High-frequency-response turbulent flow control steering engine and assembling method thereof

Abstract

The invention discloses a high-frequency-response turbulent flow control steering engine and an assembling method thereof, and aims to solve the problem that a traditional steering engine system cannot meet the requirements of high-frequency response and high-precision control in a high-speed rotating aircraft. The steering engine comprises a direct-current brushless motor, a speed reducing mechanism, a ball screw, a spoiler, a displacement sensor and a controller, the rotary motion of the motor is converted into linear motion through the ball screw, and therefore accurate control over the spoiler is achieved. The axial direction of a rotating shaft of the direct-current brushless motor is perpendicular to the flight direction, the rotating shaft is connected with the spoiler through the speed reducing mechanism, impact borne by the spoiler cannot be transmitted to the motor, and therefore the working stability of the motor is guaranteed. The steering engine system adopts a modular design, has lower assembly difficulty and efficient assembly process, meanwhile, has better stability and following performance when facing external interference, effectively improves the position control precision, and can meet the requirement of a high-rotating-speed aircraft on the steering engine.

Description

Technical Field

[0001] This invention relates to the field of aircraft control technology, specifically to a high-frequency response turbulence control servo and its assembly method. Background Technology

[0002] In the flight control of modern aircraft, especially for high-speed rotating aircraft such as missiles and projectiles, there are extremely high requirements for the control precision and response speed of spoilers. As a key component for adjusting flight status, the accuracy of spoiler control and the speed of response directly affect the aircraft's handling performance and flight safety.

[0003] Traditional servo systems typically control an aircraft's attitude by adjusting the angle of a control plate. While control plates located at the tail adjust attitude through angle deflection, this approach often fails to meet the high-frequency response requirements of high-speed rotating aircraft due to the control plate's position and operating method.

[0004] Furthermore, existing servo systems lack stability and tracking ability when facing external disturbances such as load shocks, and their position control accuracy is difficult to achieve within 1mm. This limits their application in high-performance aircraft. Summary of the Invention

[0005] In view of this, the present invention provides a high-frequency response servo for turbulence control, which can quickly respond and accurately control the extension and retraction of the spoilers under high speed conditions; moreover, the servo system adopts a modular design, which has low assembly difficulty and efficient assembly process, while ensuring good stability and following performance when facing external interference, and improving position control accuracy, which can meet the strict requirements of high-speed aircraft for servos.

[0006] To solve the above-mentioned technical problems, the present invention is implemented as follows.

[0007] A high-frequency response turbulence control servo motor includes: a DC brushless motor, a reduction mechanism, a ball screw, a turbulence plate, a displacement sensor, and a controller;

[0008] The DC brushless motor is connected to the ball screw through a reduction mechanism; the deflector has an L-shaped structure, with one arm being the fixed part and the other arm being the deflector part. The fixed part is installed as a nut sleeve on the movable nut of the ball screw.

[0009] The axis of the DC brushless motor shaft and the axis of the ball screw are both perpendicular to the flight direction of the carrier on which the servo is located; the spoiler moves in extension and retraction perpendicular to the flight direction according to the drive of the DC brushless motor.

[0010] The displacement sensor is installed on the side of the spoiler, and the spoiler is connected to the displacement sensor through a connecting kit to transmit the displacement of the spoiler;

[0011] The controller connects to the brushless DC motor and the displacement sensor.

[0012] Preferably, it further includes a cabin and a hatch; the cabin and the hatch are fastened together to form a servo compartment, providing installation space; a DC brushless motor, a ball screw and a spoiler are installed inside the installation space; two displacement sensors are symmetrically installed at sensor mounting positions on both sides of the cabin, and the sensor mounting positions have windows for transmitting position signals.

[0013] The hatch has an outlet for the spoiler to extend outwards, and the deceleration mechanism is installed on the hatch.

[0014] Preferably, the cabin has a double-layer structure, with the upper layer having a mounting slot adapted to the shape of the brushless DC motor for mounting and fixing the brushless DC motor; the lower layer provides space for the installation and movement of the ball screw and spoilers.

[0015] Preferably, the reduction mechanism adopts a gear transmission assembly; the plane on which the gear is located is parallel to the flight direction.

[0016] Preferably, the displacement sensor is a miniature dual-potentiometer type displacement sensor, which is installed on both sides of the baffle.

[0017] Preferably, the connection kit between the displacement sensor and the spoiler adopts a modular assembly structure;

[0018] The connecting kit includes a positioning shaft and a moving shaft; one end of the positioning shaft is fixedly connected to the fixed part and the moving nut, and the other end of the positioning shaft is engaged with the moving shaft, achieving position matching through groove engagement; the dimension of the moving shaft not connected to the positioning shaft is adapted to the dynamic shaft connecting groove of the displacement sensor and is inserted into the dynamic shaft connecting groove; the extension length of the dynamic shaft connecting groove is greater than the stroke of the spoiler, and when the spoiler moves, the moving distance is transmitted to the dynamic shaft connecting groove through the positioning shaft and the moving shaft, forming a potential change.

[0019] Preferably, the connecting kit further includes a nut needle roller and a needle roller sleeve; the nut needle roller is placed on the outer surface of the positioning shaft, and the needle roller sleeve is fitted over the nut needle roller to form a complete needle roller bearing pair;

[0020] The high-frequency response turbulence control servo is installed in the servo compartment, which provides upper and lower support surfaces for the needle roller bearing pair to limit the movement of the connecting kit in the flight direction.

[0021] Preferably, the controller communicates with an external guidance and control system via an RS422 data bus.

[0022] Preferably, the two ends of the ball screw are supported by angular contact bearings.

[0023] The present invention also provides an assembly method for any of the above-mentioned high-frequency response turbulence control servos, the method comprising:

[0024] Servo assembly: Assemble the ball screw and spoiler together, install positioning shafts on both sides of the spoiler, as well as nut needle rollers and needle roller sleeves on the outer periphery of the positioning shafts; insert the DC brushless motor, ball screw and spoiler into the rectangular hole of the hull and tighten with screws;

[0025] Sensor installation: Install the moving shaft from the opening of the sensor mounting position on both sides of the cabin to the end face of the positioning shaft, and then install the displacement sensor into the sensor mounting position. Insert the moving shaft into the dynamic shaft guide groove of the displacement sensor.

[0026] Servo module assembly: Combine the module body with the cover, connect the DC brushless motor and ball screw to the reduction mechanism on the cover to complete the electric servo assembly; install the assembled electric servo into the servo module.

[0027] Controller installation: Place the controller in the designated area of ​​the servo compartment;

[0028] Electrical connection: The electrical wiring connecting the controller and the electric servo motor.

[0029] Beneficial effects:

[0030] (1) The present invention converts the rotational motion of the motor into linear motion through a ball screw, thereby achieving precise control of the spoiler, ensuring rapid response and precise control of the extension and retraction of the spoiler under high speed conditions, so as to meet the control requirements of high-speed aircraft.

[0031] (2) The DC brushless motor is installed perpendicular to the flight direction and is connected to the spoiler through the reduction mechanism. The impact on the spoiler is interrupted at the reduction mechanism and will not be transmitted to the motor, thus ensuring the stability of the motor operation.

[0032] (3) The servo system adopts a modular design. Through structural design, the coupling of various components is reduced. For example, the upper and lower structure of the cabin, the connection kit between the displacement sensor and the spoiler, and the installation method of the gear transmission assembly on the canopy. Therefore, the servo structure of the present invention has a lower assembly difficulty, supports an efficient assembly process, and ensures good stability and following performance when facing external interference. The position control accuracy reaches within 1mm, which can meet the strict requirements of high-speed aircraft for servos.

[0033] (4) The electric servo motor structure also integrates a miniature dual-potentiometer displacement sensor, which is installed in a specific location to achieve dual redundancy feedback of the stroke position. This design improves the reliability and accuracy of the system, ensuring accurate feedback of the spoiler position even in extreme environments. Moreover, due to its extremely small mass, the impact force it experiences in shock environments is negligible.

[0034] (5) This system includes a servo compartment consisting of a hull and a cover. The structure is customized to the dimensions required by the design to accommodate all components of the electric servo system. The structural design takes into account space constraints and meets space requirements, including connectors and installation tolerances, to ensure the system's compactness and ease of installation.

[0035] (6) The ball screw is made of high-hardness material and is supported at both ends by angular contact bearings to overcome axial and radial forces. The design of the ball screw takes into account starting torque and dynamic load to ensure stability under high-speed operation and high load.

[0036] (7) The transmission mechanism consists of a spur gear reduction mechanism and a ball screw, which realizes the functions of speed reduction and torque amplification. This structure has the characteristics of large reduction ratio, lightweight structure and strong load-bearing capacity while meeting the spatial layout requirements of the actuator.

[0037] (8) The servo compartment adopts a drawer-type installation method and is inserted into the servo compartment structure, which facilitates the installation and maintenance of electric servo motors. This not only reduces the requirements for operating space, but also effectively reduces the assembly difficulty of the linear servo motor rotation mechanism and improves the assembly efficiency.

[0038] In summary, the servo system of the present invention features fast response, high stability and precise control. It can maintain good stability and following performance when facing external interference such as load impact, and the position control accuracy reaches within 1mm, meeting the stringent requirements of modern aircraft for servo performance. Attached Figure Description

[0039] Figure 1 This is an exploded view of the overall structure of a high-frequency response turbulence control servo.

[0040] Figure 2 This is a schematic diagram of spoiler 4.

[0041] Figure 3 This is a schematic diagram of ball screw 3.

[0042] Figure 4 This is a schematic diagram of the assembly of the baffle plate 4 and the displacement sensor 5.

[0043] Figure 5 This is a schematic diagram of hatch 9.

[0044] Figure 6 This is a schematic diagram of cabin 8.

[0045] Figure 7 This is a schematic diagram of the assembly of displacement sensor 5 and the connecting kit.

[0046] Figure 8 This is a schematic diagram showing the connection between the positioning axis 6 and the moving axis 7, and the subsequent connection of the baffle plate and ball screw.

[0047] Figure 9 A schematic diagram of the assembly of a DC brushless motor, a reduction gear, a ball screw, a spoiler, and a hatch.

[0048] Figure 10 This is a side view of the assembled high-frequency response turbulence control servo. Detailed Implementation

[0049] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0050] This invention provides a high-frequency turbulence control servo, such as... Figure 1 As shown, it includes: a DC brushless motor 1, a reduction mechanism 2, a ball screw 3, a baffle 4, a displacement sensor 5, and a controller 13.

[0051] The DC brushless motor 1 is connected to the ball screw 3 via a reduction gear 2. The baffle 4 has an L-shaped structure, such as... Figure 2 , Figure 3 As shown, one arm is the fixed part 41, and the other arm is the deflector part 42. The fixed part 41 has an opening, the size of which must be adapted to the movable nut on the ball screw 3 structure. Through the opening, the deflector 4, as a nut sleeve, passes through the screw 31 of the ball screw and is fixed to the movable nut 32. The ball screw converts the rotational motion of the motor into linear motion, thereby achieving precise control of the deflector and ensuring rapid response and precise control of the deflector's extension and retraction under high speed conditions. The two parts of the deflector 4 are machined as a single piece, avoiding the local stress concentration problem that may occur due to tensile force in traditional screw connections, thereby improving the tensile strength and durability of the overall assembly.

[0052] Regarding the installation direction, the axial direction of the DC brushless motor 1 shaft and the axial direction of the ball screw 3 are both perpendicular to the flight direction. The spoiler 4 extends and retracts perpendicular to the flight direction according to the drive of the DC brushless motor 1. The shaft of the DC brushless motor 1 does not directly drive the spoiler 4, but is connected to the spoiler through a reduction mechanism. The impact on the spoiler is interrupted at the reduction mechanism and is not transmitted to the motor, thus ensuring the stability of the motor operation.

[0053] Displacement sensor 5 is installed on the side of spoiler 4 to detect the displacement of spoiler 4. The installation position is as follows: Figure 4 As shown. In a preferred embodiment, the displacement sensor 5 is a miniature dual-potentiometer displacement sensor, symmetrically mounted on both sides of the spoiler 4 to achieve dual redundant feedback of the stroke position, thereby improving the reliability and accuracy of the system and ensuring accurate feedback of the spoiler position even in extreme environments.

[0054] In a preferred embodiment, a servo compartment is designed to house the aforementioned components, excluding the controller. For example... Figure 1 As shown, the servo compartment includes a housing 8 and a cover 9, which are fastened together to provide installation space. A DC brushless motor 1, a ball screw 3, and a spoiler 4 are installed inside this space. Two displacement sensors 5 are symmetrically mounted at sensor mounting positions 83 on both sides of the housing 8. The sensor mounting positions 83 have windows for accommodating the connection kit between the displacement sensors 5 and the spoiler 4 to transmit position signals. The cover 9 has an extension opening 91 for the spoiler 4 to extend outwards. A reduction gear 2 is mounted on the cover 9. Figure 5 As shown. This structural design takes space constraints into account, mounting the components separately on the inner cavity, side walls, and hatch, reasonably accommodating all components of the electric servo system, and meeting space requirements including connectors and installation tolerances, ensuring the system's compactness and ease of installation.

[0055] Preferably, the hull 8 is designed as a double-layer structure, see [reference]. Figure 6 The upper layer has a mounting slot 81 that is adapted to the shape of the DC brushless motor 1 for mounting and fixing the DC brushless motor 1. The mounting slot that is adapted to the shape of the motor can provide good support and fixation for the motor. The lower space provides mounting and movement space 82 for the ball screw 3 and the baffle 4.

[0056] In practical applications, the servo compartment may also include an outer shell 10 (see...). Figure 1 This design encloses the servo motor housing within the aircraft. The servo motor housing's shape can be designed to accommodate the servo module structure to which it will be installed, providing a mechanical interface between the servo module and the servo module structure. Preferably, the servo motor housing is installed in a drawer-type configuration, inserted into the servo module structure, and sealed with an outer shell 10. This facilitates the installation and maintenance of the electric servo motor, reduces the required operating space, effectively lowers the assembly difficulty of the linear servo motor's rotation mechanism, and improves assembly efficiency.

[0057] like Figure 7 and Figure 8As shown, a connecting kit is used between the displacement sensor and the spoiler. The design of the connecting kit facilitates modular assembly. The displacement sensor body has a dynamic shaft guide groove 51 for guiding and fixing one end of the moving shaft. The connecting kit includes a positioning shaft 6 and a moving shaft 7. The positioning shaft 6 and the moving shaft 7 can be plugged into each other. One end of the moving shaft 7 is adapted to the size of the dynamic shaft guide groove 51 and is inserted into the dynamic shaft guide groove 51 to achieve initial alignment. The moving shaft 7 contacts the groove arm. Different positions of the moving shaft in the dynamic shaft guide groove 51 correspond to different potentials, which are then identified by the displacement sensor. The other end of the moving shaft 7 is inserted into the corresponding groove of the positioning shaft 6 to ensure accurate positioning during movement. The positioning shaft 6 plays a crucial role in positioning and alignment. One end of the positioning shaft 6 is combined with the moving shaft 7, achieving position matching through groove engagement; the other end is designed with an insertion function, which can be embedded into the positioning hole of the spoiler fixing part 41 for precise docking and fixing. The fixed connection between the positioning shaft 6, the fixing part 41, and the moving nut 32 can be achieved by the positioning shaft 6 passing through the positioning hole of the fixing part 41 and inserting the moving nut 32. The extension length of the dynamic shaft connecting guide groove 51 is greater than the stroke of the spoiler. When the spoiler moves, the moving distance is transmitted to the dynamic shaft connecting guide groove through the positioning shaft 6 and the moving shaft 7, forming a potential change.

[0058] In a preferred embodiment, the connecting kit further includes a nut needle roller 14 and a needle roller sleeve 15. For example... Figure 7 As shown, a nut needle roller 14 is mounted on the outer surface of the positioning shaft 6. Its main function is to provide rolling support and axial guidance, ensuring smooth and stable movement. A needle roller sleeve 15 covers the nut needle roller 14, forming a complete needle roller bearing pair. As an outer protective sleeve, the needle roller sleeve 15 not only provides fixation and protection but also prevents foreign object intrusion. Furthermore, its cooperation with the servo gear compartment structure maintains the running accuracy and assembly stability of the needle rollers. Figure 6 As shown, the lower level of the cabin has protruding spaces on the left and right sides. The upper and lower sides of these spaces provide upper and lower support surfaces for the needle roller sleeves in the connecting kit, restricting the movement of the connecting kit in the flight direction. Through the combination of the above components, the accuracy and smoothness of displacement detection can still be guaranteed under high-frequency vibration or large loads.

[0059] As can be seen, the connecting kit used in this embodiment allows the installation of the spoiler and displacement sensor to be distributed inside the cabin and on the outer wall of the cabin. The connection assembly can be disassembled into the connection of several parts, which has low assembly difficulty, supports an efficient assembly process, and ensures good stability and following performance when facing external interference.

[0060] Controller 13 connects to the brushless DC motor 1 and displacement sensor 5 (this electrical connection is not shown in the figure). Controller 13 communicates with an external guidance and control system via an RS422 data bus, enabling functions such as servo deflection control commands and servo status information exchange. Wiring channels can be designed on controller 13 for all external wiring of the servo motors and internal wiring to the control driver. Controller 13 is the electronic component of the servo system. When installed in the servo head, it is arranged in two radially oriented fan-shaped areas at the large end of the servo head. The control board is inserted into the servo head via a slot, and the cover plate is secured with screws.

[0061] In a preferred embodiment, the reduction mechanism 2 employs a gear transmission assembly, such as... Figure 5 As shown, the gear transmission assembly, mounted on the canopy 9, comprises multiple meshing gears, with the plane of the gears parallel to the flight direction. The gear transmission assembly occupies a flat space, and its placement on the canopy 9 not only makes full use of space but also ensures good positional stability. Furthermore, this design prevents the impact of the spoiler on the motor from being transmitted. A side view of the assembled structure of the DC brushless motor 1, reduction gear 2, ball screw 3, spoiler 4, and canopy 9 is shown below. Figure 9 As shown.

[0062] In a preferred embodiment, the ball screw is made of a high-hardness material and supported at both ends by angular contact bearings to overcome axial and radial forces. The ball screw is designed with starting torque and dynamic loads in mind to ensure stability under high-speed operation and high loads.

[0063] Regarding the selection of structure and materials, high-strength, lightweight materials were chosen in the design of the electric servo system of this invention to ensure that the system has sufficient strength and weight advantages. For key components, such as the motor housing, reducer, and control driver housing, aluminum alloy or titanium alloy materials are used to reduce weight while maintaining sufficient strength. In addition, to improve the system's high-temperature resistance and corrosion resistance, some components are treated with anti-corrosion coatings to ensure that the system can operate stably for a long time under harsh environmental conditions.

[0064] To improve the system's stability in high-noise, high-electromagnetic-interference environments, the control driver of this invention employs an anti-interference design. Through shielding, filtering, and overload protection measures, the system is ensured to operate normally even under extreme environmental conditions.

[0065] The system design includes redundant power supplies and redundant feedback loops to ensure automatic switchover to the backup system in the event of a failure, guaranteeing the normal operation of the servo system. Furthermore, all internal modules have undergone rigorous reliability testing to ensure their stability under high overload and high-impact environments.

[0066] In summary, the servo system of the present invention features fast response, high stability and precise control. It can maintain good stability and following performance when facing external interference such as load impact, and the position control accuracy reaches within 1mm, meeting the stringent requirements of modern aircraft for servo performance.

[0067] Its design features are summarized as follows:

[0068] System design requirements: This system comprehensively considers functional requirements, performance requirements, electrical requirements, structural interface requirements, and environmental conditions to meet the technical specifications for specific application scenarios.

[0069] Servo Gear Compartment Structure Design: The servo gear compartment structure of this system is custom-sized according to design requirements to accommodate all components of the electric servo system. The structural design takes into account space constraints and meets space requirements, including connector and installation tolerances, ensuring system compactness and ease of installation.

[0070] Electric servo motor structural design: As the core actuator of the system, the electric servo motor's structural design meets specific dimensional requirements to accommodate the space constraints of the servo compartment structure. The electric servo motor includes key components such as the motor, reducer, and feedback sensor, all of which are optimized for layout according to design requirements.

[0071] Ball screw design: The system employs a miniature ball screw made of high-hardness material, supported at both ends by angular contact bearings to overcome axial and radial forces. The ball screw design takes into account starting torque and dynamic load, ensuring stability under high-speed operation and high load.

[0072] Displacement sensor layout: The system uses dual potentiometer displacement sensors, installed in specific locations to achieve dual redundant feedback of travel position. This design improves the system's reliability and accuracy, ensuring performance even in extreme environments.

[0073] Transmission mechanism design: The transmission mechanism consists of a spur gear reduction mechanism and a ball screw, achieving speed reduction and torque amplification. This structural form, while meeting the spatial layout constraints of the actuator, features a large reduction ratio, lightweight structure, and high load-bearing capacity.

[0074] High overload resistance design: The system design takes into account the stability under high overload environment, including the motor mounting method and the reinforcement of the control drive, to ensure the reliability of the system under high shock and vibration environment.

[0075] Structural interface requirements: The system design meets the quality requirements and mechanical interface requirements.

[0076] Operating environment conditions: The system design meets the impact resistance requirements, and the product's impact resistance in the flight direction meets specific standards.

[0077] The working principle of the high-frequency response turbulence control servo motor of this invention is as follows:

[0078] Step S1: Control command reception: The system receives control commands from the host computer through the communication interface. These commands contain the target position information of the spoiler and are used to adjust the attitude of the projectile.

[0079] Step S2: Position feedback: The dual potentiometer displacement sensor monitors the position of the spoiler in real time and feeds it back to the controller to achieve dual redundant feedback of the stroke position.

[0080] Step S3: Control Algorithm Processing: The control algorithm inside the controller calculates the difference, i.e., the error signal, based on the received position feedback signal and the target position command, and adjusts the movement of the motor to ensure that the spoiler moves to the correct position.

[0081] Step S4: Motor drive: The controller adjusts the drive current and direction of the motor according to the output of the control algorithm, so that the motor generates the corresponding torque and drives the spoiler to perform telescopic movement.

[0082] Step S5: Spoiler movement: The spoilers move in accordance with the motor drive, and adjust the attitude of the aircraft to meet the system's requirements for high-frequency response.

[0083] Step S6: Real-time monitoring and adjustment: The system continuously monitors the position of the spoiler and adjusts it according to real-time feedback to ensure that the spoiler can accurately track changes in the target position command.

[0084] The servo motor of this invention uses closed-loop control, which enables the system to respond quickly to external commands and adjust the motor output according to the error signal, ensuring precise control of the spoiler position with the error kept within 1mm.

[0085] The assembly process of the high-frequency response turbulence control servo motor of this invention is as follows:

[0086] Servo assembly: Assemble the ball screw 3 and spoiler 4 together. Install positioning shafts 6 on both sides of the spoiler 4, along with nut sleeves on the outer periphery of the positioning shafts 6. Insert the electric servo structure, including the DC brushless motor 1, ball screw 3, and spoiler 4, into the rectangular hole in the servo compartment and tighten it with screws. Ensure that the interface between the servo structure and the servo compartment structure is compatible and meets the structural interface requirements.

[0087] Sensor installation: Install the moving shaft 7 from the openings of the sensor mounting positions on both sides of the cabin 8 toward the end face of the positioning shaft 6, and then install the displacement sensor 5 into the sensor mounting position. Insert the moving shaft 7 into the dynamic shaft guide groove of the displacement sensor 5.

[0088] Servo section assembly: Combine the cabin body 8 with the hatch 9, connect the DC brushless motor 1 and the ball screw 3 to the reduction mechanism 2 on the hatch 9, and extend the spoiler end out of the hatch's protrusion 91 to complete the electric servo assembly; install the assembled electric servo into the servo section; ensure that the interface between the servo and the section structure is matched and meets the structural interface requirements.

[0089] Controller installation: Place the controller in the designated area of ​​the servo compartment. Specifically, the controller can be placed in two radially fan-shaped areas at the large end of the servo compartment, inserted into the servo compartment via a slot, and the cover plate is tightened with screws.

[0090] Electrical Connections: Connect the electrical lines between the controller and the electric servo motor, ensuring all signal and power connections are correct.

[0091] System testing: After assembly, system testing is carried out, including electrical performance testing, mechanical motion testing and environmental adaptability testing, to ensure that the system meets all design specifications.

[0092] Final check and adjustment: After system testing, a final check is performed to adjust any deviations and ensure that the system reaches its optimal working state.

[0093] The electric servo system of this invention has broad application prospects, especially in high-dynamic, precision control applications such as high-speed aircraft, missiles, and drones. This system can provide precise and stable spoiler control in these high-frequency response environments, ensuring that the aircraft can effectively adjust its attitude and improve flight stability and handling performance. Specific application examples include, but are not limited to, the following areas:

[0094] Missile control system: By precisely controlling the position of spoilers, the missile's attitude and flight trajectory are adjusted, thereby improving accuracy.

[0095] The UAV control system provides high-frequency, high-precision control surfaces, ensuring rapid response to external disturbances and improving flight stability. Based on real-time sensor data, the system adjusts spoiler angles to achieve stable flight. During flight, the system can handle various disturbances, such as airflow changes and external wind interference, precisely adjusting the aircraft's attitude to ensure it flies along a predetermined trajectory. In practical applications, the system's high responsiveness ensures the UAV can quickly react to unexpected events in the flight environment. Test results show that under high-frequency wind disturbances, the system can adjust the control surface position within 0.5 seconds, reducing flight attitude deviations and enhancing flight stability.

[0096] High-speed aircraft control system: Applied in supersonic or hypersonic aircraft, this system achieves high-precision attitude control, ensuring good stability and maneuverability under various flight conditions. In a supersonic aircraft application, the system utilizes the electric servo control motor of this invention. In this application, the aircraft's flight speed reaches Mach 2.5, requiring high-frequency extension and retraction control of the spoiler during flight to cope with the aerodynamic torque caused by changes in flight attitude. Through the servo system of this invention, the aircraft can precisely adjust the spoiler angle, maintaining a stable flight attitude throughout flight and ensuring the missile's flight accuracy and stability. During testing, the system demonstrated excellent high-frequency response capabilities, completing the maximum displacement of the spoiler within 10ms, with the position error consistently within ±0.5mm. Through redundant design, the system can continue to operate even in the event of a power failure, ensuring the missile's mission completion.

[0097] The specific embodiments described above only illustrate the design principles of the present invention. The shapes and names of the components in this description may differ and are not limited. Therefore, those skilled in the art can modify or make equivalent substitutions to the technical solutions described in the foregoing embodiments; and these modifications and substitutions do not depart from the inventive spirit and technical solutions of the present invention, and should all fall within the protection scope of the present invention.

Claims

1. A high-frequency response turbulence control servo motor, characterized in that, include: DC brushless motor (1), reduction mechanism (2), ball screw (3), baffle (4), displacement sensor (5) and controller (13); The DC brushless motor (1) is connected to the ball screw (3) through the reduction mechanism (2); the baffle (4) has an L-shaped structure, with one arm being a fixed part (41) and the other arm being a baffle part (42). The fixed part (41) is installed as a nut sleeve on the movable nut (32) of the ball screw (3). The shaft axis of the brushless DC motor (1) and the screw axis of the ball screw (3) are both perpendicular to the flight direction of the carrier on which the servo motor is located; the spoiler (4) moves in extension and retraction perpendicular to the flight direction according to the drive of the brushless DC motor (1); The displacement sensor (5) is installed on the side of the spoiler (4), and the spoiler (4) is connected to the displacement sensor (5) through the connecting kit to transmit the displacement of the spoiler (4); The controller (13) is connected to the brushless DC motor (1) and the displacement sensor (5).

2. The high-frequency response turbulence control servo as described in claim 1, characterized in that, Further includes a cabin (8) and a hatch (9); the cabin (8) and the hatch (9) are fastened together to form a servo compartment, providing installation space; a DC brushless motor (1), a ball screw (3) and a spoiler (4) are installed inside the installation space; two displacement sensors (5) are symmetrically installed at sensor mounting positions on both sides of the cabin (8), and the sensor mounting positions have windows for transmitting position signals; An extension opening (91) for the outward extension of the spoiler (4) is provided on the hatch (9), and the deceleration mechanism (2) is installed on the hatch (9).

3. The high-frequency response turbulence control servo motor as described in claim 2, characterized in that, The cabin (8) has a double-layer structure. The upper layer has an installation slot that matches the shape of the DC brushless motor (1) for installing and fixing the DC brushless motor (1). The lower layer provides space for the installation and movement of the ball screw (3) and the baffle (4).

4. The high-frequency response turbulence control servo motor as described in claim 1, characterized in that, The deceleration mechanism (2) adopts a gear transmission assembly; the plane on which the gear is located is parallel to the flight direction.

5. The high-frequency response turbulence control servo as described in claim 1, characterized in that, The displacement sensor (5) is a miniature dual potentiometer type displacement sensor, which is installed on both sides of the baffle (4).

6. The high-frequency response turbulence control servo as described in claim 1, characterized in that, The connection kit between the displacement sensor (5) and the baffle (4) adopts a modular assembly structure; The connecting kit includes a positioning shaft (6) and a moving shaft (7); one end of the positioning shaft (6) is fixedly connected to the fixing part (41) and the moving nut (32), and the other end of the positioning shaft (6) is connected to the moving shaft (7), and the position is matched by the groove; the size of the end of the moving shaft (7) not connected to the positioning shaft (6) is adapted to the dynamic shaft guide groove (51) of the displacement sensor (5), and is inserted into the dynamic shaft guide groove (51); the extension length of the dynamic shaft guide groove (51) is greater than the stroke of the spoiler. When the spoiler moves, the moving distance is transmitted to the dynamic shaft guide groove through the positioning shaft (6) and the moving shaft (7), forming a potential change.

7. The high-frequency response turbulence control servo as described in claim 6, characterized in that, The connecting kit further includes a nut needle roller (14) and a needle roller sleeve (15); the nut needle roller is placed on the outer surface of the positioning shaft (6), and the needle roller sleeve (15) is fitted on the outside of the nut needle roller (14) to form a complete needle roller bearing pair; The high-frequency response turbulence control servo is installed in the servo compartment, which provides upper and lower support surfaces for the needle roller bearing pair to limit the movement of the connecting kit in the flight direction.

8. The high-frequency response turbulence control servo motor as described in claim 1, characterized in that, The controller (13) communicates with the external guidance and control system via an RS422 data bus.

9. The high-frequency response turbulence control servo motor as described in claim 1, characterized in that, The two ends of the ball screw (3) are supported by angular contact bearings.

10. A method for assembling a high-frequency response turbulence control servo motor as described in any one of claims 1-9, characterized in that, The method includes: Servo assembly: Assemble the ball screw (3) and the spoiler (4) together, install the positioning shaft (6) on both sides of the spoiler (4), and the nut needle roller (14) and needle roller sleeve (15) on the outer periphery of the positioning shaft (6); insert the DC brushless motor (1), the ball screw (3) and the spoiler (4) into the rectangular hole of the cabin (8) and tighten them with screws; Sensor installation: Install the moving shaft (7) from the opening of the sensor mounting position on both sides of the cabin (8) toward the end face of the positioning shaft (6), and then install the displacement sensor (5) to the sensor mounting position. Insert the moving shaft (7) into the dynamic shaft guide groove of the displacement sensor (5). Servo module assembly: Combine the module (8) with the cover (9), connect the DC brushless motor (1) and the ball screw (3) to the reduction mechanism (2) on the cover (9) to complete the electric servo assembly; install the assembled electric servo into the servo module; Controller installation: Place the controller in the designated area of ​​the servo compartment; Electrical connection: The electrical wiring connecting the controller and the electric servo motor.

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