RU2436031C1 - Guided missile control method - Google Patents

Abstract

FIELD: weapons and ammunition. ^ SUBSTANCE: method involves alignment of two sighting lines with target at sharp angle between them, capture of controlled missile, measurement of deviations of controlled missile from both sighting lines, transmission of control commands to missile, which correspond to those deviations, supply to missile control members of the signal corresponding to sum of both control commands, and periodic change of brightness of laying marks of sighting lines. Stability margins of each guidance system and the smallest one of them are pre-determined as to phase, and missile control information areas are formed and aligned with each sighting line. Roll angles of each of them and relative roll angle between them is measured relative to the shooting plane, values of smaller stability margin as to phase and relative roll angle are compared between missile control information areas, colour of laying marks is changed if value of relative roll angle between missile control information areas exceeds the smallest value of stability margin of one guidance systems. Periodic variation of brightness of laying mark of each sighting line is performed at available capture of missile with the appropriate guidance system, availability and duration of conjoint capture of missile is determined simultaneously in both guidance systems and frequency of variation of brightness of both laying marks is doubled by this time. ^ EFFECT: increasing guidance efficiency of controlled missiles, protection of guidance systems and shooting objects.

Description

The invention relates to military equipment, and more specifically, to methods for guiding guided missiles, in particular, installed as part of guided missile systems both on ground installations and at various objects, such as, for example, tanks, infantry fighting vehicles, self-propelled launchers installation, etc.

Aiming shells and missiles during their flight can significantly improve the accuracy of weapon systems installed both on the ground and at various moving objects. The firepower of such machines also increases significantly due to the addition of conventional weapons (artillery, small arms) with guided missile weapons. The effectiveness of the guidance system also determines the effectiveness of the weapons complex.

There is a method of pointing guided missiles of the first generation, which consists in pointing the aiming line at the target, the eye measuring the deviation of the guided missile from it, affecting the missile controls in accordance with these deviations before combining the guided missile with the target (see, for example, A.N. Latukhin "Anti-tank weapons", M., Military Publishing House, 1974, S.192-236). The first generation includes guided missiles with manual guidance systems: French SS - 10, SS - 11, SS - 12, Entak, English Vigilent, Malkara, West German Cobra, Swedish Bantam, Swiss Mosquito -64 ", domestic" Bumblebee "," Baby ", etc.

First-generation ATGMs and their guidance methods have obvious drawbacks: the low speed of the rocket, realized in them, and, consequently, a very long flight time (20-25 s), the presence of an unaffected zone in front of the firing position with a depth of 300-600 m, etc. Training personnel is very expensive and difficult, since manual control requires rigorous selection and thorough training of operators. Therefore, gunners (operators) ATGM are subject to strict requirements. In addition, with this control method it is practically impossible to eliminate one of the main disadvantages: the low flight speed of the guided missile. The fact is that with an increase in the flight speed of the rocket, the work of the gunner is greatly complicated, since control is usually carried out using commands based on the relative position of the rocket and the target. The gunner does not have time to respond in a timely manner to changes in the direction of flight of a high-speed rocket, there is no objective information about the current distance of the guided missile from the target and the moment it reaches the target, which causes operator tension.

A known method of guiding a guided missile complex guided missile weapons 9K112-1 "Cobra" (see, for example, "The armament complex of the tank - T-64B. Textbook materials, M., VABTV, 1977, S.8-51). The guidance method of the guided missile of the 9K112-1 “Cobra” complex consists in forming an aiming line and combining it with a target, measuring the deviation of the guided missile during its flight from the aiming line by the guidance system, automatically generating and transmitting to the missile a control command corresponding to this deviation, automatic generating and applying to the rocket controls a signal corresponding to this command.

This method differs from the previous one in that the gunner (operator) conducts continuous tracking of the target, combining the aiming line with it, and tracking the missile, measuring its deviations from the aiming line, generating and transmitting commands on board the flying rocket, and then on it controls are made by the guidance system automatically. This method in comparison with the previous one provides (see ibid.): An increase in the flight speed of the rocket up to 220-500 m / s; reducing the flight time of the rocket to the maximum range; reduction of the "dead zone" to 75 m or less from the firing position; higher efficiency and stability of firing results in various situations of anti-tank combat; simplification of the operator’s work (its functions are reduced only to combining the aiming line with the target), which increases the accuracy of shooting and reduces the impact on the results of the characteristics of the operator; facilitating the selection of operators, simplifying the process and reducing the cost of training.

However, this method also has disadvantages. The need for long-term retention of the aiming line on a target, the lack of objective information about the moment of approaching a guided missile to it leads to the appearance of operator tension and the danger of losing a guided missile, especially when light or dust interference appears in the operator's field of vision. The presence on board the rocket of the radiation source necessary for the formation of light feedback and a closed control loop make it difficult for the gunner to track the target, creating him light interference. As a result of all this, significant errors in combining the aiming line with the target remain, which leads to miss or missile loss and constant operator tension. Control commands are transmitted on board the missile via a radio channel, and from the enemy’s side it is possible to use anti-radar missiles on a firing complex, which further increases the operator’s tension.

There is also a known method of guiding guided missiles according to the patent of the Russian Federation for invention No. 2213926, including forming and combining for the purpose of two aiming lines with an acute angle between them, launching and capturing a guided missile, measuring guiding missile deflection systems during its flight from both aiming lines , automatic generation and transmission to the missile of control commands corresponding to these deviations, automatic generation and transmission to the missile control organs of a signal corresponding to the sum both control commands, and periodic changes in the brightness of the sighting marks of the aiming lines.

This method according to the technical essence and essential features is the closest to the claimed method and is taken as its prototype. At the same time, it is also the basic object of the proposed method.

Using this method eliminates a number of noted disadvantages. In particular, to improve the guidance dynamics of guided missiles, to increase noise immunity (the effect of light and dust interference is reduced), and to optimize the time for solving fire missions. However, this method also has disadvantages. Changing the brightness of sighting marks starts from the moment the guided missile is launched, that is, even before it is captured by guidance systems, which misinforms gunners about the start of control (at least 1-1.5 s). The same goes for achieving a missile-guided target. The lack of reliable information about the real guidance process (information about the termination of guidance by one or both guidance systems due to malfunctions, interference, etc.) does not allow optimizing the time of use of guidance systems, in particular, promptly transferring guidance to other targets, and switching to other functions etc. In these cases, the gunner’s time loss for both one and the other firing systems can be commensurate with the UR flight time at the maximum range (more than 10 seconds for the prototype).

In addition, the prototype does not take into account the roll angles of the information areas of missile control in guidance systems, as well as the relative roll angle of the information areas between them.

The information area of missile control in guidance systems is the space in which it is possible to determine the coordinates of the rocket, measure its deviation from a given position and transmit control commands to it (in the prototype, the joint space of the field of view of the coordinator and the control radio beam, in radiation systems, the information control beam) . In command guidance systems, information control areas are characterized by the presence of measuring and command coordinate systems and the ability to determine their position relative to the vertical and horizontal. Their mismatch in the plane of the roll leads to the appearance of angles of "twisting coordinates."

With an increase in these angles, the dynamic characteristics of guidance systems deteriorate (see, for example, F. Neupokoev, “Anti-aircraft missile firing.” M, Military Publishing House, 1970, pp. 99-121). When firing using only one guidance system, operators have the ability to only visually and approximately control the angle of heel of its control information area and if the angle of heel is greater than the permissible (in the prototype more than 15 degrees), the guided missile cannot be fired. However, with such a determination of the angle of heel, errors are inevitable and control failures are possible. And with the joint guidance of a guided missile, the measurement of the relative angle of heel is not performed at all, and its value may exceed the permissible level. With acceptable roll angles in each guidance system, for example, in the first +10 degrees, and in the second -10 degrees, the value of the relative roll angle (20 degrees) exceeds the permissible level (15 degrees) and the likelihood of a control failure is further increased.

The objective of the present invention is to increase the guidance efficiency of guided missiles, the security of guidance systems and firing objects, and also to eliminate the disadvantages of the prototype.

This problem is solved by the fact that in the guided missile guidance method, including the formation and alignment of two aiming lines with an acute angle between them, launching and capturing a guided missile, measurement of guided missile deviation guidance systems during its flight from both aiming lines, automatic formation and transmission to the guided missile of control commands corresponding to these deviations, automatic generation and transmission to the missile control organs of a signal corresponding to the sum of both control commands, and a periodic change in the brightness of the sighting marks of the aiming lines, first determine the stability margins of each guidance system in phase and the value of the smaller of them, form and adjust the information control areas of the missile with each aiming line, measure the heel angles of each of them relative to the firing plane and the relative angle of heel between them, comparing the values of a smaller margin of stability in phase and the relative angle of heel between the information areas of rocket control d, change the color of the aiming marks, if the value of the relative roll angle between the information areas of the missile control exceeds a lower value of the stability margin of one of the guidance systems, periodically changes the brightness of the aiming mark of each aiming line in the presence of a guided missile capture by the corresponding guidance system, determines the presence and duration of the joint capture guided missiles simultaneously in both guidance systems and double at this time the frequency of brightness changes both their sighting marks,

The application of the proposed method is as follows. Preliminary determine the stability margins of each guidance system in phase and the value of the smaller of them, form and align with each line of aim information areas of missile control. Both firing objects are set in such a way, relative to the target and relative to each other, that in accordance with their technical characteristics while simultaneously targeting and launching the guided missile, one of them could capture the guided missile and its further guidance by the second complex. For example, for complexes implementing the prototype, this distance between objects should be no more than 50 m (when shooting at a maximum range of 4000 m). Having received a command to hit the target (when the weapon systems equipment is prepared for operation), the gunners of the firing objects prepare the guidance systems for their intended use, form the aiming lines with the information areas of the missile control that are aligned with them (check and adjust the aiming drives of the aiming lines (aiming marks), establish initial brightness of sighting marks, etc.), combine the aiming lines of their sights with the aim so that there is an acute angle between them. The roll angles of each rocket control information area and the relative roll angle between them are measured relative to the firing plane, the values of the smaller phase stability margin and the relative roll angle between the rocket control information areas are compared. If the value of the relative roll angle between the information areas of the missile control exceeds a smaller value of the safety margin (one of the guidance systems), the color of the reticle is changed. This indicates that the dynamic characteristics of guidance systems, especially when they are guided jointly by a guided missile, will significantly deteriorate and, in order to avoid reducing firing efficiency, in this case it is more advisable to switch to guidance by one guidance system.

After launching a guided missile, the guidance systems of both firing complexes alternately or jointly capture it. The moment of capture of the guided missile is fixed, its duration is determined and fixed. From the moment of capture, the brightness of the aiming mark of the aiming line of the corresponding guidance system (in which the capture was made) is periodically changed, and this change continues throughout the capture time. The presence and duration of the joint capture of a guided missile simultaneously by both guidance systems is determined. In the presence of a joint capture of a guided missile simultaneously by both guidance systems for all this time double the frequency of change in brightness of both aiming marks. When the joint capture disappears, the brightness frequency of the aiming marks is doubled, and when the capture disappears in one of the guidance systems, the brightness of the aiming mark of this particular guidance system is stopped.

Thus, the introduction of new features makes it possible to increase the guidance of a guided missile by additionally informing operators in both firing objects about real guidance processes, which also allows optimizing the use of firing objects (increasing their fire and tactical maneuverability, security, etc.).

As in the prototype, information about the deviation of the guided missile from the first aiming line is perceived and measured by the guidance system of the first firing object, and information about the deviation of the guided missile from the second aiming line is perceived and measured by the guidance system of the second firing object. In accordance with the measured deviations, the guidance stations of both complexes form control commands and transfer them to a guided missile via a communication line, where they are summed up (taking into account the sign) and transmitted to the missile control bodies. The control signal in this case will be determined by the product of the sum of the control commands and the gear ratio of the onboard missile control equipment.

As a result of this formation of the control signal, the missile during the flight will be between the aiming lines and, if the characteristics of the guidance systems are identical, then at an equal distance from each of the aiming lines.

Coordination of the joint operation of the guidance systems of both firing objects occurs (if necessary), as in the prototype, using the matching device, which, when giving a command to launch a rocket of one of the objects, provides the appropriate command to the guidance system of the second firing object, which transfers it to the missile control mode (without launching it), tracking it and pointing it at the target. If difficulties arise in the simultaneous transmission of control commands from two firing objects to the same missile (for example, if the command transmission channel is based on a radio channel), the synchronizing device provides alternate transmission of commands to prevent mutual interference.

The dynamics of the control process during the movement of a guided missile between the first and second lines of aiming (in a triangle formed by the target and shooting objects) is determined by the difference of the control commands, and when moving outside the triangle, by their sum. This provides an increase in the gain of the integrated guidance system with the same characteristics of each of the independent guidance systems. Due to this, a qualitatively new result is achieved (an increase in the gain) without changing the characteristics of the systems, which, with satisfactory stability of the combined system, can provide an increase in both accuracy and speed.

A periodic change in the brightness of the aiming marks of both aiming lines allows you to inform the operators about the moment of capture of the guided missile, its duration and the moment of disappearance both in a specific guidance system and in the joint (by doubling the frequency of change in brightness of the aiming marks), which eliminates the loss of time in evaluating the results firing and speed up the production of subsequent launches.

Compared to the prototype, the reliability of the method increased (by 1-2 s), since the brightness of the aiming mark changes from the moment of the capture of the guided missile, and not its launch, which at the same time allows you to speed up the decision.

A periodic change in the brightness of the aiming marks during the simultaneous guidance of the guided missile by two guidance systems (the brightness of both sighting marks occurs at a double frequency), when the image of the rocket in the field of view of each of the operators is at a considerable distance from the corresponding aiming mark, informs the operators that the guidance process is not yet complete, the guided missile has not reached the target, and both guidance systems are controlling at the same time. Information about the termination of such control can reduce the time to make a decision (in the prototype up to 10 seconds).

The color change of the reticle makes it possible to inform operators of the danger of deterioration of the dynamic characteristics of guidance systems when used together and thereby optimize the guidance process.

Using the proposed method of guided missile guidance allows you to achieve a number of other positive results. Joint guidance of a guided missile by two guidance systems allows to increase the reliability of capture and guidance in the event of failure of one of the systems; to increase the noise immunity of the system, since in case of loss of control of one system due to light or dust interference, guidance continues to the second; to increase the protection of both firing systems from anti-radar missiles of the enemy, since the enemy’s GOS of the missile, summing the signals about the location of the firing systems located at a certain distance from each other, leads to a miss (the enemy missile passes, as a rule, between firing objects).

Claims (1)

A guided missile guidance method, including forming and combining two aiming lines with an acute angle between them, launching and capturing a guided missile, measuring guidance systems for deviations of a guided missile during its flight from both aiming lines, automatic generation and transmission of commands to a guided missile control corresponding to these deviations, the automatic generation and submission to the rocket controls of a signal corresponding to the sum of both control commands, and periodically a slight change in the brightness of the sighting marks of the aiming lines, characterized in that the stability margins of each guidance system in phase and the value of the smaller one are preliminarily determined, information areas of the missile control are formed and adjusted with each aiming line, the heeling angles of each of them and the relative the angle of heel between them, compare the values of the smaller margin of stability in phase and the relative angle of heel between the information areas of the missile control, change the color aiming marks, if the value of the relative roll angle between the information areas of the missile control exceeds a lower value of the stability margin of one of the guidance systems, periodically change the brightness of the aiming mark of each aiming line in the presence of a guided missile capture by the corresponding guidance system, determine the presence and duration of the joint guided missile simultaneously in both guidance systems and double at this time the frequency of the brightness changes of both aiming m rock.