CN105135944B - The method that rocket sighting system obtains reference bearing by pendulum-type north finder automatically north seeking - Google Patents
The method that rocket sighting system obtains reference bearing by pendulum-type north finder automatically north seeking Download PDFInfo
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- CN105135944B CN105135944B CN201510537065.4A CN201510537065A CN105135944B CN 105135944 B CN105135944 B CN 105135944B CN 201510537065 A CN201510537065 A CN 201510537065A CN 105135944 B CN105135944 B CN 105135944B
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Abstract
The method that rocket sighting system obtains reference bearing by pendulum-type north finder automatically north seeking, including preparation process and measuring process, wherein preparation process includes: fixing pendulum-type north finder in aiming on service tower, is fixed with corner cube prism on pendulum-type north finder top；The prism normal of corner cube prism and leaf sight keeping parallelism；Start pendulum-type north searching instrument, accumulate and effectively seek north data for 6 times and try to achieve average as north, orientation on the basis of the azimuth between corner cube prism normal and greatly north greatly on pendulum-type north finder；Determine the order aiming point that the horizontal groove of length of leaf sight is formed with short perpendicular groove；Pointing instrumentation and selected aiming point are to the heart；Record the orientation angle between pendulum-type north finder, corner cube prism, used group prism by pointing instrumentation, be scaled the measuring process at the initial orientation angle of rocket body.The purpose of azimuth reference high accuracy transmission can be reached, meet carrier rocket Ground-Aiming-Equipment and use requirement.
Description
Technical field
The present invention designs a kind of photoelectric measurement method, particularly relates to a kind of azimuthal photoelectric measurement method.
Background technology
A new generation's rocket overall plan there are differences with the design of active service rocket.Require to hold in the case of the unmanned of launching site
Continuous supervision rocket body sighting angle, until to launching time of ignition.Existing rocket sighting system cannot meet aiming at the need.
In practice, rocket is navigated by inertance element, and inertance element device outer case assembling corner cube prism, i.e. rocket are taken aim at
Quasi-prism (also referred to as used group prism), before rocket takes off, by Ground-Aiming-Equipment, measures and calculates this corner cube prism method of acquisition and put down
Face and the orientation angle of the earth north (N), can complete ground aiming work.The most fast and accurately reference of reference side is taken aim in transmitting
Position records and is accurately delivered to the aiming on service tower Nei, and gives Ground-Aiming-Equipment, is to need new rocket totally side
The aiming key technology that case is improved.
In service tower, with Ground-Aiming-Equipment, by launching, receiving aiming beam, to rocket alignment prism method
Plane measures with the orientation angle in the earth north, and reference bearing data are passed to rocket control system, it is simply that determines and takes aim at
The orientation angle that the aiming beam (i.e. aiming at optical axis) that quasi-equipment is launched is northern with the earth.
(photoelectricity) pointing instrumentation can be used for accurate angle and measures, and by collimating with the corner cube prism on north finder, carries out benchmark
Orientation introduce function, can complete directive angle bookbinding and photoelectricity alignment function, have anti-light disturbance and export quick district signal and
Aiming symbol function, and the functions such as closed loop automation aiming can be realized together with rocket control system.
North finder corner cube prism can cooperatively form stable optical axis with light source, can serve as the laying ginseng of leaf sight
Examining, fast and easy establishes the operating position of pointing instrumentation.
Pendulum-type (gyro) north finder can on quiet pedestal round-the-clock automatic indicating position, rely on the inertance element sensitivity earth from
The completing of tarnsition velocity horizontal component seeks north function.
Summary of the invention
It is an object of the invention to provide a kind of carrier rocket sighting system on launching service tower, obtain the side of reference bearing
Method, utilizes pendulum-type north finder automatically north seeking to solve cannot quick and precisely record and transmit on higher service tower the technology of reference bearing
Problem.
The method that the rocket sighting system of the present invention obtains reference bearing by pendulum-type north finder automatically north seeking, including preparing step
Rapid and measuring process, wherein preparation process includes:
In aiming on service tower, fixing pendulum-type north finder, is fixed with corner cube prism on pendulum-type north finder top；
The prism normal of the corner cube prism of pendulum-type north finder and leaf sight keeping parallelism；
Start pendulum-type north searching instrument, accumulate and effectively seek north data for 6 times to try to achieve average the most northern as the earth, corner cube prism normal
And orientation on the basis of the azimuth between the earth north；
Determine the order aiming point that the horizontal groove of length of leaf sight is formed with short perpendicular groove；
Pointing instrumentation is directed at selected aiming point；
Record the azimuth between the corner cube prism of pendulum-type north finder, used group prism by pointing instrumentation, formed and be scaled rocket body
The measuring process at initial orientation angle.
Described measuring process includes:
The corner cube prism of pendulum-type north finder is aimed at, it is thus achieved that reference bearing angle A by pointing instrumentationjz；
Used group prism is aimed at, it is thus achieved that collimation deviation angle beta by pointing instrumentation；
The azimuth rotation angle α between the prism normal aiming at used group prism and corner cube prism is obtained by pointing instrumentation；
Reference bearing angle AjzAnd the orientation angle theta between used group of prism, and the initial orientation angle A of used group prismmzRoot
Obtain according to below equation:
θ=a+ β ... ... ... ... ... ... ... ... ... ... ... ... ... (2).
Described leaf sight is made up of a long horizontal groove and several short perpendicular grooves, each short perpendicular groove and long horizontal groove
Perpendicular intersection is exactly an aiming point, line width 0.5mm, perpendicular ruling span 50mm.
The corner cube prism plane of incidence length of described pendulum-type north finder is not less than 50mm, and width is not less than 30mm.
The rocket sighting system of the present invention obtains the side of reference bearing (initial orientation angle) by pendulum-type north finder automatically north seeking
Method all can reach the purpose of azimuth reference high accuracy transmission, meets carrier rocket Ground-Aiming-Equipment and uses requirement.
Accompanying drawing explanation
Fig. 1 is that rocket sighting system of the present invention is by utilizing pendulum-type in pendulum-type north finder automatically north seeking acquisition reference bearing method
North finder obtains and transmits angular surveying schematic diagram.
Detailed description of the invention
Below in conjunction with the accompanying drawings the detailed description of the invention of the present invention is described in detail.
Shown in Fig. 1, the acquisition reference bearing method of the present invention mainly includes following preparation process:
In aiming on service tower, fixing pendulum-type north finder 03, is fixed with corner cube prism 02 on pendulum-type north finder top,
The angle of corner cube prism normal and north finder sensitivity between centers is demarcated in advance；
The prism normal of corner cube prism 02 and leaf sight 04 keeping parallelism (substantially parallel)；
Starting pendulum-type north finder 03 and seek north, accumulate and effectively seek north data for 6 times to try to achieve average the most northern as the earth, this value is exactly straight
The earth north of angle prism normal；
Determine the order aiming point that the horizontal groove of length of leaf sight is formed with short perpendicular groove；
Pointing instrumentation 05 and selected aiming point are to the heart；
Preparation process is concrete, and the measuring process that can optimize further provides quickly to be measured and parameter angular transition
Necessary physics reference basis, remains the mapping relations with geodetic azimuth for improving the algorithm of certainty of measurement further.
Record corner cube prism 02, used group angle difference between prism 01, geodetic azimuth by pointing instrumentation 05, form conversion
Measuring process for the reference azimuth of rocket body.
The acquisition reference bearing method of the present invention mainly includes following measuring process:
The normal of corner cube prism 02, optical alignment is aimed at, it is thus achieved that angle-data demarcates verification with mapping by pointing instrumentation 05
Conversion obtains reference bearing angle Ajz；
Used group prism 01 is aimed at, it is thus achieved that collimation deviation angle beta by pointing instrumentation 05；
The azimuth rotation angle α between the prism normal aiming at used group prism 01 and corner cube prism 02 is obtained by pointing instrumentation 05；
Reference bearing angle AjzAnd the orientation angle theta between used group of prism 01, and the initial orientation angle of used group prism 01
AmzObtain according to below equation:
θ=a+ β ... ... ... ... ... ... ... ... ... ... ... ... ... (2)
The method that the rocket sighting system of the present invention obtains reference bearing by pendulum-type north finder automatically north seeking can realize surpassing
High measurement accuracy, angular error is little, measures persistence good.Use this method, can be by quick for initial orientation angle before rocket launching
Data conversion transmission is completed in being mapped in plane quadrant.
The present invention obtains the leaf sight 04 used in reference bearing method by a long horizontal groove and several short perpendicular grooves
Constituting, each short perpendicular groove is exactly an aiming point with the perpendicular intersection of long horizontal groove, line width 0.5mm, perpendicular ruling span
50mm, determines the horizontal scribe length of leaf sight and the quantity of aiming point according to concrete sighting scope.
Corner cube prism plane of incidence length is not less than 50mm, and width is not less than 30mm.
The above, the only present invention preferably detailed description of the invention, but protection scope of the present invention is not limited thereto,
Any those familiar with the art in the technical scope that the invention discloses, the change that can readily occur in or replacement,
All should contain within protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of claims
Enclose and be as the criterion.
Claims (4)
1. the method that rocket sighting system obtains reference bearing by pendulum-type north finder automatically north seeking, including preparation process and measurement step
Suddenly, wherein preparation process includes:
In aiming on service tower, fixing pendulum-type north finder (03), is fixed with corner cube prism (02) on pendulum-type north finder top；
The prism normal of the corner cube prism (02) of pendulum-type north finder and leaf sight (04) keeping parallelism；
Start pendulum-type north finder (03) and seek north, accumulate and effectively seek north data for 6 times to try to achieve average the most northern as the earth, corner cube prism (02)
Orientation on the basis of azimuth between normal and the earth north；
Determine the order aiming point that the horizontal groove of length of leaf sight is formed with short perpendicular groove；
Pointing instrumentation (05) is directed at selected aiming point；
Recording the azimuth between the corner cube prism (02) of pendulum-type north finder, used group prism (01) by pointing instrumentation (05), formation is changed
Calculate the measuring process at the initial orientation angle being rocket body.
2. the method that rocket sighting system obtains reference bearing by pendulum-type north finder automatically north seeking as claimed in claim 1, it is special
Levy and be: described measuring process includes:
The corner cube prism (02) of pendulum-type north finder is aimed at, it is thus achieved that reference bearing angle A by pointing instrumentation (05)jz；
Used group prism (01) is aimed at, it is thus achieved that collimation deviation angle beta by pointing instrumentation (05)；
The azimuth rotation angle α between the prism normal of used group prism (01) and corner cube prism (02) is obtained by pointing instrumentation (05)；
Reference bearing angle AjzAnd the orientation angle theta between used group of prism (01), and the initial orientation angle of used group prism (01)
AmzObtain according to below equation:
θ=a+ β ... ... ... ... ... ... ... ... ... ... ... ... ... (2).
3. the method that rocket sighting system obtains reference bearing by pendulum-type north finder automatically north seeking as claimed in claim 2, it is special
Levy and be: described leaf sight (04) is made up of a long horizontal groove and several short perpendicular grooves, each short perpendicular groove and long horizontal quarter
The perpendicular intersection of line is exactly an aiming point, line width 0.5mm, perpendicular ruling span 50mm.
4. the method that rocket sighting system obtains reference bearing by pendulum-type north finder automatically north seeking as claimed in claim 3, it is special
Levying and be: the corner cube prism plane of incidence length of described pendulum-type north finder is not less than 50mm, width is not less than 30mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510537065.4A CN105135944B (en) | 2015-08-27 | 2015-08-27 | The method that rocket sighting system obtains reference bearing by pendulum-type north finder automatically north seeking |
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| CN201510537065.4A CN105135944B (en) | 2015-08-27 | 2015-08-27 | The method that rocket sighting system obtains reference bearing by pendulum-type north finder automatically north seeking |
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| CN105135944B true CN105135944B (en) | 2016-12-07 |
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| CN111141282B (en) * | 2020-01-09 | 2023-07-14 | 北京航天发射技术研究所 | Positioning aiming control method and device based on Loongson processor aiming computer |
| CN112146681B (en) * | 2020-09-12 | 2023-03-10 | 中国运载火箭技术研究院 | Method and device for testing installation error of inertial group prism and computer storage medium |
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| US4444086A (en) * | 1981-12-23 | 1984-04-24 | The United States Of America As Represented By The Secretary Of The Army | Missile azimuth aiming apparatus |
| US4495850A (en) * | 1982-08-26 | 1985-01-29 | The United States Of America As Represented By The Secretary Of The Army | Azimuth transfer scheme for a strapdown Inertial Measurement Unit |
| CN2752796Y (en) * | 2004-11-05 | 2006-01-18 | 深圳市金凯进光电仪器有限公司 | Charged hand wheel structure of telescope |
| CN102661738B (en) * | 2012-05-23 | 2018-01-09 | 北京理工大学 | Aim at inertia system meridian orienting device |
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