CN103575167B - Trajectory correction method for civil interceptor missiles - Google Patents
Trajectory correction method for civil interceptor missiles Download PDFInfo
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- CN103575167B CN103575167B CN201310546516.1A CN201310546516A CN103575167B CN 103575167 B CN103575167 B CN 103575167B CN 201310546516 A CN201310546516 A CN 201310546516A CN 103575167 B CN103575167 B CN 103575167B
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Abstract
The invention discloses a trajectory correction method for civil interceptor missiles. The method is achieved through command and control equipment, a fire control computer, a firing table generating device, a meteorological measurement device, a pneumatic parameter extracting module, a firing table data calculating module and a correction parameter acquiring module, and a temperature sensor and an anemograph are arranged on the command and control equipment. The command and control equipment carries out information interaction with the firing table generating device; the fire control computer is connected with the firing table generating device through the Ethernet; the command and control equipment and the meteorological measurement device are connected through a serial bus. Pneumatic parameters of various civil interceptor missiles are extracted through the pneumatic parameter extracting module; the firing table data calculating module completes calculation of firing table data under non-standard working conditions; the correction parameter acquiring module acquires trajectory correction parameters of the corresponding missile types. The trajectory correction method for civil interceptor missiles effectively overcomes the defects that a traditional trajectory correction method is more in correction parameters, large in data processing load, complex in calculation process of trajectory correction quantities, limited in application range and the like, and the trajectory correction method is made to be more adaptable in a civil intercepting system.
Description
Technical field
The present invention relates to a kind of trajectory modification method, particularly a kind of civilian interceptor trajectory modification method.
Background technology
Present stage, it is no longer the speciality of military field that low flyer is implemented to hit, catch, and the small aircraft of interception low-latitude flying becomes the new demand in security, anti-terrorism field gradually.The intercepting system of civilian direction, its system realization is compared relative simple with military weapon, and hardware configuration should not be too complicated, and system cost is unsuitable too high.But, in use, affect the motion of interceptor and the factor of trajectory data is a lot, as all can making interceptor trajectory, meteorological condition, initial velocity, bullet weight, geographic latitude etc. produce relatively large deviation.Firing table under a single set of standard conditions is difficult to realize the effective interception to target, and uses many covers firing table of corresponding multiple non-standard condition can significantly improve the hardware configuration cost of blocking apparatus, affects product practicality.For addressing this problem, the general method that the trajectory data under standard conditions is revised that adopts, traditional trajectory modification method is that the trajectory under the different elevations angle is met to calculating, obtain the corrected parameter under the different elevations angle, simultaneously, also to obtain medicine temperature correction factor by experiment and computation, bullet rebuilding positive coefficient, jump angle height probable error, jump angular direction probable error, many corrected parameters such as initial velocity probable error, parameter is many, data processing amount is large, the computational process complexity of trajectory correction, and depart from standard value when little in each influence factor, the computational accuracy of guarantee correction.
Summary of the invention
The object of the present invention is to provide a kind of civilian interceptor trajectory modification method, solve in traditional trajectory modification method that corrected parameter is many, data processing amount large, trajectory correction computational process complexity, the limited problem of the scope of application.
A kind of concrete steps of civilian interceptor trajectory modification method are:
The first step is disposed ground trajectory update the system
Ground trajectory update the system, comprising: Command Control Equipment, fire control computer, firing table generating apparatus, meteorological measuring arrangement, aerodynamic parameter extraction module, firing table data computation module and corrected parameter acquisition module.Described meteorological measuring arrangement, comprising: temperature sensor and airspeedometer, temperature sensor is placed on Command Control Equipment and is fixedly connected with airspeedometer.Command Control Equipment, fire control computer, firing table generating apparatus work alone separately, be connected and carry out information interaction between Command Control Equipment and firing table generating apparatus by Ethernet; Between fire control computer and firing table generating apparatus, be connected by Ethernet and carry out information interaction; Command Control Equipment is connected by universal serial bus with meteorological measuring arrangement and carries out information interaction.Aerodynamic parameter extraction module resides in fire control computer, for completing the extraction of various civilian interceptor aerodynamic parameter; Firing table data computation module resides in firing table generating apparatus, for completing the calculating of non-standard operating mode firing table data; Corrected parameter acquisition module resides in firing table generating apparatus, for obtaining the trajectory corrected parameter of corresponding bullet type.
Second step aerodynamic parameter extraction module completes standard firing table data acquisition
Aerodynamic parameter extraction module is according to actual measurement exterior ballistic test data, carry out Aerodynamic Parameter Identification in conjunction with CFD Numerical Wind Tunnel data and engineering calculation result, by theory of solving trajectory in theoretical definite aerodynamic parameter substitution outer trajectory equation group, determine that a launch velocity is as service velocity, aerodynamic parameter extraction module completes the calculating that meets to trajectory under the condition of the different elevations angle, and using obtained ballistic data as standard firing table data, deposit in fire control computer.
The 3rd step Command Control Equipment obtains local meteorological condition and geographic latitude
Command Control Equipment gathers local environment temperature, wind speed and direction by meteorological measuring arrangement, and determine accordingly the medicine temperature scope of application and the wind speed scope of application, the local geographic latitude information of artificial input, and be converted to height above sea level information, Command Control Equipment by Ethernet by environment temperature, wind speed, wind direction, height above sea level communication to firing table generating apparatus.
The 4th step firing table generating apparatus completes non-standard firing table data and prepares
Firing table generating apparatus arranges difference according to parameter and realizes automation computing function, firing table data computation module is used and the fire control computer identical aerodynamic parameter of firing table that prestores, and complete non-standard firing table data calculating by different operating mode influence factors, concrete influence factor comprises bullet initial velocity, bullet weight, bullet feature area and length, mass eccentricity, wind direction, wind speed, height above sea level, wherein, the medicine temperature that bullet initial velocity is known by inference by environment temperature obtains, bullet weight, bullet feature area and length, mass eccentricity is manually inputted according to the concrete civilian interceptor bullet type using, wind direction, wind speed, the measured value that height above sea level adopts Command Control Equipment to send.Computational process selects ballistic data corresponding to each influence factor to calculate step-length according to actual needs, and firing table generating apparatus finally completes the preparation of non-standard firing table data.
The 5th step corrected parameter acquisition module completes trajectory corrected parameter and calculates
, bullet feature area heavy at bullet initial velocity, bullet and length, mass eccentricity, wind direction, wind speed, height above sea level are all in fixed situation, the basic relevant parameter of ballistic data comprises the elevation angle and flight time, therefore, adopt and about the expression formula of the initial elevation angle and time, the ballistic data under non-standard condition is revised, concrete form is as follows:
(1)
Wherein,
for trajectory under non-standard condition exists
the X-axis coordinate in moment,
for trajectory under standard conditions exists
the X-axis coordinate in moment,
for the initial elevation angle,
for projectile time of flight,
,
,
for corrected parameter to be asked.Corrected parameter acquisition module, by the ballistic data substitution formula (1) under ballistic data and non-standard condition under standard conditions, obtains parameter
,
,
.The corrected parameter obtain manner of Y-axis, Z axis coordinate and the same X-axis of formula form.Corrected parameter acquisition module by the corrected parameter group of the each influence factor of correspondence of obtaining (
,
,
) in firing table generating apparatus, completing storage, firing table generating apparatus is sent to fire control computer by Ethernet.
The 6th step fire control computer completes the application of trajectory corrected parameter
Use first, ground trajectory update the system obtains after trajectory corrected parameter, using, bullet type is constant, and the meteorological condition of environment for use and geographic latitude do not exceed in the situation of preset range, the trajectory corrected parameter that fire control computer sends according to the firing table generating apparatus receiving carries out Firing data calculation application.
So far realized the correction of civilian interceptor trajectory.
This method is for the different operating modes including the influence factors such as bullet initial velocity, bullet weight, bullet feature area and length, mass eccentricity, wind direction, wind speed, height above sea level, extract outer trajectory corrected parameter, be different from the situation that traditional trajectory meets the corresponding single parameter in the single elevation angle while calculating, applied widely, computational process is easy, and corrected parameter is simplified.At present, the method application of having succeeded in actual product, has reduced complexity and the hardware configuration cost of system to greatest extent.
Detailed description of the invention
A kind of concrete steps of civilian interceptor trajectory modification method are:
The first step is disposed ground trajectory update the system
Ground trajectory update the system, comprising: Command Control Equipment, fire control computer, firing table generating apparatus, meteorological measuring arrangement, aerodynamic parameter extraction module, firing table data computation module and corrected parameter acquisition module.Meteorological measuring arrangement comprises temperature sensor and airspeedometer, and temperature sensor is placed on Command Control Equipment and is fixedly connected with airspeedometer.Command Control Equipment, fire control computer, firing table generating apparatus work alone separately, be connected and carry out information interaction between Command Control Equipment and firing table generating apparatus by Ethernet; Between fire control computer and firing table generating apparatus, be connected by Ethernet and carry out information interaction; Being connected and carrying out information interaction by universal serial bus of Command Control Equipment and meteorological measuring arrangement.Aerodynamic parameter extraction module resides in fire control computer, for completing the extraction of various civilian interceptor aerodynamic parameter; Firing table data computation module resides in firing table generating apparatus, for completing the calculating of non-standard operating mode firing table data; Corrected parameter acquisition module resides in firing table generating apparatus, obtains the trajectory corrected parameter of corresponding bullet type.
Second step aerodynamic parameter extraction module completes standard firing table data acquisition
Aerodynamic parameter extraction module is according to actual measurement exterior ballistic test data, carry out Aerodynamic Parameter Identification in conjunction with CFD Numerical Wind Tunnel data and engineering calculation result, by theory of solving trajectory in theoretical definite aerodynamic parameter substitution outer trajectory equation group, determine that a launch velocity is as service velocity, aerodynamic parameter extraction module completes the calculating that meets to trajectory under the condition of the different elevations angle, and using obtained ballistic data as standard firing table data, deposit in fire control computer.
The 3rd step Command Control Equipment obtains local meteorological condition and geographic latitude
Command Control Equipment gathers local environment temperature, wind speed and direction by meteorological measuring arrangement, and determine accordingly the medicine temperature scope of application and the wind speed scope of application, the local geographic latitude information of artificial input, and be converted to height above sea level information, Command Control Equipment by Ethernet by environment temperature, wind speed, wind direction, height above sea level communication to firing table generating apparatus.
The 4th step firing table generating apparatus completes non-standard firing table data and prepares
Firing table generating apparatus arranges difference according to parameter and realizes automation computing function, firing table data computation module is used and the fire control computer identical aerodynamic parameter of firing table that prestores, and complete non-standard firing table data calculating by different operating mode influence factors, concrete influence factor comprises bullet initial velocity, bullet weight, bullet feature area and length, mass eccentricity, wind direction, wind speed, height above sea level, wherein, the medicine temperature that bullet initial velocity is known by inference by environment temperature obtains, bullet weight, bullet feature area and length, mass eccentricity is manually inputted according to the concrete civilian interceptor bullet type using, wind direction, wind speed, the measured value that height above sea level adopts Command Control Equipment to send.Computational process selects ballistic data corresponding to each influence factor to calculate step-length according to actual needs, select initial velocity, wind speed to be spaced apart 1m/s, mass eccentricity is spaced apart 1%, and height above sea level is spaced apart 100m, and firing table generating apparatus finally completes the preparation of non-standard firing table data.
The 5th step corrected parameter acquisition module completes trajectory corrected parameter and calculates
, bullet feature area heavy at bullet initial velocity, bullet and length, mass eccentricity, wind direction, wind speed, height above sea level are all in fixed situation, the basic relevant parameter of ballistic data comprises the elevation angle and flight time, therefore, adopt and about the expression formula of the initial elevation angle and time, the ballistic data under non-standard condition is revised, concrete form is as follows:
(1)
Wherein,
for trajectory under non-standard condition exists
the X-axis coordinate in moment,
for trajectory under standard conditions exists
the X-axis coordinate in moment,
for the initial elevation angle,
for projectile time of flight,
,
,
for corrected parameter to be asked.Corrected parameter acquisition module, by the ballistic data substitution formula (1) under ballistic data and non-standard condition under standard conditions, can obtain parameter
,
,
.The corrected parameter obtain manner of Y-axis, Z axis coordinate and the same X-axis of formula form.Corrected parameter acquisition module by the corrected parameter group of the each influence factor of correspondence of obtaining (
,
,
) in firing table generating apparatus, completing storage, firing table generating apparatus is sent to fire control computer by Ethernet.
The 6th step fire control computer completes the application of trajectory corrected parameter
Use first, ground trajectory update the system obtains after trajectory corrected parameter, using, bullet type is constant, and the meteorological condition of environment for use and geographic latitude do not exceed in the situation of preset range, the trajectory corrected parameter that fire control computer sends according to the firing table generating apparatus receiving carries out Firing data calculation application.
So far realized the correction of civilian interceptor trajectory.
Claims (1)
1. a civilian interceptor trajectory modification method, is characterized in that the concrete steps of this method are:
The first step is disposed ground trajectory update the system
Ground trajectory update the system, comprising: Command Control Equipment, fire control computer, firing table generating apparatus, meteorological measuring arrangement, aerodynamic parameter extraction module, firing table data computation module and corrected parameter acquisition module; Described meteorological measuring arrangement, comprising: temperature sensor and airspeedometer, and temperature sensor is placed on Command Control Equipment and is fixedly connected with airspeedometer; Command Control Equipment, fire control computer, firing table generating apparatus work alone separately, be connected and carry out information interaction between Command Control Equipment and firing table generating apparatus by Ethernet; Between fire control computer and firing table generating apparatus, be connected by Ethernet and carry out information interaction; Command Control Equipment is connected by universal serial bus with meteorological measuring arrangement and carries out information interaction; Aerodynamic parameter extraction module resides in fire control computer, for completing the extraction of various civilian interceptor aerodynamic parameter; Firing table data computation module resides in firing table generating apparatus, for completing the calculating of non-standard operating mode firing table data; Corrected parameter acquisition module resides in firing table generating apparatus, for obtaining the trajectory corrected parameter of corresponding bullet type;
Second step aerodynamic parameter extraction module completes standard firing table data acquisition
Aerodynamic parameter extraction module is according to actual measurement exterior ballistic test data, carry out Aerodynamic Parameter Identification in conjunction with CFD Numerical Wind Tunnel data and engineering calculation result, by theory of solving trajectory in theoretical definite aerodynamic parameter substitution outer trajectory equation group, determine that a launch velocity is as service velocity, aerodynamic parameter extraction module completes the calculating that meets to trajectory under the condition of the different elevations angle, and using obtained ballistic data as standard firing table data, deposit in fire control computer;
The 3rd step Command Control Equipment obtains local meteorological condition and geographic latitude
Command Control Equipment gathers local environment temperature, wind speed and direction by meteorological measuring arrangement, and determine accordingly the medicine temperature scope of application and the wind speed scope of application, the local geographic latitude information of artificial input, and be converted to height above sea level information, Command Control Equipment by Ethernet by environment temperature, wind speed, wind direction, height above sea level communication to firing table generating apparatus;
The 4th step firing table generating apparatus completes non-standard firing table data and prepares
Firing table generating apparatus arranges difference according to parameter and realizes automation computing function, firing table data computation module is used and the fire control computer identical aerodynamic parameter of firing table that prestores, and complete non-standard firing table data calculating by different operating mode influence factors, concrete influence factor comprises bullet initial velocity, bullet weight, bullet feature area and length, mass eccentricity, wind direction, wind speed, height above sea level, wherein, the medicine temperature that bullet initial velocity is known by inference by environment temperature obtains, bullet weight, bullet feature area and length, mass eccentricity is manually inputted according to the concrete civilian interceptor bullet type using, wind direction, wind speed, the measured value that height above sea level adopts Command Control Equipment to send, computational process selects ballistic data corresponding to each influence factor to calculate step-length according to actual needs, and firing table generating apparatus finally completes the preparation of non-standard firing table data,
The 5th step corrected parameter acquisition module completes trajectory corrected parameter and calculates
, bullet feature area heavy at bullet initial velocity, bullet and length, mass eccentricity, wind direction, wind speed, height above sea level are all in fixed situation, the basic relevant parameter of ballistic data comprises the elevation angle and flight time, therefore, adopt and about the expression formula of the initial elevation angle and time, the ballistic data under non-standard condition is revised, concrete form is as follows:
(1)
Wherein,
for trajectory under non-standard condition exists
the X-axis coordinate in moment,
for trajectory under standard conditions exists
the X-axis coordinate in moment,
for the initial elevation angle,
for projectile time of flight,
,
,
for corrected parameter to be asked; Corrected parameter acquisition module, by the ballistic data substitution formula (1) under ballistic data and non-standard condition under standard conditions, obtains parameter
,
,
; The corrected parameter obtain manner of Y-axis, Z axis coordinate and the same X-axis of formula form; Corrected parameter acquisition module by the corrected parameter group of the each influence factor of correspondence of obtaining (
,
,
) in firing table generating apparatus, completing storage, firing table generating apparatus is sent to fire control computer by Ethernet;
The 6th step fire control computer completes the application of trajectory corrected parameter
Use first, ground trajectory update the system obtains after trajectory corrected parameter, using, bullet type is constant, and the meteorological condition of environment for use and geographic latitude do not exceed in the situation of preset range, the trajectory corrected parameter that fire control computer sends according to the firing table generating apparatus receiving carries out Firing data calculation application;
So far realized the correction of civilian interceptor trajectory.
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| CN104154818B (en) * | 2014-07-25 | 2016-01-20 | 北京机械设备研究所 | A kind of launching without control hits angle determination method |
| CN104457744B (en) * | 2014-12-18 | 2018-04-27 | 扬州天目光电科技有限公司 | Hand-held target detecting instrument and its method for detecting and ballistic solution method |
| CN105095661A (en) * | 2015-08-07 | 2015-11-25 | 路伟志 | Sniper ballistic calculating system |
| CN105550497B (en) * | 2015-12-04 | 2018-07-24 | 河海大学 | A kind of high-precision projectile correction method |
| CN107194111B (en) * | 2017-06-06 | 2020-12-18 | 中北大学 | Projectile full trajectory optimization design method based on ISIGIT software |
| CN110162735B (en) * | 2019-07-04 | 2023-07-14 | 北京缔科新技术研究院(有限合伙) | Ballistic trajectory calculation method and system based on laser ranging telescope |
| CN111539131B (en) * | 2020-05-29 | 2023-10-27 | 于浩 | Shooting data resolving method, resolver and self-propelled antiaircraft gun |
| CN112711816B (en) * | 2021-03-26 | 2021-06-29 | 南京信息工程大学 | Flight projectile trajectory correction method based on meteorological grid |
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| US5464174A (en) * | 1993-11-25 | 1995-11-07 | Aerospatiale Societe Nationale Industrielle | Air defence system and defence missile for such a system |
| JP5283861B2 (en) * | 2007-06-01 | 2013-09-04 | 株式会社東芝 | Unit operation system |
| CN102087082A (en) * | 2010-11-22 | 2011-06-08 | 北京机械设备研究所 | Firing table fitting-based low-altitude low-speed small object intercepting method |
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