A support system for large maneuver simulation of buried weapon trajectory capture test

Abstract

The present application relates to the technical field of experimental aerodynamics, and specifically discloses a support system for large maneuver simulation of buried weapon trajectory capture test, including a missile model, a strain balance placed inside the missile model, and a tail support mechanism and a head support mechanism connected to both ends of the strain balance for different segmented attack angle ranges; the tail support is used for the attack angle range of 0 to 90 degrees, and the head support is used for the attack angle range of 90 degrees to 180 degrees; the tail support mechanism is connected to one end of the strain balance facing the tail of the missile model, and extends from the tail of the missile model; the head support mechanism is connected to one end of the strain balance facing the head of the missile model, and extends from the head of the missile model; an auxiliary abdominal support and an abdominal support + a fake head support are used to connect the strain balance to correct the interference of the head support. The wind tunnel simulation of the 0 to 180 degree flipping of the missile during the over-stall over-shoulder launch is realized by relaying.

Description

Technical Field

[0001] The present application relates to the technical field of experimental aerodynamics, and in particular to a support system for realizing a 0-180° flip maneuver trajectory capture test of an embedded weapon in a wind tunnel. Background Art

[0002] The separation of multiple bodies, such as the separation of the aircraft and missile, the separation of the interstage, the separation of the booster, and the separation of the cowl, are key technical issues facing aerospace vehicles. During the separation process of multiple bodies, complex multi-body interference flows will occur. During the development of the aircraft, if the separation scheme is not designed reasonably, there will be a risk of collision or loss of control of the separated bodies. At present, omnidirectional attack capability is the trend and direction of the development of the new generation of air-launched missiles, which requires the missile to have the technology of over-stall over-the-shoulder launch, that is, the ability to fly in a rapid turn.

[0003] As an advanced multi-body separation ground simulation technology, the trajectory capture wind tunnel test technology organically combines wind tunnel model tests with flight mechanics. Its outstanding advantages are high prediction accuracy, the ability to obtain test results that are basically consistent with full-scale flight test data, and the ability to simulate complex separation conditions (such as auxiliary drop force, the thrust of the external attachment itself, etc.) and special flight states (such as pitch, climb or accelerated flight, etc.) of external attachments in the test through computer software. It is suitable for launches under certain envelope flight states of the aircraft, and can directly give the external attachment separation trajectory in the test, timely evaluate the separation characteristics, and modify the relevant parameters at any time for testing when necessary. The test can not only obtain the full-scale condition separation trajectory, but also directly measure the aerodynamic load of the external attachment at each measurement point on the separation trajectory, which is conducive to the analysis and improvement of the external attachment separation characteristics. Therefore, the capture trajectory test is a type of wind tunnel test that must be carried out before the air-launched weapon model is finalized.

[0004] Limited by the movement ability and actuation space of the mechanism itself, the existing trajectory capture wind tunnel test support system can usually only achieve movement in the direction of attack angle not exceeding 90° with the help of relay technology, and does not have the test simulation capability of 0~180°, and cannot meet the test requirements of over-stall over-shoulder launch after missile separation. Therefore, it is urgent to develop corresponding simulation capabilities to broaden the scope of use of such test technology. The present invention is proposed under such practical background. Summary of the invention

[0005] In order to meet the requirements of trajectory capture wind tunnel test of over-stall over-shoulder launch after missile separation, the present invention provides a support system for realizing 0-180° flip maneuver trajectory capture test of embedded weapons in a wind tunnel. In the trajectory capture wind tunnel test, the wind tunnel simulation of the over-stall over-shoulder launch process of the missile can be realized by relay mode, and a method and specific measures for correcting the model appearance damage and support interference caused by the head support are proposed.

[0006] This application adopts the following technical solutions:

[0007] A support system for large maneuver simulation of buried weapon trajectory capture test, comprising a missile model, a strain balance placed inside the missile model, a tail support mechanism and a head support mechanism connected to both ends of the strain balance for different segmented attack angle ranges, a belly support system for correcting interference of the head support mechanism, and a belly support with a fake head support system;

[0008] The tail support mechanism is used for tests with an attack angle range of 0 to -90°, and the head support mechanism is used for tests with an attack angle range of -90° to -180°.

[0009] The tail support mechanism is connected to one end of the strain balance toward the tail of the missile model and extends from the tail of the missile model; the head support mechanism is connected to one end of the strain balance toward the head of the missile model and extends from the head of the missile model.

[0010] The strain balance is used to measure the aerodynamic force exerted on the model during the test and provide aerodynamic input for the trajectory capture solution program.

[0011] In the above-mentioned support system, the tail support mechanism includes a tail straight support rod and at least one tail pre-bent support rod applicable to a gradually decreasing range of segmented attack angles, and the head support mechanism includes at least one head pre-bent support rod and a head straight support rod applicable to a gradually decreasing range of segmented attack angles;

[0012] The tail straight support rod, the tail pre-bent support rod, the head straight support rod, and the head pre-bent support rod all include a straight tail rod and a support rod, and a transition section is connected between the straight connecting rod and the support rod;

[0013] The straight connecting rod of the tail straight support rod is coaxially arranged with the missile model and extends from the tail of the missile model, and the preset angle between the support rod and the missile model is 0; the straight connecting rod of the head straight support rod is coaxially arranged with the missile model and extends from the head of the missile model, and the preset angle between the support rod and the missile model is -180°;

[0014] The straight connecting rod of the tail pre-bending support rod is coaxially arranged with the missile model and extends from the tail of the missile model. The preset angle between the supporting rod and the missile model is any angle of 0 to -90°; the straight connecting rod of the head pre-bending support rod is coaxially arranged with the missile model and extends from the head of the missile model. The preset angle between the supporting rod and the missile model is any angle of -90° to -180°.

[0015] In the above-mentioned support system, the 0~-180° attack angle range can be arbitrarily segmented into at least 4 attack angle ranges, and as the attack angle becomes smaller, the strain balance sequentially connects the tail straight strut, at least one tail pre-bent strut, at least one head pre-bent strut, and the head straight strut. In different attack angle segments, the corresponding preset angles of the tail straight strut, the tail pre-bent strut, and the head pre-bent strut to the head straight strut are within the range of the attack angle segment.

[0016] Preferably, within the different attack angle segments, the corresponding preset angles of the tail straight strut, the tail pre-bent strut, and the head pre-bent strut to the head straight strut are the middle values ​​of the attack angle segment range.

[0017] Therefore, the number of segments and specific segment angles of the attack angle range are not limited.

[0018] Specifically, in the attack angle range of 0 to -30°, the tail straight strut is connected to the strain balance; in the attack angle range of -30° to -90°, the tail pre-bent strut is connected to the strain balance; in the attack angle range of -90° to -120°, the head pre-bent strut is connected to the strain balance; in the attack angle range of -120° to -180°, the head straight strut is connected to the strain balance.

[0019] In the above-mentioned support system, each head support model corresponds to a set of abdominal support system and abdominal support with fake head support system, the abdominal support system includes abdominal support model 6.1 and abdominal support support rod 3.1, and the abdominal support with fake head support system includes abdominal support with fake head support model 6.2 and support rod 3.2.

[0020] During the design, it is necessary to consider that there is no interference with the openings of the missile model. The size of the strut and the opening form and size of the missile model at the position where the belly connecting rod is extended are determined by estimating the aerodynamic loads and corresponding elastic deformations of the model. This ensures that the missile model does not collide with the belly supporting strut during the entire test process, and that the damage to the original missile model's appearance is minimized.

[0021] In the above-mentioned support system, during the subsonic test, the distance that the dummy head support protrudes from the head of the missile model is not less than 3 times the closing diameter of the head of the missile model.

[0022] In the above-mentioned support system, during the supersonic test, the distance that the dummy head support protrudes from the missile model is not less than 1.5 times the diameter of the head closing.

[0023] In the above-mentioned support system, the displacements in three directions and the attitude angles in three directions of the missile model at the relay points between different attack angle segments remain exactly the same.

[0024] In the above-mentioned support system, the length of the straight tail rod extending out of the missile model is not less than 3 times the bottom diameter of the missile model.

[0025] The limitation of the length of the straight tail rod is to minimize the support interference at the bottom of the missile model, and the limitation of the length of the dummy head support under different sound speed experimental conditions is to truly simulate the flow conditions near the head support.

[0026] Specifically, the straight tail rod is a straight section or a nearly straight section. When the straight tail rod is a nearly straight section, its gradient angle is less than 1.5°.

[0027] In the above support system, the correction steps of the head support interference are as follows: the aerodynamic quantity measured by the head support mechanism of the missile model is C 0 , the head support mechanism is replaced by the abdominal support system, and the pneumatic quantity measured under the same conditions is C 1 ; Then the abdominal support system is replaced by the abdominal support with dummy head system, and the pneumatic quantity measured under the same conditions is C 2 , the corrected aerodynamic quantity C R =C 0 -(C 2 -C 1 ).

[0028] In summary, the present application includes at least one of the following beneficial technical effects:

[0029] 1. The present invention can realize the change of the missile model attack angle direction in the range of 0~-180° in the wind tunnel trajectory capture test, obtain the trajectory and attitude angle changes of the entire rollover maneuver process, greatly broaden the test capability, and obtain more complete test data.

[0030] 2. The present invention adopts the design of a head support model when realizing the test in the attack angle range of -90~-180°, develops a test method combining a belly support system and a belly support with a fake head system, and corrects the support interference of the head support model and the shaping damage of the head support, thereby ensuring the reliability and accuracy of the test results. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 This is a support system for realizing a 0~-180° attack angle flip maneuver CTS test in an embodiment of the present application.

[0032] Figure 2 Abdominal support mechanism with correction for head support interference.

[0033] Figure 3 Schematic diagram of a typical trajectory capture CTS test.

[0034] Description of reference numerals:

[0035] 11. Straight tail rod; 12. Support rod; 13. Connecting section;

[0036] 21. Tail straight support rod; 22. Tail pre-bent support rod; 23. Head pre-bent support rod; 24. Head straight support rod;

[0037] 3.1. Abdominal support rod; 3.2. Abdominal support rod with false head support rod;

[0038] 4. Missile model;

[0039] 51. Abdominal connecting rod; 52. Abdominal support rod; 53. Dummy head support;

[0040] 6.1. Abdominal support model; 6.2. Abdominal support with false head support model;

[0041] 7. Strain balance; 8. Aircraft carrier model;

[0042] 9. Rolling motion mechanism; 10. Multi-degree-of-freedom motion mechanism. DETAILED DESCRIPTION

[0043] The following is combined with Figure 1-3 The present application is further described in detail with specific embodiments:

[0044] During the wind tunnel test, the aircraft model 8 maintains a fixed posture, and the initial position of the missile model 4 is the missile release position. After the wind tunnel flow field stabilizes, the aerodynamic load of the missile model 4 measured by the strain balance 7 is used as the load input of the missile's six-degree-of-freedom dynamics equation, and the position of the missile model 4 in the wind tunnel at the next moment is solved, and the full-scale relative displacement and relative posture of the missile relative to the aircraft are recorded. The tail straight support rod 21, the strain balance 7 and the missile model 4 are driven to move to the next moment position through the terminal multi-degree-of-freedom mechanism, and the above process is repeated to capture all trajectory points within the separation time.

[0045] Limited by the movement capability and action space of the mechanism itself, the existing trajectory capture wind tunnel test support system can usually only achieve movement in the direction of attack angle not exceeding 90° with the help of relay technology, and cannot meet the test requirements of 0~-180° attack angle of over-stall over-the-shoulder launch after missile separation.

[0046] The embodiment of the present invention discloses a support system for realizing a 0-180° flip maneuver trajectory capture test of an embedded weapon in a wind tunnel.

[0047] Reference Figure 1 and Figure 2 A support system for large-maneuver simulation of buried weapon trajectory capture test, including a carrier model 8, a missile model 4, a strain balance 7 with internal strain of five or six components, a tail support mechanism and a head support mechanism for different segmented angle of attack ranges connected to both ends of the strain balance 7, a correction system for correcting head support interference connected to the strain balance 7, a rolling motion mechanism 9 for driving the missile model 4 to achieve accurate rolling, and a multi-degree-of-freedom motion mechanism 10 for driving the missile model 4 to move.

[0048] The tail support mechanism is connected to one end of the strain balance 7 facing the tail of the missile model 4, and extends from the tail of the missile model 4; the head support mechanism is connected to one end of the strain balance 7 facing the head of the missile model 4, and extends from the head of the missile model 4. The tail support mechanism includes a tail straight strut 21 and at least one tail pre-bent strut 22, and the head support mechanism includes at least one head pre-bent strut 23 and a head straight strut 24, and the tail straight strut 21, the tail pre-bent strut 22, the head pre-bent strut 23, and the head straight strut 24 all include a straight tail rod 11 and a support rod 12, and a connecting section 13 is connected between the straight connecting rod and the support rod 12; the straight connecting rod of the tail straight strut 21 is connected to the missile Model 4 is coaxially arranged and extends from the tail of missile model 4, and the preset angle between support rod 12 and missile model 4 is 0; the straight connecting rod of head straight support rod 24 is coaxially arranged with missile model 4 and extends from the head of missile model 4, and the preset angle between support rod 12 and missile model 4 is -180°; the straight connecting rod of tail pre-bent support rod 22 is coaxially arranged with missile model 4 and extends from the tail of missile model 4, and the preset angle between support rod 12 and missile model 4 is 0~-90° any angle; the straight connecting rod of head pre-bent support rod 23 is coaxially arranged with missile model 4 and extends from the head of missile model 4, and the preset angle between support rod 12 and missile model 4 is -90°~-180° any angle. The length of straight tail rod 11 extending from missile model 4 is not less than 3 times of the bottom diameter of missile model 4.

[0049] Reference Figure 2 Each head support model corresponds to a set of abdominal support system and abdominal support with fake head support system, the abdominal support system includes the abdominal support model 6.1 and the abdominal support rod 3.1, and the abdominal support with fake head support system includes the abdominal support with fake head support model 6.2 and the rod 3.2. The abdominal support model 6.1 and the abdominal support with fake head support model 6.2 both include a modified missile model and a strain balance 7 located in the modified missile model, and the abdominal support rod 3.1 and the rod 3.2 are both connected to the strain balance 7. The opening position of the modified missile model for installing the abdominal support rod 3.1 or the rod 3.2 is different from the opening position on the missile model 4, and the others are the same.

[0050] The belly support rod 3.1 includes a belly connecting rod 51 and a belly support rod 52. The belly connecting rod 51 is used to connect the belly support rod 52 and the strain balance 7. The belly connecting rod 51 is connected to the end of the strain balance 7 facing the head of the corrected missile model. The preset angle between the belly support rod 52 and the missile model is the same as the preset angle of the corresponding head support model. The support rod 3.2 includes the belly support rod 3.1 and a fake head support 53. The fake head support 53 is fixedly connected to the belly connecting rod 51, and the fake head support 53 extends from the head of the corrected missile model. During the subsonic test, the distance between the fake head support 53 and the belly support belt fake head support model 6.2 is not less than 3 times the diameter of the head closing of the corrected missile model. During the supersonic test, the distance between the fake head support 53 and the belly support belt fake head support model 6.2 is not less than 1.5 times the diameter of the head closing.

[0051] The entire trajectory line is simulated in sections. In this embodiment, the tail straight strut 21 is connected to the strain balance 7 in the range of 0 to -30° attack angle, the tail pre-bent strut 22 is connected to the strain balance 7 in the range of -30 to -90° attack angle, the head pre-bent strut 23 is connected to the strain balance 7 in the range of -90 to -120° attack angle, and the head straight strut 24 is connected to the strain balance 7 in the range of -120 to -180° attack angle. It should be particularly noted that the displacements of the model in the three directions and the attitude angles in the three directions at the relay point remain exactly the same.

[0052] In this embodiment, the preset angle between the support rod 12 of the tail straight strut 21 and the missile model 4 is 0°, the preset angle between the support rod 12 of the tail pre-bent strut 22 and the missile model 4 is -60°, the preset angle between the support rod 12 of the head pre-bent strut 23 and the missile model 4 is -120°, and the preset angle between the support rod 12 of the head straight strut 24 and the missile model 4 is -180°.

[0053] For the aerodynamic data of the tail support in the range of 0~-90° attack angle, it is used directly without correction during the test; for the aerodynamic data of the tail support in the range of -90°~-180° attack angle, considering the damage to the model shape caused by the head support and the aerodynamic interference between the head support and the model, the aerodynamic data measured each time must be corrected during the test. Figure 2 The abdominal support system and the abdominal support with false head support system shown in the figure are used to correct the interference of the head support model. The specific correction method is as follows:

[0054] I. Under certain conditions, the aerodynamic quantity of the missile model 4 joint support mechanism test was measured to be C 0 , at this time the model attitude angle is (ɑ, β, γ);

[0055] II. Under the same conditions, the belly support model 6.1 is placed at the corresponding attitude angles (ɑ, β, γ), and the aerodynamic quantity measured by the combination of the belly support mechanism and the belly support model 6.1 is C 1; (The model here is not 4, but 6.1)

[0056] III. Under the same conditions, the belly support with fake head support model 6.2 is placed at the corresponding posture angle (ɑ, β, γ), and the aerodynamic quantity measured by the combination of the belly support with fake head support mechanism and model 6.2 is C 2 ;

[0057] IV. Correct the pneumatic quantity of the head support test to obtain the corrected pneumatic quantity C R =C 0 -(C 2 -C 1 ), the corrected aerodynamic quantity C R Input the missile's six-degree-of-freedom dynamics equation and solve it to obtain its position and posture in the wind tunnel at the next moment.

[0058] Any feature disclosed in this specification (including any additional claims, abstract and drawings), unless otherwise stated, may be replaced by other equivalent or alternative features with similar purposes. That is, unless otherwise stated, each feature is only an example of a series of equivalent or similar features.

[0059] The present invention is not limited to the above-mentioned specific embodiments, but extends to any new features or any new combination disclosed in this specification, as well as any new method or process steps or any new combination disclosed.

[0060] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A support system for large maneuver simulation of buried weapon trajectory capture test, characterized by: It comprises a missile model (4), a strain balance (7) placed inside the missile model (4), a tail support mechanism and a head support mechanism connected to both ends of the strain balance (7) for different segmented attack angle ranges, a belly support system for correcting interference of the head support mechanism, and a belly support with a fake head support system; The tail support mechanism is used in the attack angle range of 0 to -90°, and the head support mechanism is used in the attack angle range of -90° to -180°; The tail support mechanism is connected to one end of the strain balance (7) facing the tail of the missile model (4) and extends from the tail of the missile model (4); the head support mechanism is connected to one end of the strain balance (7) facing the head of the missile model (4) and extends from the head of the missile model (4); The tail support mechanism comprises a tail straight support rod (21) and at least one tail pre-bent support rod (22) for which the range of segmented attack angles is gradually reduced, and the head support mechanism comprises at least one head pre-bent support rod (23) and a head straight support rod (24) for which the range of segmented attack angles is gradually reduced; The tail straight support rod (21), the tail pre-bent support rod (22), the head pre-bent support rod (23), and the head straight support rod (24) all comprise a straight tail rod (11) and a support rod (12), and a transition section (13) is connected between the straight tail rod (11) and the support rod (12); The straight connecting rod of the tail straight support rod (21) is coaxially arranged with the missile model (4) and extends from the tail of the missile model (4), and the preset angle between the support rod (12) and the missile model (4) is 0; the straight connecting rod of the head straight support rod (24) is coaxially arranged with the missile model (4) and extends from the head of the missile model (4), and the preset angle between the support rod (12) and the missile model (4) is -180°; The straight connecting rod of the tail pre-bent support rod (22) is coaxially arranged with the missile model (4) and extends from the tail of the missile model (4), and the preset angle between the support rod (12) and the missile model (4) is an arbitrary angle of 0 to -90 degrees; the straight connecting rod of the head pre-bent support rod (24) is coaxially arranged with the missile model (4) and extends from the head of the missile model (4), and the preset angle between the support rod (12) and the missile model (4) is an arbitrary angle of -90 degrees to -180 degrees; In the attack angle range of 0 to -30°, the tail straight support rod (21) is connected to the strain balance (7); in the attack angle range of -30° to -90°, the tail pre-bent support rod (22) is connected to the strain balance (7); in the attack angle range of -90° to -120°, the head pre-bent support rod (23) is connected to the strain balance (7); in the attack angle range of -120° to -180°, the head straight support rod (24) is connected to the strain balance (7); Each of the head support mechanisms corresponds to a set of abdominal support systems and abdominal support with dummy head support systems, wherein the abdominal support system comprises an abdominal support model (6.1) and an abdominal support rod (3.1), and the abdominal support with dummy head support system comprises an abdominal support with dummy head support model (6.2) and a rod (3.2); the abdominal support model (6.1) and the abdominal support with dummy head support model (6.2) both comprise a modified missile model and a strain balance (7) located inside the modified missile model, and the abdominal support rod (3.1) and the rod (3.2) are both connected to the strain balance (7); the position of the opening of the modified missile model for installing the abdominal support rod (3.1) or the rod (3.2) is different from the position of the opening on the missile model (4), and the others are the same; The belly support rod (3.1) comprises a belly connecting rod (51) and a belly support rod (52), wherein the belly connecting rod (51) is used to connect the belly support rod (52) and the strain balance (7), and the belly connecting rod (51) is connected to one end of the strain balance (7) facing the head of the corrected missile model; the support rod (3.2) comprises a belly support rod (3.1) and a dummy head support (53), wherein one end of the dummy head support (53) close to the strain balance (7) is fixedly connected to the belly connecting rod (51), and the dummy head support (53) extends from the head of the belly support with dummy head support model (6.2); During the subsonic test, the distance between the dummy head support (53) protruding from the belly support and the head of the dummy head support model (6.2) is not less than 3 times the diameter of the head closing of the corrected missile model; during the supersonic test, the distance between the dummy head support (53) protruding from the belly support and the dummy head support model (6.2) is not less than 1.5 times the diameter of the head closing of the corrected missile model.

2. The support system for large maneuver simulation of buried weapon trajectory capture test according to claim 1, characterized in that: The attack angle range of 0 to -180 degrees can be segmented into at least four attack angle ranges, and as the attack angle decreases, the strain balance (7) sequentially connects the tail straight support rod (21), at least one tail pre-bent support rod (22), at least one head pre-bent support rod (23), and the head straight support rod (24), and within different attack angle segments, the corresponding preset angles of the tail straight support rod (21), the tail pre-bent support rod (22), the head pre-bent support rod (23) to the head straight support rod (24) are within the attack angle segment range.

3. The support system for large maneuver simulation of buried weapon trajectory capture test according to claim 1, characterized in that: The missile model (4) maintains completely the same displacements in three directions and attitude angles in three directions at the relay points between different attack angle segments.

4. The support system for large maneuver simulation of buried weapon trajectory capture test according to claim 1, characterized in that: The length of the straight tail rod (11) extending out of the missile model (4) is not less than 3 times the diameter of the bottom of the missile model (4).

5. The support system for large maneuver simulation of buried weapon trajectory capture test according to claim 1, characterized in that: The correction steps of the head support interference are as follows: the aerodynamic quantity of the missile model (4) is measured by using a head support mechanism as C0, the head support mechanism is replaced by an abdominal support system, and the aerodynamic quantity measured under the same conditions is C1; the abdominal support system is then replaced by an abdominal support with a fake head support system, and the aerodynamic quantity measured under the same conditions is C2. The corrected aerodynamic quantity C R =C0-(C2-C1).

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