RU2709121C1 - Jet projectile control unit - Google Patents

Abstract

FIELD: military equipment.

SUBSTANCE: invention relates to military equipment and, in particular, to guided missiles. Control unit includes power supply source, onboard equipment for remote reception of flight task, electric steering drive and control equipment. Control equipment comprises onboard computer, unit of inertial sensors and satellite navigation equipment. Control unit of jet projectile provides initial flight of projectile along ballistic trajectory. This unit includes wing. It has at least two cantilevers and mechanism of propulsion unit separation. Control unit is installed between warhead and propulsion unit. Equipment for remote reception of flight task is intended for reception of coordinates of target and cyclogram of operation of control unit in flight. Onboard computer is used to start execution of the cyclogram and generate control commands to the electric steering drive. During separation of propulsion system it is possible to open aerodynamic rudders and cantilevers of wing, as well as volplaning flight of projectile to target with height exceeding with subsequent defeat of target from dive.

EFFECT: enlarging combat capabilities of reactive artillery during firing at small-size targets.

4 cl, 3 dwg

Description

The invention relates to military equipment, in particular to guided missiles.

Known rockets, for example 9M22U and 9M521 [1].

The reasons that impede the achievement of the technical result indicated below when using known rockets are that in known rockets the flight to the target is carried out along a ballistic trajectory without compensating for deviations from the trajectory required to hit the target, as a result of which they have low firing accuracy, which increases the consumption of ammunition and more time to perform a combat mission, in addition, the maximum firing range is limited by energy capabilities motor shell installation, an increase of which in the framework of a given length and caliber of the projectile is extremely difficult.

The closest device of the same purpose to the claimed invention in terms of features and adopted for the prototype is a missile control unit containing a cylindrical hinge on two rolling bearings with an axis of rotation coinciding with the longitudinal axis of the missile, a power source, on-board equipment for remote reception of a flight mission, fuse, control equipment, electric steering gear (patent RU No. 2627334) [2].

The main disadvantage when using the known device is that after installing this unit on a missile, the lifting force that the projectile can develop is insufficient to carry out a planned flight over a considerable range, due to the insufficient lift of the missile, because for initially uncontrolled shells, the developed aerodynamic plumage (wing), on which the bulk of the lifting force is generated, is not required. In addition, the projectile on approaching the target has a considerable length, and therefore a large effective area of dispersion (EPR) of radio emission.

As a result, the disadvantages of the prototype are a slight increase in the flight range relative to the standard projectile, which does not allow placing a firing position deep in its territory from the line of contact with the enemy, the vulnerability of the missile itself to missile defense systems (ABM).

The technical objective of this solution is to increase the firing range of a guided missile and reduce the likelihood of being hit by missile defense, increase the reliability of the control system, including in the conditions of the enemy using electronic warfare.

The technical result is the expansion of the combat capabilities of rocket artillery by increasing the firing range and reducing the consumption of ammunition for hitting a small target protected by missile defense and electronic warfare.

The specified technical result is achieved in that the missile control unit, including a power source, on-board equipment for remote reception of the flight mission, electric steering gear, control equipment that includes an on-board computer, an inertial sensor unit and satellite navigation equipment, includes a wing having at least at least two consoles, and a propulsion mechanism. The missile control unit is installed between the warhead and the propulsion system of the missile. The antenna of satellite navigation equipment can be made in the form of an antenna array, which increases the noise immunity of satellite navigation equipment to the effects of deliberate interference from enemy electronic countermeasures by 20-30 dB. The control equipment may include an Earth’s magnetic field sensor to increase operational reliability by additionally determining the spatial position of the munition by the Earth’s magnetic field. To exclude the effect of distortion of the surrounding magnetic field caused by the ammunition on its readings, it is installed at a minimum distance from the wing end chord, which is made of non-magnetic materials.

In FIG. 1 is a diagram of a missile control unit; in FIG. 2 - a missile with a control unit, in FIG. 3 - flight path of a projectile equipped with a missile control unit.

The rocket control unit (1) includes a housing (2), inside which there is installed satellite navigation equipment (3) with an antenna (4), flight task reception equipment (5), on-board computer (6), inertial sensors block (7), sensor (8) Earth's magnetic field, power source (9), wing (10), separation mechanism (11) from the propulsion system (12), electric steering gear with independent aerodynamic rudders (13) and DC electric motors (14), torque transmission torque from the electric motor to the steering shaft is through eduktor (15), the warhead of the projectile (16) is attached to the front of the body (2) of the projectile control unit.

The operation of the unit (1) control missile is as follows. At the firing position, the calculation loads the missile with the missile control unit (1) into the launch guide of the combat vehicle, after which the target coordinates and the flight operation sequence are entered into the missile control unit (1) using the flight mission receiving equipment (5). After the launch of the projectile, the on-board computer (6) starts the execution of the cyclogram, and the satellite navigation equipment (3) determines the current coordinates of the projectile. The initial section of the flight of the projectile is carried out along a ballistic trajectory. Depending on the firing range and in accordance with the cyclogram, at the estimated time, on the command of the on-board computer (6), the propulsion unit (12) is separated by the separation mechanism (11) (for example, by means of pyrotechnic means), simultaneously the aerodynamic rudders (13) and consoles wing (10), a controlled flight of the warhead begins as part of the warhead (16) and missile control unit (1), while the length of the ammunition is significantly reduced with a corresponding reduction in ESR, making it difficult to detect defeat and missile defense. Based on the signals from the angular velocity sensors located in the inertial sensor block (7), the on-board computer (6) generates commands for stabilizing the roll and damping the vibrations of the rocket, and according to data on the position of the projectile in space, determined by the control equipment and the target coordinates set during launch in accordance with the selected control law, generates target guidance commands transmitted to the electric steering gear. Due to the presence of the wing, a large lifting force is created, which ensures the planning of the projectile over significant distances. To reduce range errors and increase the effectiveness of the warhead of a missile, the target is hit by a dive (see Fig. 3).

All elements used to create the invention are known from the prior art and are not unknown to specialists in this field of technology.

Thus, the above information indicates the fulfillment of the following set of conditions when using the claimed invention:

- a tool embodying the claimed invention in its implementation, is intended for use in military equipment, namely in rockets;

- for the claimed device in the form described in the independent clause of the claims, the possibility of its implementation using the means and methods described in the application or known prior to the priority date is confirmed;

- a device embodying the claimed invention in its implementation is capable of achieving the achievement of the technical result perceived by the applicant, namely, it expands the capabilities of the combat use of rocket artillery by increasing the firing range and reducing the consumption of ammunition for hitting a small target protected by missile defense and electronic warfare.

Therefore, the claimed invention meets the condition of "industrial applicability".

Sources of information

1. Karpenko A. Modern multiple launch rocket systems. Bastion Publishing House, 2003

2. Patent RU No. 2627334 C1, IPC F42B 15/00, F42B 15/01 of 08/24/2016.

Claims (4)

1. The control unit of a missile, including a power source, on-board equipment for remote reception of a flight mission, an electric steering gear, control equipment that contains an on-board computer, an inertial sensor unit and satellite navigation equipment, characterized in that the missile control unit provides an initial projectile flight along a ballistic trajectory and includes a wing having at least two consoles and a mechanism for separating the propulsion system, the control unit installed between the warhead and the propulsion system, the equipment for the remote reception of the flight mission is designed to receive the coordinates of the target and the operation diagram of the control unit in flight, the on-board computer is used to start the execution of the sequence diagram and the formation of control commands for the electric steering gear, while the propulsion system is opened, the aerodynamic can be opened the rudders and wing consoles, as well as the planning projectile flight to the target with an excess in height with the subsequent destruction of the target and with a dive. 2. The rocket control unit according to claim 1, characterized in that the antenna of the satellite navigation equipment is made in the form of an antenna array. 3. The rocket control unit according to claim 1, characterized in that the control equipment includes at least one sensor of the Earth's magnetic field. 4. The rocket control unit according to claim 3, characterized in that the Earth's magnetic field sensor is installed at a minimum distance from the wing end chord, the wing being made of non-magnetic materials.

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