CN115638806B - Horizontal calibration device and calibration method for aircraft inertial navigation system - Google Patents
Horizontal calibration device and calibration method for aircraft inertial navigation system Download PDFInfo
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- CN115638806B CN115638806B CN202211162312.3A CN202211162312A CN115638806B CN 115638806 B CN115638806 B CN 115638806B CN 202211162312 A CN202211162312 A CN 202211162312A CN 115638806 B CN115638806 B CN 115638806B
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000006073 displacement reaction Methods 0.000 claims description 11
- 239000011324 bead Substances 0.000 claims description 6
- 239000010687 lubricating oil Substances 0.000 claims description 2
- 239000003921 oil Substances 0.000 claims description 2
- 238000009434 installation Methods 0.000 description 9
- 238000005259 measurement Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000003028 elevating effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 230000001360 synchronised effect Effects 0.000 description 1
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Abstract
The invention belongs to the technical field of aviation assembly, and relates to a horizontal calibration device and a calibration method of an aircraft inertial navigation system. When the device is used, the micro-cylinders on the three adjusting and measuring devices are adjusted to change the angles of the top plate and the horizontal plane, so that the adjustment of the plane formed by the datum points is realized, the accurate adjustment quantity is read out through the scales of the micro-cylinders, and accurate data are provided for the adjustment of the later aircraft inertial navigation system.
Description
Technical Field
The invention belongs to the technical field of aviation assembly, and relates to a device for rapidly determining the accurate displacement size of a datum point after horizontal leveling of an aircraft inertial navigation system.
Background
When the aircraft inertial navigation system is installed, the aircraft inertial navigation system needs to be parallel to the horizontal plane, the general technological mode is that 3 datum points are selected, the heights of the three datum points are adjusted, the plane formed by the 3 datum points is parallel to the horizontal plane, and then the state is fixed by a fixing device after the height value is determined. It is important how quickly and accurately the height value is determined. The main technological method at present is to use the adjustable support to adjust to the demand state first, then use caliper or other measuring tools to measure, influence the accuracy that both influences work efficiency and also influences the measurement.
In the technology of installing and adjusting an inertial navigation system of an aircraft, patent CN209870765U proposes an inertial navigation device installation and calibration device for the aircraft, which comprises an aircraft installation table, a fixed seat, a micro hydraulic cylinder and a support installation plate; the aircraft mounting table is provided with a plurality of fixing seats, each fixing seat is provided with a miniature hydraulic cylinder, and piston rods of the miniature hydraulic cylinders are connected to the bottom of the support mounting plate; the inertial navigator is arranged on the supporting mounting plate; the bottom of the supporting mounting plate is provided with a plurality of ultrasonic distance meters; one side of the fixed seat is provided with a vertical plate, the vertical plate is provided with an infrared receiver, and one side of the inertial navigator opposite to the vertical plate is provided with an infrared generator which is used for receiving infrared signals emitted by the infrared generator; the device also comprises a control box, and the infrared receiver, the ultrasonic distance meter and the miniature hydraulic cylinder are all in communication connection with the control box. Although the device can be used for installing and adjusting an aircraft inertial navigation system, the device has a complex structure, needs to be matched with other auxiliary mechanisms, has high requirements on the field, and has great difficulty in realizing the method in some external field environments.
Disclosure of Invention
Technical problem to be solved
The method realizes synchronous adjustment and reading of the height of the datum point when the horizontal state of the inertial navigation system of the airplane is adjusted, the height value can be quickly read after the adjustment is in place, and the read height value is accurate to 0.05mm.
Technical proposal
The invention provides a horizontal calibration device of an aircraft inertial navigation system, which consists of a top plate, an adjusting and measuring device, a bottom plate and a top rod, wherein the adjusting and measuring device comprises 3 groups which are respectively and correspondingly arranged at three datum points, are connected with the top plate through springs, are overlapped with the triangle center formed by the datum points and are supported by the top rod, and the adjusting and measuring device and the top rod are both fixed on the bottom plate; when in use, the micro-cylinders on the three adjusting and measuring devices are adjusted to change the angles of the top plate and the horizontal plane, so that the adjustment of the plane formed by the datum points is realized, and the accurate adjustment quantity is read out through the scales of the micro-cylinders.
Further, the adjusting and measuring device consists of a sliding block, a jacking column, a micro-cylinder, a sliding rail and a spring, wherein the sliding block and the jacking column are arranged in the sliding rail, the micro-cylinder is arranged on a bottom plate through a mounting support, and the sliding block is connected with the mounting support of the micro-cylinder through the spring to keep a jacking state; the differential head of the differential cylinder is contacted with the rear part of the sliding block, and the front part of the sliding block is matched with one end of the jacking column; and adjusting the micro-cylinder, and pushing the sliding block to move by the micro-head so as to push the jacking column matched with the sliding block to move.
Further, the sliding block is in a wedge shape; one end matched with the top column is an inclined plane with a certain inclination angle.
Furthermore, one end of the jacking column matched with the sliding block is of a triangular structure, and the other end of the jacking column is of a ball head structure.
Furthermore, in order to facilitate the sliding of the sliding block and the jacking column in the sliding rail, an oil groove is arranged at the contact position of the sliding rail and the jacking column, and a little lubricating oil can be added during use.
Further, the sliding block is contacted with an inclined plane at 45 degrees below the jacking column, the inclined plane is kept smooth, and the roughness is not more than 0.8.
Further, the ejector rod consists of a bottom rod, a spring and a nail bead, wherein the bottom rod is fixed in the bottom plate, the upper end of the bottom rod is provided with a groove, and the nail bead is embedded into the groove of the bottom rod after pressing the spring.
Further, the ball head at the top end of the nail bead is embedded into the top plate and kept in a propped state through a spring.
The invention also provides a horizontal calibration method of the aircraft inertial navigation system, which comprises the following steps:
step S1, according to three preset padding positions on the mounting surface of the inertial navigation system platform, placing a horizontal calibration device in the center of the padding positions, so that three datum points of the calibration device correspond to the three padding positions respectively.
And S2, placing the level measuring instrument at the center of a top plate of the calibrating device, adjusting the three micro-cylinders of the calibrating device until the level measuring instrument displays that the level position is reached, and then reading the displacement sizes of the three micro-cylinders.
And S3, removing the calibrating device, respectively heightening the displacement sizes read out by the corresponding micro-cylinders at three padding positions of the inertial navigation system platform, directly placing the level measuring instrument on the inertial navigation system platform, checking whether the level is still displayed as the level, and if the displacement sizes read out by the micro-cylinders are accurate enough, ensuring that the level is still displayed at the moment, then completing the calibration of the inertial navigation system platform. If the level is not displayed, the previous steps are repeated to obtain a new adjustment.
Beneficial technical effects
The invention provides a device, which can level a plane formed by 3 datum points through simple and convenient operation in a relatively narrow working space, adjust a vertical jacking column through a horizontally placed micro-cylinder in a 45-degree angle contact surface mode, has the convenience and accuracy of operation, enables the whole device to form a whole through spring connection, keeps a fastening state, and enables the micro-cylinder to be more accurate in reading by selecting 0.02mm precision.
The calibration of the plane inertial navigation system platform takes three points as a principle, three fixed elevating points are preset, and the installation surface of the inertial navigation system platform can be simulated and projected on the top plate of the calibration device as long as three datum points of the calibration device correspond to the positions of the three elevating points. At this time, the top plate is adjusted to be horizontal by adjusting the heights of the three datum points, and then the height displacement value of the top plate is accurately heightened at the three heightened pad positions of the through guide system platform, so that the system platform is also horizontal; the horizontal calibration device for the aircraft inertial navigation system is simple in structure, can level the platform of the aircraft inertial navigation system without depending on other auxiliary optical instruments, breaks through the conventional leveling thought in the field, has a large popularization value in the field test, and is particularly suitable for field-limited field environments.
Drawings
The invention comprises 5 drawings, the drawings are described as follows:
FIG. 1 is a top view of the device;
FIG. 2 is a block diagram of an adjustment measurement device;
FIG. 3 is a cross-sectional view of an adjustment measurement device;
FIG. 4 is a block diagram of a center post rod and top plate;
FIG. 5 is a schematic view of the angle and displacement between the parts of FIGS. 2a and 2 b;
wherein: 1. the device comprises a top plate, an adjusting and measuring device, a sliding block, a top column, a micro cylinder, a sliding rail, a first spring, a bottom plate, a top rod, a bottom rod, a second spring and a nail bead.
Detailed Description
The invention provides a horizontal calibration device of an aircraft inertial navigation system, which is described in detail by referring to the accompanying drawings:
referring to fig. 1, in the implementation of the present invention, a horizontal calibration device for an aircraft inertial navigation system is designed, three reference points are correspondingly designed according to a mounting seat of the aircraft inertial navigation system, three adjustment measuring devices 2 are arranged at the positions of the three determined reference points, a top plate 1 is arranged above the adjustment measuring devices, and the top plate 1 is connected with the adjustment measuring devices 2 through a first spring 2e, so that a tight propping state is maintained. The three adjusting and measuring devices 2 are fixedly arranged on the bottom plate 3, in order to ensure that the initial state of the mounting surface of the through guide system can be accurately projected on the top plate of the calibrating device in the use process, and the parallelism between the upper surface of the top plate and the lower surface of the bottom plate is not more than 0.1 when the adjusting and measuring devices are in the initial position.
The top of the device is provided with a top plate for placing a level measuring instrument, 3 reference points below the top plate are respectively provided with 3 adjusting and measuring devices, the adjusting and measuring devices are fixedly arranged on a bottom plate, and the circle center of the top plate is placed on the triangle center formed by the three reference points so as to support the circle center by the bottom plate. The top plate is connected with the adjusting and measuring device through a spring, and the top plate is kept in a tight-pushing state.
The center of the top plate is arranged on the triangle center formed by the three datum points, and is supported by the ejector rod 4, the bottom end of the ejector rod is fixed on the bottom plate, the top end of the ejector rod is in hemispherical assembly with the top plate, and the ejector rod is kept in a propping state through the second spring 4b.
The adjusting and measuring device consists of a sliding block 2a, a top column 2b, a micro cylinder 2c, a sliding rail 2d and a first spring 2e, wherein the top column 2d is perpendicular to the moving direction of the sliding block 2a, the lower 45-degree inclined surface is contacted with the sliding block, the rear part of the sliding block 2a is contacted with the micro cylinder 2c, and the sliding block is connected with a micro cylinder support through the first spring 2e to keep a propped state.
When the device is used, a horizontal measuring instrument is placed on the top plate, then the differential cylinders of the three adjusting and measuring devices are respectively adjusted, the differential cylinders are pushed to move forwards by the sliding block, and meanwhile, the jacking columns are also pushed by the sliding block to move vertically upwards, so that the angle between the top plate and the horizontal direction is adjusted until the instrument is displayed and leveled, the numerical values of the 3 differential cylinders are read at the moment, and the displacement quantity is determined.
As shown in FIG. 5, under the condition of 45-degree contact inclined plane, the ratio of the horizontal displacement of the sliding block to the vertical displacement of the jacking column can be 1:1, and other angles can be selected in practical application, and the same ratio can be converted.
The initial installation of the platform of the inertial navigation system of the aircraft needs to enable the installation surface of the platform to be consistent with the theoretical horizontal plane, generally adopts the principle that one plane is determined by three points, establishes three adjustment positions, corresponds three reference points of a calibration device to the three adjustment positions, enables the installation surface of the initial platform to be simulated and projected on the calibration device, simulates accurate adjustment amounts required by the three adjustment positions through the calibration device, then enables the adjustment amounts to act on the installation surface of the platform, and finally achieves the installation requirement of the platform of the inertial navigation system.
The above detailed description or examples are only for illustrating the technical scheme of the present invention, and are not limiting, and the detailed description is not to be taken as conventional technical means or common general knowledge in the art; those of ordinary skill in the art will appreciate that: based on the design concept of the present application, the technical solutions described in the foregoing embodiments should be adaptively modified, or some or all of the technical features thereof may be equivalently replaced, where these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present invention.
Claims (5)
1. The horizontal calibration device of the aircraft inertial navigation system is characterized by comprising a top plate, an adjusting and measuring device, a bottom plate and a top rod, wherein the adjusting and measuring device comprises 3 groups which are respectively and correspondingly arranged at three datum points, are connected with the top plate through springs, are overlapped with the triangle center formed by the datum points and are supported by the top rod, and the adjusting and measuring device and the top rod are fixed on the bottom plate; when the device is used, the micro-cylinders on the three adjustment measuring devices are adjusted to change the angles of the top plate and the horizontal plane, so that the adjustment of the plane formed by the datum points is realized, and the accurate adjustment quantity is read out through the scales of the micro-cylinders;
the adjusting and measuring device consists of a sliding block, a jacking column, a differential cylinder, a sliding rail and a spring, wherein the sliding block and the jacking column are arranged in the sliding rail, the differential cylinder is arranged on a bottom plate through a mounting support, and the sliding block is connected with the mounting support of the differential cylinder through the spring to keep a jacking state; the differential head of the differential cylinder is contacted with the rear part of the sliding block, and the front part of the sliding block is matched with one end of the jacking column; adjusting the micro-cylinder, and pushing the sliding block to move by the micro-head so as to push the jacking column matched with the sliding block to move; the sliding block is in a wedge shape; one end matched with the top column is an inclined plane with a certain inclination angle; one end of the jacking column, which is matched with the sliding block, is of a triangular structure, and the other end of the jacking column is of a ball head structure; the ejector rod consists of a bottom rod, a spring and a nail bead, wherein the bottom rod is fixed in the bottom plate, the upper end of the bottom rod is provided with a groove, and the nail bead is embedded into the groove of the bottom rod after pressing the spring.
2. The horizontal calibration device for an aircraft inertial navigation system according to claim 1, wherein an oil groove is arranged at the contact position of the sliding rail and the top column, and a small amount of lubricating oil can be added during use.
3. The horizontal alignment device of an aircraft inertial navigation system of claim 1, wherein the slider is in contact with the top post at a 45 degree incline below the top post, the incline remaining smooth with a roughness of no more than 0.8.
4. The horizontal calibration device for an aircraft inertial navigation system according to claim 1, wherein the ball head at the top end of the nail is embedded in the top plate and kept in a tightly-pressed state by a spring.
5. An aircraft inertial navigation system horizontal calibration method, characterized in that the calibration method adopts the aircraft inertial navigation system horizontal calibration device according to any one of claims 1-4, and the calibration method comprises the following steps:
step S1, according to three preset padding positions on a platform mounting surface of an inertial navigation system, placing a horizontal calibration device in the center of the padding positions, so that three datum points of the calibration device correspond to the three padding positions respectively;
s2, placing a horizontal measuring instrument in the center of a top plate of the calibrating device, adjusting three differential cylinders of the calibrating device until the horizontal measuring instrument displays that the horizontal position is reached, and then reading the displacement sizes of the three differential cylinders;
s3, removing the calibrating device, respectively heightening the displacement size read out by the corresponding micro-cylinder at three padding positions of the inertial navigation system platform, and then directly placing a level measuring instrument on the inertial navigation system platform to check whether the level measuring instrument is still displayed as level; if the level is not displayed, the previous steps are repeated to obtain a new adjustment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211162312.3A CN115638806B (en) | 2022-09-23 | 2022-09-23 | Horizontal calibration device and calibration method for aircraft inertial navigation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211162312.3A CN115638806B (en) | 2022-09-23 | 2022-09-23 | Horizontal calibration device and calibration method for aircraft inertial navigation system |
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| Publication Number | Publication Date |
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| CN115638806A CN115638806A (en) | 2023-01-24 |
| CN115638806B true CN115638806B (en) | 2024-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202211162312.3A Active CN115638806B (en) | 2022-09-23 | 2022-09-23 | Horizontal calibration device and calibration method for aircraft inertial navigation system |
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| WO2022160559A1 (en) * | 2021-01-26 | 2022-08-04 | 武汉工程大学 | Intelligent alignment system and method for aircraft wing |
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| CN104422419A (en) * | 2013-08-23 | 2015-03-18 | 怀集登云汽配股份有限公司 | Outer diameter V-shaped measurement method and V-shaped gauge of valve retainer outer diameter |
| CN110313235B (en) * | 2015-07-17 | 2017-11-10 | 中国人民解放军第五七〇六工厂 | The adjustment method of airplane inertial navigation installation calibration apparatus based on gyroscope north searching instrument |
| KR20190116748A (en) * | 2018-04-05 | 2019-10-15 | (주)비씨디이엔씨 | Foldable landing gear and Vibration-free gimbal device having it |
| CN211452365U (en) * | 2020-01-09 | 2020-09-08 | 河南省焦作地质勘察设计有限公司 | Quick calibrating device of survey and drawing centering rod circle level ware |
| WO2021245175A1 (en) * | 2020-06-05 | 2021-12-09 | Macgregor Norway As | Pile installation facility and methods thereof |
| WO2022160559A1 (en) * | 2021-01-26 | 2022-08-04 | 武汉工程大学 | Intelligent alignment system and method for aircraft wing |
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