阅读说明：本技术 面向飞机部件调姿对接的自动测量方法及装置 (Automatic measurement method and device for attitude adjustment butt joint of airplane components ) 是由 李现坤 雷沛 潘登 杨阳 何晓煦 曾超 于 2021-10-26 设计创作，主要内容包括：本发明公开一种面向飞机部件调姿对接的自动测量方法,用于终端设备,所述方法包括以下步骤：利用多个预设测量仪器对目标飞机部件的多个调姿点进行测量,获得多个所述预设测量仪器对应的多个调姿点信息,一个调姿点信息包括一个预设测量仪器对应的调姿点的调姿点坐标；获取多个所述预设测量仪器的多个仪器位置信息；基于每个所述预设测量仪器的仪器位置信息和每个所述预设测量仪器对应的调姿点坐标,获得所述目标飞机部件的最终调姿点信息。本发明还公开一种面向飞机部件调姿对接的自动测量装置、终端设备以及计算机可读存储介质。利用本发明的方法,并不需要测量人员手动操作,大大节省了测量时间,提高了测量效率。(The invention discloses an automatic measurement method for attitude adjustment docking of airplane components, which is used for terminal equipment and comprises the following steps: measuring a plurality of attitude adjusting points of a target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point information corresponding to the plurality of preset measuring instruments, wherein one attitude adjusting point information comprises an attitude adjusting point coordinate of the attitude adjusting point corresponding to one preset measuring instrument; acquiring a plurality of instrument position information of a plurality of preset measuring instruments; and obtaining final attitude adjusting point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument. The invention also discloses an automatic measuring device facing the airplane component posture adjusting butt joint, terminal equipment and a computer readable storage medium. By using the method of the invention, manual operation of measuring personnel is not needed, thereby greatly saving the measuring time and improving the measuring efficiency.)

1. An automatic measurement method facing attitude adjustment docking of airplane components is characterized by being used for terminal equipment, and comprises the following steps:

measuring a plurality of attitude adjusting points of a target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point information corresponding to the plurality of preset measuring instruments, wherein one attitude adjusting point information comprises an attitude adjusting point coordinate of the attitude adjusting point corresponding to one preset measuring instrument;

acquiring a plurality of instrument position information of a plurality of preset measuring instruments;

and obtaining final attitude adjusting point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument.

2. The method of claim 1, wherein the step of obtaining the plurality of instrument position information for the plurality of preset measurement instruments is preceded by the method further comprising:

determining a setting area of the target aircraft component, the setting area having a plurality of preset measurement points;

arranging a plurality of preset measuring instruments in the arrangement area;

determining a primary measurement point corresponding to each preset measurement instrument in the plurality of preset measurement points;

determining first measuring point position information of an initial measuring point of each preset measuring instrument;

and determining the instrument position information of each preset measuring instrument by using the first measuring point position information of each preset measuring instrument.

3. The method of claim 2, wherein prior to the step of determining the instrument position information for each of the preset measurement instruments using the first measurement point position information for each of the preset measurement instruments, the method further comprises:

determining a reselected measuring point of each preset measuring instrument in the plurality of preset measuring points;

determining second measuring point position information of a reselected measuring point of each preset measuring instrument;

the step of determining the instrument position information of each preset measuring instrument by using the first measuring point position information of each preset measuring instrument includes:

and determining the instrument position information of each preset measuring instrument by using the second measuring point position information and the first measuring point position information of each preset measuring instrument.

4. The method of claim 1, wherein prior to the step of measuring a plurality of attitude points of the target aircraft component using a plurality of predetermined measurement instruments, obtaining a plurality of attitude point information corresponding to the plurality of predetermined measurement instruments, the method further comprises:

numbering a plurality of preset measuring instruments to obtain a plurality of instrument numbers;

the step of measuring a plurality of attitude adjusting points of a target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point information corresponding to the plurality of preset measuring instruments comprises the following steps:

measuring the plurality of attitude adjusting points by using a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point coordinates of the plurality of attitude adjusting points, wherein one preset measuring instrument corresponds to one attitude adjusting point and one preset measuring instrument corresponds to one attitude adjusting point coordinate;

establishing a first mapping relation between the instrument number of each preset measuring instrument and the attitude adjusting point coordinate of each preset measuring instrument;

and acquiring the attitude adjusting point information of each preset measuring instrument based on the instrument number of each preset measuring instrument, the attitude adjusting point coordinate of each preset measuring instrument and the first mapping relation.

5. The method of claim 4, wherein the step of obtaining the plurality of instrument position information for the plurality of preset measurement instruments is preceded by the method further comprising:

creating a second mapping relation between the instrument number of each preset measuring instrument and the instrument position information of each preset measuring instrument;

creating an address table based on the instrument number of each preset measuring instrument, the instrument position information of each preset measuring instrument and the second mapping relation;

the step of acquiring instrument position information of a plurality of preset measuring instruments includes:

extracting the instrument number of each preset measuring instrument from the position information of each capital allocation point;

and based on the extracted instrument number of each preset measuring instrument, determining instrument position information corresponding to each preset measuring instrument in the address table by using the second mapping relation.

6. The method of claim 1, wherein the predetermined measurement instrument comprises a Leica AT901/LTD series laser tracker or an API laser tracker.

7. The method of claim 3, wherein the number of initially selected measurement points of each of the predetermined measurement instruments is at least 3, and the number of re-selected measurement points of each of the predetermined measurement instruments is at least 8.

8. An automatic measuring device for attitude-adjusting docking of aircraft components, for use with a terminal device, the device comprising:

the measurement module is used for measuring a plurality of attitude adjusting points of a target aircraft component by utilizing a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point information corresponding to the plurality of preset measuring instruments, and the attitude adjusting point information comprises an attitude adjusting point coordinate of the attitude adjusting point corresponding to one preset measuring instrument;

the acquisition module is used for acquiring a plurality of instrument position information of a plurality of preset measuring instruments;

and the obtaining module is used for obtaining the final attitude adjusting point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument.

9. A terminal device, characterized in that the terminal device comprises: memory, a processor and an automatic measurement program stored on the memory and running on the processor for pose alignment docking of an aircraft component, the automatic measurement program for pose alignment docking of an aircraft component when executed by the processor implementing the steps of the method for automatic measurement for pose alignment docking of an aircraft component of any of claims 1 to 7.

10. A computer-readable storage medium, characterized in that the computer-readable storage medium has stored thereon an automatic measurement program for pose-adjusted docking of an aircraft component, which when executed by a processor implements the steps of the method for automatic measurement for pose-adjusted docking of an aircraft component according to any one of claims 1 to 7.

Technical Field

The invention relates to the field of airplane assembly measurement, in particular to an automatic measurement method and device for airplane component posture adjustment butt joint.

Background

The large airplane component posture adjusting butt joint is an important part in the airplane assembly process, and mainly comprises the steps of measuring a fuselage posture adjusting point by using digital measuring equipment, transmitting a measuring data result to a master control system, and controlling a numerical control positioner to move by the master control system through calculating the posture relation between the current posture and the theoretical posture of the airplane component, so that the posture adjusting butt joint of the large airplane component is realized. Compared with a manual operation mode using a traditional tool, the mode can greatly improve the assembly precision and efficiency.

At present, the measurement of the attitude adjusting points of the airplane components mainly adopts a manual measurement mode, namely, a measurer uses SA software to measure the attitude adjusting points of the airplane body one by one in a manual light guiding mode.

However, the existing manual measurement mode is limited by the complex assembly environment of the assembly site, the posture adjustment and butt joint efficiency of large parts of the airplane is limited, and the measurement efficiency is low.

Disclosure of Invention

The invention mainly aims to provide an automatic measurement method and device for attitude adjustment and butt joint of airplane components, and aims to solve the technical problem of low measurement efficiency in the prior art.

In order to achieve the above object, the present invention provides an automatic measurement method for attitude adjustment docking of an aircraft component, which is used for a terminal device, and the method includes the following steps:

measuring a plurality of attitude adjusting points of a target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point information corresponding to the plurality of preset measuring instruments, wherein one attitude adjusting point information comprises an attitude adjusting point coordinate of the attitude adjusting point corresponding to one preset measuring instrument;

acquiring a plurality of instrument position information of a plurality of preset measuring instruments;

and obtaining final attitude adjusting point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument.

Optionally, before the step of obtaining the instrument position information of the preset measurement instruments, the method further includes:

determining a setting area of the target aircraft component, the setting area having a plurality of preset measurement points;

arranging a plurality of preset measuring instruments in the arrangement area;

determining a primary measurement point corresponding to each preset measurement instrument in the plurality of preset measurement points;

determining first measuring point position information of an initial measuring point of each preset measuring instrument;

and determining the instrument position information of each preset measuring instrument by using the first measuring point position information of each preset measuring instrument.

Optionally, before the step of determining the instrument position information of each preset measuring instrument by using the first measuring point position information of each preset measuring instrument, the method further includes:

determining a reselected measuring point of each preset measuring instrument in the plurality of preset measuring points;

determining second measuring point position information of a reselected measuring point of each preset measuring instrument;

the step of determining the instrument position information of each preset measuring instrument by using the first measuring point position information of each preset measuring instrument includes:

and determining the instrument position information of each preset measuring instrument by using the second measuring point position information and the first measuring point position information of each preset measuring instrument.

Optionally, before the step of measuring a plurality of attitude adjustment points of the target aircraft component by using a plurality of preset measuring instruments and obtaining a plurality of attitude adjustment point information corresponding to the plurality of preset measuring instruments, the method further includes:

numbering a plurality of preset measuring instruments to obtain a plurality of instrument numbers;

the step of measuring a plurality of attitude adjusting points of a target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point information corresponding to the plurality of preset measuring instruments comprises the following steps:

measuring the plurality of attitude adjusting points by using a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point coordinates of the plurality of attitude adjusting points, wherein one preset measuring instrument corresponds to one attitude adjusting point and one preset measuring instrument corresponds to one attitude adjusting point coordinate;

establishing a first mapping relation between the instrument number of each preset measuring instrument and the attitude adjusting point coordinate of each preset measuring instrument;

and acquiring the attitude adjusting point information of each preset measuring instrument based on the instrument number of each preset measuring instrument, the attitude adjusting point coordinate of each preset measuring instrument and the first mapping relation.

Optionally, before the step of obtaining the instrument position information of the preset measurement instruments, the method further includes:

creating a second mapping relation between the instrument number of each preset measuring instrument and the instrument position information of each preset measuring instrument;

creating an address table based on the instrument number of each preset measuring instrument, the instrument position information of each preset measuring instrument and the second mapping relation;

the step of acquiring instrument position information of a plurality of preset measuring instruments includes:

extracting the instrument number of each preset measuring instrument from the position information of each capital allocation point;

and based on the extracted instrument number of each preset measuring instrument, determining instrument position information corresponding to each preset measuring instrument in the address table by using the second mapping relation.

Optionally, the preset measuring instrument includes a Leica AT901/LTD series laser tracker or an API laser tracker.

Optionally, the number of the initially selected measurement points of each preset measurement instrument at least includes 3, and the number of the reselected measurement points of each preset measurement instrument at least includes 8.

In addition, in order to achieve the above object, the present invention further provides an automatic measuring device for adjusting and docking an airplane component, which is used for a terminal device, and the device includes:

the measurement module is used for measuring a plurality of attitude adjusting points of a target aircraft component by utilizing a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point information corresponding to the plurality of preset measuring instruments, and the attitude adjusting point information comprises an attitude adjusting point coordinate of the attitude adjusting point corresponding to one preset measuring instrument;

the acquisition module is used for acquiring a plurality of instrument position information of a plurality of preset measuring instruments;

and the obtaining module is used for obtaining the final attitude adjusting point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument.

In addition, to achieve the above object, the present invention further provides a terminal device, including: the automatic measurement program for the attitude-adjusting docking of the airplane component is stored in the memory and runs on the processor, and when being executed by the processor, the automatic measurement program for the attitude-adjusting docking of the airplane component realizes the steps of any one of the automatic measurement methods for the attitude-adjusting docking of the airplane component.

In addition, in order to achieve the above object, the present invention further provides a computer readable storage medium, on which an automatic measurement program for pose adjusting docking of an aircraft component is stored, and when the automatic measurement program for pose adjusting docking of an aircraft component is executed by a processor, the steps of the automatic measurement method for pose adjusting docking of an aircraft component according to any one of the above are implemented.

The technical scheme of the invention provides an automatic measurement method facing attitude adjustment butt joint of airplane components, which comprises the steps of measuring a plurality of attitude adjustment points of a target airplane component by utilizing a plurality of preset measurement instruments to obtain a plurality of attitude adjustment point information corresponding to the preset measurement instruments, wherein one attitude adjustment point information comprises an attitude adjustment point coordinate of an attitude adjustment point corresponding to one preset measurement instrument; acquiring a plurality of instrument position information of a plurality of preset measuring instruments; and obtaining final attitude adjusting point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument.

In the existing method, a measurer uses software to measure the attitude adjusting points of the machine body one by one in a manual light guiding mode, so that the measuring speed is low, and the measuring efficiency is low. By adopting the method, the terminal equipment automatically measures the multiple attitude adjusting points to obtain the final attitude adjusting point information without manual operation of measuring personnel, thereby greatly saving the measuring time and improving the measuring efficiency.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a terminal device in a hardware operating environment according to an embodiment of the present invention;

FIG. 2 is a schematic flow chart of a first embodiment of the automatic measurement method for attitude adjustment docking of aircraft components according to the present invention;

fig. 3 is a structural block diagram of a first embodiment of the automatic measuring device for adjusting attitude and docking of airplane components according to the present invention.

The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1, fig. 1 is a schematic structural diagram of a terminal device in a hardware operating environment according to an embodiment of the present invention.

In general, a terminal device includes: at least one processor 301, a memory 302, and an automatic measurement program for aircraft component pose-adjusted docking stored on the memory and executable on the processor, the automatic measurement program for aircraft component pose-adjusted docking being configured to implement the steps of the automatic measurement method for aircraft component pose-adjusted docking as described above.

The processor 301 may include one or more processing cores, such as a 4-core processor, an 8-core processor, and so on. The processor 301 may be implemented in at least one hardware form of a DSP (Digital Signal Processing), an FPGA (Field-Programmable Gate Array), and a PLA (Programmable Logic Array). The processor 301 may also include a main processor and a coprocessor, where the main processor is a processor for processing data in an awake state, and is also called a Central Processing Unit (CPU); a coprocessor is a low power processor for processing data in a standby state. In some embodiments, the processor 301 may be integrated with a GPU (Graphics Processing Unit), which is responsible for rendering and drawing the content required to be displayed on the display screen. Processor 301 may also include an AI (Artificial Intelligence) processor for processing operations related to the automated measurement method for aircraft component pose alignment docking, such that the model for the automated measurement method for aircraft component pose alignment docking may be trained autonomously for learning, improving efficiency and accuracy.

Memory 302 may include one or more computer-readable storage media, which may be non-transitory. Memory 302 may also include high speed random access memory, as well as non-volatile memory, such as one or more magnetic disk storage devices, flash memory storage devices. In some embodiments, a non-transitory computer readable storage medium in memory 302 is used to store at least one instruction for execution by processor 301 to implement the automatic measurement method for aircraft component pose docking provided by method embodiments herein.

In some embodiments, the terminal may further include: a communication interface 303 and at least one peripheral device. The processor 301, the memory 302 and the communication interface 303 may be connected by a bus or signal lines. Various peripheral devices may be connected to communication interface 303 via a bus, signal line, or circuit board. Specifically, the peripheral device includes: at least one of radio frequency circuitry 304, a display screen 305, and a power source 306.

The communication interface 303 may be used to connect at least one peripheral device related to I/O (Input/Output) to the processor 301 and the memory 302. In some embodiments, processor 301, memory 302, and communication interface 303 are integrated on the same chip or circuit board; in some other embodiments, any one or two of the processor 301, the memory 302 and the communication interface 303 may be implemented on a single chip or circuit board, which is not limited in this embodiment.

The Radio Frequency circuit 304 is used for receiving and transmitting RF (Radio Frequency) signals, also called electromagnetic signals. The radio frequency circuitry 304 communicates with communication networks and other communication devices via electromagnetic signals. The rf circuit 304 converts an electrical signal into an electromagnetic signal to transmit, or converts a received electromagnetic signal into an electrical signal. Optionally, the radio frequency circuit 304 comprises: an antenna system, an RF transceiver, one or more amplifiers, a tuner, an oscillator, a digital signal processor, a codec chipset, a subscriber identity module card, and so forth. The radio frequency circuitry 304 may communicate with other terminals via at least one wireless communication protocol. The wireless communication protocols include, but are not limited to: metropolitan area networks, various generation mobile communication networks (2G, 3G, 4G, and 5G), Wireless local area networks, and/or WiFi (Wireless Fidelity) networks. In some embodiments, the rf circuit 304 may further include NFC (Near Field Communication) related circuits, which are not limited in this application.

The display screen 305 is used to display a UI (User Interface). The UI may include graphics, text, icons, video, and any combination thereof. When the display screen 305 is a touch display screen, the display screen 305 also has the ability to capture touch signals on or over the surface of the display screen 305. The touch signal may be input to the processor 301 as a control signal for processing. At this point, the display screen 305 may also be used to provide virtual buttons and/or a virtual keyboard, also referred to as soft buttons and/or a soft keyboard. In some embodiments, the display screen 305 may be one, the front panel of the electronic device; in other embodiments, the display screens 305 may be at least two, respectively disposed on different surfaces of the electronic device or in a folded design; in still other embodiments, the display screen 305 may be a flexible display screen disposed on a curved surface or a folded surface of the electronic device. Even further, the display screen 305 may be arranged in a non-rectangular irregular figure, i.e. a shaped screen. The Display screen 305 may be made of LCD (liquid crystal Display), OLED (Organic Light-Emitting Diode), and the like.

The power supply 306 is used to power various components in the electronic device. The power source 306 may be alternating current, direct current, disposable or rechargeable. When the power source 306 includes a rechargeable battery, the rechargeable battery may support wired or wireless charging. The rechargeable battery may also be used to support fast charge technology.

Those skilled in the art will appreciate that the configuration shown in fig. 1 does not constitute a limitation of the terminal device and may include more or fewer components than those shown, or some components may be combined, or a different arrangement of components.

In addition, an embodiment of the present invention further provides a computer-readable storage medium, where an automatic measurement program for pose adjusting docking of an aircraft component is stored on the computer-readable storage medium, and when executed by a processor, the automatic measurement program for pose adjusting docking of an aircraft component implements the steps of the automatic measurement method for pose adjusting docking of an aircraft component as described above. Therefore, a detailed description thereof will be omitted. In addition, the beneficial effects of the same method are not described in detail. For technical details not disclosed in embodiments of the computer-readable storage medium referred to in the present application, reference is made to the description of embodiments of the method of the present application. It is determined that the program instructions may be deployed to be executed on one terminal device, or on multiple terminal devices located at one site, or distributed across multiple sites and interconnected by a communication network, as examples.

It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by a computer program, which can be stored in a computer-readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. The computer-readable storage medium may be a magnetic disk, an optical disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), or the like.

Based on the hardware structure, the embodiment of the automatic measurement method for the attitude adjustment butt joint of the airplane component is provided.

Referring to fig. 2, fig. 2 is a schematic flow chart of a first embodiment of the automatic measurement method for attitude adjustment docking of aircraft components, which is applied to a terminal device, and the method includes the following steps:

step S11: the method comprises the steps of measuring a plurality of attitude adjusting points of a target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point information corresponding to the plurality of preset measuring instruments, wherein one attitude adjusting point information comprises an attitude adjusting point coordinate of the attitude adjusting point corresponding to one preset measuring instrument.

It should be noted that the execution main body of the invention is the terminal device, the terminal device is provided with the automatic measurement program facing the attitude adjusting docking of the airplane component, and the step of the automatic measurement facing the attitude adjusting docking of the airplane component of the invention is realized when the terminal device executes the automatic measurement program facing the attitude adjusting docking of the airplane component.

In a specific application, a target aircraft component is an aircraft component to be subjected to attitude point adjustment measurement, the target component is usually a large component of an aircraft, such as a wing, a fuselage, an empennage and the like of the aircraft, the target aircraft component usually needs a plurality of preset measurement instruments to perform measurement, one measurement instrument is used for measuring one attitude point to obtain attitude point adjustment information of one attitude point, and each attitude point adjustment information includes an attitude point adjustment coordinate (a theoretical coordinate measured by the preset measurement instrument) corresponding to the attitude point and an instrument number of the corresponding preset measurement instrument.

Further, before the step of measuring a plurality of attitude adjustment points of the target aircraft component by using a plurality of preset measuring instruments and obtaining a plurality of attitude adjustment point information corresponding to the plurality of preset measuring instruments, the method further includes: numbering a plurality of preset measuring instruments to obtain a plurality of instrument numbers; correspondingly, the step of measuring a plurality of attitude adjustment points of the target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of attitude adjustment point information corresponding to the plurality of preset measuring instruments includes: measuring the plurality of attitude adjusting points by using a plurality of preset measuring instruments to obtain a plurality of attitude adjusting point coordinates of the plurality of attitude adjusting points, wherein one preset measuring instrument corresponds to one attitude adjusting point and one preset measuring instrument corresponds to one attitude adjusting point coordinate; establishing a first mapping relation between the instrument number of each preset measuring instrument and the attitude adjusting point coordinate of each preset measuring instrument; and acquiring the attitude adjusting point information of each preset measuring instrument based on the instrument number of each preset measuring instrument, the attitude adjusting point coordinate of each preset measuring instrument and the first mapping relation.

It can be understood that, in the present invention, each measuring instrument can be controlled by presetting the instrument number of the measuring instrument, and the number of each preset measuring instrument is different. The attitude adjusting point information corresponding to each preset measuring instrument comprises the attitude adjusting point coordinates of the attitude adjusting points and the instrument numbers of the preset measuring instruments.

And the terminal equipment controls each preset measuring instrument to automatically perform light guiding measurement so as to obtain the corresponding attitude adjusting point coordinates. In general application, the predetermined measurement instrument comprises a Leica AT901/LTD series laser tracker or an API laser tracker.

Step S12: and acquiring a plurality of instrument position information of a plurality of preset measuring instruments.

The method for acquiring the instrument position information of each preset measuring instrument comprises the following steps: determining a setting area of the target aircraft component, the setting area having a plurality of preset measurement points; arranging a plurality of preset measuring instruments in the arrangement area; determining a primary measurement point corresponding to each preset measurement instrument in the plurality of preset measurement points; determining first measuring point position information of an initial measuring point of each preset measuring instrument; and determining the instrument position information of each preset measuring instrument by using the first measuring point position information of each preset measuring instrument. Before the step of determining the instrument position information of each preset measuring instrument by using the first measuring point position information of each preset measuring instrument, the method further includes: determining a reselected measuring point of each preset measuring instrument in the plurality of preset measuring points; determining second measuring point position information of a reselected measuring point of each preset measuring instrument; correspondingly, the step of determining the instrument position information of each preset measuring instrument by using the first measuring point position information of each preset measuring instrument includes: and determining the instrument position information of each preset measuring instrument by using the second measuring point position information and the first measuring point position information of each preset measuring instrument.

The area where the target aircraft component is placed for measurement is a setting area, an ERS point which is a preset measurement point for measurement is set in the setting area, and a plurality of preset measurement instruments are set in the setting area. Then, for each preset measuring instrument, 3 preset measuring points closest to the preset measuring instrument are determined as the initial selected measuring points corresponding to the preset measuring instrument from the plurality of preset measuring points, the initial position of the preset measuring instrument is determined by using the coordinates of the initial selected measuring points (the first measuring point position information of the initial measuring points), then the reselected measuring points of each preset measuring instrument (usually, 8-10 preset measuring points farthest from the preset measuring instrument are determined) are determined from the plurality of preset measuring points, and then the preset accurate position-instrument position information of the preset measuring instrument is obtained based on the coordinates of the reselected measuring points (the second measuring point position information of the reselected measuring points).

Further, before the step of obtaining the plurality of instrument position information of the plurality of preset measuring instruments, the method further includes: creating a second mapping relation between the instrument number of each preset measuring instrument and the instrument position information of each preset measuring instrument; creating an address table based on the instrument number of each preset measuring instrument, the instrument position information of each preset measuring instrument and the second mapping relation; the step of acquiring instrument position information of a plurality of preset measuring instruments includes: extracting the instrument number of each preset measuring instrument from the position information of each capital allocation point; and based on the extracted instrument number of each preset measuring instrument, determining instrument position information corresponding to each preset measuring instrument in the address table by using the second mapping relation.

In the invention, the acquisition of the instrument position information of the preset measuring instrument is realized by presetting the instrument number of the measuring instrument.

Step S13: and obtaining final attitude adjusting point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument.

And after the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument are obtained, carrying out coordinate conversion by using the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument, thereby obtaining the final coordinate of the plurality of attitude adjusting points of the target aircraft component, namely the final attitude adjusting point information.

In the specific application, the multiple preset measuring instruments are controlled based on the SA secondary development interface SDK to obtain the attitude adjusting point coordinates measured by the multiple preset measuring instruments.

The technical scheme of the invention provides an automatic measurement method facing attitude adjustment butt joint of airplane components, which comprises the steps of measuring a plurality of attitude adjustment points of a target airplane component by utilizing a plurality of preset measurement instruments to obtain a plurality of attitude adjustment point information corresponding to the preset measurement instruments, wherein one attitude adjustment point information comprises an attitude adjustment point coordinate of an attitude adjustment point corresponding to one preset measurement instrument; acquiring a plurality of instrument position information of a plurality of preset measuring instruments; and obtaining final attitude adjusting point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjusting point coordinate corresponding to each preset measuring instrument.

In the existing method, a measurer uses software to measure the attitude adjusting points of the machine body one by one in a manual light guiding mode, so that the measuring speed is low, and the measuring efficiency is low. By adopting the method, the terminal equipment automatically measures the multiple attitude adjusting points to obtain the final attitude adjusting point information without manual operation of measuring personnel, thereby greatly saving the measuring time and improving the measuring efficiency.

Referring to fig. 3, fig. 3 is a block diagram of a first embodiment of the automatic measuring device for adjusting the attitude and docking of airplane components, which is used for terminal equipment, and based on the same inventive concept as the previous embodiment, the device comprises:

the measurement module 10 is configured to measure a plurality of attitude adjustment points of a target aircraft component by using a plurality of preset measurement instruments, and obtain a plurality of attitude adjustment point information corresponding to the plurality of preset measurement instruments, where one attitude adjustment point information includes an attitude adjustment point coordinate of an attitude adjustment point corresponding to one preset measurement instrument;

an obtaining module 20, configured to obtain a plurality of instrument position information of a plurality of preset measuring instruments;

an obtaining module 30, configured to obtain final pose adjustment point information of the target aircraft component based on the instrument position information of each preset measurement instrument and the pose adjustment point coordinates corresponding to each preset measurement instrument.

It should be noted that, since the steps executed by the apparatus of this embodiment are the same as the steps of the foregoing method embodiment, the specific implementation and the achievable technical effects thereof can refer to the foregoing embodiment, and are not described herein again.

The above description is only an alternative embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.