RU2766029C1 - Rocket launcher - Google Patents

Abstract

FIELD: space technology.

SUBSTANCE: invention relates to the field of rocket technology, and more specifically to launchers. The rocket launcher contains a base with adjustable supports with a fixed gear block. A pivoting support device with the possibility of rotation in a horizontal plane is installed on the base, with a spring-lever mechanism fixed in the selected position. Platforms swinging on a fixed axis with blocks of guides for placing rockets are installed on the bed of the support-rotary device. The spring-lever mechanism is equipped with a set of wedges sliding in a vertical plane in a sealed housing and pressed by a set of springs to a profile gear block, as well as a lever swinging in a vertical plane, the short arm of which goes into the grooves of the wedges. The rocket launcher contains a digital rocket launch control system. The system includes a compact remote control unit, a launch unit, an azimuth sensor, elevation angle sensors, microswitches, and an indication unit. The pivoting device is equipped with a spring-lever mechanism. The elevation angle of each swinging platform is adjusted separately.

EFFECT: increased reliability is achieved.

5 cl, 6 dwg

Description

The invention relates to rocket technology and can be used to protect agricultural crops and plantations from hail damage or artificial induction and redistribution of precipitation.

Known designs of anti-hail rocket launchers with manual control, for influencing atmospheric processes, containing a base, a rack, with a swivel placed on the rack with the ability to rotate around an axis, a platform (cradle) mounted on a swivel with guides for placing missiles, guidance drives for a rocket launcher in elevation and azimuth, equipped with locking devices for fixing the missile launcher at pointing angles (Bibilashvili N.Sh., Burtsev I.I., Seregin Yu.A. Guidelines for organizing and carrying out anti-hail work. - L .: Gidrometeoizdat, 1981 , pp. 40-46).

The disadvantages of the known missile launchers include low efficiency and reliability, as well as the inability to re-equip the installation with a block of guides for launching anti-hail products of various calibers and types.

A rocket launcher is known, comprising a base, a rack placed on a rack with the possibility of rotation around an axis, a turntable mounted on a turntable, an oscillating platform with guides for placing missiles, actuators for pointing the rocket launcher in elevation and azimuth, equipped with locking devices for fixing the missile launcher at pointing angles, as well as blocks for indicating azimuth and elevation angles, while the azimuth angle indexing block contains a pointer attached to the turntable in its lower part and placed under the pointer on the fixed base of the rack limb, and the block for indicating elevation angles located in the upper part of the turntable, contains a pointer attached at the output to the axis of the swing platform and a fixed limb attached to the sidewall of the turntable (RF Patent No. 2299556 C1, A01G 15/00, F42B 12/00, 2007).

The well-known launcher called "Eliya-MR" is made universal, with interchangeable stacks of multi-tiered guides for anti-hail missiles of various calibers and types. Guide packages are unified in terms of dimensions, fastening to the platform for their placement.

The main disadvantage of the known rocket launcher is the lack of fixation of the launch time of missiles when firing at clouds, as well as the control system for setting the azimuth and elevation angles. As a result of this shortcoming, the effectiveness of the impact on clouds is significantly reduced and the possibility of accounting for actually used missiles is excluded.

An automated anti-hail rocket launcher is known, containing a control system consisting of a radio modem, a control computer, a controller for controlling electrical wires, control units for electric drives of azimuth and elevation angle, consisting of engines with two-stage gearboxes and absolute angular position sensors, a controller for starting circuits that generates a missile launch impulse at the coincidence of the azimuth and elevation codes issued by the computer and angle sensors, as well as blocking the launch of missiles on an alarm from a security alarm. Replaceable guide packages, consisting of two blocks unified in terms of dimensions and fastening, allow launching anti-hail missiles of various types - with folding into a caliber and rigid tail, as well as with dynamic and jet launch. The installation operates on the commands of the central computer in automatic mode without the participation of personnel (except for charging rockets) (RF Patent No. 2370943 C1, A01G 15/00, F42B 12/00, 2009).

A disadvantage of the well-known automated anti-hail rocket launcher is the complexity of the design, the high complexity of manufacturing, the high cost of manufacturing. In addition, the operation of an automated installation in difficult weather conditions (exposure to atmospheric moisture, temperature changes, etc.) often leads to failure of the control system, the launch of the rocket does not occur or occurs with a time delay.

The closest analogue in technical essence to the claimed invention is a rocket launcher, containing a base, a rack, a turntable, an oscillating platform with guides for placing missiles, guidance drives with locking devices, blocks for indicating azimuth and elevation angles with a pointer, a cable network (or radio channel), an analog video monitoring system, consisting of two autonomous video devices in sealed, dust and moisture-proof compartments (cases), with backlight, video recorder, video camera. The first video device is attached to the movable turntable in its lower part above the movable pointer of the azimuth angle indexing unit, and the second video device is placed in the upper part of the turntable horizontally and directed towards the movable pointer of the elevation angle indication unit. Used as a video device, a stand-alone video recorder allows real-time recording of video, sound, the exact date and time of missile launch on a memory card. The used remote video camera provides transmission of video and audio information via communication channels to a remote terminal (monitor) of command fire control (RF Patent No. 2529043 C2, F41F 3/04, 2012).

The disadvantages of the known rocket launcher include the complexity of its design, the complexity of assembly and disassembly of its main elements and assemblies, as well as maintenance. In addition, the use of an obsolete analog video monitoring system does not allow achieving the required quality of shooting at night, as well as in adverse weather conditions, when exposed to atmospheric moisture and temperature changes, which leads to a decrease in the reliability of the launcher.

These shortcomings reduce the effectiveness of the launcher and limit its use in practice of anti-hail protection.

The technical result, to which the present invention is directed, is the creation of a rocket launcher equipped with a digital missile launch control system using new design solutions that increase the functional reliability and efficiency of active impact on hail clouds.

The technical result is achieved by the fact that in a well-known rocket launcher, containing a base, a rack, a turntable placed on the rack with the possibility of rotation, radially mounted in the upper part on the turntable, swinging on the fixed axis of the platform, with asymmetrically located blocks of guides for placement of missiles, guidance mechanisms in elevation and azimuth, equipped with locking devices for fixing the missile launcher at the guidance angles, as well as units for indicating azimuth and elevation angles, according to the invention, the rocket launcher contains a digital missile launch control system, consisting of a remote control , launch unit, azimuth sensor, elevation angle sensors, microswitches, display unit, while the turntable is equipped with a spring-lever mechanism, and the elevation angle of each swinging platform is adjusted separately.

The technical result is achieved in that the remote control is placed in a shockproof case and is equipped with a universal power supply, a memory unit and a control system.

The technical result is achieved by the fact that the spring-lever mechanism is equipped with a set of wedges sliding in a vertical plane and pressed by a set of springs to a profile toothed shoe.

The technical result is achieved by the fact that the elevation angle of the swinging platforms is controlled by forced engagement of the gears fixed on the fixed axle and on the end surface of the swinging platforms, followed by fixation with a locking device equipped with a handle.

The technical result is achieved by the fact that the digital missile launch control system keeps an event log with information recorded in the memory block.

Distinctive features of the proposed design are aimed at creating an easy-to-use, safe rocket launcher, with increased functional reliability and efficiency of active impact on hail clouds.

The digital missile launch control system, incorporating a set of automatic control devices for the necessary parameters, increases the accuracy of guidance, ensures ease of control and allows you to quickly identify and record the causes of any malfunctions in an electronic log.

The spring-and-lever mechanism mounted on the slewing device, by coupling wedges pressed by a set of springs to the profile gear block, ensures reliable fixation of the installation in a given direction in azimuth.

The constructive possibility of locating each swinging platform of the rocket launcher at a certain elevation angle makes it possible to increase the efficiency of active influence on atmospheric processes.

Therefore, each essential feature of the claimed invention is necessary, and their combination in a stable relationship is sufficient to achieve a new quality that is inherent in the signs of disunity, that is, the required technical result is achieved by the effect of the sum of features unknown from the prior art.

The comparative analysis of the claimed invention with the identified analogues of the prior art, from which the invention does not explicitly follow for a specialist in anti-hail protection, confirmed the uncertainty of the proposed technical solution, and taking into account the possibility of industrial mass production of rocket launchers, we can conclude that the patentability criteria are met.

The essence of the invention is illustrated by the drawing, which has a purely illustrative purpose and does not limit the scope of claims of the essential features of the claims.

The drawings (Fig. 1 and Fig. 2) show a general view of the rocket launcher in two projections, the drawing (Fig. 3) shows a spring-lever mechanism, the drawing (Fig. 4 and Fig. 3) shows the mechanism of the elevation angle scale and aiming the azimuth angle, the drawing (Fig. 6) schematically shows the remote control.

The rocket launcher contains a base with adjustable supports 1, with a rigidly fixed toothed block 12. A turntable 2 is coaxially mounted on the base, with the possibility of rotation in the horizontal plane by 360 degrees and reliable fixation in the selected position by a spring-lever mechanism 3. On the bed the slewing device is radially mounted swinging on a fixed axis 4 platform 5, with asymmetrically located guide blocks for placing missiles 6. The swinging platform can be set to an elevation angle of up to 85 degrees, followed by fixation with a locking device (not shown in the drawing) in the selected position.

The spring-lever mechanism is equipped with a set of wedges 9 sliding in a vertical plane in a sealed housing 10 and pressed by a set of springs 11 to a profile toothed block 12, as well as a lever 13 swinging in a vertical plane, the short arm of which enters the grooves of the wedges.

The gear wheels 8 of the elevation angle mechanism are fixed on the fixed axis 4 and on the end surface of the swinging platforms 5. Fixation is carried out by a locking device equipped with a handle 7.

Rocket launcher contains a limb 20, coaxially fixed on the base of the installation 1 and pointer 21 attached to the turntable 2 in its lower part, for guidance in azimuth, as well as limbs 22 rigidly attached to the swinging platforms and pointers 23 mounted on a fixed axes 4 for aiming at elevation angles. When pointing the installation in azimuth, the limb 20 remains stationary, and the pointer 21 rotates together with the turntable. When pointing rocking platforms with guides for placing missiles at elevation angles, the limbs 22 rotate relative to the fixed axis and the pointer 23.

The digital missile launch control system includes: a compact remote control (hereinafter referred to as the remote control) located at the workplace of the firing operator, a launch unit 14 mounted on a turntable, an azimuth sensor 15, the body of which is attached to the turntable and rotated along with the installation, and the shaft is attached to a fixed base, elevation angle sensors 16, fixed in the direction of the descent of missiles on rocking platforms, microswitches 17, display unit 18, voice (sound) detector 19.

The remote control is made in a portable impact-resistant case and is designed to organize the safe control of missile launches. Equipped with a power supply unit, a memory unit, power connectors (from a 24V battery and from a 220V mains), connectors for connecting 3 rocket launchers. On the front panel of the remote control there are: a general power button 24, power switches for missile launch circuits on installations 25, a missile launch button 26, an emergency button to interrupt the "stop" circuit 27, a liquid crystal display (LCD) 28, US V connectors for connecting keys access, as well as USB flash drives 29.

The LCD display of the remote control displays the current time, the location of the launches, the number of the impact point (edited by the launch manager), azimuth, elevation angles, active icons depicting missiles, reflecting their status (the presence / absence of ready-to-launch, in the launch queue, the launch has been completed success, failure to launch due to an open circuit, the rocket did not leave the guide), directions in azimuth in which rocket launches are prohibited (up to three prohibited sectors), active icon of the stop button, display brightness, sounder volume.

The rocket launcher works like this:

After charging the launcher with missiles and turning on the remote control, the launch unit 14 is turned on, which starts polling the azimuth sensor 15 and elevation sensors 16. The information received is transmitted to the remote control, displayed on the LCD display, display unit 18, and duplicated by the voice detector 19.

Further, on commands from the control center for anti-hail operations, focusing on the readings of the display unit, remote control and sound detector 19, the missile launcher is directed and fixed in the selected direction by the operator using the guidance mechanisms of the missile launcher in azimuth and elevation.

The desired azimuth is set by pressing the long arm of the lever 13 of the spring-lever mechanism, while the short arm raises the wedges 9, which, in turn, compress the springs 11 and disengage from the fixed gear block 12. In this position of the lever, the turntable with swinging platforms gets the ability to turn in a horizontal plane relative to the base. To fix the launcher in the selected position, the long arm of the lever is smoothly lowered, the wedges, under the action of the springs, engage with the teeth of the gear block.

The angle of elevation of the swinging platforms is set by engaging the gear wheels 8 fixed on the fixed axis 4 and on the end surface of the swinging platforms 5, followed by fixation with a locking device equipped with a handle 7. The swinging platforms are fixed by rotating the handle. When this occurs, the displacement of the swinging platforms along the axis in the direction of the gears fixed on the fixed axle, followed by engagement with the gears of the end surface of the swinging platforms.

After setting and fixing the guidance angles in elevation and azimuth, the launcher is ready to fire. The operator, upon completion of the preparatory work, leaves the site with the launcher and goes into cover.

When the switch of the corresponding missile launcher on the remote control is moved to the position for launching missiles, the launcher begins to constantly check the missile launch circuits and transmit the received information about the presence of missiles to the remote control. Based on the information received, the operator programs the missile launch sequence by clicking on the appropriate icons on the control panel display. After that, by pressing the "start" button on the front panel of the remote control, the selected missiles are launched in a given sequence and with pre-programmed time intervals between launches.

During launches, the control system maintains an event log, where information about the launches is recorded: date, time and place of launch, azimuth, elevation angle, number of missiles fired, information about failures (if any).

The launch control system of the launcher distinguishes between the following failures:

- after giving an impulse to launch the rocket, there is no break in the electrical circuit (the rocket did not descend);

- in the process of launching rockets, the chain of the rocket in the launch queue is interrupted until an electrical launch impulse is received (the rocket did not go down due to an open circuit).

The remote control has two-level access (personification) to settings management - operator, manager.

The missile launcher has the ability to program up to three forbidden sectors in azimuth. When the installation is oriented along the forbidden azimuth, the launch of missiles will be prohibited, and a corresponding warning will appear on the remote control screen.

When the swinging platforms are lowered to a loading angle (less than 20 degrees) in order to avoid unauthorized launch of missiles during reloading, the launch unit programmatically prohibits missile launches, and the launch circuits are opened by the corresponding microswitches.

The inventive design of the rocket launcher, with manual guidance and a digital missile launch control system, provides the ability to control the guidance angles, the exact time of the missile launch, the state of the missiles, and the azimuth direction along which missile launch is prohibited on a real-time scale. Keeping an event log with recording information in the memory block about the launches, indicating the date, time and place of the launch, guidance angles, the number of missiles fired, about the failures of the missiles to leave the guides, indicating the reasons (if any), allows for timing and analysis of the produced works, monitor compliance with the requirements stipulated by the technology of influencing clouds in accordance with the established regulations.

Claims (5)

1. A rocket launcher containing a base, a rack, a turntable placed on the rack with the possibility of rotation, radially mounted in the upper part on the turntable, swinging on a fixed axis of the platform with asymmetrically located guide blocks for placing missiles, guidance mechanisms along the angle elevation and azimuth, equipped with locking devices for fixing the missile launcher at pointing angles, as well as units for indicating azimuth and elevation angles, characterized in that the missile launcher contains a digital missile launch control system, consisting of a remote control, launch unit, sensor azimuth, elevation angle sensors, microswitches, display unit, while the turntable is equipped with a spring-lever mechanism, and the elevation angle of each swinging platform is adjusted separately. 2. Rocket launcher according to claim. 1, characterized in that the remote control is located in a shockproof housing and is equipped with a universal power supply, memory unit and control system. 3. Rocket launcher according to claim 1, characterized in that the spring-lever mechanism is equipped with a set of wedges sliding in a vertical plane and pressed by a set of springs to a profile gear block. 4. Rocket launcher according to claim 1, characterized in that the elevation angle of the oscillating platforms is regulated by forced engagement of gears mounted on a fixed axle and on the end surface of the oscillating platforms, followed by fixation with a locking device equipped with a handle. 5. Rocket launcher according to claim. 1, characterized in that the digital missile launch control system keeps an event log with information recorded in the memory block.

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