An aircraft transmission attitude adjustment system

Abstract

The application provides an aero transmission device posture adjusting system, which comprises an upper cast iron platform, a lower cast iron platform, an upper Hooke joint base, an upper Hooke joint, an upper hinged lug, a lower Hooke joint base, a lower Hooke joint, a lower hinged lug, an electric cylinder, a motor connecting seat and a motor; the aero transmission device posture adjusting system is used for realizing the axial telescopic function and the eccentric adjusting function of the input end coupling of a transmission product; the system adopts a guide rail and a sliding block structure as a moving guide mechanism, adopts a motor+electric cylinder as a moving execution mechanism, and realizes the six-degree-of-freedom posture change of a test piece.

Description

Technical Field

[0001] This application belongs to the field of aviation transmission technology, and particularly relates to an aviation transmission attitude adjustment system. Background Technology

[0002] An attitude adjustment system for an aircraft transmission device is used to realize the axial extension and retraction (0-300mm) and eccentricity adjustment (horizontal ±5mm, vertical ±20mm) functions of the coupling at the input end of the transmission product. By designing an attitude adjustment system for an aircraft transmission device, the axial extension and retraction and eccentricity adjustment functions of the coupling at the input end of the transmission product can be realized, simulating the flight attitude of the transmission product. Summary of the Invention

[0003] The purpose of this invention is to achieve six-degree-of-freedom attitude changes of the test piece by using a guide rail + slider structure as the moving guide mechanism and a motor + electric cylinder as the moving actuator.

[0004] This application provides an attitude adjustment system for an aircraft transmission device, the system comprising an upper cast iron platform, a lower cast iron platform, an upper hinge point, a lower hinge point, an electric cylinder, and a motor;

[0005] The upper and lower cast iron platforms are connected to six electric cylinders via six hinge points. The upper hinge point consists of an upper Hooke hinge base, an upper Hooke hinge, and an upper hinge lug. The lower hinge point consists of a lower Hooke hinge base, a lower Hooke hinge, and a lower hinge lug. The upper cast iron platform is equipped with six evenly distributed upper end caps, each with six through holes for fixing the upper Hooke hinge base; the lower cast iron platform is equipped with six evenly distributed lower end caps, each with six through holes for fixing the lower Hooke hinge base. The upper and lower Hooke hinge bases are provided with a through hole for connecting to the hinge lug; the hinge lug is provided with two coaxial through holes for connecting to the Hooke hinge. After the parallel electric cylinders are connected in parallel with the lower cast iron platform and the upper cast iron platform, one or more electric cylinders move simultaneously or differentially, and the end of the movement is a spatial rotational swing. The electric cylinder is driven by an electric motor to extend and retract.

[0006] Preferably, the upper cast iron platform serves as the installation reference for the entire system; the structure of the upper cast iron platform is constructed by bolting together aluminum profiles; the connection points of the three sets of hinge supports are connected by profiles to form a whole, thereby ensuring the overall strength and rigidity of the upper cast iron platform.

[0007] Preferably, the lower cast iron platform is constructed by bolting together profiles and is designed with connecting and positioning iron plates to enhance the connection strength and positioning accuracy of the platform; the lower cast iron platform is fixedly connected to the pre-embedded high-strength anchor bolts to ensure the safe and reliable operation of the moving platform.

[0008] Preferably, the electric cylinder consists of a servo motor, a ball screw, a screw support, a cylinder barrel, a piston rod, and a synchronous pulley.

[0009] Preferably, after the motor is powered on, it rotates clockwise or counterclockwise, driving the synchronous pulley to rotate, which in turn transmits the rotation to the lead screw. The rotation of the lead screw pushes the lead screw nut to make reciprocating linear motion along the lead screw axis. The lead screw nut is assembled and fixed to the piston rod. The lead screw, lead screw support and cylinder are connected together. The piston rod and cylinder move linearly relative to each other, realizing the extension and retraction motion of the electric cylinder.

[0010] Preferably, the output speed and angle of the motor can be varied in order to control the piston rod speed and stroke of the electric cylinder, thereby achieving high-precision operation of the motor.

[0011] Preferably, the system has complete six degrees of freedom in space. By changing the length of the electric cylinder, it can achieve three translational movements (translation around the XYZ axes) and rotation around the three coordinate axes (rotation around the XYZ axes).

[0012] Preferably, the cylinder barrel of the electric cylinder is a piston rod motion guide rail; the piston rod transmits the push and pull force of the lead screw nut, and the lead screw nut is mounted on a base; the synchronous pulley transmits the torque and speed of the servo motor synchronously to the ball screw; the rotational support of the ball screw bears the axial push and pull force of the lead screw.

[0013] The beneficial technical effects of this application are as follows: The attitude adjustment system of the aviation transmission device provided in this application rotates clockwise or counterclockwise after the motor is powered on, driving the synchronous pulley of the electric cylinder to rotate. The lead screw rotates and pushes the lead screw nut to perform reciprocating linear motion along the screw axis. The lead screw nut is assembled and fixed to the piston rod. The lead screw, lead screw support and cylinder are connected together. The piston rod and cylinder move linearly relative to each other, realizing the extension and retraction of the electric cylinder. One or more electric cylinders move simultaneously or differentially, and the upper cast iron platform rotates and swings in space, realizing six degrees of freedom attitude change of three translational motions and rotation around three coordinate axes. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 A schematic diagram of the overall structure of the attitude adjustment system provided in this application; Figure 2 This is the highest attitude front view of the attitude adjustment system provided in this application; Figure 3 This is the center-mounted attitude main view of the attitude adjustment system provided in this application; Figure 4 A front view of the forward tilt posture of the attitude adjustment system provided in this application; Figure 5 The front view of the pitch posture of the attitude adjustment system provided in this application; Figure 6 The main view of the roll attitude of the attitude adjustment system provided in this application; Figure 7 The front view of the attitude adjustment system provided in this application for forward movement; Figure 8 The front view of the attitude adjustment system provided in this application for backward attitude adjustment; Figure 9 The front view of the lateral displacement attitude of the attitude adjustment system provided in this application; Figure 10 A schematic diagram of the Hooke hinge base provided in this application; Figure 11 A schematic diagram of the Hooke's hinge provided for this application; Figure 12 A schematic diagram of the hinged lug provided in this application; Figure 13 A schematic diagram of the motor connector provided in this application; Figure 14 A schematic diagram of the end cap provided in this application; Figure 15 A schematic diagram of the tie rod provided in this application; Figure 16 A partial structural diagram of the attitude adjustment system provided in this application. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, 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.

[0017] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0018] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0019] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0020] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0021] The following is a description of the embodiments and appendices. Figure 1 -Appendix Figure 16 The present invention will be described in further detail, but the embodiments of the present invention are not limited thereto.

[0022] This invention relates to an attitude adjustment system for an aircraft transmission device, the system comprising an upper cast iron platform 1, a lower cast iron platform 2, an upper Hooke hinge base 3, an upper Hooke hinge 4, an upper hinge lug 5, a lower Hooke hinge base 6, a lower Hooke hinge 7, a lower hinge lug 8, an electric cylinder 9, a motor connector 10, and a motor 11.

[0023] The attitude adjustment system for aerospace transmission devices is used to realize the axial extension and retraction (0-300mm) and eccentricity adjustment (horizontal ±5mm, vertical ±20mm) functions of the coupling at the input end of the transmission product. The system employs a guide rail + slider structure as the moving guide mechanism and a motor + electric cylinder as the moving actuator to achieve six-degree-of-freedom attitude changes in the test piece.

[0024] After the motor 11 of the aircraft transmission attitude adjustment system is powered on, it rotates clockwise or counterclockwise, driving the synchronous pulley of the electric cylinder 9 to rotate. The lead screw a rotates like a screw, pushing the lead screw nut b to perform reciprocating linear motion along the screw axis. The lead screw nut b is assembled and fixed to the piston rod c. The lead screw a, the lead screw support d and the cylinder e are connected together. The piston rod c and the cylinder e move linearly relative to each other, realizing the extension and retraction of the electric cylinder 9. One or more electric cylinders 9 move simultaneously or differentially, and the upper cast iron platform 1 undergoes spatial rotation and oscillation, realizing six degrees of freedom attitude changes including three translational movements and rotation around three coordinate axes.

[0025] The present invention provides an attitude adjustment system for an aircraft transmission device, comprising an upper cast iron platform 1, a lower cast iron platform 2, an upper Hooke hinge base 3, an upper Hooke hinge 4, an upper hinge lug 5, a lower Hooke hinge base 6, a lower Hooke hinge 7, a lower hinge lug 8, an electric cylinder 9, a motor connector 10, and a motor 11.

[0026] Furthermore, the upper cast iron platform 1 serves as the installation reference for the entire system; the structure of the upper cast iron platform 1 is constructed by bolting together aluminum profiles; the connection points of the three sets of hinge supports are connected by profiles to form a whole, thereby ensuring the overall strength and rigidity of the upper cast iron platform.

[0027] Furthermore, the lower cast iron platform 2 is constructed by bolting together profiles and is designed with connecting and positioning iron plates to enhance the connection strength and positioning accuracy of the platform. The lower cast iron platform 2 is fixedly connected to the pre-embedded high-strength anchor bolts to ensure the safe and reliable operation of the moving platform.

[0028] Furthermore, the system has a total of six sets of hinges: three sets of upper hinges and three sets of lower hinges. The hinges adopt a silent, high-precision Hooke hinge structure, characterized by a large swing angle, small clearance, stable transmission, flexible movement, and convenient maintenance.

[0029] Furthermore, the system as a whole includes an upper cast iron platform 1 and a lower cast iron platform 2, which are connected to six electric cylinders 9 through six hinge points. The connection points have been specially reinforced in structure to provide better safety.

[0030] Furthermore, the upper hinge point consists of the upper Hooke hinge base 3, the upper Hooke hinge 4, and the upper hinge lug 5. The lower hinge point consists of the lower Hooke hinge base 6, the lower Hooke hinge 7, and the lower hinge lug 8.

[0031] Furthermore, the upper cast iron platform 1 is equipped with six evenly distributed upper end caps, each with six through holes, for fixing the upper Hooke hinge base 3; the lower cast iron platform 2 is equipped with six evenly distributed lower end caps, each with six through holes, for fixing the lower Hooke hinge base 6.

[0032] Furthermore, a through hole is provided on the upper Hooke hinge base 3 and the lower Hooke hinge base 6 for connecting with the hinge lug.

[0033] Furthermore, the upper Hooke hinge base 3 and the lower Hooke hinge base 6 are provided with a through hole for connecting to the hinge lug; the hinge lug is provided with two coaxial through holes for connecting to the Hooke hinge.

[0034] Furthermore, the electric cylinder 9 mainly consists of a servo motor, a ball screw, a screw support, a cylinder barrel, a piston rod, and a synchronous pulley. The electric cylinder 9 is a direct-drive type, with a screw lead of 5mm and a stroke of 300mm.

[0035] Furthermore, after the motor 11 is powered on, it rotates clockwise or counterclockwise, driving the synchronous pulley to rotate, which in turn transmits the rotation of the lead screw. The rotation of the lead screw drives the lead screw nut to perform reciprocating linear motion along the lead screw axis. The lead screw nut is assembled and fixed to the piston rod, and the lead screw, lead screw support and cylinder are connected together. The piston rod and cylinder move linearly relative to each other, realizing the extension and retraction of the electric cylinder 9.

[0036] Furthermore, after the parallel electric cylinders 9 are connected in parallel with the lower cast iron platform 2 and the upper cast iron platform 1, one or more electric cylinders 9 move simultaneously or differentially, and the end of the movement is a spatial rotational swing.

[0037] Furthermore, the output speed and angle of motor 11 can be varied in order to control the piston rod speed and stroke of electric cylinder 9, thereby achieving high-precision operation of the control motor.

[0038] Furthermore, the extension and retraction of the electric cylinder 9 driven by the motor 11 has the characteristics of fast response speed, high control precision, low noise, and large torque, resulting in better restoration effect.

[0039] The device according to claim 1 is characterized in that the system has complete six degrees of freedom in space, and by changing the length of the electric cylinder 9, it can realize the change of posture of three translational movements (translation around the XYZ axes) and rotation around the three coordinate axes (rotation around the XYZ axes).

[0040] Furthermore, the motor provides torque, position, and speed to the system.

[0041] Furthermore, the cylinder barrel of electric cylinder 9 is a piston rod motion guide; the piston rod transmits the push and pull force of the lead screw nut, and the lead screw nut is mounted on a base; the synchronous pulley transmits the torque and speed of the servo motor synchronously to the ball screw; the rotational support of the ball screw bears the axial push and pull force of the lead screw.

[0042] Furthermore, the worktable dimensions are as follows: maximum dynamic load 800kg, maximum pitch (tilt) offset ±15.5°, maximum roll offset ±15.8°, maximum yaw offset ±19°, maximum lift offset 290mm, maximum left-right offset ±188mm, maximum front-back offset ±180mm, maximum single-axis travel ≥±100mm in the X-axis direction, ≥±150mm in the Y-axis direction, ≥±100mm in the Z-axis direction, and angular motion ≥±15°.

[0043] After the motor 11 of the aircraft transmission attitude adjustment system is powered on, it rotates clockwise or counterclockwise, driving the synchronous pulley of the electric cylinder 9 to rotate. The lead screw rotates and pushes the lead screw nut to perform reciprocating linear motion along the screw axis. The lead screw nut is assembled and fixed to the piston rod. The lead screw, lead screw support and cylinder are connected together. The piston rod and cylinder move linearly relative to each other, realizing the extension and retraction of the electric cylinder 9. One or more electric cylinders 9 move simultaneously or differentially, and the upper cast iron platform 1 undergoes spatial rotation and oscillation, realizing six degrees of freedom attitude change including three translational motions and rotation around three coordinate axes.

[0044] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. An attitude adjustment system for an aircraft transmission device, characterized in that, The system includes an upper cast iron platform, a lower cast iron platform, an upper hinge point, a lower hinge point, an electric cylinder, and a motor; The upper and lower cast iron platforms are connected to six electric cylinders via six hinge points. The upper hinge point consists of an upper Hooke hinge base, an upper Hooke hinge, and an upper hinge lug. The lower hinge point consists of a lower Hooke hinge base, a lower Hooke hinge, and a lower hinge lug. The upper cast iron platform is equipped with six evenly distributed upper end caps, each with six through holes for fixing the upper Hooke hinge base; the lower cast iron platform is equipped with six evenly distributed lower end caps, each with six through holes for fixing the lower Hooke hinge base. The upper and lower Hooke hinge bases are provided with a through hole for connecting to the hinge lug; the hinge lug is provided with two coaxial through holes for connecting to the Hooke hinge. After the parallel electric cylinders are connected in parallel with the lower cast iron platform and the upper cast iron platform, one or more electric cylinders move simultaneously or differentially, and the end of the movement is a spatial rotational swing. The electric cylinder is driven by an electric motor to extend and retract.

2. The system according to claim 1, characterized in that, The upper cast iron platform serves as the installation benchmark for the entire system; its structure is constructed from bolted aluminum profiles; the three sets of hinged supports are connected by profiles to form a unified whole, thus ensuring the overall strength and rigidity of the upper cast iron platform.

3. The system according to claim 1, characterized in that, The lower cast iron platform is constructed by bolting together profiles and is designed with connecting and positioning iron plates to enhance the connection strength and positioning accuracy of the platform. The lower cast iron platform is fixedly connected to the pre-embedded high-strength anchor bolts to ensure the safe and reliable operation of the moving platform.

4. The system according to claim 1, characterized in that, The electric cylinder consists of a servo motor, ball screw, screw support, cylinder barrel, piston rod, and synchronous pulley.

5. The system according to claim 1, characterized in that, After the motor is powered on, it rotates clockwise or counterclockwise, driving the synchronous pulley to rotate, which in turn transmits the rotation to the lead screw. The rotation of the lead screw pushes the lead screw nut to make reciprocating linear motion along the lead screw axis. The lead screw nut is assembled and fixed to the piston rod. The lead screw, lead screw support and cylinder are connected together. The piston rod and cylinder move linearly relative to each other, realizing the extension and retraction of the electric cylinder.

6. The system according to claim 1, characterized in that, The output speed and angle of the motor can be varied in order to control the piston rod speed and stroke of the electric cylinder, thereby achieving high-precision operation of the motor.

7. The system according to claim 1, characterized in that, The system has complete six degrees of freedom in space. By changing the length of the electric cylinder, it can achieve three translational movements (translation around the XYZ axes) and rotation around the three coordinate axes (rotation around the XYZ axes).

8. The system according to claim 4, characterized in that, The cylinder barrel of the electric cylinder serves as the piston rod's motion guide; the piston rod transmits the push and pull force of the lead screw nut, which is mounted on the lead screw nut's mounting base; the synchronous pulley transmits the servo motor's torque and speed synchronously to the ball screw; the ball screw's rotational support bears the axial push and pull force of the lead screw.

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