Unit of control system of rocket projectile launched from tubular guide

FIELD: weapons and ammunition.

SUBSTANCE: unit of control system of rocket projectile comprises a housing with ogive part, aerodynamic controllers folding-out in flight with actuators and a control unit, mounted on the ogive part. Each controller is equipped with abutment. The abutment is located in front of the front edge of the controller coaxially with the axis of folding-out. The profile of the front part of the abutment is congruent to the profile of the ogive part of the housing. The diameter of the maximum circumscribed circle of the abutments of all the controllers does not exceed the unit gauge. Folding-out axes of the controllers are biased to the axis of the unit relative to its gauge by an amount at least 0.5 of the maximum thickness of the controller at the root chord of its folding-out part.

EFFECT: improvement of accuracy of projectile shooting.

4 cl, 2 dwg

 

The invention relates to a control system rockets systems of volley fire.

The object of the invention is a flow control system rockets with increased shooting accuracy, intended to arm the rocket and artillery units, and may find wide application in the field of rocketry.

To fight ground targets are widely used reactive multiple rocket systems (MLRS), which include unguided rockets, each of which is equipped with monoblock or cassette head part, a solid rocket motor and aerodynamic stabilizer. The advantage of these systems is the possibility of applying a sudden massive attack on a spatially extended targets with the simplicity of the design, maintenance, and combat application. However, with increasing distance shooting achieved such shells accuracy characteristics of fire do not provide the required performance targets.

Currently, to improve the accuracy, precision, use different control systems of missiles (rockets), allowing for increased accuracy characteristics and accuracy compared with unguided projectiles.

For example, the famous run of pipe rocket on the patent of Russian Federation №2071027, BI is 36, publ. 27.12.1996, adopted by the authors for similar, with gas-dynamic system angular stabilization (control system). Due to the expiration of the nozzles of the gas-dynamic system angular stabilization normal to the longitudinal axis of the rocket a working fluid in a direction opposite to the direction of action of the total perturbing forces, creates a corrective force, preventing the development of a deviation of the longitudinal axis of the rocket from the given direction, providing increased accuracy characteristics and accuracy compared with unguided projectiles.

Thus, the objective of this technical solution was to develop missiles with improved performance accuracy and precision, ensuring satisfactory characteristics firing rockets systems of volley fire.

Common features with we offer authors the unit control system rockets are in the presence of a rocket-analog control system capable of improving the accuracy characteristics of fire.

At the same time, further increase the range achieved for such missiles characteristics of accuracy and precision shooting do not provide the required performance targets.

Famous rocket (controlled missile) M anti-aircraft missile system TOR-1 (leaflet JOINT STOK COMPANY "VMP "AVITEC" 1A, Octyabrsky pr., Kirov, Russia), adopted by the authors for the prototype run of box-shaped guide rail and comprising placed on her bow folding in flight aerodynamic control surfaces through which the flight control is carried out almost throughout its length, which provides the possibility of the rocket to the target. The desired magnitude of the aerodynamic control surfaces is achieved by the use of the start box guide and placing missiles in it so that the aerodynamic controls were located towards the corners of the box-shaped guide.

Thus, the objective of this technical solution of the prototype was to develop rockets with aerodynamic controls, providing the required parameters of shooting through the start of the box-shaped guide due to the location of the aerodynamic controls in the direction of the corners of the box-shaped guide.

Common features with we offer authors the unit control system rockets launched from the tubular guide is the case with ogival part, folding in flight aerodynamic rudder actuators and control unit mounted on the arched part.

Unlike the prototype, the proposed authors of the block of the control system of the rocket projectile, run from the tubular guide, each wheel is equipped with a buttress, buttress placed in front of the front edge of the wheel coaxial with the axis of the opening, the profile of the front of the buttress congruent profile ogival part of the body, while the maximum diameter of the circumscribing circle of the buttresses of all control surfaces do not exceed the gauge block and the axis of folding of the rudder offset to the axis of the block relative to its caliber on the value of not less than 0.5 of the maximum thickness of the steering wheel at the root of the chord folding his part.

In special cases, i.e. in the specific forms of embodiment, the buttress made teardrop shape, and the axis of the folding control surfaces are at an angle to the longitudinal axis of the block.

It allows to make a conclusion about the causal connection between the set of essential features of the proposed technical solution and achievable technical result.

These characteristics, distinctive features of the prototype, and to which the requested amount of legal protection, in all cases sufficient.

Object of the present invention is to provide a unit of the control system of the rocket projectile, providing loading and launching guided missiles, from standard tubular rails designed to run previously developed unmanaged and corrected rape the s reactive systems of volley fire.

A new set of structural elements, expressed in the presence of nodes that are new in comparison with the prototype, the relative locations of the nodes and the links between them, allow, in particular, due to:

- equipping each steering buttress placed in front of the front edge of the wheel coaxial with the axis of the wheel, and not exceeding the maximum diameter of the circumscribing circle of the buttresses of all surfaces of the gauge block to provide a block reference management system with aerodynamic controls when charged in a regular tubular guide designed to run previously developed unguided and guided shells reactive systems of volley fire;

- complete profile of the front of the buttress congruent with the profile of the fore part of the body to provide the desired structure of the incoming air stream in front of the rudders and the nature of their flow, and thereby reduce the influence of the buttresses on the effectiveness of the control in the control channels;

- offset folding of the rudders to the axis of the block relative to its caliber on the value of not less than 0.5 of the maximum thickness of the steering wheel at the root of the chord folding his part to protect the aerodynamic profile of the steering wheel from damage during movement of the tubular guide when you load and start.

The characteristic feature of the image is the group of specific forms of execution, allow, in particular, due to:

- perform buttress teardrop shape to improve the flow characteristics of the air flow in the vicinity of the root chord of the aerodynamic steering;

- the location of the axis of folding of the rudder at an angle to the longitudinal axis of the block to increase the area aerodynamically clean (not distorted loops) surface of the steering wheel than to increase its efficiency.

The invention consists in that in the power management system rocket, launched from the tubular guide comprising a housing with ogival part, a folding in-flight aerodynamic control surfaces actuators and control unit mounted on the arched portion, unlike the prototype, according to the invention, each wheel is equipped with a buttress, buttress placed in front of the front edge of the wheel coaxial with the axis of the opening, the profile of the front of the buttress congruent profile ogival part of the body, while the maximum diameter of the circumscribing circle of the buttresses of all control surfaces do not exceed the caliber of the block, and the axis of folding of the rudder offset to the axis of the block relative to its caliber on the value of not less than 0.5 of the maximum thickness of the steering wheel at the root of the chord its folding parts, and buttresses made teardrop shape, and the axis of the folding control surfaces are at an angle to the longitudinal axis of the block.

usnot of the invention is illustrated by drawings, where in Fig.1 shows a General view of the proposed power management system of Fig.2 is a front view of one of the aerodynamic control surfaces.

The proposed power management system of the rocket projectile includes a housing 1 with ogival part 2, the aerodynamic control surfaces 3, includes a base 4 and a folding part 5, the actuator 6 and the control unit 7. Each of the wheels 3 provided with a rib 8, placed in front of the front edge 9 of the steering wheel 3 coaxially with its axis of wheel 10. The profile of the front part 11 of the buttress 8 congruent profile 12 ogival part 2 of the housing 1, the diameter D maximum circumcircle of buttresses 8 all rudders 3 does not exceed the caliber Dmp unit management system. The axis of the opening 10 of the rudder 3 is offset to the longitudinal axis 13 of the block of the control system relative to its caliber Dmp at a value not less than 0.5 of the maximum thickness b of the steering wheel 3 at the root of the chord X its folding part 5. In some cases, of the execution of the buttresses 8 made teardrop shape, and the axis of the opening 10 of the rudder 3 is located at an angle to the longitudinal axis 13 of the unit management system.

Describes the power management system rocket, launched from the tubular guide is as follows.

In the process of reactive loading of the projectile casing 1 with ogival part 2 unit control system fitted coaxially with the tube on rallyusa 14 from its breech and push in the direction of the muzzle end 15. Buttresses 8 does not interfere with its free promotion inside the tubular guide 14, as the diameter D maximum describing the circumference of the buttresses 8 all rudders 3 does not exceed the caliber Dmp unit management system. At the same time buttresses 8 prevent possible (due to deviations from the alignment of the housing 1 with ogival part 2 and the guide 14) the interactions of the base 4 and the folding part 5 of the steering wheel 3 with the inner surface of the guide 14 by means of displacement of the axis of the opening 10 of the rudder 3 to the longitudinal axis 13 of the block of the control system relative to its caliber on the value of not less than 0.5 of the maximum thickness b of the steering wheel 3 at the root of the chord X its folding part 5. In the event of displacement of the axis of the opening 10 of the rudder 3 to the longitudinal axis 13 of the block of the control system relative to its caliber on a value less than 0.5, the maximum thickness b of the steering wheel 3 at the root of the chord X its folding part 5 the outer edge of the root chord X comes out of the "shadows" of the rib 8 and the protection of the aerodynamic profile of the steering wheel 3 from mechanical damage during movement of the tubular guide 14 loading and start-up is not provided. Located at an angle to the longitudinal axis 13 of the unit control system the axis of the opening 10 of the rudder 3 increase aerodynamically clean the surface area of the folding portions 5 of the steering wheel 3, increasing their efficiency is awn, the implementation of the buttresses 8 teardrop shape improves the flow characteristics of the air flow in the vicinity of the root chord X rudders 3.

The execution unit control system rockets launched from the tubular guide, in accordance with the invention has enabled the launch of guided missiles from a standard tubular rails designed to run previously developed unguided and guided shells reactive systems of volley fire.

1. The power management system rocket, launched from the tubular guide comprising a housing with ogival part, a folding in-flight aerodynamic control surfaces actuators and control unit mounted on the arched portion, characterized in that each wheel is equipped with a buttress, buttress placed in front of the front edge of the wheel coaxial with the axis of the opening, the profile of the front of the buttress congruent profile ogival part of the body, while the maximum diameter of the circumscribing circle of the buttresses of all control surfaces do not exceed the caliber of the block, and the axis of folding of the rudder offset to the axis of the block relative to its caliber on the value of not less than 0.5 of the maximum thickness of the steering wheel at the root of the chord folding his part.

2. The power control system of the rocket projectile p. 1, characterized in that contror is performed teardrop shape.

3. The power control system of the rocket projectile p. 1, characterized in that the axis of the folding control surfaces are at an angle to the longitudinal axis of the block.



 

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