CN104457696B - Non-leveling type horizontal measuring method - Google Patents
Non-leveling type horizontal measuring method Download PDFInfo
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- CN104457696B CN104457696B CN201410743980.4A CN201410743980A CN104457696B CN 104457696 B CN104457696 B CN 104457696B CN 201410743980 A CN201410743980 A CN 201410743980A CN 104457696 B CN104457696 B CN 104457696B
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- Prior art keywords
- missile
- index point
- datum
- datum plane
- measurement
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C9/00—Measuring inclination, e.g. by clinometers, by levels
Abstract
The invention relates to a non-leveling type horizontal measuring method, belonging to the technical field of measurement. The non-leveling type horizontal measuring method comprises the following steps: installing a guided missile on a universal bracket, performing basic leveling by using two side missile wings as the criterion; selecting three datum points on a missile bay section, wherein the three datum points are respectively positioned on two measurement datum profiles of the missile bay section; establishing a datum plane for guided missile horizontal measurement, wherein the datum plane is on the missile shaft of the guide missile, and an included angle is formed between the X direction of the datum plane and the measurement platform; measuring the height data from a front mark point and a rear mark point on the missile wings of the guide missile to the measurement platform, calculating the included angle epsilon between the X direction of the wing profiles and the datum plane, and calculating the included angle beta between the wing profiles and the datum plane; and finally, obtaining the missile wing installation angle deviation gamma.
Description
Technical field
The present invention relates to a kind of non-leveling formula level measurement method, belong to field of measuring technique.
Background technology
On guided missile, the relative position between each part all has special technical requirements.They are with respect to theoretical installation site
The degree of accuracy will directly influence flying quality and the accuracy at target of guided missile.Visible horizon measurement is to ensure that guided missile docking is coordinated
The highly important operation in road.
And the three-level of guided missile safeguards the dismounting being related to guided missile.If having dismounted bay section and pneumatic during product repairing
By horizontal survey, face, then should determine whether its bay section and the installation accuracy in pneumatic face still meet technology after guided missile reconfigures
Index request.
At present, domestic main employing or traditional leveling formula level measurement method, this method in use,
Need strict leveling between bomb body measuring basis plane and reference platform, needs design special in guided munition mounting bracket
Levelling device, and need to can be only achieved leveling requirement by multiple manual adjustment repeatedly, operating efficiency is relatively low.
Content of the invention
In order to overcome drawbacks described above, it is an object of the invention to provide a kind of non-leveling formula level measurement method, during measurement
Need not tested guided missile leveling.
The principle of this measuring method is the height with height gauge datum mark to measuring table, determines datum plane and survey
The angle of amount platform, then measure other measurement points to the height of platform with height gauge, determine actual measurement plane and measuring table
Angle, finally calculate horizontal survey deviation data.
In order to realize above-mentioned technical purpose, the present invention adopts the following technical scheme that：
A kind of non-leveling formula level measurement method, it comprises the steps：
1. guided missile is arranged on universal mount, is defined by both sides missile wing and carries out basic leveling；
2., as measurement point, this 3 datum marks are located at missile bay respectively for 3 datum marks A, B, C on selection missile cabin
On two measuring basis sections of section, measure three datum marks to the high number of degrees of measuring table with high accuracy number height gauge
According to,、、, according to the coordinate of this 3 datum marks A, B, C,（,,）、（,,）、（,,
）, set up the datum plane of guided missile horizontal survey, on the bullet axle of guided missile, this datum plane is in X-direction and measurement for this datum plane
Platform angleFor：
；
3. measurement guided missile missile wing on front index point and rear index point to measuring table altitude information,With, front mark
The coordinate value of will point and rear index point is respectively（,,）、（,,）, calculate airfoil in X-direction and benchmark
The angle ε of plane：
AC is the range difference that index point and index point arrive measuring table, OA for index point and index point X-direction range difference；
4. calculate the angle β of airfoil and datum plane：
BD is the range difference that index point and index point arrive datum plane, OB for index point and index point X-direction range difference；
5. finally can obtain missile wing installation angular displacement γ is：.
Beneficial effects of the present invention：The present invention improves the efficiency of guided missile horizontal survey, need not set level guided missile, measure behaviour
Make simple, accuracy height, be with a wide range of applications.
Brief description
Fig. 1 is the schematic diagram of missile cabin in the present invention；
Fig. 2 is guided missile side-looking angle schematic diagram in the present invention；
Fig. 3 is the coordinate schematic diagram calculating angle in the present invention；
Fig. 4 is the structural representation of general level test desk in the present invention.
In Fig. 4：5 measuring tables, 9 height gauges, 10 data processor compositions, 11 missile wings, general before and after 12
Support.
Specific embodiment
Describe the present invention below in conjunction with the accompanying drawings：
A kind of non-leveling formula level measurement method is it is characterised in that it comprises the steps：
1. guided missile is arranged on universal mount 12, is defined by both sides missile wing 11 and carries out basic leveling；
2., as measurement point 1, this 3 datum marks are located at missile bay respectively for 3 datum marks A, B, C on selection missile cabin
On two measuring basis sections 2 of section, measure three datum marks to the high number of degrees of measuring table 5 with high accuracy number height gauge
According to,、、, according to the coordinate of this 3 datum marks A, B, C,（,,）、（,,）、（,,）,
Set up the datum plane 6 of guided missile horizontal survey, on the bullet axle 4 of guided missile, this datum plane 6 is in X-direction and survey for this datum plane
Amount platform 5 angleFor：
；
3. measure the front index point 7 on guided missile missile wing 11 and rear index point 8 arrive the altitude information of measuring table,With,
The coordinate value of front index point 7 and rear index point 8 is respectively（,,）、（,,）, calculate airfoil in X-direction
Angle ε with datum plane 6：
AC is the range difference that index point 7 and index point 8 arrive measuring table, and OA is for index point 7 and index point 8 in X-direction
Range difference；
4. calculate the angle β of airfoil and datum plane：
BD is the range difference that index point 7 and index point 8 arrive datum plane, and OB is for index point 7 and index point 8 in X-direction
Range difference；
5. finally can obtain missile wing installation angular displacement γ is：.
As Fig. 4：The present invention design level measurement method may be used in general level test desk, this horizontal survey platform by
Measuring table 5, in front and back universal mount 12, height gauge 9 data processor 10 form, and wherein, measuring table 5 is horizontal survey
Benchmark；Universal mount 12 is used for supporting in the measurements guided missile in front and back；Height gauge 9 is High Precision Automatic photoelectric measuring carpenters square, for right
The height of horizontal survey point measures；Data processor 10 is responsible for receiving and press process horizontal survey data, finally by beating
Measurement result is printed by print machine.
Claims (1)
1. a kind of non-leveling formula level measurement method is it is characterised in that it comprises the steps：
1. guided missile is arranged on universal mount（12）On, with both sides missile wing（11）It is defined and carry out basic leveling；
2. 3 datum marks A, B, C on selection missile cabin are as measurement point（1）, this 3 datum marks are respectively positioned at missile cabin
Two measuring basis sections（2）On, measure 3 datum marks to measuring table with high accuracy number height gauge（5）Height
Data、、, according to the coordinate of this 3 datum marks A, B, C（,,）、（,,）、（,,）,
Set up the datum plane of guided missile horizontal survey（6）, this datum plane is in the bullet axle of guided missile（4）On, this datum plane（6）In X side
To with measuring table（5）AngleFor：
；
3. measure guided missile missile wing（11）On front index point（7）With rear index point（8）Altitude information to measuring tableWith,
Front index point（7）With rear index point（8）Coordinate value be respectively（,,）、（,,）, calculate airfoil in X
Direction and datum plane（6）Angle ε：
AC is front index point（7）With rear index point（8）To the range difference of measuring table, OA is front index point（7）With rear index point
（8）Range difference in X-direction；
4. calculate the angle β of airfoil and datum plane：
BD is front index point（7）With rear index point（8）To the range difference of datum plane, OB is front index point（7）With rear index point
（8）Range difference in X-direction；
5. finally can obtain missile wing installation angular displacement γ is：.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410743980.4A CN104457696B (en) | 2014-12-09 | 2014-12-09 | Non-leveling type horizontal measuring method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410743980.4A CN104457696B (en) | 2014-12-09 | 2014-12-09 | Non-leveling type horizontal measuring method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104457696A CN104457696A (en) | 2015-03-25 |
| CN104457696B true CN104457696B (en) | 2017-02-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410743980.4A Active CN104457696B (en) | 2014-12-09 | 2014-12-09 | Non-leveling type horizontal measuring method |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105021094B (en) * | 2015-07-15 | 2017-04-26 | 江西洪都航空工业集团有限责任公司 | Small-aspect-ratio missile horizontal measuring method |
| CN106595616A (en) * | 2016-11-24 | 2017-04-26 | 江西洪都航空工业集团有限责任公司 | Method for horizontal measurement of guided missile with laser tracker |
| CN107102315B (en) * | 2017-04-24 | 2019-11-12 | 重庆钢铁(集团)有限责任公司 | A kind of laser range finder calibration method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5145011B2 (en) * | 2007-10-26 | 2013-02-13 | 株式会社トプコン | Laser survey system |
| FI121399B (en) * | 2007-11-26 | 2010-10-29 | Autorobot Finland | Procedure and measurement tool for vehicle measurement |
| CN202361986U (en) * | 2011-12-06 | 2012-08-01 | 江西洪都航空工业集团有限责任公司 | Horizontal laser measuring system for airplanes |
| CN103759708B (en) * | 2013-12-31 | 2015-10-07 | 北京金风科创风电设备有限公司 | The measuring method of the degree of tilt of pylon |
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| Publication number | Publication date |
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| CN104457696A (en) | 2015-03-25 |
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