RU2391624C2 - Controlled aviation bomb - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: controlled aviation bomb comprises body and detachable yokes for fixation of solid-propellant rocket engine to bomb body. Yokes are arranged with the possibility for fixation of rocket engines of various capacity and comprises device for separation of engine from bomb in process of flight. Device for engine separation is connected to system of homing and control. It is preferable to make yokes from two halves, which cover bomb body and are tightened to each other by means of pyropushers. It is also preferable to equip the rocket engine with indicator of pressure reduction in engine chamber, connected to system of homing and control. System of homing and control may be provided with the unit that generates and distributes command for actuation of pyropushers as per specified time.

EFFECT: invention provides for the possibility to replace rocket engine for variation of application range in process of operation depending on urgent tasks.

6 cl, 3 dwg

Description

The invention relates to ammunition, to aircraft bombs, and in particular to structures of guided aircraft bombs equipped with an engine designed to increase the range of their planning.

Known for the prototype guided aerial bomb (PSA) (Jane's Strategic Wearpon Systems, Edited bu Duncan Ltnnjx, ISBN 0710608802, Copyright 2005 bu Jane's information Group Limited, pp. 164, 165) PGM-2000, comprising a housing, plumage, suspension units, guidance system and solid rocket engine (solid propellant rocket engine) protruding from the body bypass. The common essential features of the prototype with the proposed technical solution are as follows - the UAB contains a housing, plumage, suspension units, a guidance and control system that extends beyond the contours of the solid propellant rocket motor, cable RTTT communication line with the guidance and control system.

The specified UAB does not provide for the change of the solid propellant rocket engine and its separation from the UAB in flight, which leads to a narrow range of applications and the impossibility of changing the range of applications in operating conditions; leads to an increase in aerodynamic drag and mass due to the overhang of the solid propellant overhangs and, as a result, to a short range and limited maneuverability at the final guidance site.

The proposed invention solves the problem of the possibility of replacing solid propellant rocket engines to change the range of applications during operation depending on combat missions, expanding the range of applications, standardizing products, increasing the efficiency of applications by increasing range and improving maneuverability at the final guidance site, and the possibility of equipping solid-propellant rocket engines with armament.

To ensure quick removal and installation of solid propellant rocket motors during operation in the proposed UAB, comprising a housing, plumage, suspension units, a guidance and control system protruding beyond the contours of the solid rocket motor, connected by a cable line to the guidance and control system, the solid rocket motor is attached to the UAB housing using removable clamps.

To ensure the change and expansion of the UAB application range, the clamps are made with the possibility of installing solid propellant motors of various capacities (for example, through the use of standardized brackets).

To increase the range and improve maneuverability at the final guidance site, the solid fuel rocket engine mounting clamps contain a device for separating the engine from the bomb in flight, connected to the guidance and control system, while the communication line is equipped with a disconnection device. To do this, the clamps, for example, can be made of two halves covering the bomb body, and are pulled together with pyro-pushers or other separation devices, for example, explosive bolts. The cable communication line has a disconnecting device, for example, a tear-off connector, a shear knife, etc.

To control the separation of the solid propellant rocket motor from the UAB, the solid propellant rocket motor is equipped with a pressure reduction indicator in the engine chamber connected to the guidance and control system. The pressure signaling device gives a signal about the end of the solid propellant rocket motor operation, and the guidance and control system generates and issues a command for the operation of the pushers. As another option for controlling the solid propellant rocket compartment or for the solid propellant rocket compartment until the end of its operation, the guidance and control system is equipped with a unit that generates and issues a command for the operation of the pyro-pushers according to the set time.

Distinctive features of the proposed UAB from the above is that the solid-state motor vehicle is attached to the body of the UAB using removable clamps, the cable communication line of the solid-rocket motor with the guidance and control system has a disconnecting device; the clamps are made with the possibility of installing solid propellant rocket motors of various capacities; solid fuel rocket engine mounting clamps comprise a device for separating the engine from the bomb in flight, connected to the guidance and control system, the communication line provided with a disconnecting device; the clamps are made of two halves, covering the bomb body, and are pulled together by pushers; The solid propellant rocket motor is equipped with a pressure reduction indicator connected to the guidance and control system; the guidance and control system is equipped with a unit that generates and issues a command for the operation of the pushers according to the set time.

Due to the presence of these distinctive features, the following technical results are achieved: the possibility of rapid replacement of solid propellant rocket engines is ensured, the range of applications is selected and extended during operation depending on combat missions, the products are unified, and the application efficiency is improved by increasing the range and improving maneuverability at the end guidance site.

The ability to quickly change solid propellant rocket engines increases the efficiency of bombing attacks, taking into account the type and range of detected targets.

The increase in the UAB flight range is achieved by the fact that after the solid propellant rocket motor operation is completed, the UAB further flies to the target without the solid propellant rocket propeller, which reduces the overall aerodynamic drag of the UAV and improves the UAB maneuverability in the final guidance section. The increase in the UAB flight range allows the use of UAB without entering a carrier aircraft into the range of the enemy’s near air defense means.

The proposed technical solution can find application in the design of the UAB, as well as for the modernization of the armed UAB.

The proposed UAB is illustrated by the drawings shown in figures 1-3.

Figure 1 shows the UAB,

figure 2 shows a view along arrow A (front view of the UAB),

figure 3 shows a section bB on the clamp.

1-3 UAB shown in FIG. 1 comprises a housing 1, a plumage 2, suspension units 3, a guidance and control system 4, an RTTT 5, detachable parts of the clamps 6 and 7, brackets 8, a retainer 9, a pusher 10, a cable communication line of the RTTT with the system guidance and control 11, the detachable connector 12, the pressure switch 13, the unit for the formation and issuance of a command to operate the pyro-pushers 14.

RDTT 5 is attached to the housing of the UAB using the detachable parts of the clamps 6 and 7, pulled together by pushers 10. The unified brackets 8 provide suspension to the UAB of the RDTT of any required power. The latch 9 centers the solid propellant rocket motor and transmits traction from the solid propellant rocket motor to UAB. The pressure switch 13 according to the pressure drop in the chamber of the solid rocket motor transmits a signal about the end of the solid rocket motor to the guidance and control system 4 via the cable communication line 11. A detachable connector 12 connects the electric circuit of the solid rocket motor 5 (pressure switch, igniter, pressure sensors, etc.) to the guidance system and management 4.

Preparation of the proposed UAB for use and its implementation is as follows. Upon receipt of a specific combat mission, the RDBT 5, required by power, is installed on the UAB using the clamps 6 and 7, which are pulled together by the pushers 10. At the same time, the detachable connector 12 is connected. After the UAB is reset from the carrier aircraft, the RDTT and UAB are switched on by a command from the navigation and control system accelerates along a predetermined path to the desired flight speed. At the end of the operation of the solid-propellant rocket motor 5, the pressure switch 13, according to the pressure drop in the solid rocket motor chamber 5, gives a signal to the navigation and control system 4, which generates and issues a command for actuating the pushers 10. As a result of the operation of the pyro-guns 10, the solid-state rocket control 5 and the detachable parts of the clamps 6 and 7 are separated from UAB. Further, the UAB moves towards the goal by the commands of the navigation and control system. If it is necessary to retarget the carrier aircraft (for example, to a closer target), the RDTT 5 and the detachable parts of the clamps 6 and 7 are separated by a command from the unit for generating and issuing a command for the operation of the pyro-pushers 14.

Claims (6)

1. Managed aircraft bomb, comprising a housing, tail, suspension units, guidance and control system and a solid fuel rocket engine protruding beyond the body contours, connected by a communication line to the guidance and control system, which is equipped with removable clamps for attaching the rocket engine to the bomb body, the clamps are made with the possibility of installing rocket engines of different power and contain a device for separating the engine from the bomb in flight, connected to the guidance and control system, and a communication line equipped with a device for its separation. 2. The bomb according to claim 1, in which the clamps are made of two halves, which cover the bomb body and pulled together with pushers. 3. The bomb according to claim 1, in which the rocket engine is equipped with a pressure reduction indicator in the engine chamber connected to the guidance and control system. 4. The bomb according to claim 1, in which the guidance and control system is equipped with a unit that generates and issues a command for the operation of the pyro-pushers at a given time. 5. The bomb according to claim 2, in which the solid fuel rocket engine is equipped with a pressure switch in the engine chamber connected to the guidance and control system. 6. The bomb according to any one of paragraphs.2-4, in which the guidance and control system is equipped with a unit that generates and issues a command for the operation of the pushers on a given time.

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