Missile interception system

Abstract

The invention provides a missile interception system, and relates to the technical field of missile interception, through reasonable layout and clear division of labor of three radar stations A, B and C. A point A is responsible for initial detection and data transmission, a point B is responsible for launching an interception missile, and a point C is responsible for short-distance accurate command, so that the interception success rate is increased; ground projection point coordinates are measured through laser ranging and radar reflection waves, the distance between an enemy satellite and the ground and a flight path equation are calculated through the triangle principle, parameters form a sky buoy equation, accurate guidance is provided for interception, the distance between a point A and a point B is 830 kilometers, data transmission and missile launching time is ensured, and the interception efficiency is improved. The point A transmits a parameter equation to the point B and the point C after identifying the enemy satellite, the point B launches a missile and reminds the point C, the point C receives the command right after finding the missile, interference is avoided, when the enemy satellite flies again, the point B and the point C have more preparation time, and the interception rate is further increased.

Description

Technical Field

[0001] The present invention relates to the field of missile interception technology, and specifically to a missile interception system. Background Art

[0002] A missile is a high-tech weapon system that combines propulsion, guidance and control systems to accurately strike targets at long distances. Missiles are generally divided into two categories: ballistic missiles and cruise missiles, each with different flight trajectories and combat characteristics. Ballistic missiles fly at high speeds outside the atmosphere, using gravity to return to the earth and penetrate defenses; cruise missiles approach targets in the atmosphere at low altitudes similar to airplanes. Missiles need to be intercepted because they have strong destructive power and strategic deterrence. For example, ballistic missiles can carry nuclear warheads, which will cause devastating blows to the enemy once launched, so intercepting them has become an important part of strategic defense. The means of intercepting missiles include the use of interceptor missiles, high-energy lasers, electromagnetic guns, etc., with the aim of shooting down or destroying enemy missiles before they reach the target, thereby protecting one's own territory, infrastructure, military forces and the lives and property of the people. Through effective missile interception, the success rate of enemy attacks can be significantly reduced, the country's own defense capabilities can be enhanced, and national security and strategic stability can be maintained.

[0003] The existing missile interception technology has the limitation of a single radar station, which is easily interfered or attacked by the enemy, causing the radar station to malfunction and affecting the overall interception effect; the detection accuracy is insufficient, especially in complex electromagnetic environments, it is difficult to accurately determine the trajectory and speed of the target, resulting in a lower hit rate of the interception missile; the reaction time is long, and the time interval between target identification, data processing and missile launch is long, especially in close-range interception, it may not be able to respond in time, missing the best interception opportunity; the coverage is limited, ground-based interception systems usually have limited coverage, and although sea-based and air-based systems can increase the coverage, they are subject to the platform's movement speed and deployment time; the coordination capability is weak, and most of the existing systems operate independently, lacking an efficient coordination mechanism between multiple sites, and cannot achieve all-round and multi-level interception; the anti-interference capability is poor, the modern battlefield environment is complex, and the enemy may use a variety of interference methods. The existing system has weak anti-interference capability, which may cause radar data distortion or communication interruption; the flexibility is insufficient. When dealing with different types of missiles and threats from different directions, the adjustment speed and flexibility are insufficient, making it difficult to quickly adapt to battlefield changes. Summary of the invention

[0004] In view of the deficiencies of the prior art, the present invention provides a missile interception system, which solves the problems of low flexibility and interception efficiency.

[0005] To achieve the above objectives, the present invention is implemented through the following technical solutions: a missile interception system, the system comprising:

[0006] Establish a coordinate system on the ground to determine the longitude and latitude of point A and point B;

[0007] A radar and friend-or-foe satellite identification system are installed at point A, a radar and air defense missiles are installed at point B, and a close-range command radar is installed at point C;

[0008] The coordinates of the enemy satellite's projection point H on the ground are measured by the radar at point A;

[0009] Calculate the distance L between the enemy satellite and the ground, and construct the sky mark equation;

[0010] Transmit the Sky Mark equation to point B. After the radar at point B receives the attack order, it will immediately launch an air defense missile.

[0011] The radar at point C takes over command and directs the air defense missile to fly along the trajectory of the enemy satellite's sky beacon equation until it intercepts the enemy satellite.

[0012] Preferably, the distance between point A and point B is 830 kilometers, so that when the enemy satellite flies over for the second time, the radar at point B can receive the attack order in time and launch an air defense missile.

[0013] Preferably, the coordinates of the enemy satellite projection point H are measured by the following steps:

[0014] S1. Measure the distance P from point A to the enemy satellite;

[0015] S2. Measure the angle α between the radar reflection wave at point A and the ground;

[0016] S3. Calculate the length of AH by the triangle principle, AH = Pcosα;

[0017] S4. Measure the distance BD from point D to the baffle by a laser rangefinder;

[0018] S5. Calculate the length of AB,

[0019] S6. Determine the coordinates of point H.

[0020] Preferably, the distance L between the enemy satellite and the ground is calculated by the following formula:

[0021] L=Ps inα.

[0022] Preferably, the C point radar is set as follows:

[0023] Point C has 15 more latitudes than point A;

[0024] The radar at point C is used for close-range command to improve the success rate of interception.

[0025] Preferably, the latitude and longitude of point A and point B are determined as follows:

[0026] Determine the longitude and latitude of point A;

[0027] Move north 7.54 degrees of latitude to find the longitude and latitude of point B.

[0028] Preferably, when the distance from the x-axis intersection of the coordinates at point B to point B exceeds 70 kilometers, point B and point A are adjusted to re-establish the coordinate system, so as to make it more convenient for the radar operator to command the missile flight and improve the interception rate.

[0029] Preferably, issuing an attack order when the enemy satellite flies overhead again in the next cycle can improve the interception success rate so that points B and C have more preparation time.

[0030] The present invention provides a missile interception system. It has the following beneficial effects:

[0031] The invention provides a missile interception system. The invention ensures the comprehensive coverage and efficient operation of the system through the reasonable layout of three radar stations A, B and C. Point A is used for initial detection and data transmission, point B is used for launching interception missiles, and point C is used for close-range precise command. Each station has a clear functional positioning, which improves the accuracy and success rate of interception. Next, the invention introduces in detail how to calculate the flight trajectory equation of the enemy satellite through the coordinates of the ground projection point. The specific method is to use a laser rangefinder and a radar reflection wave to measure the value of the distance BD from the point D to the baffle, combine with a fixed known AD value, calculate the value of AB through the triangle principle, and then obtain AH=Pcosα and L=Ps i by measuring the angle α between A0 and AH and the distance P from the radar point to the satellite. nd, where L is the distance between the enemy satellite and the ground. These parameters constitute the sky mark equation of the enemy satellite's flight trajectory. With the sky mark equation, the present invention illustrates how to use the ground coordinate system to guide interception. Point A and Point B are 830 kilometers apart, ensuring that there is enough time for data transmission after identifying the enemy satellite at Point A and for Point B to launch a missile. In actual operation, after the system reminds point A, the radar operator immediately transmits the parameter equation to Point B and Point C. Point B immediately launches an air defense missile after receiving the attack order and sends a reminder signal to Point C. The radar at Point C immediately takes over the command after discovering the air defense missile and notifies Point B to stop issuing instructions to avoid interference. Finally, when the enemy satellite flies over again in the next cycle, an attack order is issued, and Points B and C have more preparation time, thereby improving the interception rate. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 A schematic diagram of a coordinate system established with point A as the origin in the present invention;

[0033] Figure 2 It is a schematic diagram of the ground coordinate system of the present invention;

[0034] Figure 3 This is a schematic diagram of a couplet coordinate system with points A and B as origins of the present invention;

[0035] Figure 4 It is a schematic diagram of a long-distance interception coordinate system couplet at a height of 400 kilometers above the ground according to the present invention. DETAILED DESCRIPTION

[0036] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] like Figure 1-4 As shown, an embodiment of the present invention provides a missile interception system, the system comprising:

[0038] Establish a coordinate system on the ground to determine the longitude and latitude of point A and point B;

[0039] A radar and friend-or-foe satellite identification system are installed at point A, a radar and air defense missiles are installed at point B, and a close-range command radar is installed at point C;

[0040] The coordinates of the enemy satellite's projection point H on the ground are measured by the radar at point A;

[0041] Calculate the distance L between the enemy satellite and the ground, and construct the sky mark equation;

[0042] Transmit the Sky Mark equation to point B. After the radar at point B receives the attack order, it will immediately launch an air defense missile.

[0043] The radar at point C takes over command and directs the air defense missile to fly along the trajectory of the enemy satellite's sky beacon equation until it intercepts the enemy satellite.

[0044] The distance between point A and point B is 830 kilometers, so that when the enemy satellite flies over for the second time, the radar at point B can receive the attack order in time and launch air defense missiles.

[0045] Measure the coordinates of the enemy satellite projection point H by following the steps below:

[0046] S1. Measure the distance P from point A to the enemy satellite;

[0047] S2. Measure the angle α between the radar reflection wave at point A and the ground;

[0048] S3. Calculate the length of AH by the triangle principle, AH = Pcosα;

[0049] S4. Measure the distance BD from point D to the baffle by a laser rangefinder;

[0050] S5. Calculate the length of AB,

[0051] S6. Determine the coordinates of point H.

[0052] The distance L between the enemy satellite and the ground is calculated by the following formula:

[0053] L=Ps inα.

[0054] The setting method of the radar at point C is:

[0055] Point C has 15 more latitudes than point A;

[0056] The radar at point C is used for close-range command to improve the success rate of interception.

[0057] The latitude and longitude of point A and point B are determined as follows:

[0058] Determine the longitude and latitude of point A;

[0059] Move north 7.54 degrees of latitude to find the longitude and latitude of point B.

[0060] When the distance from the x-axis intersection of point B to point B exceeds 70 kilometers, point B and point A are adjusted to re-establish the coordinate system, so that it is more convenient for radar operators to command missile flight and improve the interception rate. Issuing an attack order when the enemy satellite flies over again in the next cycle can increase the interception success rate and give points B and C more preparation time.

[0061] Reference Figure 1 As shown, specifically, a plane coordinate system is established at point A of the first ground radar station, point 0 is the enemy satellite, point H is the projection point of the enemy satellite on the plane, i.e., the ground, and a laser rangefinder is installed at point D. AD is a straight line and moves with the wireless movement of the radar, AD⊥BD;

[0062] Point A is the origin. The radar reflected wave starts a relay, which is normally open and connected to the power supply of a laser rangefinder. The flying axis is equipped with a spring baffle. The laser ruler measures the distance BD from point D to the baffle. Since the value of AD is fixed and known, the value of AB can be inferred. Measure the angle α between A0 and AH, and the distance from the radar point to the satellite, let it be P, and we can get AH = Pcos(α);

[0063] According to the triangle principle, where:

[0064]

[0065] Let the distance between the enemy satellite and the ground be L, then L = Ps in (d);

[0066] AE value and L value are important parameter values ​​of the sky mark equation that constitutes the flight trajectory of the enemy satellite. The parametric equation can be obtained based on the coordinates of the two H points. The parametric equation is transmitted to a radar point. If a goniometer is used, it is also OK. The angle d between the radar reflection wave and the ground, and the size of the HAE angle are measured. In this way, L=Ps i na, AH=Pcosd, AE=AHcos, ∠AAE. It is also easy to get the coordinates of point H.

[0067] Reference Figure 2 As shown in the figure, both point A and point B are equipped with radars, and point A is located in the south, point B is located in the north, and the two points are 830 kilometers apart. The main reason for the large distance is that most air defense missiles need to reach an altitude of 150 kilometers above the ground, which takes about 50 to 100 seconds. Of course, the actual measured time parameters shall prevail. Here it is assumed to be 90 seconds, because the radar at point A is detecting the distance to the south, including calculating the data, and transmitting it to point B. Theoretically, it is more than 1,300 kilometers, which is enough time for point A to immediately transmit the signal when it detects the enemy satellite for the second time.

[0068] Point B immediately launches an air defense missile to intercept the target. Since the satellite cycle is 83.3 minutes, the second time, we only need to wait for 83.3 minutes.

[0069] ① Determine point A and point B. First determine point A, measure the longitude and latitude of point A, then go north along the same longitude, and add the latitude (830+110=7.54), that is, add 7.54 latitudes, and find this point to determine point B. Point A is also equipped with an enemy and friend satellite identification system, and coordinates of points A and B are linked, and radars are connected.

[0070] ②. When the identification center at point A issues an attack order, it immediately transmits the information to point B, which immediately launches an air defense missile and commands the missile to fly along the trajectory of the target equation.

[0071] If the calculated distance from the x-axis intersection of the enemy satellite trajectory equation at point B to point B exceeds 70 kilometers, then point B must be moved closer to the intersection, and point A must of course also be moved, and the coordinate system must be re-established. This will make it easier for radar operators to command missile flight and improve the interception rate.

[0072] Reference Figure 3 As shown, they are of the same longitude and axis, i.e., the y-axis, but different latitudes of the x-axis. The principle is to translate the trajectory equation obtained with point A as the origin into the coordinate system with point B as the origin to obtain a new trajectory equation. The air defense missile uses the new trajectory equation to intercept.

[0073] The appropriate distance between points A and B depends entirely on the time it takes for the country's air defense missiles to reach the specified altitude. Generally, a high-performance air defense missile takes 170 seconds to fly to a low-Earth orbit 400 kilometers above the ground. So a distance of 20 degrees of latitude between the two points is sufficient. The actual time parameter can be calculated by using the time it takes for the country's air defense missiles to fly to this altitude.

[0074] Reference Figure 4 As shown in the figure, radars are installed at points A, B and C, and an enemy and friend satellite identification system is also installed at point A. Anti-aircraft missiles are placed at point B, and a close-range command radar is placed at point C to improve the interception rate. This is because enemy satellites and anti-aircraft missiles meet obliquely above this point. If point B is 20 degrees more latitude than point A, then point C is only 15 degrees more latitude than point A. Moreover, the three coordinate systems do not necessarily have to be on the same y axis. Because the satellite flight trajectory is special, coaxiality is also acceptable.

[0075] Multi-point coordinate system operation

[0076] ① When the A point identification system prompts, the radar operator immediately transmits the parameter equation to points B and C.

[0077] ② When point B receives the attack order, it immediately launches air defense missiles and sends a warning signal to point C. When the radar at point C finds the air defense missiles, it immediately takes over the command and notifies point B to stop issuing commands to avoid interference. When the radar at point C finds the target, it commands the air defense missiles to rush towards the enemy satellite.

[0078] Command the air defense missile to fly along the trajectory of the enemy satellite's sky mark equation. It's just opposite to the enemy satellite's direction. And note that there is only an 80% interception rate. And if you shoot down an enemy satellite, you will also lose a high-performance air defense missile. And first calculate the enemy satellite's sky mark trajectory equation. Wait until the enemy satellite flies over again in the next cycle, and then issue an attack order so that points B and C have more preparation time.

[0079] Radar interception is divided into low-altitude interception of targets and high-altitude interception of targets. Low-altitude targets include low-speed moving targets such as airplanes and airships in the sky. The speed of these targets is not as fast as that of air defense missiles. That is, from the time the radar detects the target, the air defense missile has enough time to fly to the height of the target. So it can be intercepted at will. High-altitude and high-speed targets are different. They require flying in the same equation trajectory and in the opposite direction. This is the first point. The second point requires radar networking interception. The main thing is to accurately measure the time it takes for one's own air defense missile to fly to the same altitude layer of the enemy target. For example, at a certain point, a radar detects an enemy satellite 400 kilometers away and 400 kilometers above the ground. If one's own air defense missile takes 130 seconds to fly to an altitude of 400 kilometers, if an air defense missile is launched immediately from that point, when our missile reaches 400 kilometers, the enemy satellite may have already flown away. Therefore, it is necessary to launch air defense at a long distance to intercept.

[0080] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A missile interception system, characterized in that: The system comprises: Establish a coordinate system on the ground to determine the longitude and latitude of point A and point B; A radar and friend-or-foe satellite identification system are installed at point A, a radar and air defense missiles are installed at point B, and a close-range command radar is installed at point C; The coordinates of the enemy satellite's projection point H on the ground are measured by the radar at point A; Calculate the distance L between the enemy satellite and the ground, and construct the sky mark equation; Transmit the Sky Mark equation to point B. After the radar at point B receives the attack order, it will immediately launch an air defense missile. The radar at point C takes over command and directs the air defense missile to fly along the trajectory of the enemy satellite's sky beacon equation until it intercepts the enemy satellite.

2. A missile interception system according to claim 1, characterized in that: The distance between point A and point B is 830 kilometers, so that when the enemy satellite flies over for the second time, the radar at point B can receive the attack order in time and launch air defense missiles.

3. A missile interception system according to claim 1, characterized in that: Measure the coordinates of the enemy satellite projection point H by following the steps below: S1. Measure the distance P from point A to the enemy satellite; S2. Measure the angle α between the radar reflection wave at point A and the ground; S3. Calculate the length of AH by the triangle principle, AH = Pcosα; S4. Measure the distance BD from point D to the baffle by a laser rangefinder; S5. Calculate the length of AB, S6. Determine the coordinates of point H.

4. A missile interception system according to claim 1, characterized in that: The distance L between the enemy satellite and the ground is calculated by the following formula: L = Psinα.

5. A missile interception system according to claim 1, characterized in that: The setting method of the C point radar is: Point C has 15 more latitudes than point A; The radar at point C is used for close-range command to improve the success rate of interception.

6. A missile interception system according to claim 1, characterized in that: The latitude and longitude of point A and point B are determined as follows: Determine the longitude and latitude of point A; Move north 7.54 degrees of latitude to find the longitude and latitude of point B.

7. A missile interception system according to claim 1, characterized in that: When the distance from the intersection of the x-axis coordinates at point B to point B exceeds 70 kilometers, point B and point A are adjusted to re-establish the coordinate system to make it easier for radar operators to command missile flight and improve the interception rate.

8. A missile interception system according to claim 1, characterized in that: Issuing an attack order when the enemy satellite flies overhead again in the next cycle can increase the interception success rate so that points B and C have more preparation time.

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