RU2751437C1 - Method for aiming when firing gun at maneuvering aerial target - Google Patents

Abstract

FIELD: military aviation.

SUBSTANCE: invention relates to the field of aviation methods for aiming and concerns the method for aiming when firing a gun at an aerial target. The method consists in determining the type of target and entering its wingspan into the calculator, calculating the predicted projectile route, the signal of which is displayed, capturing and auto-tracking a visually visible target, measuring the angular coordinates and indicating the sighting ring that determines the direction to the target being followed. The range to the air target is measured and, if there are reliable range measurements, the current range mark is displayed on the initiated projectile route, then the center of the sighting ring is combined with the current range mark on the initiated projectile route by the aircraft maneuver, aircraft own roll is aligned with the roll of the visually visible target and fire is opened.

EFFECT: reducing time and increasing accuracy of aiming when accidentally switching from “full instrumentation” to “incomplete instrumentation” and back.

3 cl, 3 dwg

Description

The invention relates to methods of aiming when firing a cannon of a fighter aircraft at a maneuvering air target.

Known methods of aiming with independent control of the sighting line (for example, "Aiming and navigation complex PrNK-23". Technical description under the editorship of A. K. Ganulich. Edition of VVIA im. Zhukovsky, 1975).

On modern aircraft, the aiming method with independent control of the sighting line "NESYNCHRONNAYA SHOOTING" is used (see, for example, "Su-27K aircraft." auto-tracking of a visually visible target by an optical locating station (OLS), measure the angular coordinates of an air target and the distance to it, indicate a sighting ring that determines the direction to the tracked target, calculate lead angles and indicate a movable crosshair that determines the position of the target required for a projectile to hit it , by maneuvering the aircraft, the movable crosshair is combined with the targeting ring, when the movable crosshair is combined with the targeting ring and the effective firing range is reached, they open fire.

This method requires angular tracking of an air target and measuring the range to it (the so-called "complete instrumentation").

There is a known aiming method (WO2005052495 (A1)), which consists in the fact that the pilot visually detects an air target on the indicator on the windshield (HUD), the distance to the target is determined by superimposing an aiming ring on the visually visible target with a diameter approximately equal to the maximum size, moreover, the specified diameter is adapted by the pilot in real time to the size of the visible target, the flight time of the projectiles and the position of the predicted point of impact of the projectiles on the target are determined, the position of the aiming mark is calculated in the coordinate system associated with the aircraft, and then in the coordinate system associated with the ILS, then the pilot puts an aiming mark on a visible aerial target and opens fire.

This method does not involve the use of radar or optical-location systems, does not allow the automation of the aiming process, as a result of which the aiming process when firing at a maneuvering air target becomes a difficult task for the pilot, which leads to a significant decrease in aiming accuracy.

In the absence of range measurements (the so-called "incomplete instrumentation"), you can use the aiming method according to patent RU 2707325 (C1), which is the closest analogue to the claimed invention and can act as a prototype.

This method (hereinafter referred to as "SHAMPOO") consists in the fact that the type of target is determined and its wingspan is entered into the computer, the predicted projectile path is calculated, the predicted projectile path signal is displayed, the visually visible target is captured and auto-tracking, the angular coordinates are measured air target and indicate the sighting ring, which determines the direction to the tracked target, and the diameter of the sighting ring is set equal to the angular size of the target's wing span for the range for which the longitudinal coordinate of the indicated projectile path is equal to the current longitudinal angular coordinate of the tracked target, the visible target is moved by maneuvering the aircraft, and the sighting ring on the indicated projected projectile path, when the wing tips of the framing sighting ring targets touching the wingtips, they open fire.

During an attack, a situation is possible when the target is accompanied by an OLS, but the range measurements are absent for some time, and then reappear. And so it repeats itself in a random way. This causes transitions from the "SHAMPOO" aiming method to the "NON-SYNCHRONOUS SHOOTING" aiming method and vice versa. Since the indication on the windshield (HUD) for these methods is significantly different, such jumps annoy the pilot, who needs additional time to change from one interface to another, which complicates and slows down the aiming process.

A similar situation occurs when tracking a target with a radar, which measures short ranges with large errors. In this case, when the range decreases to a certain threshold value, for example, 500 m, it is necessary to switch from "NON-SYNCHRONOUS SHOOTING" to "SHAMPOO".

The technical result achieved by the invention consists in reducing the aiming time while increasing the aiming accuracy in the event of a random switch from "full instrumentation" to "incomplete instrumentation" and vice versa.

This result is achieved by harmonizing the indication on the HUD of the "NON-SYNCHRONIC SHOOTING" and "SHAMPUR" aiming methods.

For this, a method of aiming when firing a cannon at an air target is proposed, which consists in determining the type of target and entering its wingspan into the computer, calculating the predicted projectile path, the signal of which is displayed, performing capture and auto-tracking of a visually visible target, measuring the angular coordinates of the air target and indicate the sighting ring, which determines the direction to the tracked target, and the diameter of the sighting ring is set equal to the angular size of the target's wing span for the range for which the longitudinal coordinate of the indicated projectile track is equal to the current longitudinal angular coordinate of the tracked target, characterized in that, measure the range to the air target and, if there are reliable measurements of the range, display the mark of the current range on the initiated projectile track, then, by maneuvering the aircraft, align the center of the sighting ring with the mark of the current range to the target on the initiated projectile track, align its own roll with the roll visa the most visible target and open fire.

In a preferred embodiment of the method, marks of the maximum and minimum effective firing range are displayed on the initiated projectile track.

In another preferred embodiment of the method, a longitudinal aiming error is generated in the form of a deviation of the current longitudinal coordinate of the tracked target from the longitudinal coordinate of the current range marker on the indicated projectile track, an aircraft control signal proportional to the longitudinal aiming error is generated and added to the aircraft manual control signal.

The essence of the proposed method is illustrated by drawings.

FIG. 1 shows the indication on the HUD for the "NON-SYNCHRONOUS SHOOTING" aiming method.

FIG. 2 shows the indication on the HUD for the aiming method according to the patent RU 2707325 (C1).

FIG. 3 shows the indication on the HUD for the proposed aiming method ("SHAMPOO") in the presence of reliable range measurements.

Figures 1, 2, 3 indicate:

1 - Tendency of speed change;

2 - current speed;

3 - Target base (target wing span in meters);

4 - Current barometric altitude;

5 - Predicted projectile track;

6 - Pitch line with digital counter of the current value;

7 - Combat set of shells;

8 - Visually visible aerial target;

9 - a sighting ring;

10 - Movable aiming crosshair;

11 - Target symbol;

12 - Zero mark of the roll scale;

13 - IZL index (radiation);

14 - Range dial - located around the target mark;

15 - One-time commands - ZPS (back hemisphere) and A (attack);

16 - Mark of the current range to the target on the predicted projectile track;

17 - Marks of the minimum and maximum effective firing range on the predicted projectile path.

In accordance with the proposed method, aiming and shooting is performed as follows.

When attacking a visually visible target (pos. 8 in Figs. 2, 3), its type is determined and its wingspan B is entered into the computer, after which it is indicated on the HUD (pos. 3 in Figs. 2, 3).

и боковым

потребным пеленгом, нахождение на которых визуально видимой цели обеспечивает попадание в нее снаряда. Эти пеленги вычисляют для дискретного набора дальностей прицельной стрельбы

:Calculate the predicted projectile track and indicate it on the ILS in the form of a broken line consisting of n segments (item 5 in Figs. 2, 3). Each node of this polyline is determined by the longitudinal

and lateral

the required bearing, the location on which a visually visible target ensures that a projectile hits it. These bearings are calculated for a discrete set of targeting ranges

:

зависят от текущих параметров полета, измеряемых датчиками самолета:Functions

depend on the current flight parameters measured by the aircraft sensors:

- carrier airspeed V;

- angles of attack and slip α, β;

- roll and pitch angles γ, υ.

зависят от баллистики снаряда, а также от скорости и ускорения цели.In addition, the functions

depend on the ballistics of the projectile, as well as the speed and acceleration of the target.

The aiming range is limited to a certain value, for example, 1400 ... 1600m.

On the predicted projectile track, the marks of the minimum and maximum effective firing range are indicated, for example, 300m and 800m, respectively.

и

. Индицируют на ИЛС визирное кольцо, определяющее направление на сопровождаемую цель. Для этого для дискретного набора дальностей

находят дальность

, для которой

равно

:Capture and auto-tracking of a visually visible target is performed by an on-board information and measurement system, for example, an OLS, and the angular coordinates of an air target are measured

and

... A sighting ring is indicated on the HUD, which determines the direction to the tracked target. For this, for a discrete set of ranges

find range

, for which

equals

:

Set the angular diameter of the sighting ring d equal to the angular size of the target's wing span for the range for which the longitudinal angular coordinate of the indicated projectile track is equal to the current longitudinal angular coordinate of the tracked target:

.

...

The distance to the air target is measured, and in the presence of reliable measurements of the distance from the laser or radio range finder, the mark of the current distance to the target is displayed on the indicated projectile track. For scaling on the indicated projectile track, the labels of the maximum and minimum effective firing ranges are also displayed (for example, 800 m and 300 m, respectively).

In this case, the pilot can observe the lateral aiming error as a deviation to the left or to the right of the sighting ring from the indicated projectile track. In the presence of reliable range measurements, he can observe the longitudinal aiming error in the form of a deviation of the current longitudinal coordinate of the tracked target from the longitudinal coordinate of the current range marker on the indicated projectile track. In addition, if the wingtips of a visually visible target touch the sighting ring framing it, then the longitudinal aiming error is zero.

Then, by maneuvering the aircraft, the center of the sighting ring is aligned with the mark of the current range to the target on the indicated projectile track, its own roll is aligned with the roll of the visually visible target, and fire is opened.

In the absence of reliable measurements of the range by maneuvering the aircraft, move the visible target and the sighting ring that coincides with it to the indicated projectile track. After that, they align their own roll with the roll of the visually visible target and move it along the indicated projectile track, achieving the touch of the target wingtips with the target ring framing it. When touched, they open fire.

In addition, in the process of aiming, a lateral aiming error is formed in the form of a deviation of the current lateral angular coordinate of the tracked target from the predicted projectile path, an aircraft control signal proportional to the lateral aiming error is generated and added to the manual control signal, thus providing combined control of the aircraft. ...

In the presence of reliable range measurements, a longitudinal aiming error is also formed in the form of a deviation of the current longitudinal coordinate of the tracked target from the longitudinal coordinate of the current range marker on the indicated projectile track, an aircraft control signal is generated proportional to the longitudinal aiming error, and it is summed up with the aircraft manual control signal. Thus, they provide combined control of the aircraft to facilitate accurate aiming at an intensively maneuvering target.

Using the proposed method allows you to reduce the time and improve the accuracy of the aiming process when randomly switching from "full instrumentation" to "incomplete instrumentation" and vice versa by harmonizing the indication on the HUD aiming methods "NON-SYNCHRONOUS SHOOTING" and "SHAMPUR".

For this, in the presence of reliable measurements of the range, the aiming crosshair of the "NONSYNCHRONNAYA SHOOTING" method is replaced by the sighting crosshair formed by the intersection of the predicted projectile track with the mark of the current range to the target. The circular range scale is replaced by the most predicted projectile track, on which, for scaling, the marks of the maximum and minimum effective firing ranges are indicated, and the length of the track is limited to the aimed firing range.

In case of accidental loss of reliable range measurements, there is no cardinal change in the indication on the HUD, only the mark of the current range disappears, and the aiming process is performed in accordance with the method according to patent RU 2707325 (C1). When reliable measurements of the range appear again, a cardinal change in the indication on the HUD also does not occur, on the predicted projectile track only a mark of the current range to the target appears.

Claims (3)

1. A method of aiming when firing a cannon at an air target, which consists in determining the type of target and entering its wingspan into the computer, calculating the predicted projectile path, the signal of which is displayed, capture and auto-tracking of a visually visible target, measure the angular coordinates air target and indicate the sighting ring, which determines the direction to the tracked target, and the diameter of the sighting ring is set equal to the angular size of the target's wing span for the range for which the longitudinal coordinate of the indicated projectile path is equal to the current longitudinal angular coordinate of the tracked target, characterized in that the range is measured to an air target and in the presence of reliable measurements of the range, display the mark of the current range on the initiated projectile track, then by maneuvering the aircraft align the center of the sighting ring with the mark of the current range to the target on the initiated projectile track, align its own roll with the roll of the visually visible target, and open fire. 2. The method according to claim 1, characterized in that marks of the maximum and minimum effective firing range are displayed on the initiated projectile track. 3. The method according to claim 1, characterized in that a longitudinal aiming error is generated in the form of a deviation of the current longitudinal coordinate of the tracked target from the longitudinal coordinate of the current range marker on the indicated projectile track, an aircraft control signal is generated proportional to the longitudinal aiming error, and it is summed up with the signal manual control of the aircraft.

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