A flexible polishing mechanism for aircraft skin

Abstract

The application discloses a kind of aircraft skin flexible polishing mechanical devices, including upper roof, the end surface lower part of the upper roof is symmetrically provided with three struts along center, the lower end of the strut is fixedly provided with spring, the lower end of the spring is provided with lower bottom plate, the upper end surface center of the lower bottom plate is provided with motor, the lower end of the motor is provided with lower baffle at the junction with the lower bottom plate, the output shaft of the motor is provided with coupling, the lower end of the coupling is provided with polishing head, the upper end of the lower bottom plate and at the side of motor is provided with displacement sensor, the end surface of the lower bottom plate and symmetrically is provided with three lugs along center, the outer end of the lug is provided with infrared distance sensor.The application drives polishing head to rotate by motor driving mode, and obtains the data on the surface of aircraft skin by the measurement of three infrared distance sensors at lower bottom plate, so as to ensure that polishing head can find out polishing curved surface position in real time and polish.

Description

Technical Field

[0001] This invention relates to the technical field of grinding equipment, specifically to a flexible grinding machine for aircraft skin. Background Technology

[0002] Patent CN202010254015.6 consists of a control system and a motion mechanism. Its principle is that the grinding head moves under the action of a pneumatic motor and cylinder. Displacement and angle sensors in the control system detect corresponding control quantities to ensure the contact surface pressure. The motion mechanism is driven by a robotic arm. The existing shortcomings of this device are that it cannot accurately locate the grinding area before grinding and cannot guarantee the grinding depth during the grinding process, easily causing damage to the workpiece. Therefore, a new grinding mechanical device has been designed to address these shortcomings. Summary of the Invention

[0003] The purpose of this invention is to provide a flexible grinding machine for aircraft skin to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a flexible grinding machine for aircraft skin, comprising an upper top plate, three pillars symmetrically arranged along the center of the lower end face of the upper top plate, a spring fixedly arranged at the lower end of the pillars, a lower base plate arranged at the lower end of the spring, a motor arranged at the center of the upper end face of the lower base plate, a lower baffle arranged at the junction of the lower end of the motor and the lower base plate, a coupling arranged on the output shaft of the motor, a grinding head arranged at the lower end of the coupling, a displacement sensor arranged on the upper end of the lower base plate and on one side of the motor, and three lugs symmetrically arranged along the center of the end face of the lower base plate, with an infrared ranging sensor arranged at the outer end of the lugs.

[0005] Preferably, the spring is divided into upper and lower sections, and a bearing is provided between the upper and lower sections.

[0006] Preferably, the upper top plate end face is provided with a threaded hole that mates with the support column.

[0007] Preferably, the number of the support column, the infrared ranging sensor, and the lugs are the same, all being three.

[0008] Preferably, the end of the lug away from the lower base plate is also provided with a threaded hole, and the infrared ranging sensor is detachably connected to the threaded hole on the end face of the lug.

[0009] Preferably, the total number of springs is six.

[0010] Preferably, the bearing is slidably disposed on the end face of the lower base plate.

[0011] Compared with the prior art, the beneficial effects of the present invention are:

[0012] 1. This invention uses a motor-driven method to drive the grinding head to rotate, and obtains data on the surface of the aircraft skin by measuring three infrared ranging sensors at the bottom plate, thereby ensuring that the grinding head can find the position of the surface to be ground in real time and perform grinding.

[0013] 2. The present invention also utilizes springs at the support column and the bottom plate. Under the support of the springs, the grinding head will have a stable grinding pressure during the grinding process. The entire grinding mechanical device can achieve constant force and flexibility, which helps to improve the grinding effect.

[0014] 3. In addition, the invention also provides a certain degree of protection for the flexible grinding machinery itself when the spring attached to the support moves up and down, reducing vibration and damage, and thus improving the work efficiency during the grinding process. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall three-dimensional structure of a flexible sanding machine for aircraft skin according to the present invention;

[0016] Figure 2 This is a schematic diagram of the overall main structure of a flexible sanding machine for aircraft skin according to the present invention;

[0017] Figure 3 This is a schematic diagram of the overall bottom view structure of a flexible sanding machine for aircraft skin according to the present invention;

[0018] Figure 4 This is a top view schematic diagram of the overall structure of a flexible sanding machine for aircraft skin according to the present invention.

[0019] In the diagram: 1. Top plate; 2. Support column; 3. Spring; 4. Bottom plate; 5. Motor; 6. Bottom baffle; 7. Coupling; 8. Grinding head; 9. Displacement sensor; 10. Lug; 11. Infrared rangefinder sensor; 12. Bearing. Detailed Implementation

[0020] 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, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] Please see Figure 1-4This invention provides a technical solution: a flexible grinding machine for aircraft skin, comprising an upper top plate 1, three support columns 2 connected by nuts with symmetrical holes along the center of the lower end face of the upper top plate 1, the support columns 2 serving as the connection and guide between the upper top plate 1 and the lower bottom plate 4, a spring 3 welded to the lower end of the support column 2, the lower bottom plate 4 sleeved on the lower end of the spring 3, a motor 5 bolted to the center of the upper end face of the lower bottom plate 4, a lower baffle 6 installed at the junction of the lower end of the motor 5 and the lower bottom plate 4, the output shaft of the motor 5 connected to a grinding head 8 via a coupling 7, a displacement sensor 9 installed by screws with a slot on the upper end of the lower bottom plate 4 and on one side of the motor 5, and three lugs 10 connected by nuts with symmetrical holes along the center of the end face of the lower bottom plate 4, an infrared ranging sensor 11 installed on the outer end of the lugs 10.

[0022] The spring 3 is divided into upper and lower sections, and a bearing 12 is installed between the upper and lower sections of the spring 3.

[0023] The top plate 1 has a threaded hole on its end face that is connected to the support column 2.

[0024] The number of support pillar 2, infrared ranging sensor 11, and lug 10 is the same, all being three.

[0025] The lug 10 also has a threaded hole at the end away from the bottom plate 4, and the infrared ranging sensor 11 is detachably connected to the threaded hole on the end face of the lug 10.

[0026] There are a total of six springs 3.

[0027] The bearing 12 is slidably connected to the end face of the lower base plate 4, and the lower base plate 4 slides through the bearing 12.

[0028] Working Principle: In use, the grinding head 8 is first connected to the motor 5 via the coupling 7. Initially, the motor 5 is connected to the lower baffle 6, with the center of the motor 5 positioned on the lower base plate 4, placing the lower base plate 4 at the original length of the spring 3. The spring 3 remains unchanged in length. When the flexible grinding mechanism is activated, the motor 5 is started via motor drive control, and the grinding head 8 begins to rotate. During the grinding process, the displacement of the grinding head 8 is measured in millimeters. Initially, the infrared ranging sensors 11 are activated, and the three infrared ranging sensors 11 mounted on the lower base plate 4 emit infrared rays that illuminate the aircraft skin surface. The distance measured by these rays determines the plane to be ground, and the grinding head 8 then contacts the aircraft skin surface via control drive. When grinding the aircraft skin surface, the lower base plate 4 moves along the support column 2 under the action of the spring 3. At this time, the upper spring 3 extends and the lower spring 3 compresses. The displacement sensor 9 installed on the lower base plate 4 measures the distance of the extension or compression of the spring 3, and then calculates the grinding force required for grinding using Hooke's Law. Then, the grinding head 8 completes a grinding operation according to the preset trajectory. After that, the control program issues a command, and the lower base plate 4 returns to the initial position. The upper spring 3 is compressed and the lower spring 3 is extended to ensure that the spring 3 returns to the initial position. The displacement sensor 9 and the infrared ranging sensor 11 measure the data and then shut down to complete a grinding operation. Finally, by observing the grinding quality of the aircraft skin surface, it can be determined whether multiple grinding operations are required according to the standard, thereby ensuring the yield of the aircraft skin.

[0029] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0030] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A flexible sanding machine for aircraft skin, comprising an upper top plate (1), characterized in that: Three pillars (2) are symmetrically arranged along the center of the lower end face of the upper top plate (1). A spring (3) is fixedly installed at the lower end of each pillar (2). A lower base plate (4) is installed at the lower end of each spring (3). A motor (5) is installed at the center of the upper end face of the lower base plate (4). A lower baffle (6) is installed at the junction of the lower end of the motor (5) and the lower base plate (4). A coupling (7) is installed on the output shaft of the motor (5). A grinding head (8) is installed at the lower end of the coupling (7). The upper end of the lower base plate (4) and the area above the motor (5) are... A displacement sensor (9) is provided on one side. Three lugs (10) are symmetrically arranged on the end face of the lower base plate (4) along the center. An infrared ranging sensor (11) is provided at the outer end of the lugs (10). The spring (3) is divided into upper and lower sections, and a bearing (12) is provided between the upper and lower sections of the spring (3). The number of the support column (2), the infrared ranging sensor (11), and the lugs (10) are the same, all being three. The total number of springs (3) is six. The bearing (12) is slidably arranged on the end face of the lower base plate (4).

2. The flexible sanding machine for aircraft skin according to claim 1, characterized in that: The top plate (1) has a threaded hole on its end face that is connected to the support column (2).

3. The flexible sanding machine for aircraft skin according to claim 1, characterized in that: The lug (10) is also provided with a threaded hole at the end away from the bottom plate (4), and the infrared ranging sensor (11) is detachably connected to the threaded hole on the end face of the lug (10).

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