CN105021094A - Small-aspect-ratio missile horizontal measuring method - Google Patents
Small-aspect-ratio missile horizontal measuring method Download PDFInfo
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- CN105021094A CN105021094A CN201510412543.9A CN201510412543A CN105021094A CN 105021094 A CN105021094 A CN 105021094A CN 201510412543 A CN201510412543 A CN 201510412543A CN 105021094 A CN105021094 A CN 105021094A
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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, particularly relate 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 parts all has special technical requirement.They will directly have influence on control performance and the flying quality of guided missile relative to the degree of accuracy of theoretical installation site.Visible horizon measurement is the operation very important together ensureing guided missile installation accuracy.
And three of guided missile grades of maintenances relate to the dismounting of guided missile.If dismounting cabin section and pneumatic in product repairing process, then by horizontal survey, guided missile should determine whether the installation accuracy of its cabin section and pneumatic still meets technical requirement after reconfiguring.
At present, domestic main employing or traditional multiple rotary guided missile, repeatedly leveling level measurement method, this method is in use to after leveling between bomb body measuring basis plane and reference platform, in order to the point measured on symmetrical pneumatic need rotate guided missile after bomb body measurement terminates, just need re-start bomb body leveling, such guided missile often rotates once, just needs to carry out a bomb body leveling job, thus adding artificial measure error, operating efficiency is lower.
Therefore, need to provide a kind of new technical scheme to solve the problems referred to above.
Summary of the invention
The technical issues that need to address of the present invention are to provide a kind of low aspect ratio guided missile level measurement method.Tested guided missile one-time leveling is only needed during measurement, can by complete for planar survey pneumatic on bullet.
For solving 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, using the unique reference of reference platform all measurement points on bullet, the height of each horizontal survey point to reference platform is measured with height gauge, middle without the need to carrying out bomb body rotation and leveling, utilize the difference in height between each measurement point to calculate horizontal survey deviation data.
A kind of low aspect ratio guided missile level measurement method, it comprises the following steps:
A, guided missile is arranged on universal mount, is as the criterion with bomb body left and right sides horizontal survey point 1 and 1' and carries out leveling;
B, the successively all measurement points 3,4,5 measured on 4 missile wings arrive the altitude information of reference platform,
,
with
;
C, according to the theoretical profile of missile wing can calculate 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,
;
The difference in height of measurement point 3 and lower measurement point 5 in utilization
;
for the actual angle of missile wing and datum plane,
; Finally can obtain missile wing upper counterangle deviation is
;
D, in like manner, can utilize the actual measurement altitude information same missile wing putting 4 and point 5 to calculate missile wing established angle deviation with theoretical level is poor;
The altitude information of e, the respective horizontal measurement point utilized on symmetrical missile wing calculates symmetrical missile wing established angle left and right difference and upper counterangle left and right difference.
Beneficial effect of the present invention: reduce repeatedly the measure error that artificial Levelling operation brings, improve precision and the efficiency of guided missile horizontal survey, meanwhile, decrease the equipment such as guided missile turnover bracket, easy to operate, reduce cost.
Accompanying drawing explanation
Fig. 1 a is the relative position figure of the measurement point 3,4,5 on 4 missile wings of the present invention.
Fig. 1 b is the left view of Fig. 1 a, for measurement point on missile wing of the present invention is to the altitude information instrumentation plan of reference platform.
Fig. 2 is theoretical level lateral distance missile wing of the present invention being put 3 and point 5
, theoretical level is poor
poor with actual height
schematic 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, front and back universal mount, 4, data processor.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the invention will be further described.Following examples, only for illustration of the present invention, are not used for limiting the scope of the invention.
A kind of low aspect ratio guided missile level measurement method of the present invention, after bomb body first leveling, using the unique reference of reference platform all measurement points on bullet, the height of each horizontal survey point to reference platform is measured with height gauge, middle without the need to carrying out bomb body rotation and leveling, utilize the difference in height between each measurement point to calculate horizontal survey deviation data.
With reference to figure 1a, Fig. 1 b, Fig. 2, for "×" type missile wing layout, concrete steps are as follows:
A, guided missile is arranged on universal mount, is as the criterion with bomb body left and right sides horizontal survey point 1 and 1' and carries out leveling;
B, the successively all measurement points 3,4,5 measured on 4 missile wings arrive the altitude information of reference platform,
,
with
;
C, according to the theoretical profile of missile wing can calculate 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,
;
The difference in height of measurement point 3 and lower measurement point 5 in utilization
;
for the actual angle of missile wing and datum plane,
, (because actual large deviations is less, thus 3 and 5 horizontal lateral distance changes extremely small, therefore also to get in actual measurement
); Finally can obtain missile wing upper counterangle deviation is
;
D, in like manner, can utilize the actual measurement altitude information same missile wing putting 4 and point 5 to calculate missile wing established angle deviation with theoretical level is poor;
The altitude information of e, the respective horizontal measurement point utilized on symmetrical missile wing calculates symmetrical missile wing established angle left and right difference and upper counterangle left and right difference.
In Fig. 3, the level measurement method of the present invention's design has been applied in general level test desk, and this horizontal survey platform is made up of measuring table 1, height gauge 2, front and back universal mount 3 and data processor 4, and wherein, measuring table 1 is the benchmark of horizontal survey; Height gauge 2 is High Precision Automatic photoelectric measuring carpenters square, for measuring the height of horizontal survey point; Front and back universal mount 3 is for supporting guided missile in the measurements; Data processor 4 is responsible for receiving and by processing horizontal measurement data, measurement result being printed finally by printer.
Claims (2)
1. a low aspect ratio guided missile level measurement method, it is characterized in that, after bomb body first leveling, using the unique reference of reference platform all measurement points on bullet, the height of each horizontal survey point to reference platform is measured with height gauge, middle without the need to carrying out bomb body rotation and leveling, utilize the difference in height between each measurement point to calculate horizontal survey deviation data.
2. a kind of low aspect ratio guided missile level measurement method according to claim 1, it is characterized in that, it comprises the following steps:
A, guided missile is arranged on universal mount, is as the criterion with bomb body left and right sides horizontal survey point 1 and 1' and carries out leveling;
B, the successively all measurement points 3,4,5 measured on 4 missile wings arrive the altitude information of reference platform,
,
with
;
C, according to the theoretical profile of missile wing can calculate 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;
The difference in height of measurement point 3 and lower measurement point 5 in utilization
;
for the actual angle of missile wing and datum plane,
; Finally can obtain missile wing upper counterangle deviation is
;
D, in like manner, can utilize the actual measurement altitude information same missile wing putting 4 and point 5 to calculate missile wing established angle deviation with theoretical level is poor;
The altitude information of e, the respective horizontal measurement point utilized on symmetrical missile wing calculates symmetrical missile wing established angle left and right difference and upper counterangle left and right difference.
Priority Applications (1)
| 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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| 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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| Publication Number | Publication Date |
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| CN105021094A true CN105021094A (en) | 2015-11-04 |
| CN105021094B CN105021094B (en) | 2017-04-26 |
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| CN201510412543.9A Active CN105021094B (en) | 2015-07-15 | 2015-07-15 | Small-aspect-ratio missile horizontal measuring method |
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Cited By (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 |
Cited By (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 |
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| Publication number | Publication date |
|---|---|
| CN105021094B (en) | 2017-04-26 |
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