RU2192603C2 - Way to guide guided rocket - Google Patents

Abstract

FIELD: military equipment. SUBSTANCE: according to invention two sight lines are formed and matched with target. Deviations of rocket from first and second sight lines are measured and control instructions are formed in correspondence with its deviation from specified sight lines and signal to controls of rocket is generated in accordance with sum of first and second control commands. EFFECT: enhanced accuracy and speed of guidance system, noise immunity and protection in process of shooting. 1 cl, 1 dwg

Description

 The invention relates to military equipment, and more specifically to methods of 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 and etc.

 Aiming shells and guided missiles during their flight can significantly improve the accuracy of weapons systems of the ground forces, installed both on the ground and in various moving objects: tanks, infantry fighting vehicles, self-propelled launchers, etc. The firepower of such vehicles increases significantly. due to the addition of conventional weapons (artillery or small arms) with guided missile weapons.

 Currently, various methods of guiding guided missiles and shells are known. The effectiveness of the weapon system of the combat vehicle as a whole depends on the effectiveness of the guidance method.

 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 control in accordance with these deviations before combining the guided missile with the target (see, for example, Latukhin A.N. Antitank weapons.- M.: Military Publishing House, 1974, p. 192-236). The first generation includes guided (anti-tank) 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", "Phalanx", "Baby" and others.

 First-generation ATGMs and their guidance methods have obvious disadvantages; the low speed of the rocket’s movement, 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 300-600 m deep, low rate of fire compared to other anti-tank weapons, etc. Training of personnel shooting rules and practical skills are very expensive and difficult, since manual control requires strict selection and careful training of operators. The low flight speed of the rocket requires the operator to continuously monitor the rocket and the target and control the rocket along the entire trajectory. Therefore, gunners (operators) ATGM are subject to strict requirements. For training and periodic training of guided missile gunners with a manual guidance system, sophisticated electron-optical simulators are required. 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 physically does not have time to respond in a timely manner to changes in the direction of flight of a high-speed rocket. He also experiences significant difficulties in bringing the rocket to the line of sight. In order to avoid pecking the rocket on the ground near the launcher (firing object), the latter gives a significant elevation angle. As a result, an unshielded zone of 600-700 m is formed (see above).

 There is also known a method of guiding a guided missile complex guided missile weapons 9K112-1 "Cobra" (see, for example, the complex weapons of the tank - T-64B. Materials of the training manual. - M .: VABTV, 1977, S. 8-51).

 This method according to the technical essence and essential features is the closest to the claimed and adopted for its prototype. At the same time, it is also the basic object of the proposed method. The guidance method of the 9K112-1 Cobra guided missile is to form the aiming line and combine it with the aim, to measure the deviation of the guided missile during its flight from the aiming line by the guidance system, to automatically form and transmit 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 automatically by the guidance system. This method in comparison with the previous one provides (see ibid.):
increase in missile flight speed up to 220-500 m / s;
reduction of missile flight time 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, and control commands are generated and transmitted to the rocket automatically), which increases firing accuracy and minimizes the impact on the results of individual operator data;
facilitating the selection of operators, simplifying the process and reducing the cost of training.

 However, this method also has disadvantages. The need for a long-term retention of the aiming line on the target leads to the danger of losing it when light or dust noise appears in the gunner’s field of vision. The presence on board the rocket of a powerful light source, necessary for the formation of light feedback and a closed control loop, makes it difficult for the gunner to track the target, creating him light interference. If the transfer of control commands on board the rocket occurs via radio channel, then from the enemy’s side it is possible to counter by using anti-radar guided missiles on the firing complex.

 The aim of the present invention is to increase the effectiveness of the guidance of the rocket and the security of the firing object.

где γ - острый угол между первой и второй линиями прицеливания,
Д_min - минимальная дальность начала совместного наведения управляемой ракеты,
Д_ц - дальность до цели,
ψ - угол расходимости поля (луча) управления системы наведения управляемой ракеты.This goal is achieved by the fact that they form and combine the second aiming line with the target, measure the deviation of the rocket from the second aiming line, form a second control command in accordance with its deviation from the second aiming line, and the signal to the rocket controls is generated in accordance with the sum of the first and second management teams. In this case, the second aiming line is formed at an acute angle to the first, the value of which is determined by the inequality

where γ is the acute angle between the first and second aiming lines,
D _min - the minimum range of the beginning of the joint guidance of a guided missile,
D _c - the distance to the target,
ψ is the divergence angle of the field (beam) of the control of the guided missile guidance system.

The invention is illustrated in the drawing, which shows the principle of the formation of two aiming lines, the guided missile flight path and the following notation: 1 - target (C), 2 - first aiming line (PL ₁ ), 3 - second aiming line (PL ₂ ), 4 - guided missile (UR), 5 - trajectory of a guided missile, 6 - first firing target, 7 - second firing target, γ - sharp angle between the first and second lines of aiming, D _min - minimum starting distance for guiding the guided missile, D _c - distance to the target, ψ - angle diverge awn field (beam) control system guidance guided missile.

Implementation (work) of the proposed method is as follows. Both firing objects are set in such a way relative to the target and relative to each other, so that in accordance with their technical characteristics while sighting the target and launching the guided missile, one of them could capture the guided missile and its subsequent 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 (with the equipment of the weapon systems prepared for operation), the gunners of the firing objects combine the aiming lines of their sights with target 1 (see drawing) and one of them launches a guided missile. Suppose that the launch was made from the first firing object 6. After launching the guided missile 4, the guidance systems of both firing complexes 6 and 7 capture it. Information about the deviation of the guided missile from the first aiming line 2 is received and measured by the guidance system of the first firing object 6, and information about the deviation of the guided missile from the second aiming line 3 is received and measured by the guidance system of the second firing object 7. In accordance with the changed deviations of the guidance station of both complexes form control commands K ₁ and K ₂ and transfer them to a guided missile 4 via a communication line, where they are summed up (taking into account the sign) and transmitted to control bodies missile rocket. The control signal in this case will be determined by the expression:
And _y = K (K ₁ + K ₂ ),
where And _y is the control signal supplied to the rocket controls, K is the gear ratio, K ₁ is the control command generated by the guidance system of the first firing object 6, K ₂ is the control command generated by the guidance system of the second firing object 7. As a result of such formation during the flight, the missile control signal 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) with the help of a matching device that, when a command is issued to launch one of the missiles, provides the appropriate command to the guidance system of the second firing object 7, which transfers it to the missile control mode (without launching it), tracking her and pointing her 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 when a guided missile moves between the first and second aiming lines (in a triangle formed by target 1 and shooting objects 6, 7) is determined by the difference in 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. If control occurs on the linear sections of each of the guidance systems that are identical in characteristics, the gain doubles. Due to this, a qualitatively new result is achieved (increase in 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.

 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. The protection of both firing complexes from anti-radar missiles of the enemy is also increased, since the GOS of the enemy’s missile, summing the signals about the location of the firing complexes located at a certain distance from each other, leads to a miss (the enemy’s missile passes, as a rule, between firing objects 6 and 7 )

Claims (2)

 1. A method of guiding a guided missile, which consists in forming an aiming line and combining it with a target, measuring by means of a guidance system the deviation of a guided missile from an aiming line during its flight, automatically generating a control command corresponding to this deviation, automatically generating and applying to missile control organs the signal corresponding to this command, characterized in that the second line of sight is formed and combined with the target, the deviation of the rocket from the second line of refining, form in accordance with its deviation from the second aiming line a second control command, and a signal to the rocket control bodies is generated in accordance with the sum of the first and second control commands. 2. The method according to p. 1, characterized in that the second aiming line is formed at an acute angle to the first, the value of which is determined by the equality

where γ is the acute angle between the first and second aiming lines;
D _min - the minimum range of the beginning of the joint guidance of the guided missile;
D _c - range to the target;
ψ is the divergence angle of the control beam of the guided missile guidance system.