CN105021094B - Small-aspect-ratio missile horizontal measuring method - Google Patents
Small-aspect-ratio missile horizontal measuring method Download PDFInfo
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- CN105021094B CN105021094B CN201510412543.9A CN201510412543A CN105021094B CN 105021094 B CN105021094 B CN 105021094B CN 201510412543 A CN201510412543 A CN 201510412543A CN 105021094 B CN105021094 B CN 105021094B
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Abstract
The invention discloses a small-aspect-ratio missile horizontal measuring method. After a missile body is leveled the first time, a reference platform serves as the only reference for all measuring points on a missile; a height gauge is used for measuring the heights of all horizontal measuring points to the reference platform, rotation and leveling of the missile body are not needed during the process, and horizontal measuring deviation data are obtained by calculating the height difference between the measuring points. Measuring errors caused by frequent manual leveling operation are reduced, and the missile horizontal measuring precision and efficiency are improved; meanwhile, a missile overturning support and other equipment are reduced, so that operation is convenient, and cost is lowered.
Description
Technical field
The present invention relates to a kind of guided missile level measurement method, more particularly to a kind of low aspect ratio guided missile level measurement method.
Belong to guided missile fields of measurement.
Background technology
Relative position on guided missile between each part has special technical requirements.They are relative to theoretical installation site
Accuracy will directly influence the control performance and flying quality of guided missile.Visible horizon measurement is ensure guided missile installation accuracy one
The highly important operation in road.
And the three-level of guided missile safeguards the dismounting for being related to guided missile.If bay section and pneumatic has been dismounted 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 is reconfigured
Index request.
At present, domestic main adopting or traditional multiple rotary guided missile, the level measurement method of multiple leveling, this
Method in use to leveling between bomb body measuring basiss plane and reference platform after, bomb body measurement is right in order to measure after terminating
Claim the point on pneumatic face rotate to guided missile, need to just re-start bomb body leveling, such guided missile often rotates once, it is necessary to
Bomb body leveling work is carried out, so as to increased artificial measurement error, operating efficiency is relatively low.
Accordingly, it is desirable to provide a kind of new technical scheme is solving the above problems.
The content of the invention
The technical problem to be solved in the invention is to provide a kind of low aspect ratio guided missile level measurement method.Only need during measurement
Tested guided missile one-time leveling, you can pneumatic planar survey on bullet is finished.
To solve the technical problem of the present invention, the technical solution used in the present invention is：
A kind of low aspect ratio guided missile level measurement method, after bomb body first leveling, reference platform is owned as on bullet
The unique reference of measurement point, measures each horizontal survey point to the height of reference platform with height gauge, and centre need not carry out bomb body rotation
Turn and leveling, horizontal survey deviation data is calculated using the difference in height between each measurement point.
A kind of low aspect ratio guided missile level measurement method, it comprises the following steps：
A, by guided missile be arranged on universal stand on, being defined by bomb body left and right sides horizontal survey point 1 and 1' carries out leveling；
B, all measurement points 3,4,5 for being measured on 4 missile wings successively arrive the altitude information of reference platform,、With；
C, according to missile wing theory profile can be calculated a little 3 and put 5 theoretical level lateral distance, theoretical level
Difference is,For the point of theory of missile wing and datum plane,；
Using upper measurement point 3 and the difference in height of lower measurement point 5；For missile wing and the actual corners of datum plane
Degree,；Missile wing upper counterangle deviation can finally be obtained is；
D, in the same manner, using the actual measurement altitude information of point 4 and point 5 on same missile wing and theoretical level difference calculating missile wing
Angular displacement is installed；
E, calculated using the altitude information of the respective horizontal measurement point on symmetrical missile wing symmetrical missile wing established angle left and right difference and
Upper counterangle left and right difference.
Beneficial effects of the present invention：The measurement error that artificial Levelling operation brings is reduced repeatedly, guided missile level is improve
The precision and efficiency of measurement, meanwhile, the equipment such as guided missile turnover bracket are reduced, it is easy to operate, reduce cost.
Description of the drawings
Fig. 1 a are the relative position figure of the measurement point 3,4,5 on 4 missile wings of the present invention.
Left views of Fig. 1 b for Fig. 1 a, is that measurement point is illustrated to the altitude information measurement of reference platform on the missile wing of the present invention
Figure.
Fig. 2 is the theoretical level lateral distance of point 3 and point 5 on the missile wing of the present invention, theoretical level is poorWith actual height
Degree is poorSchematic diagram.
Fig. 3 is the structural representation of the general level test desk that the present invention is suitable for.
In Fig. 3,1, measuring table, 2, height gauge, 3, universal stand in front and back, 4, data processor.
Specific embodiment
The invention will be further described with specific embodiment below in conjunction with the accompanying drawings.Following examples are merely to illustrate this
It is bright, it is not limited to protection scope of the present invention.
The present invention a kind of low aspect ratio guided missile level measurement method, after bomb body first leveling, using reference platform as
The unique reference of all measurement points on bullet, measures each horizontal survey point to the height of reference platform with height gauge, and centre need not be entered
Row bomb body rotates and leveling, calculates horizontal survey deviation data using the difference in height between each measurement point.
With reference to Fig. 1 a, Fig. 1 b, Fig. 2, by taking "×" type missile wing layout as an example, comprise the following steps that：
A, by guided missile be arranged on universal stand on, being defined by bomb body left and right sides horizontal survey point 1 and 1' carries out leveling；
B, all measurement points 3,4,5 for being measured on 4 missile wings successively arrive the altitude information of reference platform,、With；
C, according to missile wing theory profile can be calculated a little 3 and put 5 theoretical level lateral distance, theoretical level
Difference is,For the point of theory of missile wing and datum plane,；
Using upper measurement point 3 and the difference in height of lower measurement point 5；For missile wing and the actual corners of datum plane
Degree,,（Due to actual large deviations it is less, therefore 3 and the lateral distance change of 5 points of levels it is extremely small,
Therefore also take in actual measurement）；Missile wing upper counterangle deviation can finally be obtained is；
D, in the same manner, using the actual measurement altitude information of point 4 and point 5 on same missile wing and theoretical level difference calculating missile wing
Angular displacement is installed；
E, calculated using the altitude information of the respective horizontal measurement point on symmetrical missile wing symmetrical missile wing established angle left and right difference and
Upper counterangle left and right difference.
In Fig. 3, the present invention design level measurement method have application in general level test desk, the horizontal survey platform by
Measuring table 1, in front and back height gauge 2, universal stand 3 and data processor 4 are constituted, wherein, measuring table 1 is the base of horizontal survey
It is accurate；Height gauge 2 is High Precision Automatic photoelectric measuring carpenters square, for measuring to the height of horizontal survey point；Universal stand 3 in front and back
For supporting guided missile in the measurements；Data processor 4 is responsible for receiving and by horizontal survey data are processed, will finally by printer
Measurement result is printed.
Claims (1)
1. a kind of low aspect ratio guided missile level measurement method, it is characterised in that after bomb body first leveling, using reference platform as
The unique reference of all measurement points on bullet, measures each horizontal survey point to the height of reference platform with height gauge, and centre need not be entered
Row bomb body rotates and leveling, calculates horizontal survey deviation data using the difference in height between each measurement point；It includes following
Step：
A, by guided missile be arranged on universal stand on, with bomb body left and right sides horizontal survey point（1、1'）Being defined carries out leveling；
B, all measurement points for being measured on 4 missile wings successively（3、4、5）To the altitude information of reference platform, H3, H4 and H5；
C, according to missile wing theory profile can be calculated a little（3）And point（5）Theoretical level lateral distance L1, theoretical level is poor
For H, α is the point of theory of missile wing and datum plane, tan α=H/L1；
Using upper measurement point（3）With lower measurement point（5）Height difference H 3-H5；β is missile wing and the actual angle of datum plane, tan
β=(H3-H5)/L1；Missile wing upper counterangle deviation can finally be obtained for γ=β-α；
D, in the same manner, using point on same missile wing（4）And point（5）Actual measurement altitude information and theoretical level difference calculate missile wing
Angular displacement is installed；
E, symmetrical missile wing established angle left and right difference and upper anti-is calculated using the altitude information of the respective horizontal measurement point on symmetrical missile wing
Angle left and right difference.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510412543.9A CN105021094B (en) | 2015-07-15 | 2015-07-15 | Small-aspect-ratio missile horizontal measuring method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510412543.9A CN105021094B (en) | 2015-07-15 | 2015-07-15 | Small-aspect-ratio missile horizontal measuring method |
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| CN105021094A CN105021094A (en) | 2015-11-04 |
| CN105021094B true CN105021094B (en) | 2017-04-26 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105547060A (en) * | 2015-12-02 | 2016-05-04 | 吉林市江机民科实业有限公司 | Missile wing spreading time tester |
| 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 |
| CN112664769A (en) * | 2020-12-15 | 2021-04-16 | 北京航星机器制造有限公司 | Automatic leveling device for level measurement |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100844927B1 (en) * | 2007-01-15 | 2008-07-09 | 국방과학연구소 | Horizontal type of 3-dimensional weight measurement apparatus for cylindrical missile |
| CN103925854A (en) * | 2014-04-03 | 2014-07-16 | 北京星航机电装备有限公司 | Method for horizontally measuring missiles on basis of three-dimensional coordinate transformation principle |
| CN104061892A (en) * | 2014-07-02 | 2014-09-24 | 北京机械设备研究所 | Horizontal direction displacement measuring device of missile vertical launch initial segment |
| CN104457696A (en) * | 2014-12-09 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Non-leveling type horizontal measuring method |
-
2015
- 2015-07-15 CN CN201510412543.9A patent/CN105021094B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100844927B1 (en) * | 2007-01-15 | 2008-07-09 | 국방과학연구소 | Horizontal type of 3-dimensional weight measurement apparatus for cylindrical missile |
| CN103925854A (en) * | 2014-04-03 | 2014-07-16 | 北京星航机电装备有限公司 | Method for horizontally measuring missiles on basis of three-dimensional coordinate transformation principle |
| CN104061892A (en) * | 2014-07-02 | 2014-09-24 | 北京机械设备研究所 | Horizontal direction displacement measuring device of missile vertical launch initial segment |
| CN104457696A (en) * | 2014-12-09 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Non-leveling type horizontal measuring method |
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