RU2582308C1 - Method of firing missiles controlled by laser beam, and optical sight of missile guidance system - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: group of inventions relates to shells guidance systems. Method of firing with shells controlled by a laser beam includes measurement of the range to the target and introduction of the measured value D_T in a ground-based control system, comparison of the measured range to the target D_T with stored in memory of the ground control system range value D_min, allowing introduction of beam axis excess relative to target sighting line, setting of the excess under the condition D_T>D_min, launching of a guided shell, flight of the shell in the beam with an excess above the target sighting line until the moment of time set in the ground-based control system in accordance with the measured range to target, and alignment of the beam axis with the target sighting line. At that, when distance to the target is less than distance D_min, but more than distance D_EG, where D_EG is the range to the shell at time moment $$t_{EG}=\frac{\mathrm{2,5}\dots \mathrm{3,5}}{{\omega }_{coff}};$$

ω_coff is a cutoff frequency of the system of shell control, rad/s, the centre of information field of the beam during the time from shell launch to time moment t_M, where $$t_{М}=\frac{\mathrm{0,5}\dots \mathrm{1,5}}{{\omega }_{coff}},$$

are displaced upward relative to the axis of the beam by the value Y_EG= (0.2…0.5) R_b, where R_b is the radius of the beam, after which they are matched during the time interval from moment of t_M to moment t_EG, while, when the distance to the target is less than distance D_EG, firing is performed without any displacement of the centre of information field of the beam. Proposed device is equipped with electronic displacement generator whose input is connected to the output of the generator of time intervals, and output is connected to the first input of the adder.

EFFECT: technical result consists in ensuring a possibility to exclude a contact of the shell with the underlying surface.

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Description

The invention relates to methods of firing guided projectiles and can be used in guidance systems (SN) with tele-orientation of the projectile in the laser beam.

One of the problems solved in the development of strategic missiles guided missiles is to increase the accuracy of their guidance.

Known methods of firing guided projectiles using the “three-point” guidance method (N. Kuzovkov. Aircraft stabilization systems (ballistic and anti-aircraft missiles). M.: Higher School, 1976, p. 220), in which the projectile the flight process is on the line connecting the launch device and the target, i.e. on the line of sight of the target (LC).

In a number of known methods, the principle of teleorientation of a guided projectile in a laser beam is used, the information axis of which is combined with the LEC. Devices that implement these methods (US patent 5427328, NKI 244-3.13, 12.02.85; German patent 4137843, MKI F41G 1/38, 05/19/93), contain a sighting channel and a guidance channel with a laser radiation source, the axes of which are aligned, and also a modulator and an optical system with a variable focal length, ensuring the constancy of the linear beam size at all projectile flight ranges, starting from the moment the focal length changes (the beginning of beam narrowing). Up to this point, the beam has a constant initial angular size, and its linear size increases in proportion to the flight range.

The disadvantages of these methods are:

deterioration of the visibility of the target and low noise immunity of the communication line due to the influence of smoke from the projectile engine on the process of tracking the target and guiding the projectile;

a high probability of detecting the complex due to the fact that during the flight of the projectile the center of the beam is aimed at the target;

the flight of the projectile in close proximity to the underlying surface (soil, shrub), as a result of which there is some likelihood of contact with it, especially in the initial guidance section for shells with a low initial velocity (less than 100 m / s) having a large dispersion of trajectories.

Closest to the proposed is a method of firing a projectile controlled by a laser beam (patent RU 2126946, MKI6 F41G 7/26, 11.25.97), including measuring the distance to the target and entering the measured value of D _c in the ground control system, comparing the measured distance to the target D _p with a ground control system memory stored value range D _min, allowing the introduction of excess relative to the beam axis boresight target, setting the excess when the condition D _n> D _min, run guided projectile, the projectile flying in the beam with excess n Ad target line of sight to the point in time set in the ground-based control system in accordance with the measured range to the target, and the combination of the axis of the beam with the LCS.

The SN optical sight of a guided projectile (patent RU 2126946, MKI6 F41G 7/26, 11.25.97) that implements this method contains a coaxially mounted target sighting channel (CVC) and a guided projectile guidance channel (KH) consisting of optically coupled laser (L ), a modulator (M), a plane-parallel plate (PP) with a rotation mechanism and its control circuit (MPSU) and an optical system (OS) with a variable focal length, as well as a target range input device (ATC), the output of which is connected to the first input shaper time intervals (FVI), second whose input is connected to the projectile launch system and the output connected to the input MPSU.

According to this method, shooting in a mode with an excess of the axis of the beam relative to the LCF can be carried out at a range of at least some value of D _min , which is determined by the time the projectile rises to exceed and descends from it. Before launching the projectile in the electronic circuit of the sight, a comparison of the measured range to the target D _c with the stored in the memory value of the range D _min , allowing the introduction of excess. When D _n> D _min in shooting mode performed in excess, while D _n ≤D _min - without exceeding.

The optical sight provides firing in excess (raising the beam and its subsequent combination with the LCF, depending on the distance to the target) by rotating the plane-parallel plate.

The firing of shells with a low initial speed and subsequent acceleration with the help of an engine is characterized by a rather long transient process. It is known that the transient time τ in CH at its approximation of the first order aperiodic link with a time constant T _CH is determined by the relationship (VA Besekersky, EP Popov. Theory of Automatic Control Systems. M .: "Science" 1972 , p. 71):

τ = 3T _CH

, где ω_cp - частота среза СН, рад/с,or given that $$T_{CH}=\frac{\mathrm{one}}{{\omega }_{cp}}$$

where ω _cp is the cutoff frequency of the SN, rad / s,

The cutoff frequency of the SN, in turn, is associated with the aerodynamic characteristics of the projectile and the lower the lower its speed, which accordingly increases the duration of the transition process. This duration determines the rise time for excess.

The value of D _min , which, as indicated above, is determined by the time the projectile rises to exceed and descends from it, for shells with a low initial velocity it can be 20-25% of the maximum firing range. For example, with a total ascent-descent time of 6-8 s and an average projectile velocity in this section of 150-200 m / s, the range D _min will be 900-1600 m (hereinafter we will take the value of 1500 m as an example) with a maximum range of firing shells this class is 5000-6000 m.

The disadvantage of this method is the possible contact with the underlying surface at the initial guidance site when firing without exceeding the range D _c ≤D _min in the presence of acceleration from the action of gravity and an unfavorable combination of factors determining the dispersion of the trajectories (initial disturbances in angle and angular velocity the longitudinal axis of the projectile, disturbances when the engine is turned on, etc.).

The objective of the invention is to increase the accuracy of shooting in the mode without exceeding by reducing projectile deviations below the LCF.

; ω_ср - частота среза системы управления снарядом, рад/с, центр информационного поля луча в течение времени от запуска снаряда до момента времени t_M, где $$t_M=\frac{\mathrm{0,5}\dots \mathrm{1,5}}{{\omega }_{cp}}$$

, смещают вверх относительно оси луча на величину Y_ЭГ=(0,2…0,5)R_Л, где R_Л - радиус луча, после чего их совмещают в течение времени от момента t_M до момента t_ЭГ, а при дальности до цели менее дальности D_ЭГ стрельбу производят без смещения центра информационного поля луча.The problem is solved due to the fact that, compared with the known method of firing a projectile controlled by a laser beam, including measuring the distance to the target and entering the measured value D _c into the ground control system, comparing the measured distance to the target D _c with that stored in the memory of the ground system control the value of the range D _min , allowing the introduction of an excess of the axis of the beam relative to the line of sight of the target, setting the excess when the condition D _c > D _min , launching a guided projectile, flight of the projectile in the beam with excess above the line of sight of the target to the point in time specified in the terrestrial system control in accordance with the measured distance to the target, and alignment of the beam with the line of sight axis of the objective, new is the fact that in the proposed method, when the target range of less than distance D _min, but a range D _EG , where D _EG is the distance to the projectile at time $$t_{ER}=\frac{\mathrm{2,5}...\mathrm{3,5}}{{\omega }_{\mathrm{from}R}}$$

; ω _cf is the cutoff frequency of the projectile control system, rad / s, the center of the beam information field during the time from the projectile launch to the time t _M , where $$t_M=\frac{0.5...\mathrm{1,5}}{{\omega }_{cp}}$$

, shift upward relative to the axis of the beam by the amount of Y _EG = (0.2 ... 0.5) R _L , where R _L is the radius of the beam, after which they are combined over time from time t _M to time t _EG , and at a distance of targets less than the range D _EG shooting produce without shifting the center of the information field of the beam.

In this method, the optical sight of a guided projectile guidance system comprising a target sighting channel and a projectile guidance channel, consisting of optically conjugated laser, modulator, plane-parallel plate with a rotation mechanism and a control circuit thereof and a variable focal length optical system, as well as a range input device to the target, the output of which is connected to the first input of the shaper of time intervals, the second input of which is connected to the projectile launch system, and the output is connected to the input of the circuit To control the rotation mechanism of a plane-parallel plate, it is new that it is equipped with an electronic displacement shaper whose input is connected to the second output of the time interval shaper, and the output is connected to the first adder input, the second input of which is connected to the output of the pulse shaper, and the output is connected to the control laser input.

The essence of the proposed group of inventions is that in addition to the two existing firing modes ("without exceeding" and "with exceeding"), a third mode is introduced - electronically shifting the information field of the beam up (i.e., shifting its information zero) by Y _EG , hereinafter referred to as the “electronic slide” mode, in which firing is carried out on targets located at ranges D _EG <D _c ≤D _min . Geometric displacement of the beam itself is not performed in this mode.

The invention is illustrated by the following drawings.

In FIG. Figures 1 and 2 show the projectile trajectories in the vertical plane Y _p (solid line) with the minimum possible deviation from the LCV in the “no exceeding” and “electronic slide” modes, respectively, where it is indicated (in addition to the above notation): Y _B is the upper beam boundary; Y _H is the lower boundary of the beam (shown by dash-dotted lines). The displacement Y of the _EG (i.e., the “electronic slide" itself) is depicted in FIG. 2 dashed line.

In FIG. 3 is a structural diagram of the guidance sight of a guided projectile, where it is indicated: 1 - KVC, 2 - KN of the projectile, 3 - L, 4 - M, 5 - PP, 6 - MPSU, 7 - OS with variable focal length, 8 - FVI, 9 - ATC to the target, 10 - electronic displacement shaper (FES), 11 - adder (C), 12 - pulse shaper (FI). The double line indicates the mechanical connection.

In FIG. 4 presents a sequence diagram of the operation of the CH in the "electronic slide" mode in accordance with the proposed method and the sight realizing it.

The time t of the _EG corresponds to the end of the transient process in the SN according to dependence (1), which, taking into account possible variations in the parameters of the SN, is set as:

For example, for a projectile with a low initial velocity, the cutoff frequency of the SN can be 0.25 Hz (0.25 · 2πrad / s); wherein t _EG = 1.6 ... 2.2 s. At an average projectile speed in this area, for example 100 m / s, this time will correspond to a range of approximately 200 m.

When shooting in the "electronic slide" after this time, the center of the information field is combined with the LEC. The information zero is raised up to time t _M , which is approximately one third of the time t _EG , after which a smooth descent to zero is carried out.

Shooting in the "electronic slide" (Fig. 2) allows you to reduce the deviation of the projectile down, which can occur when shooting in the "without exceeding" mode (Fig. 1).

Thus, the shooting according to the proposed method will be carried out:

in the “no exceeding” mode with a range to the target of less than D _EG (in our example, up to 200 m);

in the “electronic slide” mode with a range to the target D _EG <D _c ≤D _min (in our example, from 200 m to 1500 m);

in the "with excess" mode with a range to the target of more than D _min (in our example, more than 1500 m).

The optical sight CH guided projectile (Fig. 3) works as follows.

KVC 1 and KN 2 are aligned coaxially. In the initial state, the PP 5 is in the neutral position. The operator points the CVC axis 1 to the selected target and enters the range to the target in ATC 9 (using the rangefinder or manually).

Range data is fed to the first input of the FVI 8, where the range data is compared with tabular values that determine one of the operating modes:

“Without exceeding” and without shifting the information center of the control field;

with the formation of the displacement of the information center of the control field ("electronic slide");

with the shift of the entire control field ("with excess").

The signal from the projectile launch system provides a countdown in time from the moment of launch.

In the "no excess" and "with excess" mode, the sight works similarly to the prototype.

In the "no exceeding" mode, the center of the beam, the information center of the guidance field and the LCS are combined during the entire projectile flight. At both outputs of FVI 8 a zero signal is formed.

In the "with excess" mode at the first output of the FVI 8, a signal is generated that arrives at the MPSU 6, and the PP 5 is rotated to the maximum angle of rotation. At the second output of FVI 8, a zero signal is formed.

In this case, the guidance beam formed by L 3, M 4, OS 7, is shifted upward relative to the line of sight by the required amount due to the rotation of PP 5. After firing, FVI 8 removes the signal at its first output (depending on the distance to the target) and under the influence of this signal PP 5 comes into neutral position. Immediately before approaching the target, the projectile flies in the center of the guidance field combined with the LCA.

In the “electronic slide” mode, when firing at the first output of the PVI 8, a zero signal is generated, and at the second output it is a single signal (Fig. 4).

At the output of the FES 10, a signal is formed, which, being summed up at C 11 with the signal from FI 12, is supplied to the control input L 3. Under the influence of this signal, the laser generates pump pulses that provide the necessary shift of the control information field relative to the center of the guidance beam in accordance with the proposed method . The projectile flies over the LCF during the time t _EG , and before meeting with a goal descends to the LCF.

KVTS 1, PP 5 with MPSU 6, OS 7 with variable focal length and ATC 9 can be implemented, as in the prototype. FVI 8, FES 10, C 11 and the electronic part of the remaining blocks can be performed on any known microprocessor, for example STM32.

L 3, M 4 and FI 12 can be performed, for example, as in patent No. 2150073 dated 06/07/1999, where the information center of the guidance field is determined by the frequency (the interval between the laser pump pulses) of the sending control signals arriving at the laser inputs and generated pulse shaper. In this case, the parameters of these signals (offset information field guidance) are formed as in this prototype or with an offset determined by the signal from the FES 10.

The frequency of the packages generated by the FI corresponds to the coordinate intervals defined by the formula

where T is the scanning period;

T ₀ - the reference value of the intervals between packages, corresponding to zero coordinates;

ΔT is the maximum deviation of the intervals between packages, corresponding to the edge of the generated field (beam);

t is the current time on the coordinate formation interval.

To shift the information center relative to the center of the guidance beam under the action of an external signal from the output of the FES 10, pulses are generated instead of dependence (2) in accordance with the formula

where K (t _p ) is the change in the duration of the interval T ₀ , which determines the amount of displacement of the information center of the control field depending on the flight time t _p and the corresponding deviation Y _EG . At K (t _p ) = 0, the information center of the guidance field is aligned with the center of the guidance beam (at zero signal with FES 10).

The application of the proposed method of firing projectiles controlled by the laser beam and the optical sight realizing it allows to increase the accuracy of pointing at the initial flight site when firing without exceeding by raising the projectile trajectory by shifting the center of the beam information field upward without shifting the beam itself.

Claims (2)

1. A method of firing a projectile controlled by a laser beam, including measuring the distance to the target and entering the measured value D _c into the ground control system, comparing the measured distance to the target D _c with the distance value D _min stored in the memory of the ground control system allowing the introduction of an excess of the axis beam relative to the target line of sight, installation exceeded when condition D _n> D _min, run guided projectile, the projectile flying in the beam with excess over target line of sight to the time set in the terrestrial control system in accordance with the measured range to the target, and combining the axis of the beam with the line of sight of the target, characterized in that when the range to the target is less than the range D _min , but more than the range D _eg , where D _eg is the distance to the projectile at time

; ω _cf is the cutoff frequency of the projectile control system, rad / s, the center of the beam information field during the time from the launch of the projectile to the time t _m , where

, shift upward relative to the axis of the beam by the amount of Y _eg = (0.2 ... 0.5) R _l , where R _l is the radius of the beam, after which they are combined over time from time t _m to time t _eg , and at a distance of targets less than the range D _eg firing is performed without shifting the center of the information field of the beam. 2. The optical sight of the guided projectile guidance system, comprising a target sighting channel and a projectile guidance channel, consisting of optically coupled laser, a modulator, a plane-parallel plate with a rotation mechanism and a control circuit for it and an optical system with a variable focal length, as well as a target range input device the output of which is connected to the first input of the shaper of time intervals, the second input of which is connected to the projectile launch system, and the output is connected to the input of the control circuit of the mechanism rotating the plane-parallel plate, characterized in that it is equipped with electronic displacement generator having an input coupled to the second output of the time slots, and an output connected to a first input of an adder, whose second input is connected to the output of the pulse shaper and an output coupled to the control input of the laser.

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