A jaw-type hood separation test device for hypersonic wind tunnel

Abstract

A chin-type hood separation test device for a hypersonic wind tunnel includes a test piece, a separation mechanism, a chin-type hood, a separation spring, a locking bolt, a balance, a straight support rod, a central axis, a locking nut, a bottom cover, and a wind tunnel angle of attack mechanism; first, the chin-type hood is fixed to the test piece through the separation spring and the separation mechanism, and secondly, the test piece is connected to the balance, the straight support rod, and the central axis through the locking bolt, and then connected to the wind tunnel angle of attack mechanism through the locking nut; finally, the balance line and the separation mechanism control line pass through the inner hole of the straight support rod and the central axis to the measurement and control room for remote control. The test device of the present invention can not only carry out the chin-type hood separation test, but also the chin-type hood can be safely separated, and at the same time, the scale reduction ratio of the chin-type hood can be increased to 1:5.

Description

Technical Field

[0001] The present application relates to the technical field of hood separation test devices, and in particular to a chin-type hood separation test device for a hypersonic wind tunnel. Background Art

[0002] Usually, air-breathing aircraft mainly adopt aerodynamic layout forms such as annular air inlets and chin-type air inlets. This invention is mainly aimed at the problem of hood separation of air-breathing aircraft adopting chin-type air inlets, that is, under the environmental conditions of an altitude of 20km-30km and a dynamic pressure of 144kpa-48kpa, on the one hand, it is found that under the above-mentioned large dynamic pressure environment, the pressure resistance borne by the chin-type hood is too large, and it is difficult to achieve safe separation; on the other hand, the chin-type hood separation process will have a significant impact on the stability of the aircraft.

[0003] At present, the dynamic test of clam hood separation of the ventilation model of the hypersonic wind tunnel that has been applied requires the test organization to have the following characteristics: 1. The test piece can be installed on the angle of attack mechanism of the wind tunnel, and a certain range of angle of attack or sideslip angle changes can be achieved; 2. The dynamic separation process of the clam hood can be obtained, and the test piece can be safely separated and not hit back; 3. During the dynamic separation process of the clam hood, the dynamic aerodynamic changes of the test piece are measured in real time; 4. Under the test conditions, the influence of the fastening and release mechanism on the dynamic aerodynamic measurement of the test piece is reduced; 5. Under the same test conditions, large-sized test pieces are used as much as possible; 6. The test piece is required to be a ventilation model. However, the separation of the clam hood (fairing) is often in the middle and high altitude, with an altitude greater than 40 km, a dynamic pressure less than 36 kpa, and a relatively small aerodynamic force. This test device is not suitable for the chin-type hood separation test. Summary of the invention

[0004] The technical problem solved by the present invention is as follows: the deficiencies of the prior art are overcome, and a chin-type hood separation test device for a hypersonic wind tunnel is provided. The separation force is combined with a separation mechanism to solve the problem that the chin-type hood is subjected to excessive pressure resistance and is difficult to achieve safe separation.

[0005] This application adopts the following technical solutions:

[0006] A chin-type head cover separation test device for a hypersonic wind tunnel, characterized by comprising: a test piece, a separation mechanism, a chin-type head cover, a separation spring, a locking bolt, a balance, a straight support rod, a central axis, a locking nut, a bottom cover, and a wind tunnel angle of attack mechanism;

[0007] The chin-type hood is fixed to the specimen through a separation spring and a separation mechanism. The specimen is connected to the balance, straight support rod and central axis through locking bolts, and then connected to the wind tunnel angle of attack mechanism through locking nuts. Finally, the balance line and the separation mechanism control line pass through the inner holes of the straight support rod and the central axis to the measurement and control room for remote control.

[0008] In summary, this application at least includes the following beneficial technical effects:

[0009] The existing technology not only cannot carry out the large dynamic pressure separation test of the chin-type hood, but also cannot separate the chin-type hood due to the excessive pressure resistance. However, the test device of the present invention can not only carry out the chin-type hood separation test, but also the chin-type hood can be separated safely, and the scale reduction ratio of the chin-type hood can be increased to 1:5. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a side view of a chin-type head cover separation test device of a hypersonic wind tunnel with a test piece in an embodiment of the present invention;

[0011] Figure 2 It is a schematic diagram of a partially enlarged structure in an embodiment of the present invention.

[0012] Description of reference numerals: 1. test piece; 2. separation mechanism; 3. chin-type head cover; 4. separation spring; 5. locking bolt; 6. balance; 7. straight support rod; 8. middle axis; 9. locking nut; 10. wind tunnel angle of attack mechanism; 11. bottom cover;

[0013] 21. Fastening wire; 22. Release device;

[0014] 12. bracket; 121. support plate; 122. connecting ring;

[0015] 61. Inner shell of the specimen; 611. Conical hole;

[0016] 62. Shell of the specimen; 621. Air inlet of the specimen;

[0017] 31. Hood dovetail; 32. Second inclined surface of dovetail. DETAILED DESCRIPTION

[0018] The present application is further described in detail below with reference to the accompanying drawings and specific embodiments:

[0019] The present application embodiment discloses a chin-type head cover separation test device for a hypersonic wind tunnel, such as Figure 1 and Figure 2 As shown, it includes a test piece 1, a separation mechanism 2, a chin-type head cover 3, a separation spring 4, a locking bolt 5, a balance 6, a straight support rod 7, a central axis 8, a locking nut 9, a bottom cover 11, and a wind tunnel attack angle mechanism 10.

[0020] The straight support rod 7 is coaxially connected to the central axis 8, the balance 6 is connected to the end of the straight support rod away from the central axis 8, the test piece 1 is connected to the end of the balance 6 away from the straight support rod 7, the chin-type head cover 3 is arranged on the outside of the test piece 1, and the wind tunnel angle of attack mechanism 10 is connected to the end of the central axis 8 away from the balance 6; the separation mechanism 2, in the first use state, the separation structure is used to stably fix the chin-type head cover 3 on the outside of the test piece 1, and in the second use state, the separation structure releases the fixation between the chin-type head cover 3 and the test piece 1; the separation spring 4 passes through the test piece 1 and is connected between the chin-type head cover 3 and the separation mechanism 2, the chin-type head cover 3 is provided with a groove on the side facing the test piece 1, and the end of the separation spring 4 is clamped in the groove, and in the first use state, the separation spring 4 is in a compressed state. The chin-type head cover 3 is fixedly connected to the test piece 1 through the separation spring 4 and the separation mechanism 2.

[0021] The separation mechanism 2 includes a fastening line 21 and a releasing device 22. The fastening line 21 passes through the specimen 1. The fastening line 21 is connected between the chin-type head cover 3 and the separation mechanism 2. The fastening line 21 is used to make the chin-type head cover 3 stably close to the outside of the specimen 1. The releasing device 22 is connected to the inside of the specimen 1 and is used to cut off the fastening line 21.

[0022] A bracket 12 is arranged inside the specimen 1, and the bracket 12 includes a support plate 121 and at least two connecting rings 122. The connecting rings 122 are close to the inner wall of the specimen 1 and are fixedly connected to the specimen 1. The support plate 121 is located inside the connecting rings 122 and is fixedly connected to the connecting rings 122. The support plate 121 and the connecting rings 122 are coaxially arranged, and the fastening line 21 is connected to the support plate 121.

[0023] The end of the balance 6 away from the straight support rod 7 is provided with the inner shell 61 of the specimen, and the end of the balance 6 close to the straight support rod 7 has a 10-degree taper, and the straight support rod 7 matches the 10-degree taper of the end of the balance 6; the end of the inner shell 61 of the specimen away from the straight support rod 7 is provided with a tapered hole 611, and the taper of the tapered hole 611 is 5 degrees. The balance 6 is located in the 5-degree tapered hole 611, and the locking bolt 5 passes through the inner shell 61 of the specimen and is threadedly connected with the balance 6, so as to realize the connection between the balance 6 and the specimen 1. The specimen 1 is sleeved on the outer wall of the end of the inner shell 61 of the specimen away from the balance 6, and the specimen 1 is connected to the inner shell 61 of the specimen by bolts, and the bottom of the tapered hole 611 is provided with a taper that matches the taper of the balance 6. The inner shell 61 of the specimen is connected to the outer shell 62 of the specimen by fastening screws, and the specimen 1 , the outer shell 62 of the specimen and the balance 6 are connected together by the locking bolts 5 and the inner shell 61 of the specimen.

[0024] like Figure 2As shown, the outer wall of the outer shell 62 of the specimen is provided with an air inlet 621 of the specimen, and the air inlet 621 of the specimen extends in the direction toward the specimen 1. The front end of the lower jaw head cover 3 near the outer shell 62 of the specimen is provided with a head cover dovetail 31, and the end of the air inlet 621 of the specimen is clamped in the head cover dovetail 31. Specifically, the size of the air inlet 621 of the specimen along the circumferential direction of the outer shell 62 of the specimen is 30-50mm. The head cover dovetail 31 includes a first inclined surface and a blocking inclined surface. The end of the air inlet 621 of the specimen is provided with a guiding inclined surface. Along the direction close to the axis of the specimen 1, the guiding inclined surface gradually inclines toward the direction close to the straight support rod 7. The first inclined surface cooperates with the guiding inclined surface, and the blocking inclined surface is located on the side of the first inclined surface away from the specimen 1. The head cover dovetail 31 formed by the first inclined surface and the blocking inclined surface is V-shaped, and the size of the blocking inclined surface along the axis direction of the specimen 1 is smaller than the size of the first inclined surface along the axis direction of the specimen 1. The end of the lower jaw head cover 3 close to the outer shell 62 of the specimen is provided with a dovetail second inclined surface 32, which is located on the side of the head cover dovetail 31 facing the inner wall of the specimen 1, and gradually tilts toward the direction close to the straight support rod 7 along the direction away from the axis of the specimen 1. This makes the end of the specimen 1 close to the straight support rod 7 no longer close, making it easier for the lower jaw head cover 3 to separate from the specimen 1. When the release device 22 cuts off the fastening line 21, the separation spring 4 gives the lower jaw head cover 3 a thrust, and the lower jaw head cover 3 rotates with the end of the air inlet 621 of the specimen as the center of rotation, thereby completing the separation of the lower jaw head cover 3.

[0025] The wind tunnel angle of attack mechanism 10 is sleeved on the outside of the central axis 8 and is located at the end of the central axis 8 away from the straight support rod 7; the end of the central axis 8 away from the straight support rod 7 is threadedly connected with a locking nut 9, and the locking nut 9 abuts against the end of the wind tunnel angle of attack mechanism 10 away from the straight support rod 7; the end of the wind tunnel angle of attack mechanism 10 away from the straight support rod 7 is threadedly connected with a bottom cover 11, and the bottom cover 11 covers the locking nut 9.

[0026] The connecting line of the balance and the control line of the separation mechanism pass through the inner holes of the support rod 7 and the central axis 8 to the measurement and control room.

[0027] The test device of the present invention is mainly used for the hypersonic wind tunnel chin-type hood separation test. This test needs to be carried out in a 1-meter-level hypersonic wind tunnel. The chin-type hood 3 is fastened to the test piece 1 through the separation spring 4 and the separation mechanism 2. The test piece 1 is connected with the balance 6, the straight support rod 7, and the central axis 8 through the locking bolt 5, and then connected with the wind tunnel angle of attack mechanism 11 through the locking nut 9. The wind tunnel establishes a uniform flow field, and the wind tunnel angle of attack mechanism 11 moves upward to project the entire test device into the uniform flow field. The separation mechanism 2 is unlocked, and the chin-type hood 3 is separated under the action of the aerodynamic force and the separation spring 4, and is measured in real time by a high-speed camera and a dynamic force measurement system. The present invention can provide services for other hypersonic wind tunnel chin-type hood separation tests.

[0028] The use process of the hypersonic wind tunnel chin-type hood separation test device is as follows:

[0029] First, the test piece 1 is connected to the balance 6, the straight support rod 7, and the front end of the central axis 8 through the locking bolt 5, and then the rear end of the central axis 8 is connected to the wind tunnel angle of attack mechanism 11 through the locking nut 9 and the bottom cover 10; the data line of the balance 3 and the control line of the separation mechanism 2 pass through the inner holes of the straight support rod 7 and the central axis 8 to the measurement and control room for remote control.

[0030] Secondly, anti-reflective paint is sprayed on the test piece 1, and marking points are attached to the lower jaw head cover 3; the lower jaw head cover 3 is fixedly connected to the test piece 1 through the separation spring 4 and the separation mechanism 2;

[0031] Third, the dynamic pressure of the wind tunnel test is reasonably selected; when the wind tunnel establishes a uniform flow field, the wind tunnel angle of attack mechanism 11 moves upward to project the entire test device into the uniform flow field, and through remote control, instructions are simultaneously sent to the separation mechanism 2, the balance 6 data collector, and three high-speed cameras; the separation mechanism 2 is unlocked, and the chin-type hood 3 is separated under the action of aerodynamic force and the separation spring 4, and real-time measurement is performed by the high-speed camera and the balance 6.

[0032] Finally, data analysis shows that due to the use of synchronization technology, the shooting speed of the high-speed camera is consistent with the data acquisition frequency of the balance 6, and the characterization characteristics of the separation process of the chin-type head cover 3 correspond one to one with the force measured by the balance 6; based on the similarity criterion, the test results can be converted to the flight state.

[0033] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A chin-type hood separation test device for a hypersonic wind tunnel, characterized in that: include Straight support rod (7); A balance (6) connected to one end of the straight support rod (7); A test piece (1) is connected to the end of the balance (6) away from the straight support rod (7); A lower jaw head cover (3) is arranged on one side outside the test piece (1); A separation mechanism (2), wherein in a first use state, the separation structure is used to stably fix the lower jaw head cover (3) to the outside of the test piece (1); in a second use state, the separation structure releases the fixation between the lower jaw head cover (3) and the test piece (1); A separation spring (4) passes through the test piece (1) and is arranged between the lower jaw head cover (3) and the separation mechanism (2); in a first use state, the separation spring (4) is in a compressed state; A wind tunnel angle of attack mechanism (10) connected to the end of the straight support rod (7) away from the balance (6); The outer shell (62) of the specimen is arranged outside the inner shell (61) of the specimen, and the outer surface of the outer shell (62) of the specimen is provided with an air inlet (621) of the specimen, the air inlet (621) of the specimen extends in a direction toward the specimen (1), and the front end of the air inlet (621) of the specimen is engaged with the dovetail (31) of the head cover; A hood dovetail (31) is provided at the front end of the lower jaw hood (3) close to the outer shell (62) of the specimen, the hood dovetail (31) includes a first inclined surface, and a guiding inclined surface is provided at the end of the air inlet (621). Along the direction close to the axis of the specimen (1), the guiding inclined surface gradually inclines towards the direction close to the straight support rod (7), and the first inclined surface cooperates with the guiding inclined surface; a dovetail second inclined surface (32) is provided at the end of the lower jaw hood (3) close to the outer shell (62) of the specimen, the dovetail second inclined surface (32) is located on the side of the hood dovetail (31) facing the inner wall of the specimen (1), and along the direction away from the axis of the specimen (1), the dovetail second inclined surface (32) gradually inclines towards the direction close to the straight support rod (7).

2. The chin-type head cover separation test device for a hypersonic wind tunnel according to claim 1, characterized in that: The lower jaw head cover (3) is provided with a groove on one side facing the test piece (1), and the end of the separation spring (4) is clamped in the groove.

3. The chin-type head cover separation test device for a hypersonic wind tunnel according to claim 1, characterized in that: The separation mechanism (2) comprises a fastening line (21) and a release device (22); the fastening line (21) passes through the specimen (1); the fastening line (21) is connected between the chin-type head cover (3) and the separation mechanism (2); the fastening line (21) is used to make the chin-type head cover (3) stably adhere to the outer side of the specimen (1); and the release device (22) is connected to the inside of the specimen (1) and is used to cut the fastening line (21).

4. The chin-type head cover separation test device for a hypersonic wind tunnel according to claim 3, characterized in that: The specimen (1) is provided with a bracket (12), the bracket (12) comprising a bracket (121) and at least two connecting rings (122), the connecting rings (122) being closely attached to the inner wall of the specimen (1) and being fixedly connected to the specimen (1), the bracket (121) being located inside the connecting rings (122) and being fixedly connected to the connecting rings (122), and the fastening wire (21) being connected to the bracket (121).

5. The chin-type head cover separation test device for a hypersonic wind tunnel according to claim 1, characterized in that: The balance (6) is provided with an inner shell (61) of a connecting piece specimen at one end away from the straight support rod (7), a tapered hole (611) is opened at one end of the inner shell (61) of the connecting piece specimen, the balance (6) is located in the tapered hole (611), the locking bolt (5) passes through the inner shell (61) of the connecting piece specimen and is threadedly connected to the balance (6), and the specimen (1) is connected to the end of the inner shell (61) of the specimen.

6. The chin-type head cover separation test device for a hypersonic wind tunnel according to claim 5, characterized in that: The end of the balance (6) away from the straight support rod (7) is provided with a taper, and the bottom of the tapered hole (611) is provided with a taper matching the end of the balance (6).

7. The chin-type head cover separation test device for a hypersonic wind tunnel according to claim 1, characterized in that: The end of the straight support rod (7) away from the balance (6) is connected to a central axis (8), and the wind tunnel angle of attack mechanism (10) is sleeved outside the central axis (8) and located at the end of the central axis (8) away from the straight support rod (7); The end of the central axis (8) away from the straight support rod (7) is threadedly connected with a locking nut (9), and the locking nut (9) abuts against the end of the wind tunnel angle of attack mechanism (10) away from the straight support rod (7); The end of the wind tunnel angle of attack mechanism (10) away from the straight support rod (7) is threadedly connected with a bottom cover (11), and the bottom cover (11) covers the locking nut (9).

8. The chin-type head cover separation test device for a hypersonic wind tunnel according to claim 7, characterized in that: The straight support rod (7) and the central axis (8) are provided with threading holes at their axial positions, and the connecting wire of the balance (6) and the control wire of the separation mechanism (2) are connected to the industrial computer through the threading holes.

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