that the degree of freedom of the rolling and yaw movement of the aircraft can be released, and the wind tunnel test verification of the aircraft with the ride quality improvement control system can be realized.

Description

An aircraft wind tunnel test model installation device

technical field

The invention relates to the technical field of aircraft wind tunnel tests, in particular to an aircraft wind tunnel test model installation device.

Background technique

At present, in the field of aviation testing, aircraft wind tunnel tests focus on testing the aerodynamic characteristics of the aircraft body. The degrees of freedom of lateral movement and yaw motion of the aircraft cannot be released, and the coupling characteristics of the control system and the aircraft cannot be tested. There is no effective and practical test device for hole test verification.

Contents of the invention

The object of the present invention is to provide an aircraft wind tunnel test model mounting device to solve or at least alleviate at least one of the problems in the background art.

The technical scheme adopted in the present invention is: provide a kind of aircraft wind tunnel test model installation device, be used for installing test model, described aircraft wind tunnel test model installation device comprises pitch adjustment device, sliding mechanism and model mounting support; One end of the adjustment device is connected to the ground of the test wind tunnel through a first connecting rod, and the other end is connected to the sliding mechanism through a second connecting rod; the angle between the first connecting rod and the second connecting rod can be adjusted; The sliding mechanism can realize the lateral sliding of the test model, and the lateral direction refers to the connection direction of the wings on both sides of the test model; one end of the model mounting support is connected with the sliding mechanism, and the other end is connected with the The abdominal connection of the test model.

Preferably, the sliding mechanism includes a sliding base and a sliding block, the sliding base is provided with a sliding slot, one end of the sliding block can slide in the sliding slot, and the other end is connected to the model mounting support.

Preferably, the chute is configured as a dovetail groove.

Preferably, buffer devices are provided at both ends of the chute, and the buffer devices are used to limit the lateral movement of the slider.

Preferably, the buffer device includes a spring and a baffle, one end of the spring is fixedly connected to the chute, the other end of the spring is connected to the baffle, and the sliders are on both sides of the chute. slide between the end fences.

Preferably, the aircraft wind tunnel test model installation device also includes a yaw device, one end of the yaw device is connected to the model mounting support, and the other end is connected to the slider on the sliding mechanism, and the yaw device The device enables the rotation of the test model around the model mounting support.

Preferably, the yaw device includes an inner cylinder and an outer cylinder, one end of the inner cylinder is connected to the slider, the outer cylinder is sleeved on the inner cylinder, and the outer cylinder can wrap around the inner cylinder. The cylinder rotates, and the outer cylinder is connected with the mounting support of the test model.

Preferably, a rolling bearing is arranged between the inner cylinder and the outer cylinder in the radial direction, and an end bearing is arranged between the inner cylinder and the outer cylinder in the axial direction.

Preferably, when the axes of the first connecting rod and the second connecting rod coincide, it is recorded as the zero position of the pitch adjustment device, and the pitch angle adjustment range of the test model is ±20 degrees.

The beneficial effects of the present invention are:

The sliding mechanism in the installation device of the aircraft wind tunnel test model of the present invention can release the degree of freedom of lateral motion of the test model; the yaw device can release the degree of freedom of yaw motion of the test model, which improves the simulation of the wind tunnel test and can realize Wind Tunnel Test Validation of Control System Aircraft.

Description of drawings

FIG. 1 is a schematic diagram of an installation device for an aircraft wind tunnel test model according to an embodiment of the present invention.

Fig. 2 is a schematic diagram of the sliding mechanism in the installation device for the aircraft wind tunnel test model shown in Fig. 1 .

Among them, 1-pitch adjustment device, 2-sliding mechanism, 4-model mounting support, 5-test model, 11-first connecting rod, 12-second connecting rod, 21-sliding base, 22-slider, 211 - chute.

detailed description

In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

In describing the present invention, it is to be understood that the terms "central", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", The orientations or positional relationships indicated by "top", "bottom", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the Means that a device or element must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the scope of the invention.

As shown in Figures 1 and 2, an aircraft wind tunnel test model installation device is used to install a test model 5. The aircraft wind tunnel test model installation device includes a pitch adjustment device 1, a sliding mechanism 2 and a model installation support 4.

One end of the pitch adjustment device 1 is connected to the ground of the test wind tunnel through the first connecting rod 11, and the other end is connected to the sliding mechanism 2 through the second connecting rod 12; the angle between the first connecting rod 11 and the second connecting rod 12 able to adjust.

In this embodiment, when the axes of the first connecting rod 11 and the second connecting rod 12 coincide, it is recorded as the zero position of the pitch adjustment device 1 , and the pitch angle adjustment range of the test model is ±20 degrees. As shown in accompanying drawing 1, the pitch angle of test model 5 in the figure is marked as zero position, and the first connecting rod 11 keeps the position unchanged, and the second connecting rod 12 can rotate clockwise 20 degrees; Meanwhile, the first connecting rod 11 keeps The position remains unchanged, and the second connecting rod 12 can also rotate 20 degrees counterclockwise.

In this embodiment, the connecting ends of the first connecting rod 11 and the second connecting rod 12 are fixedly connected by a pin shaft, and the pin shaft includes a rotating pin shaft and a positioning pin shaft. The connection between the first connecting rod 11 and the second connecting rod 12 The end is provided with a coaxial hole, and the rotating pin shaft is inserted into the coaxial hole as the rotating shaft for adjusting the angle between the first connecting rod 11 and the second connecting rod 12. With the rotating shaft as the center, a plurality of Positioning hole, by adjusting the corresponding position of the positioning hole on the first connecting rod 11 and the second connecting rod 12, and inserting the positioning pin shaft into the positioning hole, the angle between the first connecting rod 11 and the second connecting rod 12 can be realized. adjust.

It can be understood that the positioning hole can also be set as a long circular arc hole centered on the axis of the rotating pin, and the angle scale value is set on the edge of the long circular arc hole. The advantage is that the continuous adjustment of the angle between the first link 11 and the second link 12 can be realized.

The sliding mechanism 2 can realize the lateral sliding of the test model 5 , and the lateral direction refers to the direction of the connecting line of the wings on both sides of the test model 5 . The lateral freedom of movement of the test model 5 can be released via the sliding mechanism 2 .

In this embodiment, the sliding mechanism 2 includes a sliding base 21 and a sliding block 22, the sliding base 21 is provided with a sliding groove 211, one end of the sliding block 22 can slide in the sliding groove 211, and the other end is connected with the model mounting support 4 . The sliding groove 211 is set as a dovetail groove, which has the advantage that the positioning of the slider 22 is accurate, which is beneficial to improving the test accuracy.

It can be understood that the structural form of the chute 211 can also be set according to actual conditions. For example, in an alternative embodiment, the chute is set as a rectangular trough, and the slide block is also set as a rectangular block accordingly, and a limit cover is arranged above the rectangular block to prevent the slide block from falling out of the chute. The advantage is that the structure is simple, The processing is convenient, which is beneficial to reduce the test cost.

In this embodiment, buffer devices are provided at both ends of the slide groove 211 , and the buffer devices are used to limit the lateral movement of the slider 22 . Specifically, in this embodiment, the buffer device includes a spring and a baffle, one end of the spring is fixedly connected to the chute 211, the other end of the spring is connected to the baffle, and the slider 22 is between the baffles at both ends of the chute 211. slide. The advantage is that when the slider 22 moves to one end of the chute 211, it contacts the baffle and compresses the spring, which is beneficial to prevent damage to the test model and test device caused by the collision.

One end of the model mounting support 4 is connected with the sliding mechanism 2, and the other end is connected with the abdomen of the test model 5.

In this embodiment, the aircraft wind tunnel test model installation device also includes a yaw device 3, one end of the yaw device 3 is connected with the model mounting support 4, and the other end is connected with the slide block 22 on the sliding mechanism 2, and the yaw device 3 The rotation of the test model 5 around the model mounting support 4 can be realized.

Specifically, in this embodiment, the yaw device 3 includes an inner cylinder and an outer cylinder, one end of the inner cylinder is connected to the slider 22, the outer cylinder is sleeved on the inner cylinder, the outer cylinder can rotate around the inner cylinder, and the outer cylinder and the The test model is connected to the mounting bracket 4. A rolling bearing is arranged between the inner cylinder and the outer cylinder in the radial direction, and an end bearing is arranged between the inner cylinder and the outer cylinder in the axial direction.

In this embodiment, the inner cylinder is set as a two-stage stepped sleeve with a stepped outer circle, the inner cylinder is sleeved on the end of the slider 22 away from the chute 211, and the end with a larger diameter of the outer circle is close to the chute 211 ; The outer cylinder is sleeved at the end of the inner cylinder with a smaller outer diameter, a rolling bearing is arranged between the shaft section of the inner cylinder with a smaller diameter and the radial direction of the inner hole of the outer cylinder, and the axial step of the inner cylinder and the outer cylinder is provided with a Face bearings. The advantage is that it is beneficial to realize the yaw motion of the test model 5, reduces the movement resistance between components, and is beneficial to improve the test accuracy.

The aircraft wind tunnel test model installation device of the present invention can realize the lateral movement of the test model 5 by sliding the slide block 22 in the chute 211 in the sliding mechanism, and can release the lateral movement freedom of the test model; The rotation of the device can release the degree of freedom of the yaw movement of the test model. The control system realizes the adjustment of aerodynamic force and pitching moment by controlling the deflection of the test model 5, and controls the test model by controlling the lateral movement and yaw movement of the test model. The balance of Model 5 can realize the wind tunnel test verification of the aircraft with control system.

Finally, it should be pointed out that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Although the present invention has been described in detail with reference to the aforementioned embodiments, those of ordinary skill in the art should understand that: it can still modify the technical solutions described in the aforementioned embodiments, or perform equivalent replacements for some of the technical features; and these The modification or replacement does not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims (9)

1. an aircraft model in wind tunnel erecting device, for installation test model (5), its feature exists In: described aircraft model in wind tunnel erecting device comprises pitching regulating device (1), slide mechanism (2) And model erection support (4)；

One end of described pitching regulating device (1) is connected to the ground of test air tunnel by first connecting rod (11) On face, the other end connects described slide mechanism (2) by second connecting rod (12)；Described first connecting rod (11) And the angle between second connecting rod (12) can regulate；

Described slide mechanism (2) is capable of the lateral sliding of described test model (5), described is laterally The line direction of the both sides wing of finger to finger test model (5)；

Described model erection support (4) one end is connected with described slide mechanism (2), the other end and described examination The abdominal part testing model (5) connects.

2. aircraft model in wind tunnel erecting device as claimed in claim 1, it is characterised in that: described Slide mechanism (2) comprises sliding bottom (21) and slide block (22), and described sliding bottom sets on (21) Being equipped with chute (211), can slide, separately in described chute (211) in one end of described slide block (22) One end is connected with described model erection support (4).

3. aircraft model in wind tunnel erecting device as claimed in claim 2, it is characterised in that: described Chute (211) is set to dovetail groove.

4. aircraft model in wind tunnel erecting device as claimed in claim 3, it is characterised in that: described The two ends of chute (211) are provided with buffer unit, and described buffer unit is used for limiting described slide block (22) Shifted laterally.

5. aircraft model in wind tunnel erecting device as claimed in claim 4, it is characterised in that: described Buffer unit comprises spring and baffle plate, and one end of described spring is fixing with described chute (211) to be connected, institute The other end stating spring is connected with described baffle plate, and described slide block (22) is at the two ends of described chute (211) Slide between baffle plate.

6. aircraft model in wind tunnel erecting device as claimed in claim 1, it is characterised in that: described Aircraft model in wind tunnel erecting device also comprises yaw device (3), described yaw device (3) one end with Described model erection support (4) connects, and the other end is with the slide block (22) on described slide mechanism (2) even Connecing, described yaw device (3) is capable of test model (5) around described model erection support (4) Rotate.

7. aircraft model in wind tunnel erecting device as claimed in claim 6, it is characterised in that: described Yaw device (3) comprises inner core and urceolus, and one end of described inner core is connected with described slide block (22), institute Stating urceolus to be set on described inner core, described urceolus can rotate around described inner core, described urceolus and described examination Test model erection support (4) to connect.

8. aircraft model in wind tunnel erecting device as claimed in claim 7, it is characterised in that: described Rolling bearing it is provided with, between the axial direction of described inner core and described urceolus between the radial direction of inner core and described urceolus It is provided with end face bearing.

9. aircraft model in wind tunnel erecting device as claimed in claim 1, it is characterised in that: described It is designated as the zero of pitching regulating device (1) during the dead in line of first connecting rod (11) and second connecting rod (12) Position, the luffing angle range of accommodation of test model (5) is ± 20 degree.