Guided missile

FIELD: weapons and ammunition.

SUBSTANCE: this missile comprises warhead screwed to another compartment and secured thereto by fastener composed by rectangular-section ring with arched hooks with inner cylindrical surface and ledges at end surface. End of connectable compartment comprises arched ledges with OD, sizes and quantity equal to those of fasteners. Arrangement of said hooks in angular direction complies with arrangement of ledges with threaded holes for fastening screws of warhead.

EFFECT: decreased length and weight, higher reliability and combat efficiency.

3 cl, 4 dwg

 

The invention relates to the field of armaments, particularly to rocket technology.

Known guided projectile (patent RU 2070712 C1) adopted for the prototype, which is leading the cumulative charge, contact fuse and steering gear box are connected with the next compartment by means of screws along the longitudinal axis.

The disadvantage of this type of coupling is that the threaded screw holes made in the front cover of the next compartment. Run the threaded holes for axial screws in the attached compartment reduces the strength of the compartment, as well as to a significant increase in the thickness of the front wall, thus increasing its length and weight, which leads to the deterioration of its characteristics and the characteristics of the product as a whole.

Especially this disadvantage manifests itself in cases where the join of the battery compartment is:

1. The casing of the jet engine is operating under high pressure and require high strength characteristics of the material of the engine block with high density. The increase of the thick wall casing of the engine leads to a significant increase in its mass, and consequently, to decrease the quality factor of the motor, which leads to an increase in mass of the rocket and reduce the range of its flight.

2. The casing of the warhead, shotable aemy in the form of a thin-walled shell, for maximum filling volume of the explosive. In this case, the increase in the thickness of the front wall leads to an increase in mass and decrease the military power of the missile.

In addition, the implementation of the holes in the hull compartment leads to a decrease in its strength.

The task of the invention is to increase reliability by eliminating the threaded holes in the casing attachable cover and improving efficiency by reducing the weight of the structure and improve combat performance of the rocket.

The solution of this problem is achieved by the fact that controlled the rocket containing the head compartment is connected with the next compartment by means of screws along the longitudinal axis of the missile, the fastening element head compartment to the next compartment is made in the form of a ring of rectangular cross-section with curved hooks on the inner cylindrical surface on the end surface of which is made the tabs with threaded holes for the fastening screws of the head compartment and the end attachable cover is provided arcuate projections, the external diameter of which corresponds to the inner fastening element, and the size of the tabs attached compartment in the radial direction is equal to the height of the hooks of the fastening element.

Running on the fastening element the same number is TBA rocks and ledges with the screw holes, and the coincidence of their location in the angular direction, to minimize load on the connection and eliminate circumferential movement of joined sections of the rocket after tightening.

Execution at the end attachable compartment arcuate protrusions, the outer diameter of which corresponds to the inner diameter of the fastening element, ensures alignment of joined compartments.

The exception threaded holes in the casing attachable compartment missiles can improve its strength, and therefore its reliability and reliability of the products in General, this also helps to make the compartment wall minimum thickness, thereby reducing the mass of the rocket. Introduction to the design of the fastening element made of light aluminium alloy, does not increase the weight of the structure due to the low density of the material and substantial reduction of the wall thickness of the attached compartment. The vacant volume of the compartment can also be filled with a charge of motor or warhead, thereby to increase the flight range of the missile and its military power without changing the overall mass of the product characteristics.

The positive effect of the invention is achieved by excluding the manufacture of threaded holes in the casing attachable cover that can improve reliability, reduce the length and the Assu missiles or increase its range and combat power at the expense of filling the vacant volume of the charge motor or warhead, while maintaining the original overall-mass characteristics. This will significantly improve the effectiveness of missiles in a variety of combat missions.

The proposed solution is illustrated graphic material (Fig.1-4).

In Fig.1 shows the connection of the head compartment guided missile, which includes steering gear box 1 and fairing 3, with the following compartment 2 through the fastening element 4 with axial screws 5.

In Fig.2 shows the fastening element 4 of rectangular cross-section S, is equipped with four curved hooks 8 and the four tabs with the screw holes 7.

In Fig.3 depicts compartment 2 with four arcuate protrusions 9.

In Fig.4 shows the connection compartment 2 with the fastening element 4, the outer diameter of the protrusions 9 is equal to the inner diameter of the fastening element 4, and the size of the protrusions 9 is equal to the height of the hooks 8 of the fastening element 4.

The operation of the device. When assembling the fastening element 4 is inserted with its curved hooks 8 in the grooves between the annular projections 9 of the compartment 2 and is rotated to coincide with the hooks 8 of the fastening element 4 with the tabs 9 of the compartment 2. After that, the screws 5 compartment attaches the steering actuator 1. When tightening screws at the same time the fastening compartment steering 1 and fixing the connection of the fastening element 4 compartment is m 2.

Fairing 3 is attached to the power steering gear 1 by screws 6.

Thus, the proposed solution allows to increase the reliability of the compartment due to the execution of it threaded holes, to reduce the length and mass of the rocket or to improve the combat effectiveness of the system by increasing the flight distance and the military power of the missile.

1. Guided missile containing the head compartment is connected with the next compartment by means of screws along the longitudinal axis of the missile, characterized in that in it the element mounting head compartment to the next compartment is made in the form of a ring of rectangular cross-section with curved hooks on the inner cylindrical surface on the end surface of which is made the tabs with threaded holes for the fastening screws of the head compartment and the end attachable cover is provided arcuate projections, the external diameter of which corresponds to the inner diameter of the fastening element, and the size of the tabs attached compartment in the radial direction is equal to the height of the hooks of the fastening element.

2. Guided missile under item 1, characterized in that the number of hooks of the fastening element is equal to the number of tabs with threaded holes for the fastening screws of the head compartment.

3. Guided missile under item 1 or 2, Otley is audacia fact, the location of the hooks of the fastening element in the angular direction coincides with the location of the tabs with threaded holes for the fastening screws of the head compartment.



 

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