RU2453792C9 - Device to launch rocket from mobile carrier - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: device comprises a sight of a gunner-operator with sensors of angles and angular speed of a sighting line in two mutually orthogonal planes, a unit connected to sensors to generate a signal to permit rocket launch by an angular position of the sighting line of the gunner-operator sighting line, connected to an indicator of angular position of the gunner-operator sight viewing line, a switch of a "Start" signal, an indicator to permit launch of a gunner-operator rocket, a launcher with a sensor of rocket availability, a viewing system of the gunner-operator sight, a unit to generate an integral signal to permit rocket launch and a unit to generate a signal to launch a rocket, besides, inlets of the unit to generate an integral signal to permit rocket launch are connected to the outlet of the unit to generate a signal to permit rocket launch by the angular position of the sight viewing line of the gunner-operator, a sensor of launcher rocket availability and a viewing system of the gunner-operator sight accordingly, inlets of a unit to generate a signal of rocket launch are connected to an outlet of the unit to generate an integral signal to permit rocket launch and a switch of a "Start" signal, and indicator to permit launch of a rocket of the gunner-operator is connected to the outlet of the unit to generate an integral signal to permit rocket launch.

EFFECT: higher efficiency of a complex of controlled missile armament installed on a mobile carrier.

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Description

The proposed device relates to the field of placement of weapons on a mobile carrier and can be used to launch missiles from a land, sea or air mobile carrier, such as a helicopter.

A device for launching missiles from an aircraft [1] is known, including a sight, a regulating device, measuring and actuating organs, a vertical acceleration meter, a switching element of the electric launch circuit, and a starting handle.

The starting device consists of mutually movable upper and lower parts located on a common axis.

The disadvantage of this device is the presence of a mobile launcher (PU) with servomotors, significantly (several times) increasing its weight. The increase in weight of the PU, designed for 4-8 missiles (typical combat loading of aircraft), due to the presence of movable elements and servomotors is at least 200-300 kg. This circumstance is very significant for aircraft. Due to the limited carrying capacity, the installation of mobile launchers on them will lead to a sharp decrease in payload, in particular ammunition.

A device is known for launching a rocket from a helicopter [2], which includes an operator-gun sight with sensors of angles and angular velocity of the line of sight in two mutually orthogonal planes, a rocket for launch launch enable signal generation, a start signal switch, a rocket launch circuit switch connected to the “Start” signal switch and the output of the rocket launch enable signal generation block, the arrow of the operator-launch rocket enable switch connected to the output of the permission signal generation block missile launch, and an indicator of the angular deviation of the line of sight of the sight arrow operator for the pilot, connected to the second and third outputs of the unit for generating a signal for launching permission.

This device, selected as a prototype, allows rockets to be launched from a fixed launcher, rigidly oriented relative to the longitudinal axis of the mobile carrier, in the absence of direct visibility of the target by the driver of the mobile carrier, for example, an aircraft pilot.

The launch enable signal is generated in it provided:

$$(\mathrm{one})\begin{array}{c}|\; |\; |{\alpha }_{\text{mountains}}+{\omega }_{\text{mountains}}\Delta {\text{t}}_{\text{Well}}|\; |\; |\le \varphi ;\\ |\; |\; |{\beta }_{\text{at}eRt}+{\omega }_{\text{at}eRt}\Delta {\text{t}}_{\text{Well}}|\; |\; |\le \psi ,\end{array}$$

where α _mountains , β _vert are the angular deviations of the line of sight (LP) of the sight of the operator arrow in two mutually orthogonal planes (in the horizontal and vertical planes, respectively) relative to the “zero” direction of the drug, in which the signals from the sensors of its angular position are zero (in in particular, with respect to the longitudinal axis of the movable carrier, if the “zero” direction of the drug coincides with the direction of its longitudinal axis);

ω _mountains , ω _vert - the angular velocity of the drug in two mutually orthogonal planes (horizontal and vertical planes, respectively);

Δt _well - time of an uncontrolled flight of a rocket - time of a flight of a rocket from the moment of its start to the moment of the start of its formation by the on-board control system of the steering command control commands according to the mismatch signals between the rocket and the aircraft. Mismatch signals are generated by the onboard missile control system based on the signals received from its guidance device (optical direction finder with a device for transmitting guidance commands to the missile, laser or radar guidance systems);

φ, ψ are the maximum allowable angular values within which the specified minimum range of combat use of a complex of guided missile weapons placed on a mobile carrier is ensured.

The missile launch enable signal generating unit that is part of this device, connected to the rocket launch circuit switch and the arrow indicator for the operator-launch missile, it would be more correct to call the missile launch enable signal generating unit for the angular position of the LV of the arrow of the operator-shooter. It really generates a signal for launching a missile launch, but only by one sign - by the sign of the presence of the LV sight of the operator arrow in the angular zone allowed for launching the rocket, given by formulas (1). It is understood that the missile is located on the launcher and the sight system is ready for operation (serviceable). However, the first of these conditions — the presence of a rocket on a selected launcher — is not always automatically performed.

The fact is that on a mobile carrier, as a rule, several launchers are placed (as an option, one launcher with several guides for installing missiles). Moreover, in various versions of the combat load of a mobile carrier, which can be equipped with other types of weapons other than guided missiles, missiles can be installed not on all of them, but only on some. In addition, in combat conditions, part of the initially installed missiles or even all missiles can be used up earlier - until the decision by the shooter-operator to use the missile to hit a specific target is taken.

The second condition may also not be fulfilled, since the sighting survey system may fail by the time the shooter-operator decides to use the missile, in particular as a result of combat damage to the equipment, carrier, or the consequences of this damage. Surveillance systems of modern sights through which the shooter-operator surveys the terrain, searching and finding targets, usually not optical, but television, thermal (infrared), or combined, including, for example, daytime television and round-the-clock thermal surveillance channels. The television survey system is a transmitting television camera that converts the optical signal of the image of the area into a television signal for further display on the screen of the television indicator arrow operator. The thermal imaging system is a thermal imaging camera that generates and transmits in the form of a television signal an image corresponding to the spatial distribution of the thermal radiation of the sighted objects. The malfunction of the survey system does not always manifest itself explicitly - in the absence of an image on the television indicator of the arrow operator. It can be manifested, for example, in a deterioration in image quality, in failures (i.e., reductions of a random nature) in the frequency of updating the terrain image on a television indicator of an operator-operator, etc. Such malfunctions, leading to a significant decrease in accuracy of aiming and, as a consequence, the probability of a missile hitting a target, are rather difficult to detect visually, especially in a combat situation. As a result, in order to avoid wasting ammunition in vain, the launch of a rocket in the event of a malfunction in the survey system should be prohibited.

Therefore, it is more rational to give aggregate or integral information on the launch launch resolution to the operator-shooter indicator, which takes into account the fulfillment of these three conditions (finding the operator-gunner’s LV sight in the angular zone allowed for launching the missile, the presence of the missile on the selected launcher, and the sight sight system is working properly). It makes no sense to display information on the launch arrow indicator on the launch permission if there is no missile on the selected launcher. This, in this case, false, information will only mislead the operator-shooter who will try to launch the missile to no avail, initiating the Start signal switch, which, obviously, will reduce the rate of fire, and therefore the effectiveness of the guided missile system, mounted on removable media. The launch of a rocket with a faulty sighting system of the operator-gunner’s sight will lead to a miss on the target, i.e. to the loss of a rocket and the failure to fulfill a combat mission.

Using other indicators to provide the shooter with operator information about the presence of a missile on the launcher and the health of the sighting system of the sight of the shooter operator complicates the work of the shooter operator, who, in preparation for launching a rocket in a combat situation, must take into account information from three indicators, distracting from observation the battlefield and tracking the already chosen target, and will also reduce the rate of fire of a complex of guided missile weapons installed on a mobile carrier.

The aim of the proposal is to increase the efficiency of the guided missile system installed on a mobile carrier, due to the greater reliability of the information indicated to the arrow-operator on the possibility (resolution) of launching a rocket.

To achieve a technical result, in the known device [2], which includes an operator-gun sight with sensors of angles and angular velocity of the line of sight in two mutually orthogonal planes, a unit for generating a rocket launch permission signal for the angular position of the line of sight of the arrow-operator sight, connected to the sensors, connected with an indicator of the angular position of the line of sight of the gunner-operator sight, a “Start” signal switch and an indicator of permission to launch the arrow-operator missile, a launcher has been introduced and with a missile presence sensor, the sighting system of the operator-arrow sight, an integrated rocket launch enable signal generating unit and a rocket launch signal generating unit, the inputs of the integrated missile launch enable signal generating unit are connected to the output of the rocket launch enable signal generating unit by the angular position of the line of sight sight of the arrow operator, the sensor of the presence of a rocket launcher and the surveillance system of the sight arrow operator, respectively, the inputs of the start signal conditioning unit and the missiles are connected to the output of the unit for forming the integral signal for launching permission to launch and the Start signal switch, and the indicator for allowing the launch of the arrow-operator is connected to the output of the unit for generating the integral signal for launching permission for the launch.

Figure 1 shows the functional diagram of the inventive device.

Figure 1 shows the sight of the arrow operator 1 with sensors of angles 2, 5 and angular velocity 3, 4 of the line of sight of the sight of the arrow operator in two mutually orthogonal planes, the unit for generating a signal to enable launch of the rocket by the angular position of the line of sight of the sight of the arrow operator 6 , an indicator of the angular position of the line of sight of the sight of the arrow-operator 7, a block for generating an integrated signal for launching a rocket 8, an indicator of permission for launching a rocket-operator 9, a start signal switch 10, a formation block Igna missile launch launcher 11 and 12 with sensor 13 the presence of the missile and sightseeing sight system operator arrow 14.

The device operates as follows. The signals from the sensors of the angular position 2, 5 and the angular velocity 3, 4 LV in each of the two mutually orthogonal planes are fed to the rocket of the launch launch permission signal by the angular position of the sight line of the sight arrow operator 6. From the output of the formation of the launch launch permission signal to the angular position of the line of sight of the gunner-operator sight 6 signals of angular deviations of the drug in two mutually orthogonal planes, corrected for lead, in the case of the presence of angular velocities of the drug in these planes to the input of the indicator of the angular position of the line of sight of the sight of the arrow-operator 7, providing the driver of the mobile carrier with the necessary visual information to combine the direction of movement of the mobile carrier with the direction of the drug (i.e. with the direction to the target selected by the arrow-operator) with the required accuracy. When the LV of the sight of the operator arrow is in the angular zone allowed for launching the rocket, at the output of the rocket launch permission signal generating unit by the angular position of the sighting line of the operator arrow 6, a rocket launch permission signal will be generated based on this feature, which will then be transmitted to the input of the integral formation block missile launch enable signal 8. The signal from the missile sensor 13 of the launcher 12 and the signal Al serviceability survey system sight arrow operator 14, respectively. Provided that the overview system of the gunner’s sight 14, the presence of a rocket on the launcher 12 selected by the gunner’s operator, is in good condition and the LV of the gunner’s sight is in the angular zone allowed for launching the rocket, an integral launch enable signal is generated at the output of the formation of the integral launch permit signal 8; rockets, which then goes to the input of the rocket launch signal generation block 11, making it possible for this block to generate ignition pulses to launch the rocket by pressing arrow with a switch for the “Start” signal switch 10, and on the indicator of the launch permission of the rocket operator-operator 9. When the launch permission indicator 9 shows the launch permission symbol, the arrow-operator launches the rocket by pressing the “Start” signal switch 10.

As a sight 1, or, in accordance with the terminology currently used, an overview and aiming system (since it is not just an optical sighting device, but a complex system, including, for example, a stabilizer, a range finder, a survey system, which has in its up to three survey channels (television, thermal imaging, optical), partially (optical direction finder) or fully (laser guidance system) missile guidance device) can be used, for example, round-the-clock television lovizionny scope with gyro-stabilized head mirror.

As sensors for the angular position of the LV 2, 5, for example, transformer sensors of the SKT225D type can be used.

As sensors for the angular velocity of the LV 3, 4, for example, the potentiometers of the handles of the remote control of the sight can be used, which specify the speed of movement of the gyrostabilized head mirror of the sight, i.e. optical axis or line of sight.

As an overview system of the sight of the operator-shooter 14, for example, a combined viewing system including a daytime television viewing channel implemented on the basis of the DTK-M daytime transmitting television camera and a round-the-clock thermal viewing channel made on the basis of the TPVK thermal imaging camera can be used -24NS. In this case, a sign of malfunction of the survey system is formed when both survey channels of the system malfunction.

The block for generating a signal to enable launch of a rocket according to the angular position of the line of sight of the sight of an arrow-operator 6 can be performed, for example, in accordance with the functional block diagram of a block for generating a signal for enabling a launch of a rocket given in the description of the prototype [2], with the addition of an analog- a digital converter and a controller for transmitting information about the angular deviations of the LV of the sight of the arrow operator in two mutually orthogonal planes to the input of the indicator of the angular position of the line of sight Sight arrow operator in digital serial code.

As an indicator of the angular position of the line of sight of the sight, the operator arrow 7 can be used, for example, a television indicator of the driver of a mobile carrier, on which is indicated, for example, in the form of a rectangle, the angular zone of the allowed launch of missiles. The position of the drug is marked with a certain symbol, for example, a crosshair moving around the screen of the television indicator depending on the change in the angular position of the drug.

For example, a television indicator can be used as an indicator of permission to launch a missile operator-operator 9.

The start signal switch 10 can be implemented, for example, in the form of a start button.

As a launcher 12 with a missile sensor 13 can be used, for example, a standard aviation launcher APU-4/4 with four guides for installing missiles. When installing a rocket on a rail, one of the contacts of its (rail) launching circuit is closed on the APU-4/4 housing, connected to the housing of the mobile carrier, with which, in turn, are connected the housings of all blocks of electronic equipment installed on the mobile carrier. When an arrow operator selects one or another guiding signal, the “Housing” signal coming from this contact to the unit for generating the integrated launch permit signal will be informational, indicating the presence of a rocket on this guide. When the rocket starts with the guide, the contact opens, interrupting the receipt of the “Housing” signal to the block for generating the integral signal for launch launch permission 8, which indicates the absence of the rocket on this guide.

The unit for generating the integral signal for launch launch permit 8 may include, for example, a controller and an AND circuit. The signal of readiness of the overview system of the sight of the arrow operator 14 for operation (serviceability) in a digital serial code is supplied from the information output of the overview system of the sight of the arrow operator 14 to the controller and then in the form of a logic level signal to one of the inputs of the “AND” circuit. The two other inputs of the “I” circuit respectively receive signals from the rocket of the launch permit signal for the launch according to the angular position of the sight line of the sight of the operator arrow 6 and from the presence sensor of the rocket 13 of the launcher 12. At the same time, the integral launch permit signal will be generated at the output of the block 8 only if all three conditions are met - when the LV sight of the operator arrow is within the angular zone allowed for launching the missile, the missile is on the launcher 12, and the surveillance system is operational and the arrow operator 14.

The rocket launch signal generation block 11 can be made, for example, in the form of a series-connected switch and a pulse shaper (pulses) of normalized duration to initiate the rocket ignition circuits. At the same time, the signal input of the switch is connected to the start signal switch 10, and its control input is connected to the output of the unit for generating the integral signal for launch launch permit 8.

Information sources

1. DE, patent No. 2239983, class. F41G 3/22, 1976.

2. Patent of Russia No. 2087831, IPC F41G 3/22, B64D 7/08, 1995.

Claims (1)

A device for launching a rocket from a mobile carrier, including an operator-gun sight with sensors of angles and angular velocity of the line of sight in two mutually orthogonal planes, a unit for generating a signal for launching the launch of the rocket by the angular position of the line of sight of the sight of the arrow-operator, connected to the angular indicator, connected to the sensors the position of the sighting line of the sight of the operator arrow, the “Start” signal switch and the indicator of permission to launch the arrow of the operator operator, characterized in that an installation with a missile presence sensor, a sight sighting system for an operator-operator, an integrated rocket launch enable signal generation unit and a rocket launch signal generation unit, the inputs of the integrated rocket launch enable signal generation unit being connected to the output of the rocket launch enable signal generation unit for the angular position of the line sighting of the sight of the arrow operator, the sensor of the presence of a rocket launcher and the observation system of the sight of the arrow operator, respectively, the inputs of the unit are formed The rocket launch signal is connected to the output of the integrated launch permit enable signal generating unit and the “Start” signal switch, and the operator-arrow launch enable indicator is connected to the output of the integrated launch rocket enable signal generating unit.