RU2451260C9 - Device to launch missile from moving carrier - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: device comprises master gunner sight with transducers of angles and angular speed of pointing direction in two mutually orthogonal planes, missile launch arm signal generation unit connected to said transducers, signal ''Launch'' switch, launch arm indicator, launcher with missile availability indicator, missile guidance device, launch arm integrated signal generation unit and missile launch signal generation unit. Outputs of launch arm integrated signal generation unit are connected to output of launch arm signal generation unit to launch missile by angular position of master gunner pointing direction, missile availability indicator, and missile guidance device output. Inputs of missile launch signal generation unit are connected to launch arm integrated signal generation unit and ''Launch'' signal switch, while missile launch arm signal indicator is connected to launch arm integrated signal generation unit output.

EFFECT: higher combat efficiency.

1 dwg

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, for example, 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:

$$(\mathrm{one})\begin{array}{c}|\; |\; |{\alpha }_{g\mathrm{about}R}+{\omega }_{g\mathrm{about}R}\Delta t_{n\mathrm{at}}|\; |\; |\le \varphi ;\\ |\; |\; |{\beta }_{\mathrm{at}eRt}+{\omega }_{\mathrm{at}eRt}\Delta t_{n\mathrm{at}}|\; |\; |\le \psi ,\end{array}$$

where α _mountains, β _vert - angular deflection line of sight (LOS) crosshair arrow operator in two mutually orthogonal planes (horizontal and vertical planes, respectively) with respect to the "zero" direction DX at which the sensor signals its angular position are equal to 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 signals 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 missile guidance device is ready (operational). 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 a missile guidance device (for example, an optical direction finder with a device for transmitting guidance to a missile, a laser or radar guidance system) may fail by the time the gunner-operator decides to use the missile, in particular as a result combat damage to equipment, media or the consequences of this damage.

Therefore, it is more rational to provide aggregate or integral information about the launch launch resolution to the operator-shooter indicator, taking into account the fulfillment of these three conditions (finding the arrow of the operator-gunner’s sight in the angular zone allowed for launching the missile, the presence of the missile on the selected launcher and the serviceability of the missile guidance device). 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, consequently, the effectiveness of the guided missile system mounted on a movable medium. Launching a rocket with a faulty missile guidance device will lead to missile loss and missed combat mission.

Using other indicators to provide the shooter with operator information about the presence of a missile at the launcher and the operational readiness (serviceability) of the missile guidance unit 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, being distracted from observing the battlefield and tracking an already chosen target, and will also reduce the rate of fire of a complex of guided missile weapons installed on a mobile carrier. To enter, for example, information from three indicators that would not obscure part of the terrain image, would not impair the quality of terrain visibility and, at the same time, be differentiated and perceived by the operator’s peripheral vision without difficulties, to enter the sight of an optical sight, for example, is practically impossible.

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, a missile guidance device, 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 sight line arrow- the operator, the missile launcher presence detector and the missile guidance device, respectively, the inputs of the missile launch signal generating unit are connected to output b eye forming an integral Run enable signal rockets and signal switch "Start" and start authorization indicator missile arrow operator is connected to the output of the block forming the integral signal resolution missile 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 sight line 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, the indicator of the angular position of the line of sight of the sight of the arrow-operator 7, the unit for generating the integral signal for launching the rocket 8, the indicator of permission for launching the rocket-operator 9, the start signal switch 10, the formation block missile launch signal 11, launcher 12 with a missile sensor 13 and missile guidance device 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 guidance device rocket 14, respectively. Provided that the guidance device of the rocket 14 is operational, the missile launcher 12 selected by the shooter-operator is located, and the arrow of the operator-shooter is in the angular zone allowed for launching the missile, the integral signal of launch launch permit formation is generated at the output of the integrated rocket launch enable signal. further 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 the on-arrow operator Atelier signal "Start" 10, and to permit the indicator arrow missile launch operator 9. When the display start-up missile launch authorization 9 character permits the shooter-operator produces missile launch by pressing the switch "Start" signal 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 consisting of up to three viewing channels (television, thermal imaging, optical), partially (optical direction finder) or fully (laser guidance system) missile guidance device), for example, an optical sight with gyrostabil can be used zoned 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 the guidance device of the rocket 14 can be used, for example, an optical direction finder beacon infrared spectral range mounted on the rocket, with a radio link. The direction finder determines the angular deviations of the beacon of the rocket relative to its own optical axis, verified with the direction of the drug, converted further in accordance with the selected control law into guidance signals of the rocket. In the radio link, the guidance signals undergo time-modulation and, in the form of powerful microwave pulses, are emitted by the radio antenna in the direction of the LV.

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.

As an indicator of permission to launch missiles arrow operator 9 can be used, for example, an LED inserted into the eyepiece of the sight. The radiation of the LED is fixed by the peripheral vision of the operator arrow.

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 guidance device of the rocket 14 for operation (serviceability) in a digital serial code is supplied from the information output of the guidance device of the rocket 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 rocket launch, the presence of the rocket on the launcher 12 and the operability of the pointing device r chum 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 a new installation with a missile presence sensor, a missile guidance device, 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 being connected to the output of the rocket launch enable signal generating unit by the angular position of the sight sight arrow -operator, missile launcher presence detector and missile guidance device, respectively, the inputs of the rocket launch signal generating unit are connected They are connected to the output of the unit for generating the integrated signal for launch launch permission and the Start signal switch, and the indicator for the launch arrow for the arrow-operator is connected to the output of the unit for generating the integral launch permission signal for the launch.