Model and test probe servo mechanism for high-temperature hypersonic flow field test

Abstract

The invention discloses a model and test probe servo mechanism for a high-temperature hypersonic flow field test, and relates to the technical field of aerospace test equipment. The probe scanning system has two degrees of freedom and is integrated by a probe X-direction adjusting assembly and a probe gamma-direction deflection assembly; the model supporting system has four degrees of freedom and is composed of a model Z-direction lifting assembly, a model X-direction adjusting assembly, a model beta-direction yaw adjusting assembly and a model alpha-direction attack angle adjusting assembly. Telescopic heat insulation sleeves of the heat insulation cooling system are arranged on the two sides of the probe X-direction adjusting assembly in a sleeving mode, an air cooling pipeline is connected with four servo drivers of the model supporting system in series, and a follow-up heat insulation cover plate moves along with a model at the top of the model supporting system to synchronously shield an upper flow field. Deflection degree of freedom is integrally arranged on the probe scanning system, and the high-temperature anti-interference capability is improved through the arrangement of the telescopic heat insulation sleeve, the follow-up heat insulation cover plate and the air cooling pipeline, so that the multi-working-condition efficient test requirement is met.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace test equipment, and specifically, it is a servo mechanism for a model and a test probe used in a high-temperature hypersonic flow field test. Background Technique

[0002] With the development of hypersonic vehicle technology, the requirements for the measurement accuracy and efficiency of model aerodynamic parameters are increasing day by day. In a high-temperature hypersonic flow field test, the test model and the test probe need to quickly and accurately enter the high-speed airflow region and maintain a stable attitude and position in an extreme thermodynamic environment to obtain reliable data.

[0003] However, the traditional control mechanism has the disadvantages of insufficient attitude adjustment ability and poor adaptability to high-temperature environments. Most systems only support the single-degree-of-freedom translation of the probe, lacking the lateral deflection degree of freedom, and it is difficult to achieve the dynamic coordinated cooperation of complex angles of attack and sideslip angles, restricting the flexibility of multi-condition testing. In addition, the thermal load generated by the high-temperature flow field easily causes thermal deformation of the mechanical structure, resulting in the positioning error exceeding the allowable range and making it difficult to meet the high-precision measurement requirements.

[0004] In view of the above problems, there is an urgent need to develop a servo mechanism capable of multi-degree-of-freedom coordinated control and high-temperature anti-interference to improve the reliability and accuracy of high-temperature hypersonic wind tunnel tests. Summary of the Invention

[0005] To solve the deficiencies in the background technique, the present invention provides a servo mechanism for a model and a test probe used in a high-temperature hypersonic flow field test. It integrates a deflection degree of freedom in the probe scanning system and improves the high-temperature anti-interference ability through the settings of a telescopic heat-insulating sleeve, a follow-up heat-insulating cover plate, and an air-cooling pipeline to meet the requirements of multi-condition efficient testing.

[0006] To achieve the above object, the present invention adopts the following technical solution: A servo mechanism for a model and a test probe used in a high-temperature hypersonic flow field test, including a probe scanning system, a model support system, and a heat-insulating and cooling system; The probe scanning system has two degrees of freedom and is integrally arranged by a probe X-direction adjustment component and a probe γ-direction deflection component; the probe X-direction adjustment component includes an X-direction servo driver one and a ball screw pair driven coaxially, and a transfer ring is sleeved outside the screw nut of the ball screw pair. A rib is arranged along the axial direction on the inner ring surface of the transfer ring and is connected to the screw nut through a ring key; the probe γ-direction deflection component includes a γ-direction servo driver and a hollow shaft driven by a worm and worm gear. The hollow shaft is coaxially inserted between the screw nut and the transfer ring, and a notch is machined along the axial direction on the side wall of the hollow shaft for the rib of the transfer ring to pass through, and the transfer ring fixes the probe mounting bracket; The model support system has four degrees of freedom and is composed of a model Z-direction lifting component, a model X-direction adjustment component, a model β-direction yaw adjustment component, and a model α-direction angle of attack adjustment component from bottom to top, which are controlled by four servo drives respectively; The heat insulation and cooling system includes a telescopic heat insulation sleeve, an air-cooling pipeline, and a follow-up heat insulation cover plate. The telescopic heat insulation sleeve is sleeved on both sides outside the ball screw pair of the probe X-direction adjustment component. The telescopic heat insulation sleeve is composed of multiple sub-cylinders arranged in a nested manner step by step and can be telescoped as the adapter ring moves. The air-cooling pipeline is connected in series with the four servo drives of the model support system to form a circulating cooling loop through the supply of cooling gas. The follow-up heat insulation cover plate is installed on both sides of the top of the model support system to synchronously block the upper flow field as the model moves.

[0007] Further, the model Z-direction lifting component includes a Z-direction guide rail slider module, a U-shaped support frame, and a Z-direction servo drive. An elevator platform is carried between the U-shaped support frames. Both ends of the elevator platform are slidably connected to the two vertical arms of the U-shaped support frame through the Z-direction guide rail slider module respectively, and the displacement along the Z-axis direction is controlled by the screw nut pairs on both sides. The bottoms of the screw nut pairs on both sides of the U-shaped support frame are connected by a bevel gear set through a horizontal drive shaft. The Z-direction servo drive is fixed at the middle position of the bottom of the U-shaped support frame and controls the rotation of the horizontal drive shaft through a T-shaped power divider box.

[0008] Further, the model X-direction adjustment component includes an X-direction slider, an X-direction guide rail, and an X-direction servo drive two. The X-direction servo drive two is fixed at the middle position of the surface of the elevator platform and coaxially drives the screw nut pair to control the displacement of the sliding table along the X-axis direction. The X-direction guide rails are fixed on both sides of the surface of the elevator platform where the screw nut pair is located. Both sides of the bottom of the sliding table are slidably connected to the X-direction guide rail through the X-direction slider.

[0009] Further, the model β-direction yaw adjustment component includes a rotating disk and a β-direction servo drive. The rotating disk is rotatably installed on the surface of the sliding table through a vertical central axis. The β-direction servo drive drives the rotating disk to rotate through a worm and worm gear.

[0010] Further, the model α-direction angle of attack adjustment component includes a transmission hinge, a telescopic electric cylinder, a rotating shaft, an α-direction servo drive, a yaw base, and a pitch base. The yaw base is fixedly connected to the rotating disk. The rotating shaft is horizontally installed on the top of the yaw base. The pitch base is hingedly installed on the rotating shaft and can swing in the pitch direction. A plug rod is integrally provided at the bottom of the pitch base. The upper end of the transmission hinge is provided with a slot and is inserted and matched with the pitch base. The telescopic electric cylinder is fixed at the bottom of the yaw base along the X-axis direction. The moving end of the telescopic electric cylinder is hinged to the lower end of the transmission hinge. The α-direction servo drive controls the telescopic action of the telescopic electric cylinder.

[0011] Further, the probe scanning system and the model support system are controlled by a control system for six degrees of freedom. The control system adopts a full closed-loop control based on PLC, integrates a field control terminal and a remote control terminal, and realizes linkage control by using the piecewise cubic Hermite interpolation method.

[0012] Further, brake devices are respectively configured for the servo drivers corresponding to the six degrees of freedom of the probe scanning system and the model support system to maintain braking torque during shutdown.

[0013] Compared with the prior art, the beneficial effects of the present invention are as follows: in the probe scanning system of the present invention, a γ-direction deflection degree of freedom is added and integrated with the conventional X-direction adjustment, with a simple and efficient structure, which helps to more flexibly adjust and transform the probe attitude according to different test states and requirements. In addition, through the setting of the telescopic heat insulation sleeve and the follow-up heat insulation cover plate, the high temperature of the flow field is effectively blocked, and air-cooled pipelines are arranged for each servo driver for the four-degree-of-freedom control of the model support system, improving the reliability of the high-temperature hypersonic wind tunnel test, ensuring the normal operation of the system in a high-temperature environment, enhancing the multi-degree-of-freedom coordinated control and the high-temperature anti-interference ability, being able to meet the multi-condition efficient test requirements, and significantly improving the accuracy of test data. Description of the Drawings

[0014] Figure 1 is the overall structural layout diagram of the servo mechanism of the present invention; Figure 2 is the structural diagram of the probe X-direction adjustment component in the servo mechanism of the present invention; Figure 3 is the structural diagram of the probe γ-direction deflection component in the servo mechanism of the present invention; Figure 4 is the structural diagram of the model Z-direction lifting component in the servo mechanism of the present invention; Figure 5 is the structural diagram of the model X-direction adjustment component in the servo mechanism of the present invention; Figure 6 is the structural diagram of the model β-direction yaw adjustment component in the servo mechanism of the present invention; Figure 7 is the structural diagram of the model α-direction angle of attack adjustment component in the servo mechanism of the present invention; Figure 8 is the layout diagram of the air-cooled pipeline in the servo mechanism of the present invention; Figure 9 is the principle block diagram of the control system in the servo mechanism of the present invention.

[0015] In the figure: 1. Probe X-direction adjustment component; 2. Probe γ-direction deflection component; 3. Model Z-direction lifting component; 4. Model X-direction adjustment component; 5. Model β-direction yaw adjustment component; 6. Model α-direction angle of attack adjustment component; 7. Air-cooling pipeline; 8. Follow-up heat insulation cover plate; 101. Wire lever; 102. Lead screw nut; 103. Telescopic heat insulation sleeve; 104. X-direction servo driver 1; 105. Ring key; 106. Adapter ring; 201. Worm 1; 202. Worm gear 1; 203. Hollow shaft; 204. γ-direction servo driver; 205. Probe mounting bracket; 301. Z-direction guide rail slider module; 302. U-shaped support frame; 303. Z-direction servo driver; 401. X-direction slider; 402. X-direction guide rail; 403. X-direction servo driver 2; 501. Rotary disk; 502. Slide table; 503. Worm 2; 504. Worm gear 2; 505. β-direction servo driver; 601. Transmission hinge; 602. Telescopic electric cylinder; 603. Rotating shaft; 604. α-direction servo driver; 605. Yaw base; 606. Pitch base; 701. Cooling air inlet; 702. Cooling air outlet. Detailed implementation manners

[0016] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0017] As Figures 1 to 9As shown in the figure, a model and test probe servo mechanism for high-temperature hypersonic flow field tests includes a probe X-direction adjustment component 1, a probe γ-direction deflection component 2, a model Z-direction lifting component 3, a model X-direction adjustment component 4, a model β-direction yaw adjustment component 5, a model α-direction angle of attack adjustment component 6, an air-cooling pipeline 7, a follow-up heat insulation cover plate 8, and a control system. The probe X-direction adjustment component 1 and the probe γ-direction deflection component 2 form a probe scanning system. Among them, the probe X-direction adjustment component 1 can control the horizontal displacement of the probe along the X-axis, and the probe γ-direction deflection component 2 can control the lateral swing of the probe around the X-axis, having two degrees of freedom; the model Z-direction lifting component 3, the model X-direction adjustment component 4, the model β-direction yaw adjustment component 5, and the model α-direction angle of attack adjustment component 6 form a model support system. Among them, the model Z-direction lifting component 3 can control the vertical displacement of the model along the Z-axis, the model X-direction adjustment component 4 can control the horizontal displacement of the model along the X-axis, the model β-direction yaw adjustment component 5 can control the yaw angle of the model, and the model α-direction angle of attack adjustment component 6 can control the pitch angle of the model, having four degrees of freedom; the air-cooling pipeline 7 is used to air-cool and cool the servo drivers that adjust the four degrees of freedom in the model support system to avoid the problem of increased error caused by high-temperature conditions; the follow-up heat insulation cover plate 8 is arranged on the top of the model support system to block the adverse impact of the high-temperature flow field acting on the model area on the model support system downward; the control system is used to set parameters for the total six degrees of freedom of the probe scanning system and the model support system, and uses an industrial network controller based on PLC to achieve full closed-loop control for the adjustment control of six degrees of freedom.

[0018] Combined with Figure 1 、 Figure 2As shown in the figure, the probe X-direction adjustment assembly 1 is horizontally installed above the flow field along the X-axis direction through a suspension, and includes a wire lever 101, a lead screw nut 102, a telescopic heat insulation sleeve 103, an X-direction servo driver 104, an annular key 105 and an adapter ring 106. The wire lever 101 is rotatably installed between the supports provided at both ends of the bottom of the suspension. The lead screw nut 102 is installed on the wire lever 101 and is provided with a guide rod to form a ball screw pair. The X-direction servo driver 104 is fixedly installed and coaxially drives the wire lever 101 to control the displacement of the lead screw nut 102 along the X-axis direction. The inner ring surface of the adapter ring 106 is integrally provided with ribs along its axial direction and supports on the outer side wall of the lead screw nut 102, so that the adapter ring 106 is coaxially sleeved outside the lead screw nut 102 at an interval to reserve space for the subsequent loading of the hollow shaft 203. The ribs of the adapter ring 106 and the lead screw nut 102 are connected by an annular key 105. The setting of the annular key 105 enables the adapter ring 106 to rotate around the X-axis while being able to displace with the lead screw nut 102. The telescopic heat insulation sleeve 103 is divided into two and sleeved outside the wire lever 101 at both sides of the lead screw nut 102. The telescopic heat insulation sleeve 103 is composed of a plurality of sub-cylinders arranged in a stepped manner and can be telescoped. One end of the telescopic heat insulation sleeve 103 is rotatably connected to the adapter ring 106 through a bearing, and the other end of the telescopic heat insulation sleeve 103 is rotatably connected to the corresponding support at the bottom of the suspension through a bearing to ensure that the wire lever 101 is always covered outside during the displacement of the lead screw nut 102.

[0019] Combined with Figure 1 , Figure 3 As shown in the figure, the probe γ-direction deflection assembly 2 is integrally arranged with the probe X-direction adjustment assembly 1, and includes a worm 201, a worm gear 202, a hollow shaft 203, a γ-direction servo driver 204 and a probe mounting bracket 205. The probe mounting bracket 205 is fixed below the adapter ring 106 for loading the probe in the flow field. The hollow shaft 203 is coaxially inserted between the lead screw nut 102 and the adapter ring 106. Both ends of the hollow shaft 203 are rotatably connected to the supports at both ends of the bottom of the suspension. The side wall of the hollow shaft 203 is processed with a notch along its axial direction for the rib of the adapter ring 106 to pass through, allowing the hollow shaft 203 to drive the adapter ring 106 to rotate while the lead screw nut 102 drives the adapter ring 106 to displace. The worm gear 202 is coaxially fixed at the end of the hollow shaft 203. The γ-direction servo driver 204 is fixedly installed and coaxially drives the worm 201. The worm 201 and the worm gear 202 are meshed to control the rotation of the hollow shaft 203.

[0020] Combined with Figure 1 , Figure 4As shown, the model Z-axis lifting component 3 is fixed below the flow field to control the lifting movement of the model along the Z-axis. It is the basic platform of the entire model support system, including a Z-axis guide rail slider module 301, a U-shaped support frame 302, and a Z-axis servo driver 303. An elevator platform is installed between the U-shaped support frames 302. The two ends of the elevator platform are respectively slidably connected to the two vertical arms of the U-shaped support frame 302 through the Z-axis guide rail slider module 301, and the displacement along the Z-axis is controlled by the ball screw pairs on both sides. The bottoms of the ball screw pairs on both sides of the U-shaped support frame 302 are connected by a bevel gear set through a horizontal drive shaft. The Z-axis servo driver 303 is fixed at the middle position of the bottom of the U-shaped support frame 302 and controls the rotation of the horizontal drive shaft through a T-shaped power split box, thereby synchronously driving the ball screw pairs on both sides of the U-shaped support frame 302.

[0021] Combined with Figure 1 、 Figure 5 As shown, the model X-axis adjustment component 4 is installed on the surface of the elevator platform of the model Z-axis lifting component 3 to control the displacement movement of the model along the X-axis, including an X-axis slider 401, an X-axis guide rail 402, and an X-axis servo driver II 403. The X-axis servo driver II 403 is fixed at the middle position of the surface of the elevator platform and coaxially drives a ball screw pair to control the displacement of the slide table 502 along the X-axis (for easy viewing, the slide table 502 is shown in Figure 6 . The X-axis guide rails 402 are fixed on both sides of the ball screw pair on the surface of the elevator platform. The two sides of the bottom of the slide table 502 are slidably connected to the X-axis guide rail 402 through the X-axis slider 401.

[0022] Combined with Figure 1 、 Figure 6 As shown, the model β-axis yaw adjustment component 5 is installed on the surface of the slide table 502 to control the yaw movement of the model, including a rotating disk 501, a worm II 503, a worm gear II 504, and a β-axis servo driver 505. The rotating disk 501 is rotatably installed on the surface of the slide table 502 through a vertical central axis. The worm gear II 504 is coaxially fixed to the bottom of the rotating disk 501. The β-axis servo driver 505 is fixed on the side of the slide table 502 and coaxially drives the worm II 503. The worm II 503 meshes with the worm gear II 504 to control the rotation of the rotating disk 501.

[0023] Combined with Figure 1 、 Figure 7As shown in the figure, the model α pitch angle adjustment component 6 is installed above the rotating disk 501 of the model β yaw angle adjustment component 5 for controlling the pitching motion of the model, and includes a transmission hinge 601, a telescopic electric cylinder 602, a rotating shaft 603, an α-axis servo driver 604, a yaw base 605, and a pitch base 606. The yaw base 605 is fixedly connected to the rotating disk 501, and the yaw adjustment of the top model is realized with the rotation of the rotating disk 501. The rotating shaft 603 is horizontally installed on the top of the yaw base 605. The pitch base 606 is hinged to the rotating shaft 603 and can swing in the pitching direction. The top of the pitch base 606 carries and installs the model to realize the pitch angle adjustment. A plug rod is integrally provided at the bottom of the pitch base 606. The upper end of the transmission hinge 601 is provided with a slot that is inserted and matched with the plug rod of the pitch base 606. The telescopic electric cylinder 602 is fixed to the bottom of the yaw base 605 along the X-axis direction. The moving end of the telescopic electric cylinder 602 is hinged to the lower end of the transmission hinge 601. The α-axis servo driver 604 controls the telescopic action of the telescopic electric cylinder 602.

[0024] Combined with Figure 8 As shown in the figure, the air-cooled pipeline 7 is provided for each servo driver in the four-degree-of-freedom control of the model support system. Heat shields are respectively provided outside the Z-axis servo driver 303, the second X-axis servo driver 403, the β-axis servo driver 505, and the α-axis servo driver 604, and are connected in series through the air-cooled pipeline 7. The two ends of the air-cooled pipeline 7 are respectively a cooling air inlet 701 and a cooling air outlet 702, and a circulating cooling loop is formed through the supply of cooling gas to control the temperature of the servo driver as a temperature-sensitive device. In addition, a support truss is fixedly provided at a position flush with the pitch base 606 above the lifting platform of the model Z-axis lifting component 3. The follow-up heat insulation cover plates 8 are installed on both sides of the pitch base 606 inside the support truss to block the high temperature of the flow field.

[0025] In summary, the first X-axis servo driver 104 and the γ-axis servo driver 204 in the two-degree-of-freedom control of the probe scanning system are both exposed to the outside, which helps with heat dissipation. At the same time, the telescopic heat insulation sleeve 103 is used to insulate and protect internal devices such as the ball screw pair. The follow-up heat insulation cover plate 8 is added above the model support system to block the downward action of high temperature, and the air-cooled pipeline 7 is used to cool each servo driver in the four-degree-of-freedom control by air cooling. Combined, they form a heat insulation and cooling system to ensure the normal operation of the mechanism in a high-temperature environment.

[0026] Combined with Figure 9As shown, the control system includes a field control terminal and a remote control terminal. The field control terminal is equipped with a touch screen for on-site operation and control. The remote control terminal is connected to the field control terminal through a network for remote centralized control. The PLC controller, as the core control unit of the system, realizes full closed-loop control. Furthermore, the parameters of a total of six-degree-of-freedom servo drivers of the probe scanning system and the model support system can be set in two ways: on-site and remote. Each servo driver is respectively equipped with a brake to maintain the braking torque during shutdown. The control system uses the piecewise cubic Hermite interpolation method to achieve multi-axis linkage control, ensuring the precise movement of the model in a complex flow field. Additionally, a fault diagnosis and protection module can be added to meet the real-time fault diagnosis and protection functions, capable of detecting and handling abnormal situations in a timely manner to ensure the safe operation of the system.

[0027] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent conditions of the claims are intended to be encompassed within the present invention. Any reference signs in the claims should not be regarded as limiting the claims involved.

[0028] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A model and test probe servo mechanism for high-temperature and hypersonic flow field tests, characterized in that: It includes a probe scanning system, a model support system, and a heat insulation and cooling system; The probe scanning system has two degrees of freedom and is integrally provided by a probe X-direction adjustment component (1) and a probe γ-direction deflection component (2); the probe X-direction adjustment component (1) includes an X-direction servo driver 1 (104) and a coaxially driven ball screw pair, and a transfer ring (106) is sleeved outside the screw nut (102) of the ball screw pair. The inner ring surface of the transfer ring (106) is axially provided with convex ribs and is connected to the screw nut (102) through an annular key (105); the probe γ-direction deflection component (2) includes a γ-direction servo driver (204) and a hollow shaft (203) driven by a worm and worm gear. The hollow shaft (203) is coaxially inserted between the screw nut (102) and the transfer ring (106). The side wall of the hollow shaft (203) is axially processed with a notch for the convex rib of the transfer ring (106) to pass through, and the transfer ring (106) fixes the probe mounting bracket (205); The model support system has four degrees of freedom and is composed of a model Z-direction lifting component (3), a model X-direction adjustment component (4), a model β-direction yaw adjustment component (5), and a model α-direction angle of attack adjustment component (6) from bottom to top, and is respectively controlled by four servo drivers; The heat insulation and cooling system includes a telescopic heat insulation sleeve (103), an air-cooled pipeline (7), and a follow-up heat insulation cover plate (8). The telescopic heat insulation sleeve (103) is sleeved on both sides outside the ball screw pair of the probe X-direction adjustment component (1). The telescopic heat insulation sleeve (103) is composed of multiple sequentially nested sub-cylinders and can be telescoped with the movement of the transfer ring (106). The air-cooled pipeline (7) is connected in series with the four servo drivers of the model support system to form a circulating cooling loop through the supply of cooling gas. The follow-up heat insulation cover plate (8) is installed on both sides of the top of the model support system to synchronously block the upper flow field with the movement of the model.

2. The servo mechanism for the model and test probe used in the high-temperature and high-hypersonic flow field test according to claim 1, characterized in that: The model Z-direction lifting component (3) includes a Z-direction guide rail slider module (301), a U-shaped support frame (302), and a Z-direction servo driver (303). A lifting platform is carried between the U-shaped support frames (302). The two ends of the lifting platform are respectively slidably connected to the two vertical arms of the U-shaped support frame (302) through the Z-direction guide rail slider module (301), and the displacement along the Z-axis direction is controlled by the screw nut pairs on both sides. The bottoms of the screw nut pairs on both sides of the U-shaped support frame (302) are connected by a bevel gear set through a horizontal drive shaft. The Z-direction servo driver (303) is fixed at the middle position of the bottom of the U-shaped support frame (302) and controls the rotation of the horizontal drive shaft through a T-shaped power divider box.

3. The servo mechanism for the model and test probe used in the high-temperature and high-hypersonic flow field test according to claim 2, characterized in that: The model X-direction adjustment component (4) includes an X-direction slider (401), an X-direction guide rail (402), and an X-direction servo driver II (403). The X-direction servo driver II (403) is fixed at the middle position of the lifting table surface and coaxially drives a lead screw nut pair to control the displacement of the slide table (502) in the X-axis direction. The X-direction guide rail (402) is fixed on both sides of the lead screw nut pair on the lifting table surface. Both sides of the bottom of the slide table (502) are slidably connected to the X-direction guide rail (402) through the X-direction slider (401).

4. A model and test probe servo mechanism for high-temperature and hypersonic flow field tests according to claim 3, characterized in that: The model β-direction yaw adjustment component (5) includes a rotating disk (501) and a β-direction servo driver (505). The rotating disk (501) is rotatably installed on the surface of the slide table (5002) through a vertical central axis. The β-direction servo driver (505) drives the rotating disk (501) to rotate through a worm and worm gear.

5. The servo mechanism for the model and test probe used in the high-temperature and high-hypersonic flow field test according to claim 4, characterized in that: The model α-direction angle of attack adjustment component (6) includes a transmission hinge (601), a telescopic electric cylinder (602), a rotating shaft (603), an α-direction servo driver (604), a yaw base (605), and a pitch base (606). The yaw base (605) is fixedly connected to the rotating disk (501). The rotating shaft (603) is horizontally installed on the top of the yaw base (605). The pitch base (606) is hingedly installed on the rotating shaft (603) and can swing in the pitch direction. A plug rod is integrally provided at the bottom of the pitch base (606). The upper end of the transmission hinge (601) is provided with a slot and is inserted and matched with the pitch base (606). The telescopic electric cylinder (602) is fixed along the X-axis direction at the bottom of the yaw base (605). The moving end of the telescopic electric cylinder (602) is hinged to the lower end of the transmission hinge (601). The α-direction servo driver (604) controls the telescopic movement of the telescopic electric cylinder (602).

6. A servo mechanism for a model and a test probe used in a high-temperature and high-hypersonic flow field test according to any one of claims 1 to 5, characterized in that: The probe scanning system and the model support system control six degrees of freedom through a control system. The control system adopts a full closed-loop control based on PLC, integrates a field control terminal and a remote control terminal, and uses a piecewise cubic Hermite interpolation method to achieve linkage control.

7. A servo mechanism for a model and a test probe used in a high-temperature and high-hypersonic flow field test according to claim 6, characterized in that: The servo drivers corresponding to the six degrees of freedom of the probe scanning system and the model support system are respectively configured with brakes to maintain braking torque during shutdown.

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