Aircraft external store force measurement wind tunnel test device

Abstract

The invention provides an aircraft external store force measurement wind tunnel test device, and belongs to the technical field of wind tunnel tests, and the device comprises a connecting block which is installed at a fuselage or wing hanging point and comprises a front connecting block and a rear connecting block; the transition beam, the connecting frame and the outer hanging part are arranged below the connecting block and are vertically arranged downwards in sequence; the first supporting beam penetrates through the transition beam and is fixedly connected with the connecting frame through a first strain balance, the second supporting beam is fixedly connected with the transition beam through a second strain balance, and the third supporting beam penetrates through the transition beam and the connecting frame and is fixedly connected with the external hanging part through a third strain balance; the first strain balance, the second strain balance and the third strain balance are used for simultaneously measuring loads of the connecting frame, the transition beam and the external hanging part. According to the invention, the test train number and the test cost for measuring the bearing of each structure during the wind tunnel test can be effectively reduced, the measurement of the missile frame beam in the same state can be ensured, the installation error in the test process is reduced, and the test data is more accurate.

Description

Technical Field

[0001] The present application belongs to the technical field of wind tunnel testing, and in particular relates to a wind tunnel testing device for measuring the force of aircraft external attachments. Background Art

[0002] During the flight of an aircraft, the external attachments carried by the aircraft will generate a large aerodynamic load under the influence of airflow, causing the attachment point (the connection between the external attachment and the aircraft) to bear a large load. In order to ensure the safety of the attachment point, it is generally necessary to carry out force measurement wind tunnel tests on the external attachments to determine the load characteristics of the external attachments under various flight conditions. Figure 1 The figure shows a typical wind tunnel test structure 10 for measuring the force of aircraft external attachments. The external attachments under the attachment point 12 on the lower side of the aircraft wing or fuselage 11 generally include three major components: a transition beam 13, a connecting frame 14, and an external attachment 15. In the load calculation of the aircraft attachment point 12, the aerodynamic loads and inertial loads of the transition beam 13, the connecting frame 14, and the external attachment 15 need to be considered separately. Therefore, in the force wind tunnel test, the external attachment 15, the connecting frame 14, and the transition beam 13 are usually measured separately.

[0003] In the traditional external load test, the wind tunnel can only measure the load of one component each time it is started, that is, when measuring the load of the external load 15, the load of the connecting frame 14 and the transition beam 13 are not measured; when measuring the load of the connecting frame 14, the load of the external load 15 and the transition beam 13 are not measured; when measuring the load of the transition beam 13, the load of the external load 15 and the connecting frame 14 are not measured. This test scheme is simple in design and easy to implement, but the wind tunnel can only measure the load of one component each time it is started. In order to obtain the aerodynamic load characteristics of the entire external load, the wind tunnel needs to be started three times, resulting in increased test costs. In addition, the model needs to be installed three times, and the consistency of the model state is difficult to ensure, resulting in mismatched aerodynamic load characteristics of various components of the external load under the same wind tunnel test conditions. Summary of the invention

[0004] The purpose of the present application is to provide a wind tunnel test device for measuring the force of aircraft external attachments, so as to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: a wind tunnel test device for measuring force of aircraft external attachments, comprising:

[0006] A connection block installed at a fuselage or wing hanging point, the connection block comprising a front connection block and a rear connection block;

[0007] A transition beam, a connecting frame and an external hanger are arranged under the connecting block and arranged vertically downward in sequence;

[0008] A first support beam, a second support beam and a third support beam, wherein the first support beam passes through the transition beam and is fixedly connected to the connecting frame through a first strain balance, the second support beam is fixedly connected to the transition beam through a second strain balance, and the third support beam passes through the transition beam and the connecting frame and is fixedly connected to the external hanger through a third strain balance;

[0009] The loads of the connecting frame, the transition beam and the external hanger are measured simultaneously by the first strain balance, the second strain balance and the third strain balance.

[0010] Preferably, the first strain gauge and the second strain gauge are sheet-type strain gauges, and the third strain gauge is a rod-type strain gauge.

[0011] Preferably, the transition beam and / or the connecting frame is provided with a mounting groove along the length direction, and a first gap is provided between the first support beam, the second support beam and the third support beam and the mounting groove.

[0012] Preferably, the gap is not less than 1 mm.

[0013] Preferably, a second gap is provided in the height direction between the connecting block and the transition beam, between the transition beam and the connecting frame, and between the connecting frame and the external hanger.

[0014] Preferably, the second gap is not less than 1 mm.

[0015] Preferably, the external hanger includes a front section, a middle section and a rear section, the front section is connected to the middle section via a cone sleeve, and the middle section and the rear section are connected via a cone sleeve and are respectively installed on the front and rear sides of the third strain balance.

[0016] The aircraft external load force wind tunnel test structure provided in the present application can effectively reduce the number of test vehicles and test costs for measuring the load-bearing of each structure during wind tunnel tests, and can ensure that the bomb rack beam (i.e., external load-connecting frame-transition beam) is measured in the same state, thereby reducing installation errors during the test and making the test data more accurate. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0018] Figure 1 The figure is a schematic diagram of aircraft external attachments and attachment points in the prior art.

[0019] Figure 2 This is a schematic diagram of the installation structure of the various components of the aircraft external attachments of this application.

[0020] Figure 3 A top view of a transition beam according to an embodiment of the present application. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0022] In order to achieve synchronous measurement of various components (including transition beams, connecting frames, and external hangers) of external hangers under the same hanger point of an aircraft, effectively reduce the test cost, and ensure the consistency of the status of various components of the external hangers, the present application proposes a new aircraft external hanger force measurement wind tunnel test structure.

[0023] like Figure 2 As shown, the aircraft external attachment force measurement wind tunnel test device 20 provided in the present application includes:

[0024] A connection block 21 installed at a fuselage or wing hanging point, the connection block 21 generally includes a front connection block 211 and a rear connection block 212, so as to form a stable hanging point with the fuselage or wing;

[0025] The transition beam 22, the connecting frame 23 and the external hanger 24 are arranged vertically in sequence under the connecting block 21;

[0026] The first support beam 25 to the third support beam 27, wherein the first support beam 25 passes through the transition beam 22, one end of which is fixed to the front connection block 211, and the other end is provided with a first strain balance 251, and the first strain balance 251 is fixedly connected to the connecting frame 23; the second support beam 25 has one end fixed to the front connection block 211, and the other end is provided with a second strain balance 261, and the second strain balance 261 is fixedly connected to the transition beam 22; the third support beam 27 passes through the transition beam 22 and the connecting frame 23, one end of which is fixed to the rear connection block 212, and the other end is provided with a third strain balance 271, and the third strain balance 271 is fixedly connected to the external hanger 24;

[0027] During the wind tunnel test, the loads of the connecting frame 23 , the transition beam 22 and the external hanger 24 are measured respectively by the first strain balance 251 to the third strain balance 271 .

[0028] In a preferred embodiment of the present application, the first strain balance 251 and the second strain balance 261 are plate-type strain balances, which are used to measure the lateral force, yaw moment and roll moment of the connecting frame 23 and / or the transition beam 22, and the third strain balance 271 is a rod-type strain balance, which is used to measure the lift, pitch moment, lateral force, yaw moment and roll moment of the external plug-in 24.

[0029] like Figure 3The figure shows a top view of the transition beam in this embodiment of the present application. The transition beam 22 is provided with a mounting groove 222 extending from the back to the front (according to the airflow direction) along the length direction of the transition beam. The first support beam 25, the second support beam 26 and the third support beam 27 can be arranged along the mounting groove 222. The first support beam 25 and the third support beam 27 pass through the mounting groove 222, and there is a certain gap between them and the mounting groove 222, and the gap is at least 1mm. The end of the second support beam 26 is located in the mounting groove 222, and the end of the second support beam 26 is transversely fixed to the second strain balance 261, and the second strain balance 261 is fixed to the side wall of the mounting groove 222 by a connecting piece.

[0030] In some embodiments of the present application, a transition beam cover plate 221 is provided at the tail of the transition beam 22. After the first support beam 25 for carrying the load of the connecting frame 23, the second support beam 26 for carrying the transition beam 22 and the third support beam 27 for carrying the external plug-in 24 are installed along the installation groove 222, the transition beam cover plate 221 is fixedly installed at the tail of the transition beam 22.

[0031] The connecting frame 23 in the present application has the same structural form as the transition beam 22 , and a connecting frame cover plate 231 may also be provided at the tail of the connecting frame 23 , and the specific contents will not be repeated here.

[0032] In the present application, a certain gap is provided in the height direction between the connecting block 21 and the transition beam 22, between the transition beam 22 and the connecting frame 23, and between the connecting frame 23 and the external hanger 24, and the gap is at least 1 mm. For example, in some embodiments of the present application, the gap is set to be not less than 1.2 mm.

[0033] In some embodiments of the present application, the external hanger 24 is divided into an external hanger front section 241, an external hanger middle section 242 and an external hanger rear section 243. The third strain balance 271 is assembled on the cone sleeve of the external hanger middle section 242 through the cone sleeve at the front end of the balance. The front end of the external hanger middle section 242 is installed with the external hanger front section 241 through the cone sleeve. The third strain balance 271 is assembled to the rear connecting block 212 through the third support beam 27. The external hanger rear section 243 is sleeved on the rear end of the third strain balance 271, thereby realizing the installation of the third strain balance 271.

[0034] When the force measuring wind tunnel test is performed, the three-dimensional forces acting on the connecting frame 23 and the transition beam 22 and the five-dimensional forces acting on the external hanger 24 are measured simultaneously by the first strain balance 251 , the second strain balance 261 and the third strain balance 271 .

[0035] The aircraft external load force wind tunnel test structure provided in the present application can effectively reduce the number of test vehicles and test costs for measuring the load-bearing of each structure during wind tunnel tests, and can ensure that the bomb rack beam (i.e., external load-connecting frame-transition beam) is measured in the same state, thereby reducing installation errors during the test and making the test data more accurate.

[0036] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A wind tunnel test device for measuring force of aircraft external attachments, characterized in that: include: A connection block installed at a fuselage or wing hanging point, the connection block comprising a front connection block and a rear connection block; A transition beam, a connecting frame and an external hanger are arranged under the connecting block and arranged vertically downward in sequence; A first support beam, a second support beam and a third support beam, wherein the first support beam passes through the transition beam and is fixedly connected to the connecting frame through a first strain balance, the second support beam is fixedly connected to the transition beam through a second strain balance, and the third support beam passes through the transition beam and the connecting frame and is fixedly connected to the external hanger through a third strain balance; The loads of the connecting frame, the transition beam and the external hanger are measured simultaneously by the first strain balance, the second strain balance and the third strain balance.

2. The aircraft external load force wind tunnel test device according to claim 1, characterized in that: The first strain gauge and the second strain gauge are sheet-type strain gauges, and the third strain gauge is a rod-type strain gauge.

3. The aircraft external load force wind tunnel test device according to claim 1, characterized in that: The transition beam and / or the connecting frame is provided with a mounting groove along the length direction, and a first gap is provided between the first supporting beam, the second supporting beam and the third supporting beam and the mounting groove.

4. The aircraft external load force wind tunnel test device according to claim 3, characterized in that: The gap is not less than 1 mm.

5. The aircraft external load force wind tunnel test device according to claim 1, characterized in that: A second gap is provided in the height direction between the connecting block and the transition beam, between the transition beam and the connecting frame, and between the connecting frame and the external hanger.

6. The aircraft external load force wind tunnel test device according to claim 5, characterized in that: The second gap is not less than 1 mm.

7. The aircraft external load force wind tunnel test device according to claim 1, characterized in that: The external hanger includes a front section, a middle section and a rear section. The front section is connected to the middle section via a cone sleeve, and the middle section and the rear section are connected via a cone sleeve and are respectively installed on the front and rear sides of the third strain balance.

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