CN111175029A - Target calibration instrument and aircraft target calibration method - Google Patents

Target calibration instrument and aircraft target calibration method Download PDF

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Publication number
CN111175029A
CN111175029A CN202010110825.4A CN202010110825A CN111175029A CN 111175029 A CN111175029 A CN 111175029A CN 202010110825 A CN202010110825 A CN 202010110825A CN 111175029 A CN111175029 A CN 111175029A
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China
Prior art keywords
aircraft
instrument
boresight
axis
measurement instrument
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Pending
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CN202010110825.4A
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Chinese (zh)
Inventor
王辉
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Beijing Huiwon Navigation Technology Development Co Ltd
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Beijing Huiwon Navigation Technology Development Co Ltd
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Priority to CN202010110825.4A priority Critical patent/CN111175029A/en
Publication of CN111175029A publication Critical patent/CN111175029A/en
Pending legal-status Critical Current

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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M11/00Testing of optical apparatus; Testing structures by optical methods not otherwise provided for
    • G01M11/02Testing optical properties
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01CMEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C21/00Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
    • G01C21/10Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration
    • G01C21/12Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning
    • G01C21/16Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M11/00Testing of optical apparatus; Testing structures by optical methods not otherwise provided for
    • G01M11/02Testing optical properties
    • G01M11/0207Details of measuring devices

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Automation & Control Theory (AREA)
  • Optical Radar Systems And Details Thereof (AREA)

Abstract

The application relates to a boresight instrument and an aircraft boresight method, which belong to the technical field of equipment calibration, and the boresight instrument comprises: the device comprises an inertial measurement instrument, a light collimation measurement instrument and a plane reflector, wherein the inertial measurement instrument and the light collimation measurement instrument are parallel to each other in structure axis. The heavy work of needing to push the plane in the existing scheme is saved, the requirements of calibration errors, fields and the like are reduced, and the target calibration precision and efficiency are improved.

Description

Target calibration instrument and aircraft target calibration method
Technical Field
The application relates to a target calibration instrument and an aircraft target calibration method, and belongs to the technical field of equipment calibration.
Background
The traditional target correction method is a method generally adopted by the conventional domestic airplane target correction, the method needs to keep the airplane (helicopter) horizontal, a target plate needs to be erected right in front of the airplane (helicopter), the site needs to be opened, the adjustment difficulty of the position and the verticality of the target plate is high, the human error is large, and the measurement accuracy and the measurement efficiency are not high. The time and the labor are consumed, the site is limited, and the target correcting work cannot be finished under certain conditions.
Disclosure of Invention
The application provides a target calibration instrument and an aircraft target calibration method, which can solve the problems in the existing scheme. The application provides the following technical scheme:
in a first aspect, there is provided a boresight instrument, comprising: the device comprises an inertial measurement instrument, a light collimation measurement instrument and a plane reflector, wherein the inertial measurement instrument and the light collimation measurement instrument are parallel to each other in structure axis.
Optionally, there are one or more of the planar mirrors.
Optionally, the plane mirror is configured to be mounted on a measured point of the aircraft, where the measured point includes a longitudinal axis of the aircraft, a weapon axis of the aircraft, and an aiming axis of the aircraft.
Optionally, the plane mirror is installed after the measured point, and a normal line of the plane mirror is parallel to an axis of the measured point.
Optionally, the plane mirror is installed behind the measured point, and the light collimation measuring instrument is aligned with the plane mirror during measurement.
In a second aspect, there is provided an aircraft boresight method for use in a boresight apparatus according to the first aspect, the method comprising:
obtaining measurement results of the inertial measurement instrument and the light collimation measurement instrument when the plane mirror is installed at each measured point of the aircraft, wherein the measured points comprise an aircraft longitudinal axis, an aircraft weapon axis and an aircraft aiming axis;
for each measured point, adding the measurement result of the inertial measurement instrument and the measurement result of the light collimation measurement instrument to obtain the spatial attitude data of the measured point;
and comparing the spatial attitude data of the weapon shaft and the aiming shaft of the aircraft with the spatial attitude data of the longitudinal shaft of the aircraft to obtain a boresight error.
The beneficial effect of this application lies in:
through setting up the school target appearance, the school target appearance includes: the device comprises an inertial measuring instrument, a light collimation measuring instrument and a plane reflector, wherein the inertial measuring instrument and the light collimation measuring instrument are parallel to each other in structure axis; when the target is calibrated, only the plane reflector is required to be arranged at a measured point, so that the heavy work of pushing an airplane in the prior art is omitted, the requirements of calibration errors, fields and the like are reduced, and the target calibration precision and efficiency are improved.
The foregoing description is only an overview of the technical solutions of the present application, and in order to make the technical solutions of the present application more clear and clear, and to implement the technical solutions according to the content of the description, the following detailed description is made with reference to the preferred embodiments of the present application and the accompanying drawings.
Drawings
FIG. 1 is a schematic view of the internal structure of the target calibration instrument according to the present invention.
FIG. 2 is another schematic diagram of the structure of the target calibrating apparatus according to the present invention.
Fig. 3 is a schematic view of a possible arrangement of the flat mirror according to the invention after installation in an aircraft.
FIG. 4 is a method flow diagram of an aircraft boresight method of the present invention.
Detailed Description
The following detailed description of embodiments of the present application will be described in conjunction with the accompanying drawings and examples. The following examples are intended to illustrate the present application but are not intended to limit the scope of the present application.
Referring to fig. 1, a schematic structural diagram of a boresight instrument according to an embodiment of the present application is shown, and as shown in fig. 1, the boresight instrument includes: the device comprises an inertial measurement instrument 11, a light collimation measurement instrument 12 and a plane reflector 13, wherein the inertial measurement instrument 11 and the light collimation measurement instrument 12 are parallel to each other in structure axis.
The inertial measurement unit 11 is parallel to the optical collimator 12 in terms of structural axes, so that the inertial measurement unit 11 can measure spatial attitude data of the optical collimator in real time.
In addition, one or more plane mirrors 13 in the boresight instrument can be provided. That is, in the calibration of the target, different measurement points can be measured by the plurality of plane mirrors 13, respectively. Of course, only one plane mirror 13 may be used for actual target calibration, and the other plane mirrors 13 may be used as alternatives.
Optionally, when the target calibration is required, the plane mirror 13 is mounted on the measured point of the aircraft through a tool, and the normal of the plane mirror 13 is parallel to the axis of the measured point. Wherein the measured points include an aircraft longitudinal axis, an aircraft weapon axis, an aircraft aiming axis. Therefore, when the target is calibrated, after the light collimation measuring instrument of the target calibrating instrument is aligned to the plane reflector, the parallel light emitted by the light collimation measuring instrument is reflected back to the light collimation measuring instrument through the plane reflector and is imaged on the light collimation measuring instrument, namely the light collimation measuring instrument can measure the included angle between the axis of the light collimation measuring instrument and the normal of the plane reflector.
Optionally, the method of finding the measured point of the aircraft is as follows:
aircraft longitudinal axis: a plane reflector is installed on the airplane through a tool, and the normal line of the plane reflector is parallel to the longitudinal axis of the airplane (the interface is arranged on the airplane), so that the normal line of the plane reflector can represent the longitudinal axis of the airplane.
Weapon shaft of aircraft: the plane mirror is installed on each weapon by a tool, the normal line of the plane mirror is consistent with the emission axis of the weapon, and thus, the normal line of the plane mirror represents the emission axis of the weapon.
Aiming axis of the aircraft: aiming devices (such as photoelectric pod, photoelectric radar and the like) are provided with a laser range finder which can emit a laser beam, the direction of the laser beam is the direction of an aiming axis, and the direction of the laser beam can be measured by using the device.
Referring to fig. 3, a possible schematic view of the plane mirror 13 mounted on the point to be measured is shown.
Referring to fig. 2, the boresight calibration apparatus may further include a power supply module, a computer board, a display screen, a satellite positioning module, and other components used when the aircraft is in normal operation, which is not described herein again.
Through setting up the school target appearance, the school target appearance includes: the device comprises an inertial measuring instrument, a light collimation measuring instrument and a plane reflector, wherein the inertial measuring instrument and the light collimation measuring instrument are parallel to each other in structure axis; when the target is calibrated, only the plane reflector is required to be arranged at a measured point, so that the heavy work of pushing an airplane in the prior art is omitted, the requirements of calibration errors, fields and the like are reduced, and the target calibration precision and efficiency are improved.
Referring to fig. 4, a flowchart of a method of an aircraft boresight method according to an embodiment of the present application is shown, and as shown in fig. 4, the aircraft boresight method includes:
step 401, obtaining measurement results of the inertial measurement unit and the light collimation measurement unit when the plane mirror is installed at each measured point of the aircraft, where the measured points include a longitudinal axis of the aircraft, a weapon axis of the aircraft, and an aiming axis of the aircraft;
step 402, adding the measurement result of the inertial measurement instrument and the measurement result of the light collimation measurement instrument to each measured point to obtain the spatial attitude data of the measured point;
and 403, comparing the spatial attitude data of the weapon axis and the aiming axis of the aircraft with the spatial attitude data of the longitudinal axis of the aircraft to obtain a boresight error.
When the plane mirror is installed at each measured point of the aircraft, the measurement results of the inertial measurement instrument and the light collimation measurement instrument are obtained, wherein the measured points comprise the longitudinal axis of the aircraft, the weapon axis of the aircraft and the aiming axis of the aircraft; for each measured point, adding the measurement result of the inertial measurement instrument and the measurement result of the light collimation measurement instrument to obtain the spatial attitude data of the measured point; and comparing the spatial attitude data of the weapon shaft and the aiming shaft of the aircraft with the spatial attitude data of the longitudinal shaft of the aircraft to obtain a boresight error. The heavy work of needing to push the plane in the existing scheme is saved, the requirements of calibration errors, fields and the like are reduced, and the target calibration precision and efficiency are improved.
The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.

Claims (6)

1. A boresight instrument, characterized in that, boresight instrument includes: the device comprises an inertial measurement instrument, a light collimation measurement instrument and a plane reflector, wherein the inertial measurement instrument and the light collimation measurement instrument are parallel to each other in structure axis.
2. The boresight instrument of claim 1, wherein the planar mirror is one or more.
3. The boresight instrument of claim 1, wherein the plane mirror is configured to be mounted on a measured point of the aircraft, the measured point including a longitudinal axis of the aircraft, a weapon axis of the aircraft, and an aiming axis of the aircraft.
4. The boresight instrument of claim 3, wherein the plane mirror is installed behind a measured point, and a normal line of the plane mirror is kept parallel to an axis of the measured point.
5. A boresight instrument according to claim 3 or claim 4, wherein the plane mirror is mounted behind the point to be measured, the light collimator being aligned with the plane mirror during measurement.
6. A method of boresight of an aircraft, the method being used in a boresight apparatus according to any one of claims 1 to 5, the method comprising:
obtaining measurement results of the inertial measurement instrument and the light collimation measurement instrument when the plane mirror is installed at each measured point of the aircraft, wherein the measured points comprise an aircraft longitudinal axis, an aircraft weapon axis and an aircraft aiming axis;
for each measured point, adding the measurement result of the inertial measurement instrument and the measurement result of the light collimation measurement instrument to obtain the spatial attitude data of the measured point;
and comparing the spatial attitude data of the weapon shaft and the aiming shaft of the aircraft with the spatial attitude data of the longitudinal shaft of the aircraft to obtain a boresight error.
CN202010110825.4A 2020-02-24 2020-02-24 Target calibration instrument and aircraft target calibration method Pending CN111175029A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113790739A (en) * 2021-09-17 2021-12-14 无锡市星迪仪器有限公司 Device and method for calibrating aerial gun space attitude

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Publication number Priority date Publication date Assignee Title
RU94692U1 (en) * 2010-03-01 2010-05-27 Федеральное государственное унитарное предприятие "Производственное объединение "Уральский оптико-механический завод" имени Э.С. Яламова" DEVICE FOR ADJUSTING THE VISIOR SYSTEM OF THE OPTICAL-ELECTRONIC INSTRUMENT ON THE AIRCRAFT
CN102060105A (en) * 2010-11-23 2011-05-18 中国兵器工业第二〇五研究所 Course calibration device with tilt compensation
CN106289234A (en) * 2016-08-10 2017-01-04 江苏北方湖光光电有限公司 A kind of device and method transmitting aircraft longitudinal axis attitude angle in inertia boresight
CN107727118A (en) * 2017-11-28 2018-02-23 长春理工大学 GNC subsystem equipment attitude measurement system scaling method in Large Scale Space Vehicle
CN211784204U (en) * 2020-02-24 2020-10-27 北京辉嫄通航科技发展有限公司 Target correcting instrument

Patent Citations (5)

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Publication number Priority date Publication date Assignee Title
RU94692U1 (en) * 2010-03-01 2010-05-27 Федеральное государственное унитарное предприятие "Производственное объединение "Уральский оптико-механический завод" имени Э.С. Яламова" DEVICE FOR ADJUSTING THE VISIOR SYSTEM OF THE OPTICAL-ELECTRONIC INSTRUMENT ON THE AIRCRAFT
CN102060105A (en) * 2010-11-23 2011-05-18 中国兵器工业第二〇五研究所 Course calibration device with tilt compensation
CN106289234A (en) * 2016-08-10 2017-01-04 江苏北方湖光光电有限公司 A kind of device and method transmitting aircraft longitudinal axis attitude angle in inertia boresight
CN107727118A (en) * 2017-11-28 2018-02-23 长春理工大学 GNC subsystem equipment attitude measurement system scaling method in Large Scale Space Vehicle
CN211784204U (en) * 2020-02-24 2020-10-27 北京辉嫄通航科技发展有限公司 Target correcting instrument

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Title
赵长辉;段洪伟;李波;曹巍;李伟;包湘珲;: "飞机校靶装置技术的发展", 航空精密制造技术, vol. 53, no. 02, 15 April 2017 (2017-04-15), pages 46 - 49 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113790739A (en) * 2021-09-17 2021-12-14 无锡市星迪仪器有限公司 Device and method for calibrating aerial gun space attitude
CN113790739B (en) * 2021-09-17 2024-05-24 无锡市星迪仪器有限公司 Space attitude calibration device and calibration method for aircraft gun

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