RU2467280C1 - Device to launch rocket from mobile carrier - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to missile weapons to be launched from, for example, aircraft. Proposed device comprises sight with angle transducer and transducer of two-plane sight line angular velocity, unit to generate permit signal for rocket launch by angular position of sight lines connected to sight line angular position indicator, launcher with rocket availability pickup, rocket guidance device connected to, at least one of transducers of sight line angular velocity, unit to generate integral signal of rocket launch permit with its inputs connected to unit to generate permit signal for rocket launch by angular position of sight lines, rocket availability pickup and rocket guidance device, interconnected "Launch" signal switch and rocket launch signal generator connected in series.

EFFECT: expanded operating performances.

3 cl, 3 dwg

Description

The present invention relates to the field of placing 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 is known for launching a rocket from a helicopter [1], which includes an operator-shooter with sensors for 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 allows you to launch missiles 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:

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 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 a missile is located on the launcher (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 a radar guidance system) may fail by the time the gunner-operator decides to use a missile, in particular as a result of 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 therefore the effectiveness of the guided missile system installed on removable media. Launching a rocket with a faulty missile guidance device will lead to missile loss and missed combat mission.

The use of other indicators to provide the operator-shooter with information about the presence of a missile at the launcher and the readiness (operability) of the missile guidance device complicates the work of the operator-shooter, who, in preparation for launching a rocket in a combat situation, must take into account information from three indicators, distracting from monitoring the battlefield and tracking an already chosen target, and will also reduce the rate of fire of a complex of guided missile weapons mounted 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 different and perceived by the operator’s peripheral vision without difficulties, to enter the sight of an optical sight, for example, is practically impossible.

The disadvantages of this device, selected as a prototype, can be attributed to the fact that it does not take into account the influence of the side wind affecting the launched rocket. The lateral wind leads to an increase in the dispersion zone of rockets unfolding under the influence of a lateral wind in the direction of the wind (the center of pressure of the rockets is located behind the center of gravity). Given that the field of view of the missile guidance device has relatively small angular dimensions, at high speeds of lateral wind, a launched rocket may not fall into the field of view of its guidance device oriented in the direction of the LV of the sight of the operator arrow. Therefore, at significant crosswind speeds, it is advisable to expand the field of view of the missile guidance device (for example, plane-parallel tracking plates of the direction finder), normally oriented in the direction of the LV of the sight of the operator arrow, towards the wind by a certain angle, depending on the crosswind speed (for example, proportional to the crosswind speed ), to ensure that missiles get into the field of view of the guidance device. When a rocket appears in the field of view, the guidance device switches to the mode of tracking the rocket and generating the rocket control signals according to its angular mismatches with the direction of the LV of the sight of the operator arrow.

The aim of the invention is to increase the efficiency of a complex of guided missile weapons mounted on a mobile carrier, by preventing the loss of missiles at significant speeds of crosswind.

To achieve a technical result, a device for launching a rocket from a movable carrier is proposed, which includes a 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 sight line of sight, connected to the sensors, connected to the sensors sight sight lines, launcher with missile sensor, missile guidance device, section integral signal generating unit missile launch, the inputs of which are connected to the unit for generating a missile launch enable signal by the angular position of the sight line of sight, the missile launcher presence sensor and the missile guidance device, respectively, connected in series to the Start signal switch and the missile launch signal generating unit, the second input of which is connected to the output of the unit for forming the integrated signal for launching the rocket, the indicator for allowing the launch of the rocket connected to the output of the block for generating the integral signal missile launch authorization, and a wind sensor connected to the missile guidance device.

Figure 1 shows the functional diagram of the inventive device.

Figure 2 shows the functional diagram of the inventive device when performing a reversal of the field of view of the missile guidance device according to the signal from the start signal switch.

Figure 3 shows the functional diagram of the inventive device when performing a turn of the field of view of the missile guidance device according to the signal from the missile launcher presence sensor (at the start of the rocket).

On each of figures 1, 2, 3, sight 1 is presented with sensors of angles 2.5 and angular velocity 3.4 lines of sight in two mutually orthogonal planes, a unit for generating a signal for launching a missile for the angular position of the line of sight of the sight 6, an indicator of the angular position sighting line of sight 7, the unit for generating the integral signal for launching permission for the rocket 8, the indicator for allowing the launching of the rocket 9, the switch for the Start signal 10, the block for generating the signal for launching the rocket 11, the launcher 12 with the presence sensor 13, the device eniya 14 rockets and 15 wind sensor.

The device operates as follows. The signals from the sensors of the angular position of 2.5 and the angular velocity of 3.4 LV in each of the two mutually orthogonal planes enter the block for generating a signal for launching permission of the rocket at the angular position of the sight line of sight 6. From the output of the block for generating the signal for launching permission for launching the rocket at the angular position of the line sight sight 6 signals of angular deviations of the drug in two mutually orthogonal planes, adjusted for the lead, in the case of the presence of angular velocities of the drug in these planes, are input to the indicator of the angular position sight line of sight 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 of the target selected by the arrow operator) with the required accuracy. When the LV of sight 1 is in the angular zone allowed for rocket launch, at the output of the rocket launch permission signal generation block by the angular position of the sight line of sight 6, a rocket launch permission signal will be generated based on this feature, which will then be transmitted to the input of the rocket launch permission integral signal generation block 8 . The signal from the sensor of the presence of the rocket 13 of the launcher 12 and the signal of readiness for work (serviceability) are received at the other two inputs of the block for the formation of the integral signal for launching the launch of rocket 8. missile guidance devices 14, respectively. Given the readiness for operation (serviceability) of the missile guidance device 14, the presence of the missile on the launcher selected by the operator-operator 12, and the LV sight in the angular zone allowed for the launch of the missile, an integral missile launch enable signal is generated at the output of the integrated missile launch permit 8 signal. coming 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 arrow operator VK the trigger of the Start signal 10, and to the rocket launch permission indicator 9. When the rocket launch permission indicator 9 shows the launch permission symbol, the operator-shooter launches the rocket by pressing the Start signal switch 10.

According to signals proportional to the crosswind speed coming from the wind sensor 15 in analog or digital form, the field of view of the missile guidance device 14 is rotated from the direction of the aircraft towards the wind by a certain angle, for example, proportional to the crosswind speed, which varies in time with the change in the speed of the crosswind the wind. The field of view can change its orientation (turn around) depending on the crosswind speed either from the moment the guidance device 14 is turned on, or, in order to save the resource of the tracking system of the missile guidance device, by the launch signal from the start signal switch 10, or by start missiles, information about which is received from the missile sensor 13 of the launcher 12. The launch and launch signals of the missile can be sent to the missile guidance device 14 from the Start switch 10 and the missile sensor 13, both analog and digital in the form, in particular in a digital serial code.

When a missile appears in the field of view of the guidance device 14 (for example, the light spot of the on-board infrared beacon of the rocket on the photodetector of the optical direction finder), the tracking system of the rocket guidance switches to the tracking mode of the rocket and generation of the rocket guidance signals according to its angular mismatches with the direction of the LV sight 1.

As a sight 1 or in accordance with the terminology of the sighting system currently in use (since it is not just an optical sighting device, but a complex system that includes, for example, a stabilizer, a range finder, a survey system, which has up to three viewing channels (television, thermal imaging, optical), partially (optical direction finder) or fully (laser guidance system) missile guidance device) can be used, for example, an optical sight with gyrostabilization Rowan 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.

The block for generating a launch permit signal for the launch according to the angular position of the sight line of sight 6 can be performed, for example, in accordance with the functional diagram of the rocket for launch launch permission signal generation block given in the device description [1], with the addition of an analog-to-digital converter and controller for transmitting information about the angular deviations of the LV sight in two mutually orthogonal planes to the input of the indicator of the angular position of the line of sight sight 7 in digital sequence m code.

As an indicator of the angular position of the line of sight of the sight 7 can be used, for example, a television indicator of the driver of the mobile carrier, which is displayed, 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 drug.

The unit for generating the integral signal for launch launch permit 8 may include, for example, a controller and logic circuit I. The signal that the missile guidance device 14 is ready for operation (serviceability) in a digital serial code comes from the information output of the missile guidance device 14 to the controller and then in the form a signal of a logical level to one of the inputs of the circuit I. The two other inputs of the circuit And respectively receive signals from the block for generating a signal for launching the rocket by the angular position of the line of sight I ate 6 and from the missile launch sensor 13 of the launcher 12. At the same time, the integral launch enable signal will be generated at the output of block 8 only if all three conditions are met - when the LV sight is within the angular zone allowed for missile launch, the missile is on the launcher 12 and readiness for operation (serviceability) of the missile guidance device 14.

As an indicator of permission to launch rocket 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.

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, and its control input is connected to the output of the block for the formation of the integral signal for launch launch permission.

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 a rocket is mounted on a rail, one of the contacts of the rail launch connector is shorted to 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.

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. The radio link transmits the generated guidance signals aboard the rocket. In it, the guidance signals are subjected to time-pulse modulation and in the form of powerful microwave pulses of ultrahigh frequency are emitted by the radio antenna in the direction of the LV.

According to signals proportional to the crosswind speed coming from the wind sensor 15, plane-parallel servo plates of the direction finder rotate the field of view of the direction finder towards the wind by a certain angle, for example, proportional to the speed of the crosswind. When a light spot of the onboard infrared beacon of the rocket appears on the photodetector of the optical direction finder, the latter goes into the tracking mode of the rocket and generates signals for guiding the rocket by the angular mismatches of its airborne infrared beacon with the direction of the LV sight 1 (Angular mismatch signals are signals from the angular deviation sensors of plane-parallel tracking plates of the direction finder relative to the initial direction of the field of view of the direction finder, coinciding with the direction of the drug). In order to save the resource of the tracking system of the direction finder (motors and gearboxes of the tracking plates), the rotation of plane-parallel tracking plates can be carried out by the launch signal from the Start switch 10, or by the start of the rocket, information about which comes from the presence sensor of the rocket 13 of the launcher 12.

As a wind sensor 15, for example, an OMS-160 wind sensor can be used.

Information sources

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

Claims (3)

1. A device for launching a rocket from a mobile carrier, including a sight with sensors of angles and angular velocity of the line of sight in two mutually orthogonal planes, connected to the sensors, a block for generating a signal for launching permission of the rocket by the angular position of the sight line of sight, connected to an indicator of the angular position of the sight line of sight , a launcher with a missile presence detector, a missile guidance device, an integrated signal generation unit for launch launch permit, the inputs of which are connected to the unit the formation of the launch permit signal on the angular position of the sight sight line, the presence of the launch rocket and the missile guidance device, respectively, connected in series to the Start signal switch and the rocket launch signal generation unit, the second input of which is connected to the output of the formation of the integral rocket , and a launch rocket enable indicator connected to the output of the integrated rocket launch enable signal generating unit and a wind sensor is connected output to missile guidance device. 2. The device according to claim 1, characterized in that the missile guidance device is connected to the start signal switch. 3. The device according to claim 1, characterized in that the missile guidance device is connected to a missile launcher presence sensor.

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