A rope-connected parallel support device and test system for wind tunnel dynamic testing of a rotating projectile model

Abstract

This invention discloses a rope-connected parallel support device and testing system for wind tunnel dynamic testing of a rotating projectile model. The support device includes a support assembly and a traction assembly. The rotating projectile model consists of a front part and a rear part connected as a single unit via connectors. The front end of a force balance in the support assembly is rotatably connected to the rotating projectile model via a front conical sleeve and a first bearing. The rear end of the force balance is connected to a reverse-locking sleeve via a rear conical sleeve and a second bearing. The reverse-locking sleeve is then connected to the front traction component, while the rear conical sleeve is connected to the tail support component. This support device uses the traction assembly to pull the front traction component and tail support rod of the rotating projectile model, controlling the extension and retraction of the traction cable. The rotating projectile model can achieve multi-angle coupled motions of precession, nutation, and spin.

Description

Technical Field

[0001] This invention relates to the field of rotating projectile wind tunnel testing technology, specifically to a rope-connected parallel support device and testing system for dynamic wind tunnel testing of rotating projectile models. Background Technology

[0002] When a spinning projectile is in flight, its angular motion exhibits three forms: rotation around its longitudinal axis, precession (rotation around the velocity vector axis), and nutation (rotation around a spatial axis). During flight, the projectile's attitude rapidly changes between these three coupled motions, resulting in irregular oscillations in its yaw and pitch rates. These rotational motions can lead to various instabilities, including gyroscopic instability, Magnus instability, coupled resonance, catastrophic yaw, and large-angle nutation. These not only affect the projectile's range and accuracy but can also, in severe cases, cause structural damage and flight failure. These phenomena are closely related to the unsteady aerodynamic characteristics, nonlinear flight dynamics, and flight control characteristics of spinning projectiles, as well as their coupling. Simulating the angular motion of spinning projectiles and measuring their unsteady aerodynamic forces during flight through wind tunnel testing is a crucial method for studying the dynamic aerodynamic characteristics of spinning projectiles. Therefore, developing a new type of wind tunnel test model support technology that can reproduce the high dynamic motion and aerodynamic coupling characteristics of rotating projectiles under high rotation, high overload, and high speed is of great practical significance for understanding the nutation characteristics, conical motion stability, and dynamic aerodynamic characteristics of projectiles. It is also a requirement for the country to strengthen its defense capabilities.

[0003] The applicant's earlier Chinese patent CN112179608B proposed a support component and test system for wind tunnel dynamic testing of a rotating projectile model. The support component mainly uses a force balance as a connector between the front and rear of the model, which can facilitate the installation and use of the force balance in the rotating projectile model. However, the connection method between the front and rear sections of the projectile in this support component restricts the effective transmission of aerodynamic force between the projectile and the force balance, affecting the accuracy and usability of the measurement results. Summary of the Invention

[0004] The purpose of this invention is to overcome the aforementioned defects or problems in the prior art and to provide a rope-connected parallel support device and test system for wind tunnel dynamic testing of a rotating projectile model. This improves the internal support structure design of the rotating projectile model, thereby improving the accuracy and usability of the force balance measurement results.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] Technical Solution 1: A rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model, comprising: a rotating projectile model, including a projectile front part, a projectile rear part, and a connecting member; the connecting member is fixedly connected to the projectile front part and the projectile rear part; the projectile rear part is provided with a tail fin; a support assembly, including a force balance, a front cone sleeve, a tail cone sleeve, a first bearing, a second bearing, a reverse-locking sleeve, a tail support member, a third bearing, and a front traction member; the force balance is located inside the rotating projectile model and extends from the projectile front part to the projectile rear part, its front end is fixedly connected to the inner side of the front cone sleeve, and its rear end is fixedly connected to the inner side of the tail cone sleeve; the front cone sleeve is fixedly connected to the projectile front part through the first bearing; the tail cone sleeve is fixedly connected to the projectile rear part through the second bearing; The bearing is connected to the reverse-locking sleeve and fixed to the tail support; the reverse-locking sleeve is fitted from back to front on the outside of the force balance and extends to the center of mass of the rotating projectile model, and its front end is connected to the front traction member through the third bearing; the tail support member extends out of the rear of the projectile; the front traction member is located between the front and rear of the projectile, and its outer surface is aligned with the outer surfaces of the front and rear of the projectile; and the traction assembly includes several traction cables and a retraction unit for retracting and deploying the corresponding traction cables, which supports the rotating projectile model by pulling the front traction member and the tail support member, and constrains the other degrees of freedom of the rotating projectile model except for roll, so as to control the position and attitude of the rotating projectile model in the wind tunnel.

[0007] Technical Solution 2 based on Technical Solution 1: The front end of the reverse-locking sleeve is provided with a hollow flange edge, and the hollow flange edge is provided with several through-holes; the connector is provided with a front connecting part, several connecting arms extending forward and backward and a rear connecting part, the connecting arms connect the front connecting part and the rear connecting part and pass through the hollow flange edge; the front connecting part is fixedly connected to the front part of the projectile, and the rear connecting part is fixedly connected to the rear part of the projectile.

[0008] Technical solution three based on technical solution two: there is a gap between the connecting arm and the corresponding clearance hole.

[0009] Technical Solution 4 based on Technical Solution 1: The tail support includes a tail support rod, a tail support seat, and a tail crossbar. The tail support rod extends in the front-to-back direction, the tail support seat is fixed to the rear end of the tail support rod, and the tail crossbar is fixed to the tail support seat and extends in the left-to-right direction. The traction cable of the traction assembly pulls on the left and right ends of the tail crossbar.

[0010] Technical solution five based on technical solution one: The support component also includes a bearing sleeve, which is sleeved on the outside of the outer ring of the third bearing and fixedly connected to the front traction member. It is located between the front part and the rear part of the projectile and its outer surface is aligned with the outer surface of the front part and the rear part of the projectile.

[0011] Technical Solution Six based on Technical Solution One: The traction assembly further includes several universal pulleys corresponding to the traction cables. Each universal pulley is fixed relative to the wind tunnel wall, and each traction cable is connected to the corresponding take-up and release unit through the corresponding universal pulley. The take-up and release unit adopts an electric winch or a screw-slider mechanism.

[0012] Technical solution seven based on technical solution four: The number of traction cables is seven or more.

[0013] Technical solution eight based on technical solution seven: When the number of traction cables is eight, each traction cable is as follows: two front upper traction cables connected to the front traction member and extending upward to both sides of the wind tunnel; two front lower traction cables connected to the front traction member and extending downward to both sides of the wind tunnel; two rear upper traction cables connected to both ends of the tail crossbar and extending upward to both sides of the wind tunnel; and two rear lower traction cables connected to both ends of the tail crossbar and extending downward to both sides of the wind tunnel.

[0014] Furthermore, the present invention also provides technical solution nine: a test system for wind tunnel dynamic testing of a rotating projectile model, comprising: a rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model as described in any one of technical solutions one to nine; an attitude and bearing device, which is placed on the tail support for measuring the real-time attitude angle of the rotating projectile model; a take-up and release control device, which is electrically connected to each take-up and release unit and is used to control each take-up and release unit to take up and release the traction cable; and a data acquisition and processing device, which acquires signals from the attitude and bearing device and the force balance, and obtains the aerodynamic parameters of the rotating projectile model through processing.

[0015] Technical solution ten based on technical solution nine: The take-up and release control device further includes a tension sensor, which is configured correspondingly to each of the traction cables and is used to detect the tension of the traction cable so as to keep the traction cable at appropriate tension by controlling the take-up and release unit.

[0016] As can be seen from the above description of the present invention, compared with the prior art, the present invention has the following beneficial effects:

[0017] Technical Solution 1 provides a rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model. The device includes a rotating projectile model, a support assembly, and a traction assembly. The front and rear parts of the rotating projectile model are connected as a single unit via a connector, solving the connection problem between the front and rear parts of the projectile and eliminating the need for a force balance, thus reducing the impact on the accuracy of the force balance's measurements. Simultaneously, in the support assembly, the front end of the force balance is fixedly connected to the front cone sleeve, and the rear end is fixedly connected to the tail cone sleeve. A first bearing and a second bearing connect the front end of the force balance to the rotating projectile model, and the rear end to a reverse-locking sleeve. Because of the bearing connection, the rolling of the rotating projectile model does not affect the force balance, and the rolling freedom of the rotating projectile model is fully released. Furthermore, the reverse-locking sleeve in the support assembly is fitted outside the force balance and, in addition to being connected to the force balance, is also connected to the front traction component via a third bearing.

[0018] The traction cable of the traction component pulls and supports the rotating projectile model, enabling the rotating projectile model to perform multi-degree-of-freedom coupled motion under the action of the traction component. Furthermore, since the traction cable of the traction component is pulled on the front traction member and the tail support member, the rolling degree of freedom of the rotating projectile model is released, and the rotating projectile model can roll under the action of the tail fin and the incoming flow. Therefore, the rotating projectile model as a whole can realize multi-angle coupled motion of rotation, precession and nutation.

[0019] Overall, during the force transmission process, only the front end of the force balance contacts the rotating projectile model to sense the aerodynamic forces it experiences; the rest of the balance remains in contact with the model. Therefore, during wind tunnel testing, all aerodynamic forces except for the rolling moment can be accurately measured by the force balance. When the tail fin has a deflection angle, the incoming flow will cause the rotating projectile model to roll. Since the rear end of the force balance is connected to the reverse-locking sleeve via a bearing, the force balance will not roll with the model and can follow it in other degrees of freedom. In summary, the rotating projectile testing device provided by this technical solution has advantages such as accurate force measurement, high support stiffness, large working space, and minimal impact on the flow field. It can also realize complex multi-degree-of-freedom coupled motions with rotation capabilities.

[0020] In technical solution two, a hollow flange edge is set at the front end of the reverse-locking sleeve, and the connecting arm of the connector can pass through the clearance hole on the hollow flange edge, so that the connector can be connected to the front and rear parts of the projectile through its front and rear connecting parts to form a rotating projectile model.

[0021] In technical solution three, a gap is set between the connecting arm and the corresponding clearance hole to prevent the transmission of force between the connector and the reverse sleeve.

[0022] In technical solution four, the tail support component includes a tail support rod, a tail support seat, and a tail crossbar. The tail support rod extends a certain distance from the rear end of the rotating projectile model. The tail support seat is used to connect the tail support rod and the tail crossbar. The tail crossbar is used to connect with the traction cable of the traction component to avoid interfering with the rotating projectile model.

[0023] In technical solution five, a bearing sleeve is set to cover the third bearing, and the outer surface of the bearing sleeve is aligned with the outer surfaces of the front and rear parts of the projectile to reduce the impact of the bearing sleeve on the surface aerodynamic performance of the rotating projectile model.

[0024] In technical solution six, the traction component also includes a universal pulley, which allows for easy adjustment of the position and posture of the rotating projectile model in multiple degrees of freedom via the traction cable; the take-up and release unit adopts an electric winch or a screw-slider mechanism, which can accurately control the degree of take-up and release of the traction cable.

[0025] In technical solution seven, the number of traction cables is set to seven or more, which can achieve fully constrained motion control of the rotating projectile model in six degrees of freedom, excluding rotation.

[0026] In technical solution eight, when there are eight traction cables and the position of each traction cable is limited, this arrangement can reduce the interference with the flow field around the rotating projectile model, and has high support stiffness, making it suitable for high-speed wind tunnel testing.

[0027] Technical Solution Nine provides a rotating projectile testing system, which can control the traction length of each traction cable through a release and take-off control device with a predetermined computer program, thereby controlling the rotating projectile model to achieve complex angular motion with multiple degrees of freedom, especially complex motion resulting from the coupling of precession and nutation. At the same time, the rotating projectile model is also rotating. Therefore, the whole system can realize the motion trajectory formed by the combination of three motion forms of rotation, precession and nutation according to complex laws. Furthermore, through an attitude and data acquisition and processing device, the attitude angle, rotation speed and force balance signals of the rotating projectile model can be collected and processed to obtain the aerodynamic parameters of the rotating projectile model.

[0028] In technical solution ten, the launch and recovery control device also includes a tension sensor, which can detect the tension of the traction cable to keep the traction cable in an appropriate tension state, thereby supporting the rotating projectile model. Attached Figure Description

[0029] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the following description of the embodiments are briefly introduced. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1A schematic diagram of the rotating projectile testing device provided in an embodiment of the present invention;

[0031] Figure 2 for Figure 1 Schematic diagram of some components of a rotating projectile-launcher test device;

[0032] Figure 3 for Figure 2 Rear view of some components of the rotating projectile-launch test device;

[0033] Figure 4 for Figure 3 Schematic diagram of section AA;

[0034] Figure 5 for Figure 4 An explosive schematic diagram of some components of the rotating projectile test device.

[0035] Explanation of key figure labels:

[0036] Rotating projectile model 1; Projectile front part 2; Projectile rear part 3; Connector 4; Tail fin 5; Support assembly 6; Force balance 7; Front cone sleeve 8; Tail cone sleeve 9; First bearing 10; Second bearing 11; Reverse-lock sleeve 12; Tail support 13; Third bearing 14; Front traction component 15; Traction assembly 16; Tail support rod 17; Tail support seat 18; Tail crossbar 19; Bearing sleeve 20; Front upper traction cable 21; Front lower traction cable 22; Rear upper traction cable 23; Rear lower traction cable 24; Hollowed-out flange edge 25; Clearance hole 26; Front connecting part 27; Connecting arm 28; Rear connecting part 29. Detailed Implementation

[0037] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are preferred embodiments of the present invention and should not be considered as excluding other embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0038] Unless otherwise expressly defined, the use of terms such as "first," "second," or "third" in the claims, description, and accompanying drawings of this invention is for distinguishing different objects and not for describing a specific order.

[0039] Unless otherwise expressly defined, in the claims, description, and accompanying drawings of this invention, the use of directional terms such as "center," "lateral," "longitudinal," "horizontal," "vertical," "top," "bottom," "inner," "outer," "upper," "lower," "front," "rear," "left," "right," "clockwise," and "counterclockwise" to indicate orientation or positional relationships is based on the orientation and positional relationships shown in the accompanying drawings and is only for the convenience of describing the invention and simplifying the description, and is not intended to indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the specific scope of protection of this invention.

[0040] Unless otherwise expressly defined, the terms "fixed connection" or "fixed connection" used in the claims, description and drawings of this invention should be interpreted broadly to refer to any connection in which there is no displacement or relative rotation relationship between the two parties, including non-removable fixed connection, detachable fixed connection, integral connection and fixed connection by other means or components.

[0041] In the claims, description and accompanying drawings of this invention, the terms "comprising," "having," and variations thereof are used to mean "including but not limited to."

[0042] Example 1

[0043] Reference Figure 1 Embodiment 1 of the present invention provides a rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model. The testing device mainly includes a rotating projectile model 1, a support component 6, and a traction component 16.

[0044] Reference Figure 2 The rotating projectile model 1 includes a projectile front part 2, a projectile rear part 3, and a connector 4. The connector 4 is fixedly connected to the projectile front part 2 and the projectile rear part 3; and the projectile rear part 3 is provided with a tail fin 5.

[0045] Specifically, refer to Figure 2 The rotating projectile model 1 has a projectile front part 2 consisting of a cylindrical front projectile body and a cone-shaped projectile head fixed to the front end of the front projectile body. The projectile rear part 3 is a cylindrical rear projectile body. A tail fin 5 is fixed to the rear end of the projectile rear part 3. There are four tail fins 5, which are arranged in an equidistant manner. They can be regarded as the four tail fins 5 being located at the top, bottom, left, and right positions respectively.

[0046] The front part 2 and the rear part 3 of the rotating projectile model 1 are connected by a connector 4. (See reference...) Figure 3 , Figure 4 and Figure 5The connector 4 has a front connecting portion 27, several connecting arms 28 extending forward and backward, and a rear connecting portion 29. The connecting arms 28 connect the front connecting portion 27 and the rear connecting portion 29. The front connecting portion 27 is fixedly connected to the front part 2 of the projectile, and the rear connecting portion 29 is fixedly connected to the rear part 3 of the projectile. The connector 4 is located between the front part 2 and the rear part 3 of the projectile, with the front connecting portion 27 extending into the inside of the front part 2 and the rear connecting portion 29 extending into the inside of the rear part 3. The front part 2 of the projectile is locked to the front connecting portion 27 by bolts, and the rear part 3 of the projectile is locked to the rear connecting portion 29 by bolts, so that the front part 2 and the rear part 3 of the projectile are connected as one unit.

[0047] Reference Figure 4 and Figure 5 The support assembly 6 includes a force balance 7, a front cone sleeve 8, a tail cone sleeve 9, a first bearing 10, a second bearing 11, a snap-fit ​​sleeve 12, a tail support 13, a third bearing 14, a front traction member 15, and a bearing sleeve 20. The force balance 7 is located inside the rotating projectile model 1 and extends from the front part 2 of the projectile to the rear part 3. Its front end is fixed to the inner side of the front cone sleeve 8, and its rear end is fixed to the inner side of the tail cone sleeve 9. The front cone sleeve 8 is fixed to the front part 2 of the projectile via the first bearing 10. The tail cone sleeve 9 is connected to the snap-fit ​​sleeve 12 via the second bearing 11 and is fixed to the tail support member 13. The snap-fit ​​sleeve 12 is fitted from back to front on the outside of the force balance 7 and extends to the center of mass of the rotating projectile model 1, with its front end connected to the front traction member 15 via the third bearing 14. The front end of the reverse-lock sleeve 12 is provided with a hollow flange edge 25, and the hollow flange edge 25 is provided with several through-holes 26. The tail support 13 extends out of the rear part 3 of the projectile. The tail support 13 includes a tail support rod 17, a tail support seat 18, and a tail crossbar 19. The tail support rod 17 extends in the front-rear direction. The tail support seat 18 is fixed to the rear end of the tail support rod 17. The tail crossbar 19 is fixed to the tail support seat 18 and extends in the left-right direction. The traction cable of the traction assembly 16 pulls on the left and right ends of the tail crossbar 19. The front traction member 15 is located between the front part 2 and the rear part 3 of the projectile, and its outer surface is aligned with the outer surfaces of the front part 2 and the rear part 3 of the projectile. The bearing sleeve 20 is sleeved on the outside of the outer ring of the third bearing 14 and fixed to the front traction member 15. It is located between the front part 2 and the rear part 3 of the projectile, and its outer surface is aligned with the outer surfaces of the front part 2 and the rear part 3 of the projectile.

[0048] Specifically, refer to Figure 4 and Figure 5The force balance 7 is a rod-type six-component balance, which is located inside the rotating projectile model 1, and its extension direction is also in the front-to-back direction. The front cone sleeve 8 is located at the front end of the force balance 7. The front cone sleeve 8 is roughly cylindrical, and its interior is cone-shaped to match the shape of the front end of the force balance 7, allowing the front cone sleeve 8 to be fixedly connected to the front end of the force balance 7. Similarly, the tail cone sleeve 9 is located at the rear end of the force balance 7. The tail cone sleeve 9 is also roughly cylindrical, and its interior is cone-shaped to match the shape of the rear end of the force balance 7, allowing the tail cone sleeve 9 to be fixedly connected to the rear end of the force balance 7. Furthermore, the rear end of the tail cone sleeve 9 extends rearward a certain distance, and the front end of the tail support rod 17 of the tail support member 13 extends into the rear end of the tail cone sleeve 9, and the two are fixed together by bolts.

[0049] Reference Figure 4 A first bearing 10 is fitted onto the outer surface of the front conical sleeve 8. The front conical sleeve 8 is fixedly connected to the inner ring of the first bearing 10, and the outer ring of the first bearing 10 is fixedly connected to the front connecting part 27 of the connecting piece 4, thus fixing the outer ring of the first bearing 10 to the rotating projectile model 1. Simultaneously, a second bearing 11 is fitted onto the outer surface of the tail cone sleeve 9. The tail cone sleeve 9 is fixedly connected to the inner ring of the second bearing 11, and the outer ring of the second bearing 11 is fixedly connected to the reverse-locking sleeve 12. The reverse-locking sleeve 12 extends from rear to front to the mass point position of the rotating projectile model 1, and is fitted onto the outside of the force balance 7, without contacting the force balance 7. (Refer to...) Figure 5 At the front end of the reverse-locking sleeve 12, a perforated flange edge 25 is provided. The perforated flange edge 25 has a certain thickness in the front-to-back direction to fit with the third bearing 14. A through-hole 26 is provided on the perforated flange edge 25. The through-hole 26 is fan-shaped, which can reduce the space occupied by the through-hole 26 and reduce the outer diameter of the rotating projectile model 1. The number and position of the connecting arms 28 of the connector 4 correspond to the through-hole 26. The connecting arms 28 can pass through the corresponding through-hole 26 in the front-to-back direction, thereby avoiding interference between the reverse-locking sleeve 12 and the connector 4. The outer surface of the perforated flange edge 25 at the front end of the reverse-locking sleeve 12 is connected to the inner ring of the third bearing 14. The outer ring of the third bearing 14 is fitted with a bearing sleeve 20, and the front traction member 15 is fixedly connected to the bearing sleeve 20. Furthermore, there is a gap between the clearance hole 26 on the hollow flange edge 25 and the corresponding connecting arm 28. That is to say, the vertical cross-sectional dimension of the connecting arm 28 is smaller than the vertical cross-sectional dimension of the clearance hole 26. This can prevent the transmission of force between the connector 4 and the reverse sleeve 12.

[0050] Through the above connection, when the tail fin 5 of the rotating projectile model 1 generates a rudder deflection angle, the rotating projectile model 1 will roll under the action of the incoming flow. At this time, the front part 2, the rear part 3, and the connecting part 4 of the rotating projectile model 1 will all roll. However, the front connecting part 27 of the connecting part 4 is connected to the front cone sleeve 8 through the first bearing 10, and the rear end of the reverse sleeve 12 is connected to the tail cone sleeve 9 through the second bearing 11. The front end of the reverse sleeve 12 is connected to the front traction member 15 through the third bearing 14. Therefore, the rolling of the rotating projectile model 1 will not affect the force balance 7.

[0051] Reference Figure 1 The traction assembly 16 includes several traction cables and a take-up / deployment unit (not shown in the figure) for retracting and deploying the corresponding traction cables. It supports the rotating projectile model 1 by pulling the front traction member 15 and the tail support member 13, and constrains the rotating projectile model 1's degrees of freedom other than roll, thereby controlling the rotating projectile model 1's position and orientation in the wind tunnel. The traction assembly 16 also includes several universal pulleys corresponding to the traction cables. Each universal pulley is fixed relative to the wind tunnel wall, and each traction cable is connected to its corresponding take-up / deployment unit via the corresponding universal pulley. The take-up / deployment unit employs an electric winch or a screw-slider mechanism.

[0052] Reference Figure 1 There are eight traction cables: two front upper traction cables 21 connected to the front traction member 15 and extending upwards to both sides of the wind tunnel; two front lower traction cables 22 connected to the front traction member 15 and extending downwards to both sides of the wind tunnel; two rear upper traction cables 23 connected to the tail support member 13 and extending upwards to both sides of the wind tunnel; and two rear lower traction cables 24 connected to the tail support member 13 and extending downwards to both sides of the wind tunnel. The two front upper traction cables 21 are inclined backwards and upwards, the two front lower traction cables 22 are inclined backwards and downwards, the two rear upper traction cables 23 are inclined forwards and upwards, and the two rear lower traction cables 24 are inclined forwards and downwards.

[0053] Reference Figure 4 Both the front traction component 15 and the bearing sleeve 20 are roughly annular structures, and their outer surfaces are aligned with the outer surfaces of the front part 2 and the rear part 3 of the projectile. This reduces the impact of the front traction component 15 and the bearing sleeve 20 on the surface aerodynamic performance of the rotating projectile model 1. Four evenly distributed connection points for the traction cables are located circumferentially on the outer surface of the front traction component 15, at the upper left, lower left, upper right, and lower right positions, respectively. Two upper front traction cables 21 connect to the two connection points located at the upper left and upper right, respectively, and two lower front traction cables 22 connect to the two connection points located at the lower left and lower right, respectively.

[0054] The tail support component 13 includes a tail support rod 17, a tail support seat 18, and a tail crossbar 19. The tail support rod 17 extends in the front-to-back direction, with its front end fixed to the tail cone sleeve 9 and its rear end fixedly mounted on the tail support seat 18. The tail support rod 17 can lengthen the distance between the tail crossbar 19 and the rotating projectile model 1, preventing the traction cable from interfering with the rotating projectile model 1. The tail crossbar 19 is fixedly installed on the tail support seat 18, extending to the left and right sides by equal lengths. Four traction cable connection points are provided at both ends of the tail crossbar 19, with each connection point located at the upper and lower positions, respectively. Two upper rear traction cables 23 are respectively connected to the two connection points at the upper positions of the left and right ends of the tail crossbar 19, and two lower rear traction cables 24 are respectively connected to the two connection points at the lower positions of the left and right ends of the tail crossbar 19.

[0055] This embodiment provides a rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model. The device includes a rotating projectile model 1, a support assembly 6, and a traction assembly 16. The front part 2 and rear part 3 of the rotating projectile model 1 are connected as one unit via a connector 4, solving the connection problem between the front part 2 and the rear part 3. This eliminates the need for a separate connection via a force balance 7, reducing the impact on the accuracy of the force balance 7's measurements. Simultaneously, in the support assembly 6, the front end of the force balance 7 is fixedly connected to the front cone sleeve 8, and the rear end is connected to... The tail cone sleeve 9 is fixedly connected, and the front end of the force balance 7 is connected to the rotating projectile model 1 and the rear end is connected to the reverse sleeve 12 through the first bearing 10 and the second bearing 11. Since the connection is through the bearing, the rolling of the rotating projectile model 1 will not affect the force balance 7, and the rolling freedom of the rotating projectile model 1 is also fully released. In addition, the reverse sleeve 12 in the support assembly 6 is sleeved on the outside of the force balance 7. In addition to being connected to the force balance 7, the reverse sleeve 12 is also connected to the front traction member 15 through the third bearing 14.

[0056] The traction cable of the traction component 16 pulls and supports the rotating projectile model 1, so that the rotating projectile model 1 can perform multi-degree-of-freedom coupled motion under the action of the traction component 16. Since the traction cable of the traction component 16 is pulled on the front traction member 15 and the tail support member 13, the rolling degree of freedom of the rotating projectile model 1 is released, and the rotating projectile model 1 can roll under the action of the tail fin 5 and the incoming flow.

[0057] Overall, during the force transmission process, only the front end of the force balance 7 contacts the rotating projectile model 1 to sense the aerodynamic force borne by the rotating projectile model 1; the rest of the balance does not contact the rotating projectile model 1. Therefore, during wind tunnel testing, except for the rolling moment, all other components of the aerodynamic force borne by the rotating projectile model 1 can be accurately measured by the force balance 7. When the tail fin 5 has a deflection angle, the incoming flow will cause the rotating projectile model 1 to roll. Since the rear end of the force balance 7 is connected to the reverse sleeve 12 through a bearing, the force balance 7 will not roll with the rotating projectile model 1 and can follow the rotating projectile model 1 in other degrees of freedom. In summary, the rotating projectile test device provided by this technical solution has the advantages of accurate force measurement, high support stiffness, large working space, and small impact on the flow field, and can realize complex multi-degree-of-freedom coupled motion with rotation capability.

[0058] Example 2

[0059] Embodiment 2 of the present invention provides a test system for wind tunnel dynamic testing of a rotating projectile model. This test system includes the rotating projectile test apparatus provided in Embodiment 1, as well as an attitude and bearing device, a launch and recovery control device, and a data acquisition and processing device. The attitude and bearing device is located on the tail support 13 and is used to measure the real-time attitude angle of the rotating projectile model 1. The launch and recovery control device is electrically connected to each launch and recovery unit and is used to control the launch and recovery of the traction cable by each unit. The data acquisition and processing device acquires signals from the attitude and bearing device and the force balance 7, and processes them to obtain the aerodynamic parameters of the rotating projectile model 1.

[0060] The attitude and heading reference system (ARS) is a navigation device that integrates multiple sensors to determine the precise attitude and heading of a vehicle (such as an aircraft, drone, or ship). Its core components include a three-axis gyroscope, a three-axis accelerometer, and a three-axis magnetometer. These sensors work together, employing sophisticated data fusion algorithms such as Kalman filters, to provide dynamic spatial attitude (including roll and pitch angles) and heading information.

[0061] The operation of the launch and take-off control device and related computer programs can be found in the relevant chapters of "Feasibility Study of SDM Dynamic Derivative Based on Rope-Tethered Parallel Robot Support System" published in the 38th issue of the Journal of Aeronautics on November 25, 2017.

[0062] The rotating projectile test system provided in this embodiment can control the traction length of each traction cable through a release and take-off control device with a predetermined computer program, thereby controlling the rotating projectile model 1 to achieve complex angular motion with multiple degrees of freedom, especially the complex motion formed by the coupling of precession and nutation. Of course, the rotating projectile model 1 is also rotating at the same time. Therefore, the system can simulate the motion trajectory formed by the combination of three motion forms of rotation, precession and nutation according to complex laws. Furthermore, through the attitude instrument and data acquisition and processing device, the attitude angle of the rotating projectile model 1 and the signal of the force balance 7 can be acquired and processed to obtain the aerodynamic parameters of the rotating projectile model 1.

[0063] The foregoing description of the specifications and embodiments is intended to explain the scope of protection of this invention, but does not constitute a limitation on the scope of protection of this invention. Modifications, equivalent substitutions, or other improvements to the embodiments of this invention or a portion thereof that can be obtained by those skilled in the art through logical analysis, reasoning, or limited experimentation, based on the teachings of this invention or the foregoing embodiments, in conjunction with common knowledge, general technical knowledge, and / or existing technology, should all be included within the scope of protection of this invention.

Claims

1. A rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model, characterized in that, The rotating projectile model (1) includes a projectile front part (2), a projectile rear part (3), and a connector (4); the connector (4) is fixedly connected to the projectile front part (2) and the projectile rear part (3); the projectile rear part (3) is provided with a tail fin (5). The support device includes: The support assembly (6) includes a force balance (7), a front cone sleeve (8), a tail cone sleeve (9), a first bearing (10), a second bearing (11), a reverse sleeve (12), a tail support (13), a third bearing (14), and a front traction component (15); the force balance (7) is located inside the rotating projectile model (1) and extends from the front part (2) of the projectile to the rear part (3) of the projectile, with its front end fixed to the inner side of the front cone sleeve (8) and its rear end fixed to the inner side of the tail cone sleeve (9); the front cone sleeve (8) is fixed to the front part (2) of the projectile through the first bearing (10); the tail cone... The sleeve (9) is connected to the reverse sleeve (12) via the second bearing (11) and fixed to the tail support (13); the reverse sleeve (12) is fitted from back to front on the outside of the force balance (7) and extends to the center of mass of the rotating projectile model (1), and its front end is connected to the front traction member (15) via the third bearing (14); the tail support member (13) extends out of the rear part (3) of the projectile; the front traction member (15) is located between the front part (2) and the rear part (3) of the projectile, and its outer surface is aligned with the outer surfaces of the front part (2) and the rear part (3) of the projectile; and The traction assembly (16) includes several traction cables and a take-up and take-up unit for taking up and taking down the corresponding traction cables. It supports the rotating projectile model (1) by pulling the front traction member (15) and the tail support member (13), and constrains the other degrees of freedom of the rotating projectile model (1) except for rolling, so as to control the position and orientation of the rotating projectile model (1) in the wind tunnel. The front end of the reverse-lock sleeve (12) is provided with a hollow flange edge (25), and the hollow flange edge (25) is provided with several through-holes (26); the connector (4) is provided with a front connecting part (27), several connecting arms (28) extending forward and backward and a rear connecting part (29), the connecting arms (28) connect the front connecting part (27) and the rear connecting part (29) and pass through the hollow flange edge (25); the front connecting part (27) is fixedly connected to the front part (2) of the projectile, and the rear connecting part (29) is fixedly connected to the rear part (3) of the projectile.

2. The rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model as described in claim 1, characterized in that, There is a gap between the connecting arm (28) and the corresponding clearance hole (26).

3. The rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model as described in claim 1, characterized in that, The tail support (13) includes a tail support rod (17), a tail support seat (18), and a tail crossbar (19). The tail support rod (17) extends in the front-to-back direction. The tail support seat (18) is fixed to the rear end of the tail support rod (17). The tail crossbar (19) is fixed to the tail support seat (18) and extends in the left-to-right direction. The traction cable of the traction assembly (16) pulls on the left and right ends of the tail crossbar (19).

4. The rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model as described in claim 1, characterized in that, The support assembly (6) also includes a bearing sleeve (20), which is sleeved on the outside of the outer ring of the third bearing (14) and fixed to the front traction member (15). It is located between the front part (2) and the rear part (3) of the projectile, and its outer surface is aligned with the outer surfaces of the front part (2) and the rear part (3) of the projectile.

5. The rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model as described in claim 1, characterized in that, The traction assembly (16) also includes several universal pulleys corresponding to the traction cables. Each universal pulley is fixed relative to the wind tunnel wall, and each traction cable is connected to the corresponding take-up and release unit through the corresponding universal pulley. The take-up and release unit adopts an electric winch or a screw-slider mechanism.

6. The rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model as described in claim 3, characterized in that, The number of traction cables is seven or more.

7. The rope-connected parallel support device for wind tunnel dynamic testing of a rotating projectile model as described in claim 6, characterized in that, When the number of traction cables is eight, each traction cable is as follows: two front upper traction cables (21) connected to the front traction member (15) and extending upward to both sides of the wind tunnel; two front lower traction cables (22) connected to the front traction member (15) and extending downward to both sides of the wind tunnel; two rear upper traction cables (23) connected to both ends of the tail crossbar (19) and extending upward to both sides of the wind tunnel; and two rear lower traction cables (24) connected to both ends of the tail crossbar (19) and extending downward to both sides of the wind tunnel.

8. A test system for wind tunnel dynamic testing of a rotating projectile model, characterized in that it comprises: Rope-connected parallel support device for wind tunnel dynamic testing of rotating projectile model as described in any one of claims 1-7; An attitude control system, which is placed on the tail support (13), is used to measure the real-time attitude angle of the rotating projectile model (1); A take-up and release control device, which is electrically connected to each take-up and release unit and is used to control each take-up and release unit to take up and release the traction cable; and The data acquisition and processing device acquires signals from the attitude and attitude instrument and the force balance (7), and obtains the aerodynamic parameters of the rotating projectile model (1) through processing.

9. The test system for wind tunnel dynamic testing of a rotating projectile model as described in claim 8, characterized in that, The take-up and release control device also includes a tension sensor, which is configured corresponding to each of the traction cables and is used to detect the tension of the traction cables so as to keep the traction cables properly tensioned by controlling the take-up and release unit.

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