Blunt cone virtual flight test system and method with variable head deflection angle and mass center

Abstract

The invention provides a blunt cone virtual flight test system and method with a variable head deflection angle and a variable mass center, and belongs to the technical field of wind tunnel dynamic tests. The system comprises a variable elbow mechanism, a variable centroid mechanism and a virtual flight mechanism. The variable elbow mechanism is matched with an electric push cylinder through an upper push rod and a lower push rod, so that the switching of a blunt cone head part between zero-position locking and rapid deflection is realized; the variable centroid mechanism drives a balancing weight to move axially through an electric push cylinder, and the whole centroid position is changed. The virtual flight mechanism supports the blunt cone through the supporting rod and the low-damping bearing set to achieve pitching motion. According to the invention, head deflection and centroid change can be independently or cooperatively controlled, the pneumatic / motion coupling effect of the intelligent deformable aircraft in the dynamic process is truly simulated, the limitation that the shape and the centroid are fixed in a traditional wind tunnel test is solved, and an effective means is provided for verification of a comprehensive attitude control strategy.

Description

Technical Field

[0001] This invention relates to the field of wind tunnel dynamic testing technology, and in particular to a blunt cone virtual flight test system and method with variable nose deflection angle and center of mass. Background Technology

[0002] Intelligent deformable aircraft are a current research hotspot in the aerospace field, with their shape and center of gravity changing in real time during flight. Traditional wind tunnel tests often use fixed shapes and center of gravity positions, which cannot truly reflect the aerodynamic characteristics and motion coupling effects of the aircraft during dynamic deformation. Therefore, there is an urgent need for a virtual flight test system that can simultaneously simulate nose deflection and center of gravity changes to verify the attitude control capabilities of intelligent aircraft under complex conditions. Summary of the Invention

[0003] The purpose of this invention is to provide a blunt cone virtual flight test system and method with variable head deflection angle and center of mass. The system integrates a variable head mechanism, a variable center of mass mechanism and a virtual flight mechanism, and can independently or collaboratively control the head deflection of the blunt cone and the overall center of mass position, so as to realize high-precision simulation of the dynamic characteristics of intelligent deformable aircraft in a wind tunnel environment.

[0004] According to one objective of the present invention, the present invention provides a blunt cone virtual flight test system with variable head deflection angle and center of gravity, comprising: The variable bend mechanism is used to control the deflection and locking of the blunt cone head; A variable center of mass mechanism is used to adjust the position of the overall center of mass of the blunt cone. A virtual flying mechanism used to support a blunt cone and deflect it about a specified axis of rotation.

[0005] Furthermore, the variable bend mechanism includes a blunt cone head, a blunt cone rear body, a head shaft, a bearing assembly, a bearing cover, a first electric push cylinder, an upper push rod, and a lower push rod; the blunt cone head is connected to the blunt cone rear body via the head shaft and the bearing assembly, and can deflect within a designed angle range.

[0006] Furthermore, the lower push rod, driven by the first electric cylinder, locks the blunt cone head at a zero deflection angle. When locked, the upper rear end face of the blunt cone head contacts the upper limit plane of the rear cavity of the blunt cone.

[0007] Furthermore, the upper push rod, driven by the first electric cylinder, enables the blunt cone head to deflect rapidly, with its point of action located below the head's pivot axis, generating a head-raising torque.

[0008] Furthermore, the variable center of mass mechanism includes a second electric pusher cylinder and a counterweight block, wherein the second electric pusher cylinder drives the counterweight block to move along the axial direction of the blunt cone rear body.

[0009] Furthermore, the virtual flight mechanism includes a support rod, a bearing assembly, and a bearing cover; the support rod is connected to the blunt conical rear body via the bearing assembly, and the bearing cover also serves as part of the outer surface of the blunt conical rear body.

[0010] Furthermore, the variable bending head mechanism and the variable center of mass mechanism can operate independently or in concert to simulate the blunt cone pitch posture under the combined effect of head deflection and center of mass change.

[0011] According to another objective of the present invention, the present invention provides a virtual flight test method for the above-mentioned blunt cone virtual flight test system with variable head deflection angle and center of gravity, comprising the following steps: Lock the blunt cone head at zero deflection angle; Start the wind tunnel and stabilize the flow field; Control the upper and lower push rods to achieve head deflection; Control the electric cylinder to move the counterweight and adjust the center of gravity; Record the attitude response of a blunt cone under the action of aerodynamic force and gravity.

[0012] Furthermore, head deflection and center of mass movement can be performed simultaneously or sequentially; during head deflection, the upper push rod and the lower push rod move alternately.

[0013] Furthermore, the method is applicable to hypersonic wind tunnel testing environments, with real-time feedback and adjustment of the counterweight position.

[0014] This invention integrates a variable bend, a variable center of mass, and a virtual flight mechanism to achieve independent or coordinated adjustment of the deflection angle of the blunt cone head and the overall center of mass, overcoming the limitations of fixed shape and center of mass in traditional wind tunnel tests. The system employs a dual-pushrod locking and driving mechanism, featuring a compact structure, rapid response, and effective utilization of the space behind the blunt cone, reducing the difficulty of counterweight design. The virtual flight mechanism uses low-damping, high-precision bearings, significantly improving the simulation accuracy of pitch attitude. This system can realistically simulate the aerodynamic / kinematic coupling effects of intelligent deformable aircraft during dynamic processes, providing a reliable experimental platform for verifying integrated attitude control strategies and possessing high engineering application value. Attached Figure Description

[0015] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the overall structure of an embodiment of the present invention; Figure 2This is a schematic diagram of the blunt cone head without deflection in an embodiment of the present invention; Figure 3 This is a schematic diagram of the deflection state of the blunt cone head in an embodiment of the present invention; Figure 4 This is a schematic diagram of the virtual flight mechanism according to an embodiment of the present invention; Figure 5 This is a schematic diagram of a variable center of mass mechanism according to an embodiment of the present invention; In the diagram: 1. Bending mechanism; 11. Blunt cone head; 12. Head shaft; 13. Blunt cone rear body; 14. Lower push rod; 15. Upper push rod; 16. First electric push cylinder; 2. Virtual flying mechanism; 21. Bearing cover; 22. Bearing assembly; 23. Support rod; 3. Variable center of mass mechanism; 31. Counterweight; 32. Second electric push cylinder. Detailed Implementation

[0017] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0019] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; and they may refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0020] Example 1 like Figures 1-5 As shown, a blunt cone virtual flight test system with variable head deflection angle and center of gravity includes: The variable bend mechanism 1 is used to control the deflection and locking of the blunt cone head; The variable center of mass mechanism 3 is used to adjust the overall center of mass position of the blunt cone. Virtual flying mechanism 2 is used to support the blunt cone and deflect it about a specified axis of rotation.

[0021] Specifically, the variable bend mechanism 1 includes a blunt cone head 11, a blunt cone rear body 13, a head shaft 12, a bearing assembly, an embedded bearing cover, a first electric push cylinder 16, an upper push rod 15, and a lower push rod 14. Through the coordinated action of the upper and lower push rods, the head can switch between zero-position locking and rapid deflection.

[0022] The blunt cone head 11 is connected to the blunt cone rear body 13 via a head pivot 12 and a bearing assembly, and can deflect within a designed angle range. The lower push rod 14 locks the blunt cone head 11 at zero deflection angle under the drive of the first electric push cylinder 16.

[0023] The upper push rod 15 achieves rapid deflection of the blunt cone head 11 under the drive of the first electric push cylinder 16.

[0024] When the push rod 14 is locked, the upper end face of the rear part of the blunt cone head 11 contacts the upper limit plane of the inner cavity of the blunt cone rear body 13.

[0025] When the upper push rod 15 extends, its point of action is located below the head pivot 12, generating a head-raising torque.

[0026] Specifically, the variable center of mass mechanism 3 includes a second electric pusher cylinder 32 and a counterweight block 31. The second electric pusher cylinder 32 drives the counterweight block 31 to move along the axis of the blunt cone rear body 13. The counterweight block 31 is a replaceable structure to adapt to different magnitudes of center of mass change. The blunt cone rear body 13 is equipped with a counterweight block 31 controlled by the second electric pusher cylinder 32, which can move along the axis of the blunt cone rear body 13. Different counterweight blocks 31 can be configured according to experimental requirements to simulate different magnitudes of center of mass change.

[0027] Specifically, the virtual flight mechanism 2 includes a support rod 23, a bearing assembly 22, and an embedded bearing cover 21. The support rod 23 is connected to the blunt conical rear body 13 via the bearing assembly 22. The bearing assembly 22 is a low-damping, high-precision bearing. The embedded bearing cover 21 also serves as part of the outer surface of the blunt conical rear body.

[0028] In this embodiment, the electric pusher cylinder is a servo electric pusher cylinder.

[0029] In this embodiment, the variable bend mechanism 1 and the variable center of mass mechanism 3 can operate independently or in concert.

[0030] This system is used for wind tunnel virtual flight tests to simulate the pitch motion of an intelligent deformable aircraft. During the test, the nose is first locked at zero deflection. After the wind tunnel flow field stabilizes, the nose deflection and center of mass movement are controlled by electric propulsion cylinders, and the attitude response of the blunt cone under the action of aerodynamic forces and gravity is observed.

[0031] The virtual flight test method for the aforementioned blunt cone virtual flight test system with variable head deflection angle and center of gravity includes the following steps: Lock the blunt cone head 11 at zero deflection angle; Start the wind tunnel and stabilize the flow field; Control the upper push rod 15 and the lower push rod 14 to achieve head deflection; Control the second electric pusher cylinder 32 to move the counterweight block 31 to adjust the center of gravity; Record the attitude response of a blunt cone under the action of aerodynamic force and gravity.

[0032] Specifically, head deflection and center of mass movement can be performed simultaneously or at different times.

[0033] During the head rotation, the upper push rod 15 and the lower push rod 14 move alternately.

[0034] During the movement of the center of mass, the position of the counterweight 31 can be fed back and adjusted in real time.

[0035] The method described in this embodiment is applicable to hypersonic wind tunnel testing environments.

[0036] Specifically, when the deflection angle of the blunt cone head 11 is 0, the lower push rod 14 extends, and the push rod drives the blunt cone head 11 to tend to rotate around the axis of rotation. The upper end face of the rear part of the blunt cone head 11 contacts the upper limit plane of the inner cavity of the blunt cone rear body 13, and the blunt cone head is locked in the 0 deflection angle state. When the blunt cone head needs to move, the upper push rod 15 extends and contacts the tail of the blunt cone head 11. The force direction at the contact point is below the pivot of the blunt cone head, generating a lifting torque. At this time, the lower push rod 14 retracts, releasing the blunt cone head from its locked state. The blunt cone head quickly lifts under the action of the upper push rod 15, achieving an angle deflection of the blunt cone head. When the lower end face of the rear part of the blunt cone head 11 contacts the lower limit plane of the inner cavity of the blunt cone rear body 13, the deflection angle is locked.

[0037] This embodiment combines the variable bend mechanism 1, the variable center of mass mechanism 2, and the virtual flight mechanism 3. The two modes of action, variable bend and variable center of mass, are independent of each other. In the wind tunnel, the pitch attitude change trend of the blunt cone under the combined action of bend deflection and center of mass change can be simulated, and the control effect of the integrated attitude control system combining variable bend and variable center of mass can be verified.

[0038] Example 2 like Figure 1As shown, a blunt cone virtual flight test system with variable head deflection angle and center of mass includes three parts: a variable head deflection mechanism 1, a virtual flight mechanism 2, and a variable center of mass mechanism 3, wherein: like Figure 2 As shown, the variable bend mechanism 1 consists of a blunt cone head 11, a head rotating shaft 12, a blunt cone rear body 13, a lower push rod 14, an upper push rod 15, and a first electric push cylinder 16. The blunt cone head 11 and the blunt cone rear body 13 are spherically fitted. The blunt cone head 11 is connected to the head rotating shaft 12 and to the blunt cone rear body 13 through a bearing assembly. The blunt cone head 11 can deflect around the head rotating shaft 13 within a designed angle range. The lower push rod 14 locks the blunt cone head 11 in the absence of deflection under the drive of the first electric push cylinder 16. The upper push rod 15 achieves rapid deflection of the blunt cone head under the drive of the first electric push cylinder 16.

[0039] When the blunt cone head 11 does not deflect (e.g.) Figure 2 As shown), the upper push rod 15 retracts, and the blunt cone head 11 deflects downward under its own weight until it contacts the upper surface of the inner cavity of the blunt cone rear body 13. Then the lower push rod 14 extends and contacts the lower surface of the tail section of the blunt cone head 11, locking the blunt cone head 11 to zero deflection angle. like Figure 3 As shown, when the blunt cone head 11 needs to deflect, the upper push rod 15 first extends to contact the blunt cone head 11, and then the lower push rod 14 retracts to separate from the blunt cone head 11. Under the combined action of the aerodynamic torque and the upper push rod 15, the blunt cone head 11 deflects upward until it contacts the lower surface of the inner cavity of the blunt cone rear body 13. At this time, the blunt cone head 11 locks the deflection angle under the combined action of the upper push rod 15 and the lower surface of the inner cavity of the blunt cone rear body 13.

[0040] In this embodiment, the lower push rod 14 has a long lever arm, so the thrust required by the first electric push cylinder 16 is small when locking the blunt cone head 11. Although the upper push rod 15 has a short lever arm, the rotation center of the blunt cone head 11 is located at the rear of the blunt cone head 11. Under the action of aerodynamic force, the blunt cone head 11 is in a statically unstable state. With slight disturbance, the blunt cone head 11 will tend to deviate from the 0 deflection angle. When the blunt cone head 11 deflects, the upper push rod 15 only needs a small thrust to cause the blunt cone head to deflect under the combined action of aerodynamic torque.

[0041] like Figure 4 As shown, the virtual flight mechanism 2 consists of a support rod 23, a low-damping high-precision bearing assembly 22, and an embedded bearing cover 21. The support rod 23 is connected to the blunt cone rear body 13 via the bearing assembly 22, enabling the blunt cone to deflect around a designated position. Specifically, the protruding shaft of the support rod 23 is connected to the blunt cone rear body 13 via the low-damping high-precision bearing assembly 22, and the embedded bearing cover 21, while pressing down on the bearing, also serves as part of the outer surface of the blunt cone rear body 13.

[0042] like Figure 5As shown, the variable center of mass mechanism 3 consists of a second electric push cylinder 32 and a counterweight 31. The second electric push cylinder 32 is fixed on the inner side of the blunt cone rear body 13 and drives the counterweight 31 to move along the axial direction of the blunt cone rear body 13, thereby realizing the forward and backward movement of the blunt cone center of mass.

[0043] During the test, the variable bend mechanism 1 first locks the blunt cone head 11 in a zero deflection angle state. After the wind tunnel flow field stabilizes, the three electric thrusters control the deflection of the blunt cone head 11 and the movement of the blunt cone's overall center of mass. The blunt cone moves around the protruding axis of the support rod 23 under the action of aerodynamic torque and gravitational torque.

[0044] This invention enables independent or synchronous control of head deflection and center of mass change, expanding the simulation dimensions of wind tunnel tests; it adopts a dual pushrod locking and drive mechanism, resulting in a compact structure and rapid response; the virtual flight mechanism uses low-damping high-precision bearings to improve attitude simulation accuracy; and the modular design facilitates counterweight adjustment and system expansion.

[0045] This invention combines variable bends, variable center of mass, and wind tunnel virtual flight testing to more realistically simulate the aerodynamic / kinematic phenomena during the flight of an intelligent deformable aircraft. By employing two independent push rods (upper and lower) to lock and deflect the bend, this invention fully utilizes the space behind the blunt cone and distributes the actuation mechanisms as close as possible to the virtual flight axis, reducing the difficulty of counterweighting in blunt cone wind tunnel virtual flight testing.

[0046] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A blunt cone virtual flight test system with variable head deflection angle and center of gravity, characterized in that, include: The variable bend mechanism is used to control the deflection and locking of the blunt cone head; A variable center of mass mechanism is used to adjust the position of the overall center of mass of the blunt cone. A virtual flying mechanism used to support a blunt cone and deflect it about a specified axis of rotation.

2. The blunt cone virtual flight test system with variable head deflection angle and center of mass according to claim 1, characterized in that, The variable bend mechanism includes a blunt cone head, a blunt cone rear body, a head shaft, a bearing assembly, a bearing cover, a first electric push cylinder, an upper push rod, and a lower push rod; the blunt cone head is connected to the blunt cone rear body via the head shaft and the bearing assembly, and can deflect within a designed angle range.

3. The blunt cone virtual flight test system with variable head deflection angle and center of mass according to claim 2, characterized in that, The lower push rod, driven by the first electric push cylinder, locks the blunt cone head at zero deflection angle. When locked, the upper rear end face of the blunt cone head contacts the upper limit plane of the rear cavity of the blunt cone.

4. The blunt cone virtual flight test system with variable head deflection angle and center of mass according to claim 2, characterized in that, The upper push rod, driven by the first electric cylinder, enables the blunt cone head to deflect rapidly. Its point of action is located below the head's pivot axis, generating a head-raising torque.

5. The blunt cone virtual flight test system with variable head deflection angle and center of mass according to claim 1, characterized in that, The variable center of mass mechanism includes a second electric pusher cylinder and a counterweight block. The second electric pusher cylinder drives the counterweight block to move along the axis of the blunt cone rear body.

6. The blunt cone virtual flight test system with variable head deflection angle and center of mass according to claim 1, characterized in that, The virtual flight mechanism includes a support rod, a bearing assembly, and a bearing cover; the support rod is connected to the blunt conical rear body through the bearing assembly, and the bearing cover also serves as part of the outer surface of the blunt conical rear body.

7. The blunt cone virtual flight test system with variable head deflection angle and center of mass according to claim 1, characterized in that, The variable bending head mechanism and the variable center of mass mechanism can operate independently or in conjunction to simulate the blunt cone pitch posture under the combined effect of head deflection and center of mass change.

8. The virtual flight test method for a blunt cone virtual flight test system with variable head deflection angle and center of mass according to any one of claims 1-7, characterized in that, Includes the following steps: Lock the blunt cone head at zero deflection angle; Start the wind tunnel and stabilize the flow field; Control the upper and lower push rods to achieve head deflection; Control the electric cylinder to move the counterweight and adjust the center of gravity; Record the attitude response of a blunt cone under the action of aerodynamic force and gravity.

9. The virtual flight test method according to claim 8, characterized in that, Head rotation and center of mass movement can be performed simultaneously or separately; during head rotation, the upper and lower push rods move alternately.

10. The virtual flight test method according to claim 8, characterized in that, The method is applicable to hypersonic wind tunnel testing environments, and the position of the counterweight is fed back and adjusted in real time.

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