CN215884123U

CN215884123U - Portable airplane body measurement and posture adjustment system

Info

Publication number: CN215884123U
Application number: CN202120715358.8U
Authority: CN
Inventors: 白果; 邬泽伟; 王鹏; 曾庆远
Original assignee: Chengdu Lihang Technology Co Ltd
Current assignee: Chengdu Lihang Technology Co Ltd
Priority date: 2021-04-08
Filing date: 2021-04-08
Publication date: 2022-02-22
Anticipated expiration: 2031-04-08

Abstract

The utility model discloses a portable airplane body measurement and posture adjustment system, which comprises a control terminal, a digital positioner, a posture adjustment gyroscope and a laser measuring instrument, wherein the digital positioner, the posture adjustment gyroscope and the laser measuring instrument are connected with the control terminal; the attitude adjusting gyroscope is adsorbed on the airplane body; the digital positioning devices are not less than three, and comprise two front positioning devices and one rear positioning device, the front positioning devices are respectively positioned on two sides of the front end of the airplane, and the rear positioning devices are positioned at the rear end of the airplane. The device is small and flexible, and can be set up at any place in a factory for measurement; the system carries out attitude adjustment detection on the airplane body, greatly improves the manufacturing detection time of the airplane body and can generate a report according to the number of frames; the utility model can also be applied to an omnidirectional transport vehicle, realizes the accurate suspension and posture adjustment of a plurality of wheel sets, and ensures the transportation stability and the real-time adjustment of the vehicle body posture.

Description

Portable airplane body measurement and posture adjustment system

Technical Field

The utility model relates to the field of aviation manufacturing, in particular to a portable airplane body measurement and posture adjustment system.

Background

At present, the airframe measurement of aviation manufacturing enterprises mostly uses a fixed clamp platform to carry out measurement and inspection, the clamp platform is large in size and cannot be moved, the attitude of the airframe cannot be adjusted, data after measurement cannot be recorded in equipment in real time, and the measurement and adjustment efficiency is poor. As disclosed in the published patent (application number CN201720211511.7), the structure of the digital assembly layout for the butt joint of the aircraft body and the aircraft nose comprises two aircraft body brackets, an aircraft nose posture adjusting and positioning unit, an aircraft body posture adjusting and positioning unit, two laser trackers, two butt joint surface operation tables, an aircraft body end operation table, two movable work ladders and an integrated control system operation table, wherein the two aircraft body brackets are positioned below the aircraft body, and the aircraft nose posture adjusting and positioning unit and the aircraft body posture adjusting and positioning unit are respectively arranged below the aircraft nose and the aircraft body; two laser tracker symmetries set up in the both sides in aircraft nose the place ahead, form the digital measuring field of aircraft, two butt joint face operation panels arrange respectively in aircraft nose and fuselage butt joint both sides fuselage tip operation panel set up in the tip of fuselage, two movable work ladders arrange in the fuselage both sides, integrated control system operation panel integrated measurement system, transferred appearance system, technology management and database system and accomplished the butt joint control work. The posture adjusting device disclosed by the patent is complex in structure, large in occupied space and not easy to move, and due to the fixed structure, the applied machine type is single, so that a light and convenient machine body posture adjusting measuring device capable of adjusting the position according to the machine type machine body is needed at present.

SUMMERY OF THE UTILITY MODEL

The utility model aims to overcome the defects of the prior art and provides a portable airplane body measurement and posture adjustment system.

The purpose of the utility model is realized by the following technical scheme:

a portable airplane body measurement and posture adjustment system comprises a control terminal, a digital positioner connected with the control terminal, a posture adjustment gyroscope and a laser measuring instrument; the attitude adjusting gyroscope is adsorbed on the airplane body; the number of the digital positioners is not less than three, and the digital positioners comprise two front positioners and one rear positioner.

Each digital positioner adopts the same electrical hardware configuration, and the electrical hardware comprises a controller, a motor driving module, a converter, a grating ruler, a servo motor, a load sensor and an exchanger; the controller is respectively connected with the load sensor, one end of the switch, one end of the motor driving module and one end of the converter; the other end of the motor driving module is connected with the servo motor; the other end of the converter is connected with the grating ruler; the other end of the switch is connected with the control terminal through the Ethernet.

The digital positioner adopts a uniform power supply form and is externally connected with a 380VAC power supply.

The switch is a 5-port industrial Ethernet switch, and the digital positioners are interconnected through the industrial Ethernet.

The control terminal is a PC.

The utility model has the beneficial effects that:

1. the device is small and flexible, and can be set up at any place in a factory for measurement;

2. the attitude adjustment detection is carried out on the airplane body, so that the manufacturing detection time of the airplane body can be greatly prolonged, and a report is generated according to the number of frames;

the device can be applied to an omnidirectional transport vehicle, realizes accurate suspension and posture adjustment of multiple wheel sets, and guarantees transportation stability and real-time adjustment of vehicle body posture.

Drawings

FIG. 1 is a system connection block diagram of the present invention;

FIG. 2 is a block diagram of the electrical connections of the digitizer locator.

Detailed Description

In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings.

In this embodiment, as shown in fig. 1, a portable airplane body measurement and attitude adjustment system includes a control terminal, a digital locator connected to the control terminal, an attitude adjustment gyroscope, and a laser measuring instrument; the attitude adjusting gyroscope is adsorbed on the airplane body; the number of the digital positioners is not less than three, and the digital positioners comprise two front positioners and one rear positioner.

As shown in fig. 2, the electrical hardware of each digital positioner includes a controller, a motor driving module, a converter, a grating scale, a servo motor, a load sensor, and a switch; the controller is respectively connected with the grating ruler, the load sensor, one end of the switch, one end of the motor driving module and one end of the converter; the other end of the motor driving module is connected with the servo motor; the other end of the converter is connected with the grating ruler; the other end of the switch is connected with the control terminal through the Ethernet. The switch is a 5-port industrial Ethernet switch, and all the digital positioners are interconnected through the industrial Ethernet.

The control terminal is a PC.

The digital locator main electrical element selection type is as follows table:

the digital positioner adopts a uniform power supply form and is externally connected with a 380VAC power supply. In use, 3 locators are connected with 2 connection cables. One end of each main power supply cable 1 is connected with a factory to supply power, and the other end of each main power supply cable can be inserted into any one positioner and simultaneously supplies power to the other two positioners. Each digital positioner uses an independent controller and can be used independently. The digital positioners all adopt the same electrical hardware configuration, and in the using process, electrical elements can be interchanged through simple arrangement.

The specific flow of the airplane fuselage measurement is as follows:

step 1, system power-on self-test: a power supply and a communication cable which are connected with the laser measuring instrument, the digital positioner and the control notebook; powering on the digital positioner, starting up the notebook computer and powering on the tracker for preheating; the system enters the attitude adjusting software, starts self-checking and communicates with the laser measuring instrument; self-checking, and prompting the user to log in; the preparation work (step 2) is entered.

Step 2, preparation: connecting a laser measuring instrument, and checking data of the laser measuring instrument; inputting the theoretical data and the upper station data into a system; the laser measuring instrument scans each measuring point and ERS point data in real time; selecting an initialization interface (step 3), maintaining the current situation (entering a posture adjusting interface step 4), a measurement interface (step 5) and a report interface (step 6).

Step 3, initializing an interface: lowering the positioner to the lowest position; manually jacking each point to a position (the load of each point reaches a certain value); and selecting to enter a posture adjustment interface (step 4).

Step 4, adjusting the posture interface: selecting manual or automatic posture adjustment; when the automatic adjustment is selected, the airplane is automatically adjusted to a preset attitude; when manual operation is selected, manually adjusting the airplane to a preset attitude; and entering a measurement interface (step 5) or a report interface (step 6).

Step 5, measuring an interface: selecting measurement contents (measurement menu); selecting manual measurement, selecting point by point, measuring by a laser tracker, and manually storing data; selecting automatic measurement, automatically scanning each measurement point by a laser tracker according to a measurement flow, and storing data; enter the report interface (step 6).

Step 6, report interface: displaying various reports, adjusting report data according to actual conditions, and printing and submitting the report data; and finishing the work.

The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the utility model as claimed. The scope of the utility model is defined by the appended claims and equivalents thereof.

Claims

1. A portable airplane body measurement and posture adjustment system is characterized by comprising a control terminal, a digital positioner, a posture adjustment gyroscope and a laser measuring instrument, wherein the digital positioner, the posture adjustment gyroscope and the laser measuring instrument are connected with the control terminal; the attitude adjusting gyroscope is adsorbed on the airplane body; the digital positioning devices are not less than three, and comprise two front positioning devices and one rear positioning device, the front positioning devices are respectively positioned on two sides of the front end of the airplane, and the rear positioning devices are positioned at the rear end of the airplane.

2. The portable airplane fuselage measurement and attitude adjustment system according to claim 1, wherein each digital positioner is configured by the same electrical hardware, and the electrical hardware comprises a controller, a motor driving module, a converter, a grating scale, a servo motor, a load sensor and a switch; the controller is respectively connected with the load sensor, one end of the switch, one end of the motor driving module and one end of the converter; the other end of the motor driving module is connected with the servo motor; the other end of the converter is connected with the grating ruler; the other end of the switch is connected with the control terminal through the Ethernet.

3. The portable airplane fuselage measurement and attitude adjustment system according to claim 1, wherein the digital locator is in a uniform power supply form and is externally connected with a 380VAC power supply.

4. The portable airplane body measurement and attitude adjustment system according to claim 2, wherein the switch is a 5-port industrial ethernet switch, and the digital positioners are interconnected through an industrial ethernet.

5. The portable airplane body measurement and posture adjustment system according to claim 1, wherein the control terminal is a PC.