CN103604316A - Ballistic correction method for multi-bullet shooting - Google Patents
Ballistic correction method for multi-bullet shooting Download PDFInfo
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- CN103604316A CN103604316A CN201310591968.1A CN201310591968A CN103604316A CN 103604316 A CN103604316 A CN 103604316A CN 201310591968 A CN201310591968 A CN 201310591968A CN 103604316 A CN103604316 A CN 103604316A
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Abstract
The invention discloses a ballistic correction method for multi-bullet shooting. The ballistic correction method is realized through a detector, a command and control unit, a multi-bullet shooting assembly frame, a turret system, an integrated scheduling module, an angle calculating module and a data compensation module. By the method, left and right position deviation, upper and lower position deviation, heading error angles and pitching deviation angle of frame positions of the multi-bullet shooting assembly frame and an optical axis of the detector, error in ballistic resolving can be eliminated, and shooting precision can be improved.
Description
Technical field
The present invention relates to a kind of trajectory bearing calibration, particularly a kind of trajectory bearing calibration for many bullet transmittings.
Background technology
For Shell and rocket bullet, many bullet transmittings are the effective ways that strengthen its striking capabilities, and traditional trajectory bearing calibration is by target-detection unit, to obtain orientation and the relative distance of target, thereby calculates launch azimuth and launching elevation.Once the relative bearing of target and relative distance are determined, both can get standard emission trajectory by trajectory bearing calibration, emission angle is also determined thereupon.In emission process, all chord positions adopt same emission angle to launch, and for many bullet transmittings, location deviation and misalignment of axe between different transmitting chord positions, traditional trajectory bearing calibration can not carried out the real-time adjustment of emission angle along with the difference of transmitting chord position, now the misalignment of axe of different launcher bit position deviations and different chord positions can directly cause the landing error of Shell and rocket bullet, finally affects launch accuracy error.
Summary of the invention
The object of the present invention is to provide a kind of trajectory bearing calibration for many bullet transmittings, the misalignment of axe that solves different launcher bit position deviations and different chord positions causes the landing error problem of Shell and rocket bullet.
For a trajectory bearing calibration for many bullet transmittings, its concrete steps are:
The first step is built the emission systems that play more
The emission systems that play more, comprise: sniffer, commander's control module, many bullets transmitting assembling frame, capstan head system, integrated dispatch module, angle are resolved module and compensation data module, and described integrated dispatch module, angle resolve module and compensation data module is placed in commander's control module.
The function of integrated dispatch module be realization with sniffer, capstan head system between communicate by letter, and record position and the misalignment of axe data of different chord positions and sniffer optical axis.
The function that angle is resolved module is to solve and obtain each chord position ballistic solution angle γ according to oblique line distance, the angle of pitch of target.
Position and four deviations of angle that the function of compensation data module is brought for compensation sticking position difference.
Sniffer is installed on the below of many bullet transmitting assembling framves, and many bullet transmitting assembling framves are arranged in capstan head system.Sniffer communication interface is connected by cable with integrated dispatch module communication interface, and capstan head system communication interface is connected by cable with integrated dispatch module communication interface.The communication interface that the communication interface of integrated dispatch module resolves module with angle is respectively connected by cable with the communication interface of compensation data module.
Second step sniffer is demarcated and is played axis error
The different frame bit positions of many bullet transmitting assembling framves and axis are had nothing in common with each other, and obtain the left and right position deviation of each chord position and sniffer optical axis by measuring many bullet transmitting assembling frame sizes
with upper-lower position deviation
, by measuring the optical axis of sniffer and playing axle, obtain course deviation angle
with pitch deviation angle
, and four deviation datas are recorded in integrated dispatch module.
The 3rd step sniffer aims at the mark
Sniffer aims at the mark, and by integrated dispatch module, to sniffer, sends distance measuring instruction, and sniffer is to integrated dispatch module passback sniffer to target oblique line distance
, meanwhile, capstan head system is to the angle of pitch of integrated dispatch module passback target
, azimuth
.
The 4th step data compensating module compensation plays axis error
All take sniffer and determine as position reference and azimuth reference calculate in target oblique line distance, the angle of pitch and azimuth, compensation data module is by compensating to eliminate position and four deviation datas of angle that bring due to sticking position difference, thus the required angle of pitch of transmitting on definite each chord position.
It is that α, benchmark aiming azimuth are β that the benchmark of sniffer aims at the angle of pitch.
N chord position is with respect to the aiming angle of pitch of target
, aiming azimuth
, oblique distance
be respectively
Wherein
Setting M is impact point,
for sniffer and each transmitting chord position nozzle composition plane of departure, wherein
expression sniffer,
represent n chord position guided missile,
the guided missile of expression n chord position is the vertical intersection point in the plane of departure with sniffer.
The 5th step angle is resolved the positional information that module is calculated target
Angle is resolved module and is solved and obtain target with respect to the horizontal range of elevation information and the target range launch point of sniffer according to oblique line distance, the angle of pitch of target.Solution formula is as follows:
In formula: n chord position with respect to the aiming angle of pitch of target is
, oblique distance is
,
for the elevation information of target with respect to sniffer,
horizontal range for target and sniffer.
The 6th step angle is resolved module and is completed solving of ballistic solution angle
Dynamics and solving kinematic equation that angle is resolved module foundation obtain each chord position ballistic solution angle γ.
Using the target angle of pitch and go out a speed, angular speed initial value as the primary condition that solves the differential equation, in conjunction with the aerodynamic parameter of bullet, calculate and obtain overall trajectory parameter.
So far realized for the trajectory of many bullet transmittings and having proofreaied and correct.
When this method can effectively be eliminated many bullet transmittings, the misalignment of axe of different launcher bit position deviations and different chord positions causes the landing error of Shell and rocket bullet, improves launch accuracy.
Accompanying drawing explanation
Guided missile, sniffer and the relative target bearing figure of the n chord position of a kind of trajectory bearing calibration for many bullet transmittings of Fig. 1.
The specific embodiment
For a trajectory bearing calibration for many bullet transmittings, its concrete steps are:
The first step is built the emission systems that play more
The emission systems that play more, comprise: sniffer, commander's control module, many bullets transmitting assembling frame, capstan head system, integrated dispatch module, angle are resolved module and compensation data module, and described integrated dispatch module, angle resolve module and compensation data module is placed in commander's control module.
The function of integrated dispatch module be realization with sniffer, capstan head system between communicate by letter, and record position and the misalignment of axe data of different chord positions and sniffer optical axis.
The function that angle is resolved module is to solve and obtain each chord position ballistic solution angle γ according to oblique line distance, the angle of pitch of target.
Position and four deviations of angle that the function of compensation data module is brought for compensation sticking position difference.
Sniffer is installed on the below of many bullet transmitting assembling framves, and many bullet transmitting assembling framves are arranged in capstan head system.Sniffer communication interface is connected by cable with the integrated dispatch module communication interface of commander's control module, and capstan head system communication interface is connected by cable with the integrated dispatch module communication interface of commander's control module.The communication interface that the communication interface of integrated dispatch module resolves module with angle is respectively connected by cable with the communication interface of compensation data module.
Second step sniffer is demarcated and is played axis error
The different frame bit positions of many bullet transmitting assembling framves and axis are had nothing in common with each other, and obtain the left and right position deviation of each chord position and sniffer optical axis by measuring many bullet transmitting assembling frame sizes
with upper-lower position deviation
, by measuring the optical axis of sniffer and playing axle, obtain course deviation angle
with pitch deviation angle
, and four deviation datas are recorded in integrated dispatch module.
The 3rd step sniffer aims at the mark
Sniffer aims at the mark, and by integrated dispatch module, to sniffer, sends distance measuring instruction, and sniffer is to integrated dispatch module passback sniffer to target oblique line distance
, meanwhile, capstan head system is to the angle of pitch of integrated dispatch module passback target
, azimuth
.
The 4th step data compensating module compensation plays axis error
All take sniffer and determine as position reference and azimuth reference calculate in target oblique line distance, the angle of pitch and azimuth, compensation data module is by compensating to eliminate position and four deviation datas of angle that bring due to sticking position difference, thus the required angle of pitch of transmitting on definite each chord position.
It is that α, benchmark aiming azimuth are β that the benchmark of sniffer aims at the angle of pitch.
N chord position is with respect to the aiming angle of pitch of target
, aiming azimuth
, oblique distance
be respectively
Wherein
Setting M is impact point,
for sniffer and each transmitting chord position nozzle composition plane of departure, wherein
expression sniffer,
represent n chord position guided missile,
the guided missile of expression n chord position is the vertical intersection point in the plane of departure with sniffer.
The 5th step angle is resolved the positional information that module is calculated target
Angle is resolved module and is solved and obtain target with respect to the horizontal range of elevation information and the target range launch point of sniffer according to oblique line distance, the angle of pitch of target.Solution formula is as follows:
In formula: n chord position with respect to the aiming angle of pitch of target is
, oblique distance is
,
for the elevation information of target with respect to sniffer,
horizontal range for target and sniffer.
The 6th step angle is resolved module and is completed solving of ballistic solution angle
Dynamics and solving kinematic equation that angle is resolved module foundation obtain each chord position ballistic solution angle γ.
Using the target angle of pitch and go out a speed, angular speed initial value as the primary condition that solves the differential equation, in conjunction with the aerodynamic parameter of bullet, calculate and obtain overall trajectory parameter.
So far realized for the trajectory of many bullet transmittings and having proofreaied and correct.
Claims (1)
1. for a trajectory bearing calibration for many bullet transmittings, it is characterized in that the concrete steps of this method are:
The first step is built the emission systems that play more
The emission systems that play more, comprise: sniffer, commander's control module, many bullets transmitting assembling frame, capstan head system, integrated dispatch module, angle are resolved module and compensation data module, and described integrated dispatch module, angle resolve module and compensation data module is placed in commander's control module;
The function of integrated dispatch module be realization with sniffer, capstan head system between communicate by letter, and record position and the misalignment of axe data of different chord positions and sniffer optical axis;
The function that angle is resolved module is to solve and obtain each chord position ballistic solution angle γ according to oblique line distance, the angle of pitch of target;
Position and four deviations of angle that the function of compensation data module is brought for compensation sticking position difference;
Sniffer is installed on the below of many bullet transmitting assembling framves, and many bullet transmitting assembling framves are arranged in capstan head system; Sniffer communication interface is connected by cable with integrated dispatch module communication interface, and capstan head system communication interface is connected by cable with integrated dispatch module communication interface; The communication interface that the communication interface of integrated dispatch module resolves module with angle is respectively connected by cable with the communication interface of compensation data module;
Second step sniffer is demarcated and is played axis error
The different frame bit positions of many bullet transmitting assembling framves and axis are had nothing in common with each other, and obtain the left and right position deviation of each chord position and sniffer optical axis by measuring many bullet transmitting assembling frame sizes
with upper-lower position deviation
, by measuring the optical axis of sniffer and playing axle, obtain course deviation angle
with pitch deviation angle
, and four deviation datas are recorded in integrated dispatch module;
The 3rd step sniffer aims at the mark
Sniffer aims at the mark, and by integrated dispatch module, to sniffer, sends distance measuring instruction, and sniffer is to integrated dispatch module passback sniffer to target oblique line distance
, meanwhile, capstan head system is to the angle of pitch of integrated dispatch module passback target
, azimuth
;
The 4th step data compensating module compensation plays axis error
All take sniffer and determine as position reference and azimuth reference calculate in target oblique line distance, the angle of pitch and azimuth, compensation data module is by compensating to eliminate position and four deviation datas of angle that bring due to sticking position difference, thus the required angle of pitch of transmitting on definite each chord position;
It is that α, benchmark aiming azimuth are β that the benchmark of sniffer aims at the angle of pitch;
N chord position is with respect to the aiming angle of pitch of target
, aiming azimuth
, oblique distance
be respectively
Wherein
Setting M is impact point,
for sniffer and each transmitting chord position nozzle composition plane of departure, wherein
expression sniffer,
represent n chord position guided missile,
the guided missile of expression n chord position is the vertical intersection point in the plane of departure with sniffer;
The 5th step angle is resolved the positional information that module is calculated target
Angle is resolved module and is solved and obtain target with respect to the horizontal range of elevation information and the target range launch point of sniffer according to oblique line distance, the angle of pitch of target; Solution formula is as follows:
In formula: n chord position with respect to the aiming angle of pitch of target is
, oblique distance is
,
for the elevation information of target with respect to sniffer,
horizontal range for target and sniffer;
The 6th step angle is resolved module and is completed solving of ballistic solution angle
Dynamics and solving kinematic equation that angle is resolved module foundation obtain each chord position ballistic solution angle γ;
Using the target angle of pitch and go out a speed, angular speed initial value as the primary condition that solves the differential equation, in conjunction with the aerodynamic parameter of bullet, calculate and obtain overall trajectory parameter;
So far realized for the trajectory of many bullet transmittings and having proofreaied and correct.
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|---|---|---|---|
| CN201310591968.1A CN103604316B (en) | 2013-11-22 | 2013-11-22 | Ballistic correction method for multi-bullet shooting |
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|---|---|---|---|
| CN201310591968.1A CN103604316B (en) | 2013-11-22 | 2013-11-22 | Ballistic correction method for multi-bullet shooting |
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| CN103604316B CN103604316B (en) | 2015-06-10 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104236402A (en) * | 2014-10-10 | 2014-12-24 | 王广伟 | Projectile launching testing method and system |
| CN105095661A (en) * | 2015-08-07 | 2015-11-25 | 路伟志 | Sniper ballistic calculating system |
| CN107561930A (en) * | 2017-08-28 | 2018-01-09 | 西京学院 | Guidance control method is tested in a kind of outer trajectory networking |
| CN107609307A (en) * | 2017-10-10 | 2018-01-19 | 北京理工大学 | A kind of telemedicine vehicle trajectory analysis method for considering gas bullet and the earth and influenceing |
| CN109806594A (en) * | 2019-01-17 | 2019-05-28 | 腾讯科技（深圳）有限公司 | Ballistic display method, device and equipment in virtual environment |
| CN110609972A (en) * | 2019-09-30 | 2019-12-24 | 中国科学院紫金山天文台 | Free trajectory construction method for appointed launching elevation angle |
| CN113008080A (en) * | 2021-01-26 | 2021-06-22 | 河北汉光重工有限责任公司 | Fire control calculation method for offshore target based on rigidity principle |
| CN117288047A (en) * | 2023-10-10 | 2023-12-26 | 北京理工大学 | Two-dimensional correction fuze drop point prediction control method insensitive to model errors |
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| JPH01234798A (en) * | 1988-03-15 | 1989-09-20 | Japan Steel Works Ltd:The | Firing angle control device |
| JPH06257995A (en) * | 1993-03-02 | 1994-09-16 | Mitsubishi Electric Corp | Launcher |
| CN102656417A (en) * | 2010-01-15 | 2012-09-05 | 莱茵金属防空股份公司 | Method for correcting the trajectory of a projectile, in particular of an end-phase-guided projectile, and projectile for carrying out the process |
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2013
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| EP0218742A1 (en) * | 1985-10-14 | 1987-04-22 | LITEF GmbH | Fire control system for indirectly aimed weapons |
| JPH01234798A (en) * | 1988-03-15 | 1989-09-20 | Japan Steel Works Ltd:The | Firing angle control device |
| JPH06257995A (en) * | 1993-03-02 | 1994-09-16 | Mitsubishi Electric Corp | Launcher |
| CN102656417A (en) * | 2010-01-15 | 2012-09-05 | 莱茵金属防空股份公司 | Method for correcting the trajectory of a projectile, in particular of an end-phase-guided projectile, and projectile for carrying out the process |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104236402B (en) * | 2014-10-10 | 2016-01-06 | 王广伟 | Play arrow emission test method and system |
| CN104236402A (en) * | 2014-10-10 | 2014-12-24 | 王广伟 | Projectile launching testing method and system |
| CN105095661A (en) * | 2015-08-07 | 2015-11-25 | 路伟志 | Sniper ballistic calculating system |
| CN107561930B (en) * | 2017-08-28 | 2021-08-06 | 西京学院 | External ballistic networking test guidance control method |
| CN107561930A (en) * | 2017-08-28 | 2018-01-09 | 西京学院 | Guidance control method is tested in a kind of outer trajectory networking |
| CN107609307A (en) * | 2017-10-10 | 2018-01-19 | 北京理工大学 | A kind of telemedicine vehicle trajectory analysis method for considering gas bullet and the earth and influenceing |
| CN107609307B (en) * | 2017-10-10 | 2019-09-10 | 北京理工大学 | A kind of telemedicine vehicle trajectory analysis method for considering gas bullet and the earth and influencing |
| CN109806594B (en) * | 2019-01-17 | 2022-05-17 | 腾讯科技（深圳）有限公司 | Trajectory display method, device and equipment in virtual environment |
| CN109806594A (en) * | 2019-01-17 | 2019-05-28 | 腾讯科技（深圳）有限公司 | Ballistic display method, device and equipment in virtual environment |
| CN110609972B (en) * | 2019-09-30 | 2020-12-04 | 中国科学院紫金山天文台 | Free trajectory construction method for appointed launching elevation angle |
| WO2021063073A1 (en) * | 2019-09-30 | 2021-04-08 | 中国科学院紫金山天文台 | Method for constructing free trajectory at specified launching elevation angle |
| CN110609972A (en) * | 2019-09-30 | 2019-12-24 | 中国科学院紫金山天文台 | Free trajectory construction method for appointed launching elevation angle |
| CN113008080A (en) * | 2021-01-26 | 2021-06-22 | 河北汉光重工有限责任公司 | Fire control calculation method for offshore target based on rigidity principle |
| CN113008080B (en) * | 2021-01-26 | 2023-01-13 | 河北汉光重工有限责任公司 | Fire control calculation method for offshore target based on rigidity principle |
| CN117288047A (en) * | 2023-10-10 | 2023-12-26 | 北京理工大学 | Two-dimensional correction fuze drop point prediction control method insensitive to model errors |
| CN117288047B (en) * | 2023-10-10 | 2024-04-12 | 北京理工大学 | Two-dimensional correction fuze drop point prediction control method insensitive to model errors |
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