JP2014126355A - Missile guide system and missile guide method - Google Patents

Abstract

PROBLEM TO BE SOLVED: To solve a problem that there is a possibility that an oscillation angle of a missile deviates from or exceeds an oscillation possible range for maintaining a lock-on state, and lock-off is made when thrust for terminal guidance is generated in a multi-pulse type (a plurality of pulses) missile.SOLUTION: In a multi-pulse type missile, time from lock-on to terminal guidance start is effectively used, an attitude angle is gradually changed with the usage of a rotor blade of the missile during a period from lock-on to terminal guidance start, and the attitude angle facing a target direction can be secured in the terminal guidance start. A missile guide system for achieving the enhancement includes an error calculation means for calculating heading error quantity of the missile during the period from lock-on to terminal guidance start, an attitude control means for securing the attitude angle in accordance with the calculated heading error quantity and shifting to terminal guidance in the state of maintaining the attitude angle, and an acceleration thrust generation means for generating thrust for terminal guidance.

Description

  The present invention relates to a flying object guiding method, and more particularly to a flying object guiding method at the time of transition to terminal guidance.

  With current technology in the field of flying object guidance methods, an expected meeting point with a target is calculated before lock-on (lock-on), and it is predicted until an appropriate timing is reached for terminal guidance even after lock-on. It flies toward the direction of the meeting point, and when it reaches an appropriate timing, it shifts to terminal guidance that leads to the target direction.

  In a two-pulse type flying object that separately generates thrust at the time of terminal guidance, a large attitude angle (large angle of attack) is taken at the time of terminal guidance to follow the acceleration command. Even in such a situation in which the attitude angle changes, the target is continuously captured by a gimbal (Gimbal: turntable) provided to the seeker (Seeker: target search device) of the flying object. And it meets with the target by flying according to the guidance signal from Sika.

[Related technologies]
As a related technique, a flying object guiding method is disclosed in Patent Document 1 (Japanese Patent Laid-Open No. 59-052200). In this technology, when the target is not captured by the means for detecting the relative position between the projectile and the target, the target is captured within the field of view (sight) by changing the attitude angle of the projectile, and thereby the target It is characterized by being guided to.

JP 59-052200 A

  This is not a problem with a normal flying object, but the following problem occurs with a two-pulse flying object that generates a separate thrust during terminal guidance.

  For example, when flying at a high altitude where the attitude angle of the flying object changes greatly as shown in FIG. 1, the swinging angle of the flying object deviates / exceeds the swingable range for maintaining the lock-on state. And could be locked off. In particular, when the swing angle is asymmetrical in the vertical direction (the lower swing angle is extremely small, etc.), such a phenomenon appears remarkably.

  In the present invention, in a multi-pulse (multiple pulse) type flying object, the time from lock-on to the start of terminal guidance is used effectively, and the moving blades of the flying object are used between the lock-on and the start of terminal guidance. Then, we propose a flying object guidance method that gradually changes the posture angle and sets the posture angle toward the target direction at the start of terminal guidance.

  The flying object guidance method according to the present invention is a flying object guidance method applied to a multi-pulse type flying object, and calculates an error amount for calculating the heading error amount of the flying object between lock-on and the start of terminal guidance. Means, a posture control means for taking a posture angle corresponding to the calculated heading error amount and shifting to terminal guidance while maintaining the posture angle, and acceleration thrust generating means for generating thrust for terminal guidance.

  The flying object guidance method according to the present invention is a flying object guidance method applied to a multi-pulse type flying object, and calculates a heading error amount of the flying object between lock-on and the start of terminal guidance. , Taking a posture angle corresponding to the calculated heading error amount, shifting to terminal guidance while maintaining the posture angle, and generating thrust for terminal guidance.

  The program according to the present invention is a program for causing an electronic device such as a computer to execute the process in the flying object guiding method. The program according to the present invention can be stored in a storage device or a storage medium.

  Since the attitude angle toward the final expected meeting point is already taken when the thrust for terminal guidance is generated, the change in swing angle after the start of terminal guidance is suppressed compared to the existing method (fine adjustment Opportunity decrease). Moreover, the turning performance (rise of acceleration, etc.) at the time of thrust generation for terminal guidance is improved as compared with the existing method, and the change in the angle of attack due to acceleration is reduced.

It is explanatory drawing about the existing technique. It is explanatory drawing about the structural example of the flying body guidance system which concerns on this invention. It is explanatory drawing about a heading error. It is explanatory drawing about 1st Embodiment of this invention. It is explanatory drawing about 2nd Embodiment of this invention.

  The present invention is directed to a flying object guiding method applied to a multi-pulse flying object. Here, a flying object guidance method applied to a two-pulse flying object will be described.

<First Embodiment>
Hereinafter, a first embodiment of the present invention will be described with reference to the accompanying drawings.

[Configuration example of flying object guidance method]
As shown in FIG. 2, the flying object guidance method according to the present embodiment includes an error calculation unit 10, an attitude control unit 20, and an acceleration thrust generation unit 30.

  The error calculation unit 10 calculates a heading error amount indicating an error between an expected meeting point calculated before the lock-on and a true meeting point calculated after the lock-on between the lock-on and the end guidance start. . FIG. 3 is an explanatory diagram for a heading error.

  The attitude control unit 20 takes an attitude angle (attack angle / slip angle) according to the calculated heading error amount from the lock-on to the start of terminal guidance, and moves the nose of the flying object in the direction of the expected meeting point. Direct toward the goal. For example, the posture control unit 20 controls a steering device such as a moving blade (steering blade, movable nozzle, thrust deflector plate, etc.) based on the heading error amount to change the posture angle (attitude angle command). ) To change the attitude angle by pitch rotation (rotation about the left and right axis: vertical swing) / yaw rotation (rotation about the vertical axis: left and right swing), and fly before the end guidance starts Gradually point the nose of the body toward the target. At the start of terminal guidance, the posture control unit 20 shifts to terminal guidance while maintaining the posture angle.

  The acceleration thrust generating unit 30 generates thrust for terminal guidance when the terminal thrust is shifted to terminal guidance. For example, the acceleration thrust generating unit 30 switches the main engine of the flying object from a ramjet engine to a scramjet engine. Alternatively, activate the propulsion booster. However, actually, it is not limited to these examples.

[Details of this embodiment]
Details of the present embodiment will be described with reference to FIG.

  When a flying object captures (locks on) a target during flight, it calculates an expected meeting point with the target and flies in the direction of the predicted meeting point. This operation itself is the same as that of the existing technology.

  The error calculation unit 10 calculates the heading error amount from the lock-on to the end guidance start. Note that the error calculation unit 10 may periodically calculate the heading error amount from the lock-on to the end guidance start.

  The attitude control unit 20 issues an attitude angle command to the flying blades of the flying object according to the calculated heading error amount, and gradually adjusts the attitude angle by rotating the flying object by pitch rotation / yaw rotation. The nose of the flying object is pointed in the target direction and its attitude angle is maintained.

  The acceleration thrust generation unit 30 outputs a command to the power engine of the flying object while maintaining the attitude angle with the nose of the flying object oriented in the target direction, generates thrust for terminal guidance, and Accelerate your body.

[Operation and effect of this embodiment]
In the present embodiment, the necessity of adjusting the attitude angle of the flying object after acceleration is greatly reduced as compared to the conventional case, and therefore the maximum thrust can be generated at the time of starting acceleration. Accordingly, the turning performance (such as acceleration rise) is greatly improved. In addition, the acceleration command during the terminal guidance decreases.

Second Embodiment
The second embodiment of the present invention will be described below.

  The configuration of the flying object guidance method according to this embodiment is basically the same as that of the first embodiment. That is, as shown in FIG. 2, the flying object guidance method according to the present embodiment includes an error calculation unit 10, a posture control unit 20, and an acceleration thrust generation unit 30.

  The error calculation unit 10 and the acceleration thrust generation unit 30 are basically the same as those in the first embodiment.

  In the present embodiment, the posture control unit 20 performs roll rotation (rotation about the front and rear axes) according to the calculated heading error amount, and changes the posture angle (roll angle) in a direction in which the swing range is large. This is effective when the target meeting point and the true meeting point are greatly deviated from the expected meeting point, and the response cannot be sufficiently achieved only by the pitch rotation / yaw rotation. Of course, the attitude control unit 20 according to the present embodiment may also have the same function as that of the first embodiment.

[Details of this embodiment]
Details of this embodiment will be described with reference to FIG.

  In this embodiment, when a flying object captures (locks on) a target during flight, it calculates an expected meeting point with the target and flies in the direction of the predicted meeting point. This operation itself is the same as that of the existing technology.

  The error calculation unit 10 calculates the heading error amount from the lock-on to the end guidance start. Note that the error calculation unit 10 may periodically calculate the heading error amount from the lock-on to the end guidance start.

  The attitude control unit 20 issues an attitude angle command to the flying blades of the flying object according to the calculated heading error amount, rolls the flying object to gradually adjust the attitude angle, and finally makes the flight. Direct the nose of the body in the direction where the swing range is expected to be large, and maintain its posture angle.

  The acceleration thrust generating unit 30 outputs a command to the power engine of the flying object while maintaining a posture angle in which the flying object's nose is directed in a direction in which the swing range is expected to be large, and is used for terminal guidance. The thrust is generated and the flying object is accelerated.

  As shown in FIG. 5, in this embodiment, when the end guidance is started, if the target and the true meeting point are greatly deviated from the expected meeting point, the turning acceleration is related to the target. A large turning acceleration is required, and a large acceleration command is generated. Also, with respect to the angle of attack, a large angle of attack is taken in order to generate a large turning acceleration. However, with regard to the swing angle, the flying object is rotated (turned) in a direction in which the swing range is large, so that the swing angle of the flying object does not deviate or exceed the swingable range.

[Operation and effect of this embodiment]
In this embodiment, by rotating (turning) the flying object in a direction in which the swingable range is large or in a direction that is difficult to handle only by swinging, the swinging angle of the flying object is a neck for maintaining the lock-on state. Prevents the occurrence of lock-off due to deviation / exceeding the swing range.

<Relationship between each embodiment>
Note that the above embodiments can be implemented in combination. In each of the above embodiments, the command guidance method is described. However, in actuality, the command guidance method is not limited, and the homing guidance method, the program guidance method, or a combination of other guidance methods is combined. It is also possible to adopt a guidance method.

<Example of hardware>
Below, the example of the concrete hardware for implement | achieving the flying object guidance system which concerns on said each embodiment is demonstrated.

  Although not shown, the flying object guidance system according to each of the embodiments described above is based on an electronic device such as a computer that is driven based on a program and executes predetermined processing and a memory that stores the program and various data. May be realized.

  Examples of the processor include a CPU (Central Processing Unit), a network processor (NP), a microprocessor, a microcontroller (microcontroller), or a semiconductor integrated circuit (LSI: Large Scale) having a dedicated function. Integration) or the like.

  Examples of the memory include semiconductor storage devices such as a RAM (Random Access Memory), a ROM (Read Only Memory), an EEPROM (Electrically Erasable and Programmable Read Only Memory), a flash memory, and an HDD (Hold SMD). An auxiliary storage device such as State Drive), a removable disk such as a DVD (Digital Versatile Disk), a storage medium such as an SD memory card (Secure Digital memory card), or the like is conceivable. Further, a buffer, a register, or the like may be used.

  Note that the processor and the memory may be integrated. For example, in recent years, a single chip such as a microcomputer has been developed. Therefore, a case where a one-chip microcomputer mounted on an electronic device or the like includes the processor and the memory can be considered.

  In addition, it is assumed that the electronic device such as the computer is mounted on the flying object itself, but actually, it may be a device that performs a command guidance to the flying object from the outside. In this case, it is assumed that each of the electronic devices such as the computer and the flying object includes a communication device such as an antenna or a communication interface.

  However, actually, it is not limited to these examples.

<Remarks>
As mentioned above, although embodiment of this invention was explained in full detail, actually, it is not restricted to said embodiment, Even if there is a change of the range which does not deviate from the summary of this invention, it is included in this invention.

DESCRIPTION OF SYMBOLS 10 ... Error calculation part 20 ... Attitude control part 30 ... Acceleration thrust generation part

Claims (9)

A flying object guidance method applied to a multi-pulse flying object,
An error calculating means for calculating the heading error amount of the flying object between the lock-on and the terminal guidance start;
A posture control means for taking a posture angle corresponding to the calculated heading error amount and shifting to terminal guidance while maintaining the posture angle;
A flying object guidance system comprising acceleration thrust generating means for generating thrust for terminal guidance. The flying object guiding method according to claim 1,
The attitude control means performs at least one of pitch rotation and yaw rotation according to the calculated heading error amount, and takes an attitude angle with respect to a target. The flying object guiding method according to claim 1 or 2,
The attitude control means rolls according to the calculated heading error amount and takes an attitude angle in a direction where the swingable range is large. A flying object guidance method applied to a multi-pulse flying object,
Calculating the heading error amount of the flying object between the lock-on and the start of terminal guidance;
Taking an attitude angle according to the calculated heading error amount;
Shifting to terminal guidance while maintaining the posture angle;
A flying object guidance method including generating thrust for terminal guidance. The flying object guiding method according to claim 4,
The method further includes taking at least one of pitch rotation and yaw rotation in accordance with the calculated heading error amount and taking a posture angle with respect to the target when taking the posture angle in accordance with the calculated heading error amount. Body guidance method. The flying object guiding method according to claim 4 or 5,
The method for guiding a flying object further includes taking a posture angle in a direction in which a swingable range is large when the posture angle corresponding to the calculated heading error amount is taken to roll according to the calculated heading error amount . A step of calculating the heading error amount of the flying object between the lock-on and the start of terminal guidance in the multi-pulse flying object;
Taking a posture angle according to the calculated heading error amount;
Transition to terminal guidance while maintaining the posture angle;
A program for causing an electronic device to execute a step of generating thrust for terminal guidance. The program according to claim 7,
The electronic apparatus further includes a step of taking at least one of pitch rotation and yaw rotation according to the calculated heading error amount and taking the posture angle with respect to the target when taking the posture angle according to the calculated heading error amount. A program to be executed. The program according to claim 7 or 8,
When the posture angle corresponding to the calculated heading error amount is taken, the electronic device further executes a step of rotating the roll according to the calculated heading error amount and taking the posture angle in a direction where the swingable range is large. Program for.

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