Method and apparatus for estimating position of missile

Patent metadata

Field	Value
Publication number	US-11243306-B2
Application number	US-201916674984-A
Country	US
Kind code	B2
Filing date	Nov 5, 2019
Priority date	Feb 28, 2019
Publication date	Feb 8, 2022
Grant date	Feb 8, 2022

Abstract

In a method for estimating a position of a missile, an incident angle of a signal of a radar irradiated to the moving missile is calculated. The incident angle is defined by an angle between a measurement vector indicating a direction from the radar toward the missile and a movement vector indicating a moving direction of the missile. A distance compensation value from a point on a surface of the missile to an origin point of the missile is calculated based on the calculated incident angle. A distance from the radar to the origin point of the missile is calculated based on the calculated distance compensation value and a distance from the radar to the point on the surface of the missile. A position of the missile is estimated based on a position of the radar and the calculated distance from the radar to the origin point of the missile.

First claim

What is claimed is:

1. A method for estimating a position of a missile, the method comprising:
modeling a shape of a missile;
calculating an incident angle of a signal of a radar irradiated to the moving missile, the incident angle being defined by an angle between a measurement vector indicating a direction from the radar toward the missile and a movement vector indicating a moving direction of the missile;
calculating a distance compensation value from an irradiated point on a surface of the missile to an origin point of the missile based on the calculated incident angle;
calculating a distance from the radar to the origin point of the missile based on the calculated distance compensation value and a distance from the radar to the irradiated point on the surface of the missile; and
estimating a position of the missile based on a position of the radar and the calculated distance from the radar to the origin point of the missile.

2. The method of claim 1 , wherein said modeling comprises:
modeling the missile to have a conical head and a cylindrical body such that a base surface of the conical head and one of base surfaces of the cylindrical body contact with each other;
modeling the conical head such that a vertex of the conical head is apart from the base surface of the conical head by a predetermined distance;
modeling the cylindrical body such that the remaining portion of the missile becomes the cylindrical body; and
determining a center point of said one of the base surfaces of the cylindrical body as the origin point of the missile.

3. The method of claim 2 , wherein in said calculating a distance compensation value, the distance compensation value is calculated based on a range of the incident angle.

4. The method of claim 3 , wherein the distance compensation value is calculated based on predetermined equations, where the predetermined equations include:

0
≤
θ
≤
β

,

R
c

=

b

cos
⁢

⁢
θ

;

β
≤
θ
≤
90

,

R
c

=

c
×

cos
⁡

(

θ
-
β

)

;

90
≤
θ
≤

(

90
+
α

)

,

R
c

=

r
×

cos
⁡

(

θ
-
90

)

;

and
⁢

(

90
+
α

)

≤
θ
≤
180

,

R
c

=

a
×

sin
⁡

(

θ
-
90

)

,

where θ is the incident angle, β is an angle formed by a slope line extending from the origin point of the missile to one point on a circumference of the other of the base surfaces of the cylindrical body and a center line perpendicular to the base surfaces and penetrating through the origin point, R c is the distance compensation value, b is a height of the cylindrical body, c is a length of the slope line, α is an angle formed by the center line and a lateral surface of the conical head, r is a radius of the base surface of the conical head, and a is a height of the conical head.

5. The method of claim 1 , wherein the radar includes a first radar, a second radar and a third radar which are located at different positions,
wherein the measurement vector includes a first measurement vector indicating a direction from the first radar toward the missile, a second measurement vector indicating a direction from the second radar toward the missile, and a third measurement vector indicating a direction from the third radar toward the missile, and
wherein the incident angle includes a first incident angle between the movement vector and the first measurement vector, a second incident angle between the movement vector and the second measurement vector and a third incident angle between the movement vector and the third measurement vector.

6. The method of claim 5 , wherein the distance compensation value is calculated for each radar based on the first, second and third incident angles.

7. The method of claim 6 , wherein said calculating the distance from the radar to the origin point of the missile includes calculating a distance from each radar to the origin point of the missile based on the distance compensation value for each radar and a distance from each radar to the irradiated point on the surface of the missile.

8. The method of claim 7 , wherein said estimating a position of the missile is performed based on a position of each radar and the distance from each radar to the origin point of the missile.

9. An apparatus for estimating a position of a missile, the apparatus comprising:
a modeling unit configured to model a shape of a missile;
an incident angle calculating unit configured to calculate an incident angle of

Assignees

• Agency Defense Dev

Inventors

• Yang Jae-Won
• Ryu Chung-Ho
• Lee Dong-Ju

Classifications

• G01S13/88

  Radar or analogous systems specially adapted for specific applications (electromagnetic prospecting or detecting of objects, e.g. near-field detection, G01V3/00) · CPC title

• G01S13/42 Primary

  Simultaneous measurement of distance and other co-ordinates (indirect measurement G01S13/46) · CPC title

• F42B15/00

  Self-propelled projectiles or missiles, e.g. rockets; Guided missiles (F42B10/00, F42B12/00, F42B14/00 take precedence; for practice or training F42B8/12; rocket torpedoes F42B17/00; marine torpedoes F42B19/00; cosmonautic vehicles B64G; jet-propulsion plants F02K) · CPC title

• G01S7/40

  Means for monitoring or calibrating · CPC title

• G01S13/878

  Combination of several spaced transmitters or receivers of known location for determining the position of a transponder or a reflector (G01S13/874 takes precedence) · CPC title