RU2321824C2 - Method for fire by guided artillery jet-driven projectile with homing in the terminal flight leg and device for its realization - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: the method consists in launching of the projectile from the gun barrel in a mortar trajectory and start of the jet engine in the trajectory of its flight. At and outrange fire the jet engine is started in the upward leg of the projectile flight trajectory. At a short-range fire the jet engine is started in the downward leg of the projectile flight trajectory. The projectile for realization of the method has a jet engine with a pyrotechnic igniter and an electronic equipment programmed before the start. The electronic equipment is provided with a timer for the start of the jet engine in the upward or downward leg of the projectile flight trajectory.

EFFECT: expanded functional potentialities of projectiles with homing in the terminal flight leg.

2 cl, 3 dwg

Description

The invention relates to military equipment, and specifically to methods of firing guided artillery rockets with homing in the final section of the flight path.

The firing method of the well-known 3OF39 guided artillery rocket projectile includes the projectile leaving the barrel of the artillery gun and starting the engine on the flight path of the projectile after the delayed-action beam igniter is activated by the temperature and pressure of the propellant propellant gases.

The engine runs for 1 s, reporting additional speed to the artillery guided projectile on the trajectory (see [1]).

The engine was started in this projectile through a pyrotechnic delayed-action igniter, which provided a constant time for turning on the engine on a ballistic trajectory.

Guided artillery rocket of this design has limited use, because cannot be used when shooting on mortar (more than 45 ° to the horizon) trajectories, which does not make it possible to hit targets located on the reverse slopes of the mountains, as well as when conducting anti-terrorist operations within the boundaries of a settlement with tall buildings.

When shooting on a “gentle” (less than 45 ° to the horizon) trajectory, it is possible to optimize and select a single time for switching on the rocket engine of the projectile for the entire range of firing ranges from minimum to maximum. When shooting on a mortar path (at an angle of more than 45 ° to the horizon) this is not possible, because when shooting on a gentle trajectory, the velocity of the projectile at the top of the trajectory does not decrease significantly, and the top point of the mortar path divides it into two sections:

- ascending branch, where the velocity of the projectile varies from Vstart. to significantly low (50 m / s);

- a descending branch, where the velocity of the projectile varies from 50 m / s to V end, obtained by accelerating the free fall of the projectile.

Guided artillery missiles with homing in the final section of the trajectory begin to be controlled (aiming at the target) in the final section of the trajectory, and therefore one of the main tasks in the design of such a projectile is to ensure sufficient and stable values of its velocity at the end of the flight.

When firing a known projectile along a mortar trajectory with a fixed start time of the jet engine, stable values of the velocity of the projectile in the final portion of the trajectory (in the control section) are not provided, the velocity of the projectile is insufficient for a controlled flight and hit of the projectile in a point target.

The objective of the invention is to expand the functionality of a guided artillery rocket with homing in the final section of the flight path by providing firing on mortar paths.

The solution to this problem is achieved by the fact that in the method of firing a guided artillery rocket with homing in the final section of the flight path, including the exit of the projectile from the gun’s barrel and the launch of the jet engine on the flight path of the projectile, the projectile is fired along a mortar path, and the jet engine is switched on in ascending or the descending branches of the projectile’s flight path when firing at large or small projectile ranges, respectively.

To implement this method of firing in a guided artillery rocket with homing in the final section of the flight path, containing a jet engine with a pyrotechnic igniter, a power source electrically connected to programmable electronic equipment before starting, the electronic equipment is designed to provide the function of a jet engine start timer, and pyrotechnic the igniter is equipped with an electric valve, electrically connected to electronic equipment.

Engine start times can be entered into electronic equipment programmed before start in various ways, for example:

1) from an external device through an electrical contact group on the shell of the projectile,

2) non-contact by radio channel,

3) using installation devices in the form of switches located on the shell of the projectile,

4) using a mechanical watch device installed before the start for the required time, etc.

Since programming before the start of electronic equipment can be carried out in various ways that are not the subject of this invention, programming methods and device designs are not considered in the claims and description of the invention.

Figures 1 and 2 show mortar trajectories of the projectile at short and long ranges, where Vstart is the velocity of the projectile in the initial portion of the flight path, Vfine is the velocity of the projectile in the final portion of the trajectory, Vshift is the speed communicated to the projectile by the jet engine .

Figure 3 shows the guided artillery rocket and its elements that implement the method of firing.

The guided artillery missile 1 contains a jet engine 2 with a pyrotechnic igniter 3, a power supply 4, electrically connected to a programmable electronic equipment 5 before starting, with the function of a timer for starting the jet engine 2, the pyrotechnic igniter 3 is equipped with an electric valve 6, electrically connected to the electronic equipment 5.

Before firing a guided artillery rocket along mortar paths, depending on the range of the projectile (long or short range), from an external device (for example, via a radio channel or through a contact group on the shell of the projectile), a program with a specified time is entered into electronic equipment 5 jet engine start 2.

When the propellant is fired, the projectile leaves the barrel of the gun, power is supplied to the electronic equipment 5 from the power source 4, after which the start time of the jet engine 2 starts. The projectile flies along the mortar path. After the entered time has elapsed, the electronic equipment 5 issues a command to turn on the jet engine 2 and the voltage is supplied to the electric valve 6 from the power source 4. The electric valve 6 initiates a pyrotechnic igniter 3, the jet engine 2 starts, which gives the projectile an additional flight speed.

When firing at a short range of 1500-2000 m, a guided artillery missile is fired along a “steep” path, i.e. at a large angle to the horizon (70-80 °) to a low altitude of 1700 m. Due to the “steepness” of the trajectory, the velocity of the projectile at the top of the trajectory decreases to 50 m / s. Having passed the top point of the trajectory, the projectile begins to fly in a descending trajectory to the target area. Due to the small height of the trajectory, the projectile does not have time to gain sufficient speed for control (200 m / s) only due to the acceleration of free fall, therefore, to increase the speed of the projectile on the descending branch of the trajectory, the jet engine is turned on and its speed increases to the value necessary for control on the final section of the flight path.

When firing at a long range, a guided artillery missile is fired at an angle of 45 ° to the horizon at the highest possible speed and in addition to this, a jet engine is turned on on the ascending branch of its flight path in order to bring the projectile to the highest point of the path as far as possible from the launch site, located at an altitude of 4500 m. At the same time, the projectile has a velocity of 200 m / s at the top of the trajectory, to which, during acceleration, the velocity obtained by acceleration is added to the descending branch of the trajectory I free fall, resulting in a finite portion of the flight path of the projectile has a speed sufficient to control.

The values of flight ranges, altitudes of trajectories, projectile speeds, including the speed required to control the projectile, are given as a special case, valid for a particular type of projectile and are not the subject of the invention. However, the nature of the change in velocity along the trajectory is true in all cases.

Thus, the proposed method of firing a guided artillery rocket with homing in the final section of the flight path and a device for its implementation can expand the functionality of the projectile by providing the possibility of firing at mortar paths, allowing to hit targets on the reverse slopes of the mountains, as well as during anti-terrorist operations within the boundaries of a settlement with tall buildings.

The proposed method of firing a guided artillery missile with homing in the final section of the flight path and a guided artillery missile were tested by field tests, which were completed with positive results.

The source of information

1. RU 2166726, C1, cl. F42BT 15/00, 05/10/2001.

Claims (2)

1. The method of firing a guided artillery rocket with homing in the final section of the flight path, including the exit of the projectile from the gun’s barrel and the launch of the jet engine on the flight path of the projectile, characterized in that the projectile is fired along the mortar path, and the jet engine is turned on in ascending or descending branches projectile flight paths when firing at long or short projectile ranges, respectively. 2. A guided artillery missile with homing in the final portion of the flight path, comprising a jet engine with a pyrotechnic igniter, a power source electrically connected to programmable electronic equipment before starting, characterized in that the electronic equipment is equipped with a timer to ensure that the jet engine starts on an ascending or descending projectile flight paths, and the pyrotechnic igniter is equipped with an electric fuse electrically connected to an electronic pparaturoy.

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