CN108983214B - Radar seeker target selection method - Google Patents

Radar seeker target selection method Download PDF

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CN108983214B
CN108983214B CN201810411958.8A CN201810411958A CN108983214B CN 108983214 B CN108983214 B CN 108983214B CN 201810411958 A CN201810411958 A CN 201810411958A CN 108983214 B CN108983214 B CN 108983214B
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target
distance
scanning
seeker
azimuth
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CN108983214A (en
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吴迪
马瑞
薛安翔
刘辉
张都川
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Xian Electronic Engineering Research Institute
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/66—Radar-tracking systems; Analogous systems
    • G01S13/72—Radar-tracking systems; Analogous systems for two-dimensional tracking, e.g. combination of angle and range tracking, track-while-scan radar

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

The invention discloses a target selection method for a radar seeker, which is used for accurately selecting a target under a complex background. According to the characteristics that the pitching wave beam coverage range is large and the range from the wave gate is small when the seeker flies, the invention realizes the calculation of the relative spatial distance by utilizing the target information provided by the onboard computer and the target information detected by the radar seeker, thereby achieving the purpose of correctly selecting the target. The invention overcomes the problem that the radar seeker cannot correctly select the target due to inaccurate missile indication information and interference of ground clutter and ground foreign matters, and the scheme is easy to realize, is suitable for the ground radar seeker and can also be applied to the sea radar seeker, and has high engineering value.

Description

Radar seeker target selection method
Technical Field
The invention belongs to the field of overall design of radar seeker, and particularly relates to a method for realizing target selection of a radar seeker.
Background
The radar seeker has the characteristics of all-time, all-weather and 'no matter what' hitting, and has attracted wide attention in air-ground missiles. Compared with aerial targets and marine targets, ground targets are greatly influenced by background clutter and can face the interferences of ground clutter, ground foreign matters, various buildings and the like, so that the seeker is required to have stronger target selection capability. The existing radar seeker generally adopts a target selection mode distance selection area method and an extended search map selection method, the basic idea is that a target closest to a preset set point is selected preferentially, due to the influences of factors such as thrust eccentricity, aerodynamic asymmetry, wind gust and measurement errors of inertial devices, the actual trajectory and the ideal trajectory of a missile may have a certain deviation, bound target information and actual target information also have a deviation, interference of ground clutter and ground foreign matters on the radar seeker is caused, and a correct target cannot be selected.
Disclosure of Invention
Technical problem to be solved
The invention solves the main problem that a radar seeker cannot correctly select a target due to inaccurate missile indication information and interference of ground clutter and ground foreign matters, and provides a target selection method easy for engineering realization aiming at the working characteristics of the radar seeker.
Technical scheme
A radar seeker target selection method is characterized by comprising the following steps:
step 1: the on-missile computer provides missile target distance information, azimuth pointing frame angle information and pitching pointing frame angle information relative to the target to the guide head in real time;
step 2: after the guide head is unlocked, entering a searching working mode, setting a corresponding distance searching wave gate by the guide head according to target distance information bound by the pop-up computer, and starting pitching dimensional scanning and azimuth dimensional scanning by taking a binding angle as a center;
and step 3: during azimuth dimension scanning, the shot-to-eye distance and azimuth frame angle of each detected target exceeding a detection threshold are recorded, and after each scanning period is finished, the relative spatial distance c between the position of each detected target and the position of the target sent by a pop-up control computer at the current moment is calculated according to the following methodi；
Figure BDA0001648313260000021
Figure BDA0001648313260000022
Figure BDA0001648313260000023
Wherein: r is0Providing a bullet distance relative to the target for the guidance head of the computer on the bullet;
rithe shot-eye distance of the ith target detected by the seeker;
az0an azimuth pointing frame angle is provided for the guidance head of the computer on the missile;
azimonitored for seekerThe bullet distance of i targets;
and 4, step 4: selecting a target with the minimum relative spatial distance calculation result value as a tracking target;
and 5: after the target is searched, intercepting and confirming, switching to a tracking stage, and stopping scanning; if the target cannot be searched, the scanning is continued.
And in the step 3, the scanning speed is 40 degrees/s, the scanning range is plus or minus 6 degrees, and the scanning period is 0.3 s.
Advantageous effects
The invention overcomes the problem that the radar seeker does not correctly select the target under the condition of inaccurate missile indication information and ground clutter and ground foreign matter interference, and the scheme is easy to realize, is suitable for the ground radar seeker and can also be applied to the radar seeker, and has high engineering value.
Detailed Description
During missile flight, the on-missile computer provides missile target distance information, azimuth pointer frame angle information, elevation pointer frame angle information and other relevant target indication information relative to the target to the guide head in real time.
After the seeker is started up to work, the pitching dimensional scanning and the azimuth dimensional scanning are started by taking the bound target distance and angle as the center. During the azimuth dimension scanning, the target distance information and the angle information which exceed the detection threshold are respectively stored, and after each scanning period is finished, the detected target distance information and the detected angle information are processed according to the following method:
Figure BDA0001648313260000031
Figure BDA0001648313260000032
Figure BDA0001648313260000033
wherein: r is0Providing a target phase for a computer-guided leader on a projectileDistance of bullet eyes
riFor the shot-to-eye distance of the ith target detected by the seeker
az0Azimuth pointing frame angle for computer-guided leader on a projectile
aziShot-to-shot distance of ith target monitored by seeker
ciComputing results for relative spatial distances
The detected azimuth information of the ith target and the azimuth pointing frame angle information bound by the computer on the missile in real time are subtracted, and the difference is multiplied by the relative missile-eye distance information of the target bound by the computer on the missile at the moment to obtain a parameter ai(ii) a Meanwhile, the detected ith target bullet distance is compared with the target relative bullet distance information bound by the computer on the bullet to obtain a parameter bi(ii) a According to the parameter aiAnd parameter biThe relative spatial distance c can be obtainedi. After calculation, c is selectediAnd the target with the minimum value is taken as a tracking target.
Example (b):
1. and the missile-borne control computer sends an unlocking instruction to the radar seeker, and the radar seeker enters a search mode after responding to the unlocking instruction.
2. When the radar seeker is in a search mode, the missile-borne control computer sends position information (including the shot-to-shot distance, the azimuth pointing frame angle and the elevation pointing frame angle) of a target to the radar seeker every 10 ms. After receiving the target position information, the radar seeker sets a range wave gate within a range of plus or minus 225m by taking the shot-to-eye distance as the center of the range wave gate, controls an antenna to carry out triangular scanning in the azimuth dimension by taking an azimuth pointing frame angle and a pitching pointing frame angle as angle centers, and controls the scanning speed to be 40 degrees/s, the maximum scanning range to be plus or minus 6 degrees, and the maximum scanning period to be 0.3 s.
3. When the radar seeker is in a search mode, the position information (including the shot-eye distance, the azimuth frame angle and the elevation frame angle) of each detection target is recorded, and the relative space distance between the position of each detection target and the target position sent by the pop-up control computer at the current moment is calculated.
4. When the radar seeker is in a search mode, once scanning of one scanning period is completed, target selection is carried out, and a detection target with the smallest relative space distance between the position of the detection target and the position of the target sent by the missile-borne control computer is selected to serve as a target to be intercepted.

Claims (2)

1. A radar seeker target selection method is characterized by comprising the following steps:
step 1: the on-missile computer provides missile target distance information, azimuth pointing frame angle information and pitching pointing frame angle information relative to the target to the guide head in real time;
step 2: after the guide head is unlocked, entering a searching working mode, setting a corresponding distance searching wave gate by the guide head according to target distance information bound by the pop-up computer, and starting pitching dimensional scanning and azimuth dimensional scanning by taking a binding angle as a center;
and step 3: during azimuth dimension scanning, the shot-to-eye distance and azimuth frame angle of each detected target exceeding a detection threshold are recorded, and after each scanning period is finished, the relative spatial distance c between the position of each detected target and the position of the target sent by a pop-up control computer at the current moment is calculated according to the following methodi；
Figure FDA0001648313250000011
ai＝r0*(azi-az0)/57.3
bi＝ri-r0
Wherein: r is0Providing a bullet distance relative to the target for the guidance head of the computer on the bullet;
rithe shot-eye distance of the ith target detected by the seeker;
az0an azimuth pointing frame angle is provided for the guidance head of the computer on the missile;
azithe shot-to-eye distance of the ith target monitored by the seeker;
and 4, step 4: selecting a target with the minimum relative spatial distance calculation result value as a tracking target;
and 5: after the target is searched, intercepting and confirming, switching to a tracking stage, and stopping scanning; and if the target cannot be searched, continuing to scan.
2. The method of claim 1, wherein step 3 comprises a scanning speed of 40 °/s, a scanning range of plus or minus 6 °, and a scanning period of 0.3 s.
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CN110440793A (en) * 2019-06-14 2019-11-12 上海航天控制技术研究所 A kind of target motion information estimation method based on target seeker metrical information

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CN103529437A (en) * 2013-10-15 2014-01-22 西安电子科技大学 Method used for captive-balloon-borne phased array radar to distinguish open space targets under multi-target condition
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EP1213559A2 (en) * 2000-12-07 2002-06-12 Rafael Armament Development Authority Ltd. Method for operating an air-to-air missile and corresponding missile with autonomous or semi-autonomous modes
CN102878872A (en) * 2012-08-07 2013-01-16 中国航天空气动力技术研究院 Guidance information processing method aiming at seeker loss-of-lock conditions
GB201300848D0 (en) * 2013-01-15 2013-07-24 Mbda Uk Ltd A missile seeker and guidance method
CN103529437A (en) * 2013-10-15 2014-01-22 西安电子科技大学 Method used for captive-balloon-borne phased array radar to distinguish open space targets under multi-target condition
CN107203770A (en) * 2017-05-27 2017-09-26 上海航天控制技术研究所 A kind of optics strapdown seeker image tracking method

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