U.S. patent application number 13/851107 was filed with the patent office on 2013-11-21 for low-altitude low-speed small target intercepting method based on firing table fitting.
This patent application is currently assigned to BEIJING MECHANICAL EQUIPMENT INSTITUTE. The applicant listed for this patent is BEIJING MECHANICAL EQUIPMENT INSTITUTE. Invention is credited to Xuchang DING, Jiahui LI, Yan SHEN, Lianjun WANG, Shengjie WANG, Xiaojun WANG, Nuo XU, Hongliang YAN.
Application Number | 20130311078 13/851107 |
Document ID | / |
Family ID | 44098988 |
Filed Date | 2013-11-21 |
United States Patent
Application |
20130311078 |
Kind Code |
A1 |
DING; Xuchang ; et
al. |
November 21, 2013 |
LOW-ALTITUDE LOW-SPEED SMALL TARGET INTERCEPTING METHOD BASED ON
FIRING TABLE FITTING
Abstract
Systems and methods based on firing table fitting allow
interception of a small low-altitude low-velocity target. A system
includes: a target detecting system, a directing control system, a
launch control system, an interception execution system, a
communication bus a, a communication bus b and a communication bus
c. Firing table data under a standard working condition and fitting
parameters under different working conditions are pre-stored in the
system. Based on target flight data and environment condition
parameters, a lead aiming point is predicted, a time sequence of
each stage of a fight flow is controlled, and firing data are
output to execute an interception by the launch control system. An
interception operation is simplified, a ground control of a
non-controlled bomb fight flow is realized, a single shot success
probability of an interception system is increased, and an
interception cost is reduced.
Inventors: |
DING; Xuchang; (Beijing,
CN) ; XU; Nuo; (Beijing, CN) ; WANG;
Shengjie; (Beijing, CN) ; SHEN; Yan; (Beijing,
CN) ; WANG; Lianjun; (Beijng, CN) ; WANG;
Xiaojun; (Beijing, CN) ; LI; Jiahui; (Beijing,
CN) ; YAN; Hongliang; (Beijng, CN) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
BEIJING MECHANICAL EQUIPMENT INSTITUTE; |
|
|
US |
|
|
Assignee: |
BEIJING MECHANICAL EQUIPMENT
INSTITUTE
Beijing
CN
|
Family ID: |
44098988 |
Appl. No.: |
13/851107 |
Filed: |
March 27, 2013 |
Related U.S. Patent Documents
|
|
|
|
|
|
Application
Number |
Filing Date |
Patent Number |
|
|
PCT/CN2011/076636 |
Jun 30, 2011 |
|
|
|
13851107 |
|
|
|
|
Current U.S.
Class: |
701/302 |
Current CPC
Class: |
G05D 1/12 20130101; F41H
11/02 20130101; F41G 3/06 20130101; F41G 5/08 20130101; F41G 3/08
20130101 |
Class at
Publication: |
701/302 |
International
Class: |
G05D 1/12 20060101
G05D001/12 |
Foreign Application Data
Date |
Code |
Application Number |
Nov 22, 2010 |
CN |
201010553163.4 |
Claims
1. A method based on firing table fitting for intercepting a small
target with low altitude and low velocity by a turret type
intercepting system, wherein the system comprises: a target
detecting system, a directing control system, a launch control
system, an interception execution system, a communication bus a, a
communication bus b and a communication bus c, the target detecting
system connected with the directing control system via the
communication bus a, the launch control system connected with the
directing control system via the communication bus b, a firing
table loaded in a fire control computer of the launch control
system, and the interception execution system connected with the
launch control system via the communication bus c, characterized in
that specific realization steps include: step 1, obtaining target
data information by the target detecting system, comprising:
determining a target state and obtaining a target flight data
including a flight height, a distance, an azimuth angle and a pitch
angle by the target detecting system, sending the target state and
the target flight data to the directing control system via the
communication bus a, sending the target flight data and environment
condition parameters including a temperature, an altitude, a wind
speed and a wind direction to the launch control system via the
communication bus b by the directing control system; step 2,
predicting a lead aiming point by the launch control system,
comprising: calculating a flight path of the target by the fire
control computer based on the target flight data and environment
condition parameters received, and calculation formulas as: V x = x
t = D S t cos S cos .beta. S - S t D S sin S cos .beta. S - .beta.
S t D S cos S sin .beta. S ( 1 ) V y = y t = D S t cos S sin .beta.
S - S t D S sin S sin .beta. S + .beta. s t D S cos S cos .beta. S
( 2 ) V z = z t = D S t sin S + S t D S cos S ( 3 ) ##EQU00005##
where D.sub.s is a target slant range, .epsilon..sub.s is a target
pitch angle, and .beta..sub.s is a target azimuth angle; predicting
a lead aiming point of a flight of the target with a
three-dimensional spatial calculation by the launch control system,
and a calculation formula as, where a subscript "S" represents an
initial position, and a flight time t.sub.f is determined according
to an estimated value in a pre-stored firing table: { D cos
cos.beta. - D S cos S - V x t f = 0 D sin - D S sin S - V y t f = 0
D cos sin.beta. - V z t f = 0 t f = f ( D ) ( 4 ) ##EQU00006## step
3, controlling a time sequence of each stage of a fight flow by the
launch control system, comprising: after an extraction of an
aerodynamics parameter and a statistical comparison of an actual
ballistic experimental data based on multi-projection angle and
multi-environment working condition, obtaining firing table data
under both a standard weather condition and a nonstandard weather
condition, pre-storing the firing table data under the standard
weather condition by the launch control system, and according to
different environmental influence factors including the
temperature, the altitude, the wind speed and the wind direction,
storing the firing table data under the nonstandard weather
condition by means of fitting parameters; searching a corresponding
fitting parameter according to the environmental influence factors
by the fire control computer, obtaining an actual working condition
firing table from a pre-stored standard firing table, inquiring the
firing table according to the lead aiming point to complete an
interpolation calculation, thus obtaining an encounter time between
a bullet and the target, a response time of the interception
execution system and a start time of a warhead for binding a
missile-borne computer; step 4, outputting firing data to execute
an interception by the launch control system, comprising: according
to the lead aiming point, using a spatial grid obtained from the
firing table data to determine an effective intercepting ballistic
trajectory by the fire control computer, outputting the firing data
subsequent to a comparison of an initial position of the
interception execution system, sending the firing data to the
interception execution system via the communication bus c, the
launch control system entering a nonreversible launch flow, and
outputting a firing current to start launching by a launch
execution structure in the launch control system; up to now,
completing the interception of the small target with low altitude
and low velocity based on firing table fitting.
2. (canceled)
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] The present application is a continuation of
PCT/CN2011/076636, filed Jun. 30, 2011, which claims priority to
Chinese Patent Application No. 201010553163.4, filed Nov. 22, 2010,
now Chinese Patent No. 201010553163.4. The disclosures of these
references are hereby incorporated by reference in their
entirety.
FIELD
[0002] The present disclosure relates to a method for intercepting
a target in an airspace, and more particularly to a method based on
firing table fitting for intercepting a small target with low
altitude and low velocity.
BACKGROUND
[0003] A small target with low altitude and low velocity primarily
constitutes a threat or destructive attack to important activities
or large-scale gatherings. Because there is no effective means to
defense such type of targets, conventional weapons such as a
shotgun or large weapons such as an antiaircraft gun and an
anti-aircraft missile are generally used to carry out security
defense. However, the above methods have the following
disadvantages.
[0004] (1) an effective range of a firearm is limited, and a
quality requirement to an operator is high, and thus it is
difficult to ensure an effective interception to a target in an
airspace.
[0005] (2) a single shot success probability of the antiaircraft
gun is relative low, so that generally multiple antiaircraft gun
cooperation and multiple continuous shootings are required in order
to shoot the target.
[0006] (3) although a single shot success probability of the
anti-aircraft missile is high, usage and maintenance costs are
relative high, resulting in a low return on investment.
[0007] (4) all the above weapons are destructive so that it is not
suitable to be used in crowed areas. Moreover, noise, flash and
smoke released by the weapons at a moment of shooting may cause a
scare, and wreckages of the weapons may endanger people.
[0008] Therefore, with a principle of ballistic attack by the
antiaircraft gun and a method for controlling firepower, influences
of the noise, the flash and the smoke given by the weapons at a
moment of shooting on an environment is reduced, an attack mode of
a warhead is thus changed, and a special requirement of an usage
environment may be satisfied. However, a single shot success
probability of the method is relatively low in the case of low
shooting speed of an ammunition, and it is impossible to perform a
time sequence control on a non-controlled ammunition battle flow,
and on the warhead.
SUMMARY
[0009] The present disclosure is aimed to provide a method based on
firing table fitting for intercepting a small target with low
altitude and low velocity to solve problems of low single shot
success probability of an antiaircraft gun and no time sequence
control on a non-controlled bomb fight flow and a warhead.
[0010] A method based on firing table fitting for intercepting a
small target with low altitude and low velocity is realized by a
turret type intercepting system. The system comprises: a target
detecting system, a directing control system, a launch control
system, an interception execution system, a communication bus a, a
communication bus b and a communication bus c. The target detecting
system is connected with the directing control system via the
communication bus a, the launch control system is connected with
the directing control system via the communication bus b, a firing
table is loaded in a fire control computer of the launch control
system, and the interception execution system is connected with the
launch control system via the communication bus c.
[0011] The method comprises steps of:
[0012] step 1, obtaining target data information by the target
detecting system, comprising:
[0013] determining a target state and obtaining target flight data
including a flight height, a distance, an azimuth angle, and a
pitch angle by the target detecting system, sending the target
state and the target flight data to the directing control system
via the communication bus a, sending the target flight data and
environment condition parameters including a temperature, an
altitude, a wind speed and a wind direction to the launch control
system via the communication bus b by the directing control
system;
[0014] step 2, predicting a lead aiming point by the launch control
system, comprising:
[0015] calculating a flight path of the target by the fire control
computer of the launch control system based on the target flight
data and environment condition parameters received, wherein the
calculation formulas include:
V x = x t = D s t cos S cos .beta. S - s t D S sin S cos .beta. S -
.beta. s t D S cos sin.beta. S ( 1 ) V y = y t = D s t cos S sin
.beta. S - s t D S sin S sin .beta. S + .beta. s t D S cos S cos
.beta. S ( 2 ) V z = z t = S t sin S + S t D S cos S ( 3 )
##EQU00001##
[0016] where D.sub.s is a target slant range, .epsilon..sub.s is a
target pitch angle, and .beta..sub.s is a target azimuth angle;
[0017] predicting a lead aiming point of a flight of the target
with a three-dimensional spatial calculation by the launch control
system, and a calculation formula is:
{ D cos cos.beta. - D S cos S - V x t f = 0 D sin - D S sin S - V y
t f = 0 D cos sin.beta. - V z t f = 0 t f = f ( D ) ( 4 )
##EQU00002##
[0018] where a subscript "s" represents an initial position, D is a
target slant range of the lead aiming point, .epsilon. is a target
pitch angle of the lead aiming point, .beta. is a target azimuth
angle of the lead aiming point, and a flight time t.sub.f is
determined according to an estimated value in a pre-stored firing
table and is a function of D;
[0019] step 3, controlling a time sequence of each stage of a fight
flow by the launch control system, comprising:
[0020] after an extraction of an aerodynamics parameter and a
statistical comparison of an actual ballistic experimental data
based on multi-projection angle and multi-environment working
condition, obtaining firing table data under both a standard
weather condition and a nonstandard weather condition, pre-storing
the firing table data under the standard weather condition by the
launch control system, and according to different environmental
influence factors including the temperature, the altitude, the wind
speed and the wind direction, storing the firing table data under
the nonstandard weather condition by means of fitting
parameters;
[0021] searching a corresponding fitting parameter according to the
environmental influence factors by the fire control computer of the
launch control system, obtaining an actual working condition firing
table from a pre-stored standard firing table, inquiring the firing
table according to the lead aiming point calculated by the launch
control system to complete an interpolation calculation, thus
obtaining an encounter time between a bullet and the target, a
response time of the interception execution system and a start time
of a warhead for binding a missile-borne computer;
[0022] step 4, outputting firing data to execute an interception by
the launch control system, comprising:
[0023] according to the lead aiming point, using a spatial grid
obtained from the firing table data to determine an effective
intercepting ballistic trajectory by the fire control computer of
the launch control system, outputting the firing data subsequent to
a comparison of an initial position of the interception execution
system, sending the firing data to the interception execution
system via the communication bus c, the launch control system
entering a nonreversible launch flow, and outputting a firing
current to start launching by a launch execution structure in the
launch control system.
[0024] Up to now, the interception of the small target with low
altitude and low velocity based on firing table fitting is
completed.
[0025] With the method according to embodiments of the present
disclosure, an interception and an operation of the small target
with low altitude and low velocity is simplified, a ground control
of a non-controlled bomb fight flow is realized, a single shot
success probability of an interception system is increased, and an
interception cost is lowered.
DETAILED DESCRIPTION
[0026] A method based on firing table fitting for intercepting a
small target with low altitude and low velocity is realized by a
turret type intercepting system. The system comprises: a target
detecting system, a directing control system, a launch control
system, an interception execution system, a communication bus a, a
communication bus b and a communication bus c. The target detecting
system is connected with the directing control system via the
communication bus a, the launch control system is connected with
the directing control system via the communication bus b, a firing
table is loaded in a fire control computer of the launch control
system, and the interception execution system is connected with the
launch control system via the communication bus c.
[0027] The method comprises the following steps.
[0028] In step 1, target data information is obtained by the target
detecting system.
[0029] Specifically, a target state is determined and a target
flight data is obtained by the target detecting system. The target
flight data includes: a flight height, a distance, an azimuth angle
and a pitch angle. Then the target state and the target flight data
are sent to the directing control system via the communication bus
a. Then the target flight data and environment condition parameters
including a temperature, an altitude, a wind speed and a wind
direction are sent to the launch control system via the
communication bus b by the directing control system.
[0030] In step 2, a lead aiming point is predicted by the launch
control system.
[0031] Specifically, a flight path of the target is calculated by
the fire control computer based on the target flight data and
environment condition parameters received. Calculation formulas may
be as follows:
V x = x t = D S t cos S cos .beta. S - S t D S sin S cos .beta. S -
.beta. S t D S cos S sin .beta. S ( 1 ) V y = y t = D S t cos S sin
.beta. S - s t D S sin S sin .beta. S + .beta. S t D S cos S cos
.beta. S ( 2 ) V z = z t = D S t sin S + S t D S cos S ( 3 )
##EQU00003##
[0032] where D.sub.s is a target slant range, .epsilon..sub.s is a
target pitch angle, and .beta..sub.s is a target azimuth angle.
[0033] Then, a lead aiming point of a flight of the target is
predicted with a three-dimensional spatial calculation by the
launch control system. A calculation formula may be as follows:
{ D cos cos.beta. - D S cos S - V x t f = 0 D sin - D S sin S - V y
t f = 0 D cos sin.beta. - V z t f = 0 t f = f ( D ) ( 4 )
##EQU00004##
[0034] where a subscript "s" represents an initial position, D is a
target slant range of the lead aiming point, .epsilon. is a target
pitch angle of the lead aiming point, .beta. is a target azimuth
angle of the lead aiming point, and a flight time t.sub.f is
determined according to an estimated value in a pre-stored firing
table and is a function of D.
[0035] In step 3, a time sequence of each stage of a fight flow is
controlled by the launch control system.
[0036] Specifically, after an extraction of an aerodynamics
parameter and a statistical comparison of an actual ballistic
experimental data based on multi-projection angle and
multi-environment working condition, firing table data under both a
standard weather condition and a nonstandard weather condition is
obtained. Then only the firing table data under the standard
weather condition is pre-stored by the launch control system.
According to different environmental influence factors including
the temperature, the altitude, the wind speed and the wind
direction, the firing table data under the nonstandard weather
condition is stored by means of fitting parameters.
[0037] Then a corresponding fitting parameter is searched according
to the environmental influence factors by the fire control
computer. Then an actual working condition firing table is obtained
from a pre-stored standard firing table. Then the firing table is
inquired according to the lead aiming point to complete an
interpolation calculation, thus obtaining an encounter time between
a bullet and the target, a response time of the interception
execution system and a start time of a warhead for binding a
missile-borne computer.
[0038] In step 4, firing data is output to execute an interception
by the launch control system.
[0039] Specifically, according to the lead aiming point, a spatial
grid obtained from the firing table data is used to determine an
effective intercepting ballistic trajectory by the fire control
computer. Then the firing data is output subsequent to a comparison
of an initial position of the interception execution system. Then
the firing data is sent to the interception execution system via
the communication bus c. Finally, the launch control system enters
a nonreversible launch flow, and a firing current is output to
start launching by a launch execution structure in the launch
control system.
[0040] Up to now, the interception of the small target with low
altitude and low velocity based on firing table fitting is
completed.
* * * * *