JP2016090528A - Guidance device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To solve the problem in which when performing a target detection with high resolving power using DBS (Doppler beam sharpening) processing, it is necessary to take a necessary squint angle with respect to the target and draw a missile trajectory so as to wrap with respect to the target, and for this reason, it takes much time to come across the target.SOLUTION: An estimation tracking error, the number of targets, a target shape, and target signal power are calculated from target observation information to be output by a DBS processing unit 5, and a squint angle setting unit 27 is configured to set a squint angle, using a result of the calculation, sea level information to be input to a guidance device prior to firing; target foresight information, and target information to be input from a mother aircraft after fired, which in turn enables a guidance by an optimal missile route in accordance with a situation.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a guidance device mounted on a flying object.

  There is known a guidance device that is mounted on a flying object and observes a target using a Doppler radar. A conventional induction device of this type has a Doppler frequency of a target reflected wave (hereinafter referred to as a target signal) and a Doppler frequency of a sea surface reflected wave (hereinafter referred to as a clutter) in the main lobe direction of the antenna included in the induction device. In an overlapping region (hereinafter referred to as a beam region), the target signal is buried in the clutter signal, making it difficult to detect the target signal, and the clutter signal may be erroneously detected. Further, when the guidance device targets a stealth ship having a small radar reflection area (hereinafter referred to as RCS), the target reflected wave signal becomes small and the possibility of erroneous detection of the clutter signal increases.

  On the other hand, by using a Doppler beam sharpening (hereinafter referred to as DBS) type Doppler radar, the resolution of the radar mounted on the guidance device is improved, and the target reflected wave is difficult to detect with the conventional guidance device. It is possible to detect a target whose signal is smaller than clutter and a target whose moving speed is slow and whose target signal is close to the beam region (see, for example, Patent Document 1).

JP 2000-65925 A

  By installing a DBS Doppler radar in the guidance device, it is difficult to detect with the conventional guidance device, and it is possible to detect targets whose target signal is smaller than the clutter and targets whose movement speed is slow and the target signal is close to the beam area. It becomes.

  In addition, by improving the resolution of the radar, it is possible for the guidance device to recognize the target shape, and it is possible to separate the dense targets in the antenna beam and to recognize the weak part of the target. .

  However, in order to improve the resolution of the radar in the DBS method, it is necessary to process the target reflected wave signal by the synthetic aperture processing after taking a squint angle necessary for the target direction. For this reason, it is necessary to draw a flight trajectory that wraps around the target. This wraparound increases the time until the target shoots down, leading to a reduction in range and a reduction in shoot probability. Here, the squint angle is an angle formed by the velocity vector of the flying object and the target direction as a target viewed from the flying object.

  Further, when flying along a route with a small squint angle, it is impossible for the guidance device to recognize the target shape, and it is impossible to separate dense targets in the antenna beam and to recognize a weak portion of the target.

  The present invention has been made to solve such a problem, and reduces the reduction in the range and the decrease in the probability of meeting with the target caused by the increase in the time until the meeting with the target caused by using the DBS method. For the purpose.

  The guidance device according to the present invention performs a DBS (Doppler beam sharpening) process for separating a dense target in an antenna beam transmitted from the antenna, using a received signal of a reflected wave from the target received by the antenna, A DBS processing unit that obtains target observation information including a shape; a target relative relationship calculation unit that calculates target relative relationship information representing a relative relationship between the target from the inertia information and the target observation information, and outputs the target relative relationship information; The tracking error calculation unit that calculates and outputs an estimated tracking error in target tracking using the target observation information from the DBS processing unit and the target relative relationship information from the target relative relationship calculation unit, and the DBS processing unit The target number calculation unit for calculating and outputting the target number in the antenna beam transmitted from the antenna using the target observation information from the antenna, and the DBS process A target shape is calculated using the target observation information from the unit, and is output; a target signal power calculation unit that calculates the target signal power using the target observation information from the DBS processing unit; A squint angle setting unit that calculates a squint angle command value based on outputs from the target relative relationship calculating unit, the tracking error calculating unit, the target number calculating unit, the shape information calculating unit, and the target signal power calculating unit; Based on the squint angle command value calculated by the squint angle setting device and the target relative relationship information of the target relative relationship calculation unit, a guidance for calculating an acceleration command for obtaining a desired squint angle and guiding the flying object to the target And a calculation processing unit.

  According to the present invention, it is possible to suppress a reduction in range and a decrease in the probability of meeting with a target due to an increase in time to meeting with the target due to a flight route that secures a desired squint angle. The ginger can be guided to the target more reliably.

It is a block diagram which shows the structure of the guidance device by Embodiment 1 of this invention. It is a figure for demonstrating the technical subject peculiar to the DBS system in the operation example of the guidance device by Embodiment 1 of this invention. It is a figure which shows the processing flow for solving the technical subject peculiar to the DBS system by the guidance device of Embodiment 1 of this invention. It is a figure for demonstrating the operation example which solved the technical subject peculiar to a DBS system using the guidance device by Embodiment 1 of this invention.

Embodiment 1 FIG.
FIG. 1 is a block diagram showing the configuration of the guidance device according to Embodiment 1 of the present invention. In FIG. 1, the guidance device 21 according to the first embodiment includes a signal processor 22, a receiver 3, a transmitter 4, an antenna 10, and an inertial device 7. The signal processor 22 includes a transmission / reception control unit 6, a target relative relationship calculation unit 8, a DBS processing unit 5, a tracking error calculation unit 23, a target number calculation unit 24, a target shape information calculation unit 25, A target signal power calculation unit 26, a squint angle setting unit 27, and a guidance calculation processing unit 28 are provided. The guidance device 21 is mounted on a flying body (not shown) including a steering blade and a rocket motor. Further, the flying object is mounted on an aircraft (launching mother machine) and is launched from the launching mother machine.

  The transmitter 4 transmits a transmission signal 11 toward a target (not shown) via the antenna 10. The receiver 3 receives a target reflected wave that is a reflected wave from the target via the antenna 10 and amplifies the target reflected wave to a required level, and then outputs a received signal 12 from the target to the DBS processing unit 5. The inertia device 7 outputs the inertia information 17 of the guidance device 21 to the target relative relationship calculation unit 8.

  The DBS processing unit 5 outputs target observation information 16 that is a result of DBS processing of the received signal 12 to the target relative relationship calculation unit 8. The target relative relationship calculation unit 8 uses the inertia information 17 and the target observation information 16 to calculate target relative relationship information 15 that is information representing the relative relationship between the guidance device 21 and the target. The data is output to the guidance calculation processing unit 28 and the transmission / reception control unit 6. The target relative relationship information 15 includes information such as a relative distance to the target, a relative speed, and a relative position.

  The guidance calculation processing unit 28 calculates an acceleration command 18 for guiding to the target based on the target relative relationship information 15. The transmission / reception control unit 6 generates a transmitter control signal 14 for performing transmission wave transmission timing control, transmission wave transmission direction control, and transmission wave modulation control based on the input target relative relationship information 15. Output for. In addition, the transmission / reception control unit 6 generates and outputs a receiver control signal 13 for controlling the reception timing of the target reflected wave with respect to the receiver 3.

  The transmitter 4 transmits the transmission signal 11 to the antenna 10 using the information of the transmitter control signal 14 as the transmission signal 11. The antenna 10 is directed to the target direction, irradiates the transmission signal 11 output from the transmitter 4 toward the target, receives a reflected wave from the target, and outputs the received signal 12 to the receiver 3.

  The DBS processing unit 5 generates target observation information 16 that is a result of DBS processing of the received signal 12, a target relative relationship calculation unit 8, a tracking error calculation unit 23, a target number calculation unit 24, a target shape calculation unit 25, and a target It outputs to the signal power calculation part 26.

  The target relative relationship calculation unit 8 calculates target relative relationship information 15 that is information representing the relative relationship between the guidance device 21 and the target using the inertia information 17 and the target observation information 16 output from the inertia device 7. The target relative relationship information 15 is output to the guidance calculation processing unit 28, the transmission / reception control unit 6, the tracking error calculation unit 23, and the squint angle setting unit 27.

  The tracking error calculation unit 23 calculates an estimated tracking error 29 in target tracking using the target observation information 16 and the target relative relationship information 15, and outputs the estimated tracking error 29 to the squint angle setting unit 27.

  The target number calculation unit 24 calculates the target number 30 in the antenna beam from the target observation information 16 of the DBS processing unit 5, and outputs the calculated target number 30 to the squint angle setting unit 27.

  The target shape information calculation unit 25 calculates the target shape 31 from the target observation information 16 and outputs the target shape 31 to the squint angle setting unit 27.

  The target signal power calculation unit 26 calculates the target signal power 32 from the target observation information 16 and outputs the target signal power 32 to the squint angle setting unit 27.

  The squint angle setting unit 27 includes the target relative relationship information 15, the estimated tracking error 29, the target number 30, the target shape 31, the target signal power 32, a sea level state 33 and target foreseeing information described later. 34 is input. The squint angle setting unit 27 generates a squint angle command value 35 based on the input information, and outputs the squint angle command value 35 to the guidance calculation processing unit 28. Here, the information on the sea surface state 33 is input to the guidance device 21 from the launching mother machine on which the flying object is mounted and set in the squint angle setting unit 27 before the flying object on which the guidance device 21 is mounted. Similarly, the information of the target foresight information 34 is input to the guiding device 21 from the launching mother machine on which the flying object is mounted and set in the squint angle setting device 27 before the flying object on which the guiding device 21 is mounted. . The target foresight information 34 can be updated sequentially even after launch. The target foresight information 34 includes a target number, a target RCS, and a target azimuth angle.

  The guidance calculation processing unit 28 secures a desired squint angle based on the squint angle command value using the squint angle command value 35 and the target relative relationship information 15 from the squint angle setting unit 27, and mounts the guidance device 21. An acceleration command 18 for guiding the flying object to the target is calculated.

Next, the operation of the guidance device 21 according to Embodiment 1 will be described.
FIG. 2 is a diagram for explaining a technical problem peculiar to the DBS system in the operation example of the guidance device 21 according to the first embodiment. FIG. 3 is a diagram showing a processing flow for solving the technical problem in the guidance device 21 according to the first embodiment. FIG. 4 is a diagram for explaining an operation example in which a technical problem peculiar to the DBS system is solved by using the guidance device 21 according to the first embodiment.

  In FIG. 2, the launch mother machine 51 is mounted with a flying body 52 on which the guidance device 21 is mounted and fires. After flying from the launch mother machine 51, the flying body 52 flies toward the target 53 that is stationary and moving at a low speed. The fixed and low-speed moving body 60 is located in the vicinity of the target 53. The flying object 52 has a flying object velocity vector 54 and a squint angle 56 at a relative distance 55 between the flying object 52 and the target 53, and flies through the flying path 58 when performing DBS processing. . The flight route 57 is a normal route when DBS processing is not performed. The antenna beam 59 of the guidance device 21 irradiates the target 53 and the fixed and low-speed moving body 60.

  As for a normal flying object, the flying object 52 ejected from the mother machine 51 is guided to the target 53 through the flying route 57. However, it is difficult to detect the target 53 with a small RCS and a small target reflected wave signal, or the target 60 during fixed and low-speed movement, and it is highly possible that the clutter signal is erroneously detected and does not meet the target. In addition, since it is difficult to separate a dense target (target 53 or target 60 during fixed and low-speed movement) in the antenna beam 59, an object (fixed and low-speed) that is not the designated target 53 to which the flying object 52 should be guided. There is also the possibility of being guided to a moving target 60).

  On the other hand, the flying object 52 equipped with the guidance device 21 that performs DBS processing can perform target separation and clutter signal suppression by increasing the resolution, and therefore can guide the designated target 53. However, since it is guided to the target 53 through the flight path 58, it is necessary to draw a flight trajectory that wraps around the target, which leads to a reduction in range due to an increase in time to the target shooting and a reduction in shooting probability. There are technical issues specific to the system. In addition, since the resolution decreases when flying along a route with a small squint angle, it is impossible for the guidance device to recognize the target shape, and it is impossible to separate the dense target in the antenna beam and recognize the weak part of the target. There is a problem of becoming. In the conventional guidance device, the flying object is guided based only on the target relative relationship information output from the target relative distance calculation unit from the DBS processing result.

  In contrast, the guidance device 21 according to the first embodiment uses the processing flow of FIG. 3 to cause the DBS method such as a reduction in range and a reduction in the probability of shooting down caused by an increase in time to target shooting, which is caused when the DBS method is used. Specific technical issues can be improved.

In FIG. 3, the guidance device 21 performs the following steps S101 to S109.
First, in step S <b> 101, the DBS processing unit 5 performs DBS processing on the reception signal output from the receiver 3 and outputs target observation information 16.

  Next, in step S102, the target relative relationship calculation unit 8 uses the inertia information output from the inertial device 7 and the target observation information output from the DBS processing unit 5 to target the flying object 52 and the target. The relative relationship information 15 is calculated.

  Subsequently, in step S103, the tracking error calculation unit 23 uses the target observation information output from the DBS processing unit 5 and the target relative relationship information output from the target relative relationship calculation unit 8 to estimate the tracking error in target tracking. 29 is calculated.

  Next, in step S104, the target number calculation unit 24 calculates the target number 30 in the antenna beam from the target observation information output from the DBS processing unit 5.

  Next, in step S <b> 105, the shape information calculation unit 25 calculates the target shape 31 from the target observation information output from the DBS processing unit 5.

  Next, in step S <b> 106, the target received signal power calculation unit 26 calculates the target signal power 32 from the target observation information output from the DBS processing unit 5.

  Next, in step S107, the squint angle setting unit 27 uses the processing result from S102 to S106, the sea level state set before launching, and the target information obtained from the launching mother machine before launching or after launching. The squint angle that is optimal for the current flight state is extracted from the information of the squint angle setting table stored in. If the squint angle setting unit 27 compares the extracted squint angle with the current squint angle and determines that the squint angle can be changed to a small value (angle), the squint angle setting unit 27 proceeds to the next step S108, If the angle cannot be changed, the squint angle command value 35 is not changed and the process proceeds to step S109.

  Further, in step S108, the squint angle setting unit 27 changes the squint angle command value 35 to the squint angle extracted from the squint angle setting table.

  Subsequently, in step S109, the guidance calculation processing unit 28 uses the squint angle command value 35 and the target relative relationship information 15 output by the target relative relationship calculation unit 8 to guide the flying object 52 to the target 53. The acceleration command 18 is calculated, and guidance calculation for controlling the airframe motion of the flying object 52 is performed.

  Next, an operation example in which a technical problem peculiar to the DBS system is solved by the guidance device 21 according to the first embodiment will be described. In FIG. 4, the launch mother machine 51 launches a flying object 52 on which the guidance device 21 is mounted. After flying from the launch mother machine 51, the flying body 52 flies the flying path 61 or the flying path 62 after changing the squint angle to a small value toward the target 53 that is moving at a low speed. The launch mother machine 51 transmits the sea surface state and target foresight information 63 to the guidance device 21 of the flying object 52. The flying body 52 ejected from the mother machine 51 is guided to the target 53 through the flying path 61. If it is determined by the processing flow of FIG. 3 that the squint angle can be changed to a small value, the guidance device 21 changes the route of the flying object 52 like the flying route 62. Moreover, the target information 63 transmitted from the launching mother machine 51 is sequentially updated, and the guidance device 21 of the flying object 52 resets the squint angle using the updated latest information.

  Thus, it is possible to reduce the range reduction and the reduction in shooting probability due to the increase in time to the target shooting due to the flight route that secures the squint angle. Further, the flying object 52 can be guided to the target 53 more reliably.

  As described above, the guidance device 21 according to the first embodiment uses the received signal of the reflected wave from the target received by the antenna 10 to perform DBS processing for separating the dense target in the antenna beam transmitted from the antenna 10. To obtain target observation information 16 including the shape of the target, calculate target relative relationship information 15 representing the relative relationship between the target from the inertia information 17 and the target observation information 16, and calculate the target relative relationship information. 15 using the target relative relationship calculation unit 8 that outputs 15, the target observation information 16 from the DBS processing unit 5, and the target relative relationship information 15 from the target relative relationship calculation unit 8. In the antenna beam transmitted from the antenna 10 using the tracking error calculation unit 23 for calculating and outputting the target error information and the target observation information 16 from the DBS processing unit 5 From the target number calculation unit 24 that calculates and outputs the target number, the target shape is calculated using the target observation information 16 from the DBS processing unit 5, and the shape information calculation unit 25 that outputs the target shape and the DBS processing unit 5 Target signal power calculation unit 26 that calculates target signal power using the target observation information 16, the target relative relationship calculation unit 8, the tracking error calculation unit 23, the target number calculation unit 24, and the shape information calculation unit 25 and a squint angle setting unit 27 for calculating a squint angle command value based on the output from the target signal power calculation unit 26, a squint angle command value 35 calculated by the squint angle setting unit 27, and a target relative relationship calculation unit 8 And a guidance calculation processing unit 28 for calculating an acceleration command 18 for guiding the flying object 52 to the target by obtaining a desired squint angle based on the target relative relationship information 15. And butterflies.

  Thus, it is possible to detect a target whose target signal is smaller than the clutter and a target whose movement speed is slow and the target signal is close to the beam region, which has been difficult to detect with the conventional guidance device 21. Furthermore, since it is possible for the guidance device to recognize the target shape, it is possible to separate the dense target in the antenna beam and to recognize the weak part of the target.

  3 receiver, 4 transmitter, 5 DBS processing unit, 6 transmission / reception control unit, 7 inertia device, 8 target relative calculation unit, 10 antenna, 21 guidance device, 22 signal processor, 23 tracking error calculation unit, 24 target number Calculation unit, 25 Target shape information calculation unit, 26 Target signal power calculation unit, 27 Squint angle setting device, 28 Induction signal processing unit, 51 Launching mother machine, 52 Flying object, 53 Target, 57 Flying route without DBS processing , 58 Flying route for performing DBS processing, 60 Fixed and low-speed moving object near target that is not the target, 61 Flying route before squint angle change, 62 Flying route after squint angle change.

Claims (2)

Using the received signal of the reflected wave from the target received by the antenna, DBS (Doppler beam sharpening) processing is performed to separate dense targets in the antenna beam transmitted from the antenna, and target observation information including the target shape is obtained. A DBS processor to obtain;
A target relative relationship calculation unit that calculates target relative relationship information representing a relative relationship between the target from the inertia information and the target observation information, and outputs the target relative relationship information;
Using the target observation information from the DBS processing unit and the target relative relationship information from the target relative relationship calculating unit, calculating an estimated tracking error in target tracking, and outputting a tracking error calculating unit;
Using the target observation information from the DBS processing unit, calculate the target number in the antenna beam transmitted from the antenna and output the target number;
Using the target observation information from the DBS processing unit, a shape information calculation unit that calculates and outputs a target shape;
A target signal power calculating unit that calculates target signal power using target observation information from the DBS processing unit;
A squint angle setting unit that calculates a squint angle command value based on outputs from the target relative relationship calculating unit, the tracking error calculating unit, the target number calculating unit, the shape information calculating unit, and the target signal power calculating unit; ,
Based on the squint angle command value calculated by the squint angle setting device and the target relative relationship information of the target relative relationship calculation unit, obtain the desired squint angle and calculate the acceleration command to guide the mounted flying object to the target A guidance calculation processing unit,
Guidance device with.   The squint angle setting device calculates a squint angle command value based on sea level information and target foresight information input before a mounted flying object is launched from a mother aircraft. Guidance device.

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