CN113895646B - Automatic measurement method and device for attitude adjustment butt joint of airplane components - Google Patents
Automatic measurement method and device for attitude adjustment butt joint of airplane components Download PDFInfo
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- CN113895646B CN113895646B CN202111252019.1A CN202111252019A CN113895646B CN 113895646 B CN113895646 B CN 113895646B CN 202111252019 A CN202111252019 A CN 202111252019A CN 113895646 B CN113895646 B CN 113895646B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/002—Measuring arrangements characterised by the use of optical techniques for measuring two or more coordinates
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/30—Computing systems specially adapted for manufacturing
Abstract
The invention discloses an automatic measurement method for attitude adjustment butt joint of airplane components, which is used for terminal equipment and comprises the following steps: measuring a plurality of gesture adjusting points of a target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of gesture adjusting point information corresponding to the preset measuring instruments, wherein one gesture adjusting point information comprises gesture adjusting point coordinates of gesture adjusting points corresponding to one preset measuring instrument; acquiring a plurality of instrument position information of a plurality of preset measuring instruments; and obtaining final attitude adjustment point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjustment point coordinates corresponding to each preset measuring instrument. The invention also discloses an automatic measurement device, terminal equipment and a computer readable storage medium for the attitude adjustment and docking of the aircraft components. By using the method of the invention, the manual operation of a measuring staff is not needed, the measuring time is greatly saved, and the measuring efficiency is improved.
Description
Technical Field
The invention relates to the field of aircraft assembly measurement, in particular to an automatic measurement method and device for attitude adjustment and butt joint of aircraft parts.
Background
The attitude adjustment and butt joint of the large part of the airplane is an important ring in the assembly process of the airplane, and mainly comprises the steps of measuring an attitude adjustment point of the airplane body by using digital measuring equipment, transmitting a measured data result to a master control system, and controlling a numerical control positioner to move by the master control system through calculating the attitude relation between the current attitude and the theoretical attitude of the airplane body, so that the attitude adjustment and butt joint of the large part of the airplane is realized. Compared with a manual operation mode using a traditional tool, the assembly precision and efficiency can be greatly improved.
At present, the measurement of the attitude adjustment points of the aircraft parts mainly adopts a manual measurement mode, namely, a measurer measures the attitude adjustment points of the aircraft body one by using SA software in a manual light guiding mode.
However, the existing manual measurement mode is limited by a complex assembly environment of an assembly site, so that the attitude adjustment and butt joint efficiency of large parts of the aircraft 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 butt joint of aircraft parts, and aims to solve the technical problem of lower measurement efficiency in the prior art.
In order to achieve the above purpose, the invention provides an automatic measurement method for docking an aircraft component in an attitude adjustment manner, which is used for terminal equipment, and comprises the following steps:
measuring a plurality of gesture adjusting points of a target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of gesture adjusting point information corresponding to the preset measuring instruments, wherein one gesture adjusting point information comprises gesture adjusting point coordinates of gesture adjusting points corresponding to one preset measuring instrument;
acquiring a plurality of instrument position information of a plurality of preset measuring instruments;
and obtaining final attitude adjustment point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjustment point coordinates corresponding to each preset measuring instrument.
Optionally, before the step of acquiring the plurality of instrument position information of the plurality of preset measuring instruments, the method further includes:
determining a set area of the target aircraft component, the set area having a plurality of preset measurement points;
setting a plurality of preset measuring instruments in the setting area;
determining a primary selected measuring point corresponding to each preset measuring instrument in a plurality of preset measuring points;
determining first measurement point position information of an initial measurement point of each preset measurement 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 measurement point position information of each preset measuring instrument, the method further includes:
determining reselection measuring points of each preset measuring instrument in a plurality of preset measuring points;
determining second measuring point position information of reselected measuring points 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 comprises the following steps:
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 the plurality of pose points of the target aircraft component by using the plurality of preset measuring instruments to obtain the plurality of pose 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 adjustment points of a target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of attitude adjustment point information corresponding to the preset measuring instruments comprises the following steps:
measuring a plurality of gesture adjusting points by using a plurality of preset measuring instruments to obtain a plurality of gesture adjusting point coordinates of the gesture adjusting points, wherein one preset measuring instrument corresponds to one gesture adjusting point, and one preset measuring instrument corresponds to one gesture adjusting point coordinate;
creating a first mapping relation between the instrument number of each preset measuring instrument and the pose adjustment point coordinates of each preset measuring instrument;
and acquiring pose adjustment point information of each preset measuring instrument based on the instrument number of each preset measuring instrument, the pose adjustment point coordinates of each preset measuring instrument and the first mapping relation.
Optionally, before the step of acquiring 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 the plurality of instrument position information of the plurality of preset measuring instruments includes:
extracting the instrument number of each preset measuring instrument from the position information of each financing point;
and determining the instrument position information corresponding to each preset measuring instrument in the address table by utilizing the second mapping relation based on the extracted instrument number of each preset measuring instrument.
Optionally, the preset measuring instrument comprises a Leica AT901/LTD series laser tracker or an API laser tracker.
Optionally, the initial selected measurement points of each preset measurement instrument comprise at least 3, and the reselection measurement points of each preset measurement instrument comprise at least 8.
In addition, in order to achieve the above purpose, the invention also provides an automatic measurement device facing to the attitude adjustment and docking of the aircraft component, which is used for terminal equipment and comprises:
the measuring module is used for measuring a plurality of gesture adjusting points of the target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of gesture adjusting point information corresponding to the preset measuring instruments, wherein one gesture adjusting point information comprises gesture adjusting point coordinates of gesture adjusting points corresponding to the preset measuring instruments;
the acquisition module is used for acquiring a plurality of instrument position information of a plurality of preset measuring instruments;
the obtaining module is used for obtaining final attitude adjustment point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjustment point coordinates corresponding to each preset measuring instrument.
In addition, to achieve the above object, the present invention also proposes a terminal device including: the automatic measurement method for the attitude adjustment butt joint of the airplane component comprises the steps of a memory, a processor and an automatic measurement program, wherein the automatic measurement program is stored in the memory and used for running the attitude adjustment butt joint of the airplane component on the processor, and the automatic measurement program for the attitude adjustment butt joint of the airplane component is used for realizing the automatic measurement method for the attitude adjustment butt joint of the airplane component according to any one of the above steps when being executed by the processor.
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 attitude adjustment and docking of an aircraft component is stored, where the automatic measurement program for attitude adjustment and docking of an aircraft component implements the steps of the automatic measurement method for attitude adjustment and docking of an aircraft component according to any one of the above steps when executed by a processor.
According to the technical scheme, the automatic measurement method for the gesture adjustment butt joint of the aircraft component is provided, a plurality of gesture adjustment points of a target aircraft component are measured by utilizing a plurality of preset measurement instruments, a plurality of gesture adjustment point information corresponding to the preset measurement instruments is obtained, and one gesture adjustment point information comprises gesture adjustment point coordinates of a gesture adjustment point corresponding to the preset measurement instrument; acquiring a plurality of instrument position information of a plurality of preset measuring instruments; and obtaining final attitude adjustment point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjustment point coordinates corresponding to each preset measuring instrument.
In the existing method, a measuring person measures the attitude adjusting points of the machine body one by using software 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 performs measurement of a plurality of gesture adjusting points so as to obtain final gesture adjusting point information, and measurement personnel are not required to manually operate, so that the measurement time is greatly saved, and the measurement efficiency is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic diagram of a terminal device structure of a hardware running environment according to an embodiment of the present invention;
FIG. 2 is a schematic flow chart of a first embodiment of an automatic measurement method for docking an aircraft component;
fig. 3 is a block diagram of a first embodiment of an automatic measurement device for docking an aircraft component in accordance with the present invention.
The achievement of the objects, functional features and advantages of the present invention will be further described with reference to the accompanying drawings, in conjunction with the embodiments.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1, fig. 1 is a schematic diagram of a terminal device structure of a hardware running 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 attitude oriented docking stored on the memory and operable on the processor, the automatic measurement program for aircraft component attitude oriented docking being configured to implement the steps of the automatic measurement method for aircraft component attitude oriented docking as previously described.
Processor 301 may include one or more processing cores, such as a 4-core processor, an 8-core processor, and the like. The processor 301 may be implemented in at least one hardware form of DSP (Digital Signal Processing ), FPGA (Field-Programmable Gate Array, field programmable gate array), PLA (Programmable Logic Array ). The processor 301 may also include a main processor, which is a processor for processing data in an awake state, also called a CPU (Central ProcessingUnit ), and a coprocessor; a coprocessor is a low-power processor for processing data in a standby state. In some embodiments, the processor 301 may integrate a GPU (Graphics Processing Unit, image processor) for rendering and drawing of content required to be displayed by the display screen. The processor 301 may also include an AI (Artificial Intelligence ) processor for processing automatic measurement method operations relating to aircraft component-oriented pose alignment such that an automatic measurement method model of aircraft component-oriented pose alignment may be trained and learned autonomously, 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 attitude oriented docking provided by the method embodiments herein.
In some embodiments, the terminal may further optionally 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. The respective peripheral devices may be connected to the communication interface 303 through 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 supply 306.
The communication interface 303 may be used to connect at least one peripheral device associated with an 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, either or both of the processor 301, the memory 302, and the communication interface 303 may be implemented on separate chips or circuit boards, which is not limited in this embodiment.
The Radio Frequency circuit 304 is configured to receive and transmit RF (Radio Frequency) signals, also known as electromagnetic signals. The radio frequency circuitry 304 communicates with a communication network and other communication devices via electromagnetic signals. The radio frequency circuit 304 converts an electrical signal into an electromagnetic signal for transmission, or converts a received electromagnetic signal into an electrical signal. Optionally, the radio frequency circuit 304 includes: antenna systems, RF transceivers, one or more amplifiers, tuners, oscillators, digital signal processors, codec chipsets, subscriber identity module cards, and so forth. The radio frequency circuitry 304 may communicate with other terminals via at least one wireless communication protocol. The wireless communication protocol includes, but is not limited to: metropolitan area networks, various generations of mobile communication networks (2G, 3G, 4G, and 5G), wireless local area networks, and/or WiFi (Wireless Fidelity ) networks. In some embodiments, the radio frequency circuitry 304 may also include NFC (Near Field Communication ) related circuitry, which is 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 305 is a touch screen, the display 305 also has the ability to collect touch signals at or above the surface of the display 305. The touch signal may be input as a control signal to the processor 301 for processing. At this point, the display 305 may also be used to provide virtual buttons and/or virtual keyboards, also referred to as soft buttons and/or soft keyboards. In some embodiments, the display 305 may be one, the front panel of an electronic device; in other embodiments, the display screen 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 305 may be a flexible display disposed on a curved surface or a folded surface of the electronic device. Even more, the display screen 305 may be arranged in an irregular pattern other than rectangular, i.e., a shaped screen. The display 305 may be made of LCD (LiquidCrystal Display ), OLED (Organic Light-Emitting Diode) or other materials.
The power supply 306 is used to power the various components in the electronic device. The power source 306 may be alternating current, direct current, disposable or rechargeable. When the power source 306 comprises a rechargeable battery, the rechargeable battery may support wired or wireless charging. The rechargeable battery may also be used to support fast charge technology.
It will be appreciated by those skilled in the art that the structure shown in fig. 1 does not constitute a limitation of the terminal device, and may include more or less components than illustrated, or may combine certain components, or may be arranged in different components.
In addition, the embodiment of the invention also provides a computer readable storage medium, wherein the computer readable storage medium is stored with an automatic measurement program for the attitude adjustment butt joint of the aircraft component, and the automatic measurement program for the attitude adjustment butt joint of the aircraft component realizes the steps of the automatic measurement method for the attitude adjustment butt joint of the aircraft component when being executed by a processor. Therefore, a detailed description will not be given here. In addition, the description of the beneficial effects of the same method is omitted. For technical details not disclosed in the embodiments of the computer-readable storage medium according to the present application, please refer to the description of the method embodiments of the present application. As determined as an example, the program instructions may be deployed to be executed on one terminal device or on multiple terminal devices located at one site or, alternatively, on multiple terminal devices distributed across multiple sites and interconnected by a communication network.
Those skilled in the art will appreciate that implementing all or part of the above-described methods may be accomplished by way of computer programs, which may be stored on a computer-readable storage medium, and which, when executed, may comprise the steps 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 (Random AccessMemory, RAM), or the like.
Based on the hardware structure, the embodiment of the automatic measurement method for the attitude adjustment butt joint of the aircraft component is provided.
Referring to fig. 2, fig. 2 is a schematic flow chart of a first embodiment of an automatic measurement method for docking an aircraft component in alignment according to the present invention, for a terminal device, the method includes the steps of:
step S11: and measuring a plurality of gesture adjusting points of the target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of gesture adjusting point information corresponding to the preset measuring instruments, wherein one gesture adjusting point information comprises gesture adjusting point coordinates of the gesture adjusting point corresponding to one preset measuring instrument.
The execution main body of the invention is a terminal device, the terminal device is provided with an automatic measurement program for the attitude-adjusting butt joint of the airplane component, and when the terminal device executes the automatic measurement program for the attitude-adjusting butt joint of the airplane component, the automatic measurement step for the attitude-adjusting butt joint of the airplane component is realized.
In specific applications, the target aircraft component is an aircraft component to be measured for a pose-adjusting point, the target aircraft component is usually a large component of an aircraft, such as a wing, a fuselage, a tail wing, and the like of the aircraft, the target aircraft component usually needs a plurality of preset measuring instruments for measuring, one measuring instrument is used for measuring one pose-adjusting point to obtain pose-adjusting point information of one pose-adjusting point, and each pose-adjusting point information includes pose-adjusting point coordinates (theoretical coordinates measured by the preset measuring instrument) corresponding to the pose-adjusting point and instrument numbers of the corresponding preset measuring instruments.
Further, before the step of measuring the plurality of pose points of the target aircraft component by using the plurality of preset measuring instruments to obtain the plurality of pose 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 pose adjustment points of the target aircraft component by using a plurality of preset measuring instruments to obtain a plurality of pose adjustment point information corresponding to the preset measuring instruments comprises the following steps: measuring a plurality of gesture adjusting points by using a plurality of preset measuring instruments to obtain a plurality of gesture adjusting point coordinates of the gesture adjusting points, wherein one preset measuring instrument corresponds to one gesture adjusting point, and one preset measuring instrument corresponds to one gesture adjusting point coordinate; creating a first mapping relation between the instrument number of each preset measuring instrument and the pose adjustment point coordinates of each preset measuring instrument; and acquiring pose adjustment point information of each preset measuring instrument based on the instrument number of each preset measuring instrument, the pose adjustment point coordinates of each preset measuring instrument and the first mapping relation.
It will be appreciated that in the present invention, the control of each measuring instrument may be performed by presetting the instrument number of the measuring instrument, the number of each preset measuring instrument being different. The gesture adjusting point information corresponding to each preset measuring instrument comprises gesture adjusting point coordinates of the gesture adjusting point and instrument numbers of the preset measuring instruments.
The terminal equipment controls each preset measuring instrument to automatically conduct light-guiding measurement so as to obtain corresponding gesture-adjusting point coordinates. In general applications, the preset measuring 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 obtaining the instrument position information of each preset measuring instrument comprises the following steps: determining a set area of the target aircraft component, the set area having a plurality of preset measurement points; setting a plurality of preset measuring instruments in the setting area; determining a primary selected measuring point corresponding to each preset measuring instrument in a plurality of preset measuring points; determining first measurement point position information of an initial measurement point of each preset measurement 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. Wherein 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 comprises: determining reselection measuring points of each preset measuring instrument in a plurality of preset measuring points; determining second measuring point position information of reselected measuring points 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 comprises the following steps: 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 and used for measuring is a setting area, preset measuring points for measuring, namely ERS points, are set in the setting area, and a plurality of preset measuring instruments are set in the setting area. Then, for each preset measuring instrument, determining 3 preset measuring points closest to the preset measuring instrument as initial measuring points corresponding to the preset measuring instrument in a plurality of preset measuring points, determining the initial position of the preset measuring instrument by using the coordinates (the first measuring point position information of the initial measuring points) of the initial measuring points, then continuing to determine the reselection measuring points (usually determining 8-10 preset measuring points farthest from the preset measuring instrument) of each preset measuring instrument in a plurality of preset measuring points, and then obtaining the accurate position-instrument position information of the preset measuring instrument based on the coordinates (the second measuring point position information of the reselection measuring points) of the reselection measuring points.
Further, before the step of acquiring 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 the plurality of instrument position information of the plurality of preset measuring instruments includes: extracting the instrument number of each preset measuring instrument from the position information of each financing point; and determining the instrument position information corresponding to each preset measuring instrument in the address table by utilizing the second mapping relation based on the extracted instrument number of each preset measuring instrument.
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 adjustment point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjustment point coordinates corresponding to each preset measuring instrument.
After instrument position information of each preset measuring instrument and gesture adjustment point coordinates corresponding to each preset measuring instrument are obtained, coordinate conversion is carried out by utilizing the instrument position information of each preset measuring instrument and the gesture adjustment point coordinates corresponding to each preset measuring instrument, so that final coordinates of a plurality of gesture adjustment points of a target aircraft component, namely final gesture adjustment point information, are obtained.
In a specific application, a plurality of preset measuring instruments are controlled based on an SA secondary development interface SDK so as to obtain gesture adjustment point coordinates measured by the plurality of preset measuring instruments.
According to the technical scheme, the automatic measurement method for the gesture adjustment butt joint of the aircraft component is provided, a plurality of gesture adjustment points of a target aircraft component are measured by utilizing a plurality of preset measurement instruments, a plurality of gesture adjustment point information corresponding to the preset measurement instruments is obtained, and one gesture adjustment point information comprises gesture adjustment point coordinates of a gesture adjustment point corresponding to the preset measurement instrument; acquiring a plurality of instrument position information of a plurality of preset measuring instruments; and obtaining final attitude adjustment point information of the target aircraft component based on the instrument position information of each preset measuring instrument and the attitude adjustment point coordinates corresponding to each preset measuring instrument.
In the existing method, a measuring person measures the attitude adjusting points of the machine body one by using software 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 performs measurement of a plurality of gesture adjusting points so as to obtain final gesture adjusting point information, and measurement personnel are not required to manually operate, so that the measurement time is greatly saved, and the measurement efficiency is improved.
Referring to fig. 3, fig. 3 is a block diagram illustrating a first embodiment of an automatic measurement device for attitude-adjusting docking of aircraft components according to the present invention, for a terminal apparatus, based on the same inventive concept as the previous embodiment, comprising:
the measuring module 10 is configured to measure a plurality of pose adjustment points of a target aircraft component by using a plurality of preset measuring instruments, and obtain a plurality of pose adjustment point information corresponding to the preset measuring instruments, where one pose adjustment point information includes pose adjustment point coordinates of a pose adjustment point corresponding to one preset measuring instrument;
an acquisition module 20, configured to acquire a plurality of instrument position information of a plurality of preset measurement instruments;
and 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 measuring instrument and the pose adjustment point coordinates corresponding to each preset measuring instrument.
It should be noted that, since the steps executed by the apparatus of this embodiment are the same as those of the foregoing method embodiment, specific implementation manners and technical effects that can be achieved of the apparatus of this embodiment may refer to the foregoing embodiment, and will not be repeated herein.
The foregoing description is only of the optional embodiments of the present invention, and is not intended to limit the scope of the invention, and all the equivalent structural changes made by the description of the present invention and the accompanying drawings or the direct/indirect application in other related technical fields are included in the scope of the invention.
Claims (8)
1. An automatic measurement method for attitude adjustment docking of aircraft components, which is characterized by being used for terminal equipment, comprising the following steps:
numbering a plurality of preset measuring instruments to obtain a plurality of instrument numbers;
measuring a plurality of gesture adjusting points by using a plurality of preset measuring instruments to obtain a plurality of gesture adjusting point coordinates of the gesture adjusting points, wherein one preset measuring instrument corresponds to one gesture adjusting point, and one preset measuring instrument corresponds to one gesture adjusting point coordinate;
creating a first mapping relation between the instrument number of each preset measuring instrument and the pose adjustment point coordinates of each preset measuring instrument;
acquiring pose point information of each preset measuring instrument based on the instrument number of each preset measuring instrument, the pose point coordinate of each preset measuring instrument and the first mapping relation;
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;
acquiring a plurality of instrument position information of a plurality of preset measuring instruments;
performing coordinate conversion by using the instrument position information of each preset measuring instrument and the corresponding gesture adjusting point coordinates of each preset measuring instrument to obtain final coordinates of a plurality of gesture adjusting points of the target aircraft component;
the step of acquiring the plurality of instrument position information of the plurality of preset measuring instruments comprises the following steps:
extracting the instrument number of each preset measuring instrument from the position information of each gesture adjusting point;
and determining the instrument position information corresponding to each preset measuring instrument in the address table by utilizing the second mapping relation based on the extracted instrument number of each preset measuring instrument.
2. The method of claim 1, wherein prior to the step of obtaining a plurality of instrument position information for a plurality of the predetermined measurement instruments, the method further comprises:
determining a set area of the target aircraft component, the set area having a plurality of preset measurement points;
setting a plurality of preset measuring instruments in the setting area;
determining a primary selected measuring point corresponding to each preset measuring instrument in a plurality of preset measuring points;
determining first measurement point position information of an initial measurement point of each preset measurement 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 predetermined measuring instruments using the first measurement point position information for each of the predetermined measuring instruments, the method further comprises:
determining reselection measuring points of each preset measuring instrument in a plurality of preset measuring points;
determining second measuring point position information of reselected measuring points 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 comprises the following steps:
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 the predetermined measuring instrument comprises a Leica AT901/LTD series laser tracker or an API laser tracker.
5. A method according to claim 3, wherein the preliminary selected measurement points of each of said predetermined measuring instruments comprise at least 3 and the reselection measurement points of each of said predetermined measuring instruments comprise at least 8.
6. An automatic measurement device for attitude adjustment docking of aircraft components, characterized in that it is used for terminal equipment, said device comprising:
the measuring module is used for numbering a plurality of preset measuring instruments to obtain a plurality of instrument numbers; measuring a plurality of gesture adjusting points by using a plurality of preset measuring instruments to obtain a plurality of gesture adjusting point coordinates of the gesture adjusting points, wherein one preset measuring instrument corresponds to one gesture adjusting point, and one preset measuring instrument corresponds to one gesture adjusting point coordinate; creating a first mapping relation between the instrument number of each preset measuring instrument and the pose adjustment point coordinates of each preset measuring instrument; acquiring pose point information of each preset measuring instrument based on the instrument number of each preset measuring instrument, the pose point coordinate of each preset measuring instrument and the first mapping relation;
the acquisition module is used for 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; acquiring a plurality of instrument position information of a plurality of preset measuring instruments; the step of acquiring the plurality of instrument position information of the plurality of preset measuring instruments comprises the following steps: extracting the instrument number of each preset measuring instrument from the position information of each gesture adjusting point; determining the instrument position information corresponding to each preset measuring instrument in the address table by utilizing the second mapping relation based on the extracted instrument number of each preset measuring instrument;
the obtaining module is used for carrying out coordinate conversion by utilizing the instrument position information of each preset measuring instrument and the corresponding gesture adjusting point coordinates of each preset measuring instrument to obtain the final coordinates of a plurality of gesture adjusting points of the target aircraft component.
7. A terminal device, characterized in that the terminal device comprises: the automatic measurement program for the attitude adjustment and docking of the aircraft component comprises a memory, a processor and an automatic measurement program which is stored in the memory and runs on the processor, wherein the automatic measurement program for the attitude adjustment and docking of the aircraft component realizes the steps of the automatic measurement method for the attitude adjustment and docking of the aircraft component according to any one of claims 1 to 5 when the automatic measurement program is executed by the processor.
8. A computer-readable storage medium, characterized in that the computer-readable storage medium has stored thereon an automatic measurement program for attitude adjustment docking of an aircraft component, which when executed by a processor, implements the steps of the automatic measurement method for attitude adjustment docking of an aircraft component according to any one of claims 1 to 5.
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