RU2341762C1 - Antiaircraft guided missile - Google Patents

Antiaircraft guided missile Download PDF

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Publication number
RU2341762C1
RU2341762C1 RU2007111642/02A RU2007111642A RU2341762C1 RU 2341762 C1 RU2341762 C1 RU 2341762C1 RU 2007111642/02 A RU2007111642/02 A RU 2007111642/02A RU 2007111642 A RU2007111642 A RU 2007111642A RU 2341762 C1 RU2341762 C1 RU 2341762C1
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RU
Russia
Prior art keywords
stabilizer
steering
area
rocket
stabilizers
Prior art date
Application number
RU2007111642/02A
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Russian (ru)
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RU2007111642A (en
Inventor
ев Владимир Николаевич Бел (RU)
Владимир Николаевич Беляев
Владимир Григорьевич Богацкий (RU)
Владимир Григорьевич Богацкий
Виктор Константинович Елецкий (RU)
Виктор Константинович Елецкий
Александр Павлович Кравчук (RU)
Александр Павлович Кравчук
Олег Николаевич Левищев (RU)
Олег Николаевич Левищев
Александра Дмитриевна Мажукина (RU)
Александра Дмитриевна Мажукина
Григорий Рафаилович Орелиов (RU)
Григорий Рафаилович Орелиов
зев Виктор Федорович Пир (RU)
Виктор Федорович Пирязев
Виктор Антонович Рац (RU)
Виктор Антонович Рац
Геннадий Николаевич Смольский (RU)
Геннадий Николаевич Смольский
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Открытое акционерное общество "Государственное машиностроительное конструкторское бюро "Вымпел" им. И.И. Торопова"
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Priority to RU2007111642/02A priority Critical patent/RU2341762C1/en
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Abstract

FIELD: weapons and ammunition.
SUBSTANCE: missile contains case, impellent installation placed in it, control system equipment, fighting equipment, four folding aerodynamic flight controls and four folding stabilisers. The aerodynamic flight controls are established on a tail part of the case, and the stabilisers are placed before flight controls. The stabilisers are executed with the area, smaller than the area of flight controls, and rotary parts of stabilisers in the course of disclosing are executed with possibility of their shift along the case towards the flight controls.
EFFECT: reduction of mass and dimensions parametres at maintenance of demanded aerodynamic characteristics.
3 cl, 10 dwg

Description

The present invention relates to the field of rocketry and can be used in mobile anti-aircraft systems, the storage and launch of which is carried out from transport-launch containers.
Known rocket made according to the aerodynamic scheme "duck", comprising a housing, a propulsion system placed therein, control system equipment, combat equipment, as well as four folding aerodynamic steering wheels located on the housing evenly relative to its longitudinal axis, and four folding stabilizers installed in transport position in tandem with rudders (see Karpenko A.V. “Russian missile weapons 1943 ... 1993”, 1993, St. Petersburg, pp. 83, 84, 98, missile “Top-M1”.
The above missile is selected as a prototype of the invention, as the solution closest in purpose and technical essence, coinciding in a number of ways with the invention.
In the transport position, the rudders and stabilizers of the rocket are folded, and it is placed in a container of square cross section, and its ejection from the container is carried out by a catapult located inside it. Such a placement and launch scheme are ineffective compared to the possible placement of a rocket in a pipe of circular cross section, since the ammunition is quantitatively reduced (compared to the potential load-bearing capacity of the complex) and the design for launch is complicated (a mortar launch can be used for a cylindrical container). This is mainly due to the chosen design of the rocket. Indeed, in order to ensure stabilization of the rocket along the roll, stabilizers located at the end of the hull are mounted with the possibility of rotation around its longitudinal axis (in order to eliminate the influence of oblique airflow from the rudders). This also increases the transverse dimensions of the fixed (root) part of the stabilizers. The dimensions of the rudders are also significant, since they mainly work in stall modes (the angles of attack of the rudders in the "duck" scheme are large). As a result, even with folding rudders and stabilizers, the transverse dimensions of the rocket in its transport position are excessively large.
The objective of the invention is the creation of a guided anti-aircraft missile with minimum mass-dimensional parameters while ensuring the required aerodynamic characteristics.
To achieve this objective, in an anti-aircraft guided missile containing a housing, a propulsion system, control system equipment, combat equipment, rudder drives, as well as four folding aerodynamic rudders and four folding stabilizers located in tandem and including root and rotary parts, and mechanisms their disclosure, aerodynamic rudders are installed on the rear of the hull, and stabilizers are placed in front of the rudders, and the stabilizer area is less than the rudder area, and the rotary parts of the stabilizers are made with the possibility of their shift in the process of opening along the body towards the rudders to a distance between them not exceeding 0.06 · b os , where b os is the onboard chord of the stabilizer, while the rudders and stabilizers are folded so that the diameter described around folded the rudders and stabilizers of the circle does not exceed 1.2 · d k , where d k is the diameter of the rocket hull, and the geometric parameters of the hull, stabilizers and aerodynamic rudders, as well as their relative position, are related by the following relationships:
λ k = L k / d k = 14 ... 16;
Figure 00000002
λ c = l c 2 / (2 · S c ) = 1.8 ... 2.2;
η c = b os / b cs = 2.5 ... 3.2;
Figure 00000003
λ p = l p 2 / (2 · S p ) = 1.5 ... 2.0;
η p = b op / b cr = 1.8 ... 3.0;
l ovr = (13 ... 15) d k ,
where: L k is the length of the rocket body, m;
λ to - the elongation of the rocket;
d k is the diameter of the rocket body, m;
S m - midship midship missile area, m 2 ;
S c - stabilizer area, m 2 ;
Figure 00000004
- the relative area of the stabilizer;
λ with the elongation of the stabilizer;
l with - swing stabilizer, m;
η s - narrowing of the stabilizer;
b os - onboard chord of the stabilizer, m;
b cc - end chord of the stabilizer, m;
S p - rudder area, m 2 ;
Figure 00000005
- relative rudder area;
λ p - extension of the steering wheel;
l p - wheel span, m;
η p - narrowing of the steering wheel;
b op - onboard steering chord, m;
b kr - end chord of the steering wheel, m;
l ovr - the distance from the nose of the rocket to the axis of rotation of the steering wheel, m
At the same time, the stabilizer opening mechanism is made in the form of a torsion coil spring fixed to the stabilizer root part with the possibility of acting on its rotary part, and a compression spring mounted on an axis in the stabilizer root part with the possibility of shifting the rotary part of the latter along the housing and fixed input on the rotary part of the stabilizer of the fixing pins into the corresponding grooves located in the root of the stabilizer.
The disclosure mechanism of the steering wheel is made in the form of a spring-loaded pusher located in the output shaft of the steering wheel drive, interacting with its middle part with the steering part of the steering wheel and fixing the steering part of the steering wheel in the working position.
This embodiment of the device allowed to eliminate the main disadvantages of the prototype. The rudder area was reduced, and the stabilizer area was chosen in general to a smaller rudder area, i.e. decreased most significantly. In this case, due to the large balancing angles of attack, the rocket body creates no less magnitude of lifting force than the prototype with its more developed rudders and stabilizers.
The distance between the trailing edge of the stabilizer and the leading edge of the steering wheel in the proposed rocket is advisable to choose the minimum, because in addition to the function of the regulator of the initial static stability of the rocket, the stabilizer in this case also serves as a kind of guide vanes for the air flow running on the steering wheels, thereby increasing its efficiency. The above restriction on the mutual distance between the stabilizer and the steering wheel takes this factor into account, together with technological considerations.
Due to the simpler design of the rocket glider, the mass of the rocket as a whole can be reduced. As a result of the combination of the proposed ratios and technical solutions for the disclosure mechanisms of stabilizers and rudders, it was possible to ensure the placement of the rocket in a cylindrical container with a minimum cross section and allow the use of a mortar launch. This made it possible to increase the ammunition of the complex while simplifying the missile launch scheme.
Figure 1 shows a General view of the proposed rocket. Figure 2 and 3 shows the cross-section aa and bb (see figure 1) missiles in the area of installation of stabilizers and in the area of the rudders, respectively. Figure 4 shows a front view of the rocket in its transport position (view B).
Figure 5, 6 shows the proposed mechanism for the disclosure of the rudders (in the folded and opened position, respectively), in Figure 7 - the mechanism for opening the stabilizers, and in Figure 8 - section GG (see Figure 7).
Figures 9 and 10 show (for the prototype and the proposed missile) the dependencies of the maximum balancing angle of attack and the dependence of the maximum overloads (for a height of about 5 km) on the Mach number.
The rocket according to the invention comprises a housing 1 with a front fairing 2.
Inside the housing 1 control equipment 3, combat equipment 4 and engine 5 are placed. The missile is made according to the “normal” aerodynamic design. In the rear of the housing 1 there are four differential steering wheels 6 and four stabilizers 7 installed directly in front of the steering wheels.
Folding steering wheel 6 with a mechanism for its disclosure consists of a root part 8, a rotary part 9, a shank 10, a pusher 11 with a tapered bore 12, a spring 13 and two half shafts 14.
Folding stabilizer 7 with a mechanism for its disclosure consists of a root part 15 with conical holes 16, a rotary part 17, a coil spring 19, a sleeve 20, two pins 21, a spring 22 and a stopper 23.
The functioning of the rocket after ejection from the transport and launch container is as follows. First, stabilizers 7 and rudders 6 are disclosed. Each steering wheel is disclosed as follows. The pusher 11 located in the shaft end of the rudder drive shaft, due to the pressure of the compression spring 13, presses on the rotary part 9 of the steering wheel (in the container, the rotary part of the steering wheel rests on the wall of the container). After turning the steering part of the steering wheel to the desired position, the pusher 11 moves further by some distance, ensuring that the structural element of the steering part 9 of the steering wheel enters the taper hole 12 on the front of the pusher 11 and thereby completely fixes the steering wheel 6 in its working position.
The disclosure of each stabilizer 7 is as follows.
A twisted coil spring 19 turns the stabilizer pivot 17 around the axis 18 to the operating position. After that, the compression spring 22, acting on the sleeve 20, mounted on the axis 18, moves the specified axis with the pivot 23 fixed on it by the stabilizer pivot part 17 back along the housing 1 until the pins 21 enter the cone holes 16 located on the stabilizer root part 15, and thereby fixes the stabilizer in the working position.
After the rudders and stabilizers are opened, the rocket flies in the direction of the target in accordance with the flight mission and the adopted guidance law.
As follows from the above graphs (see Figs. 9, 10), the maximum balancing angles of attack of the proposed rocket are 1.6 ... 2.5 times greater than that of the prototype, which ultimately ensured (even with smaller dimensions of the bearing surfaces ) the ability to create overloads, not less than that of the prototype, and in supersonic (main flight mode) even greater.
So, the proposed guided anti-aircraft missile with the above ratios of the dimensions of the hull, stabilizers and rudders has smaller dimensions and mass for this type of missile, while not inferior to the known missiles in terms of maneuverability. This technical solution allows to increase the ammunition of mobile anti-aircraft missile systems while maintaining their carrying capacity and overall characteristics.

Claims (3)

1. Anti-aircraft guided missile, comprising a housing, a propulsion system placed therein, control system equipment, combat equipment, four folding aerodynamic steering wheels and four folding stabilizers located in tandem and including root and rotary parts and their opening mechanisms, characterized in that the aerodynamic steering wheels mounted on the rear of the hull, and stabilizers are placed in front of the rudders, the stabilizer area being smaller than the rudder area, and the stabilizer pivots during p openings are made with the possibility of their displacement along the body towards the rudders to a distance between them not exceeding 0.06 · b oc , while the rudders and stabilizers are folded so that the diameter of the circle described around the folded rudders and stabilizers does not exceed 1.2 · d k, and the geometric parameters of the hull, stabilizers and aerodynamic control surfaces, as well as their relative positions are related as follows:
λ k = L k / d k = 14 ... 16;
Figure 00000006
;
λ c = l c 2 / (2 · S c ) = 1.8 ... 2.2;
η c = b os / b cs = 2.5 ... 3.2;
Figure 00000007
;
λ p = l p 2 / (2 · S p ) = 1.5 ... 2.0;
η p = b op / b cr = 1.8 ... 3.0;
l ovr = (13 ... 15) d k ,
where L k is the length of the rocket body, m;
λ to - the elongation of the rocket;
d k is the diameter of the rocket body, m;
S m - midship midship missile area, m 2 ;
S c - stabilizer area, m 2 ;
Figure 00000008
- the relative area of the stabilizer;
λ with the elongation of the stabilizer;
l with - swing stabilizer, m;
η s - narrowing of the stabilizer;
b os - onboard chord of the stabilizer, m;
b cc - end chord of the stabilizer, m;
S p - rudder area, m 2 ;
Figure 00000009
- relative rudder area;
λ p - extension of the steering wheel;
l p - wheel span, m;
η p - narrowing of the steering wheel;
b op - onboard steering chord, m;
b cr - the root chord of the steering wheel, m;
l ovr - the distance from the nose of the rocket to the axis of rotation of the steering wheel, m
2. The rocket according to claim 1, characterized in that the stabilizer opening mechanism is made in the form of a torsion coil coil spring mounted on the root of the stabilizer with the possibility of acting on its rotary part, and a compression spring mounted on an axis in the root of the stabilizer with the possibility of shifting the rotary part of the latter along the housing and the entrance of the fixing pins fixed on the rotary part of the stabilizer into the corresponding grooves located in the root of the stabilizer.
3. The missile according to claim 1, characterized in that the steering mechanism is made in the form of a spring-loaded pusher located in the output shaft of the rudder drive, interacting with its middle part with the steering part of the steering wheel and fixing the steering part of the steering wheel in the working position.
RU2007111642/02A 2007-03-30 2007-03-30 Antiaircraft guided missile RU2341762C1 (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2478907C1 (en) * 2011-12-14 2013-04-10 Открытое акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Unfolding wing of two-stage rocket
EA018694B1 (en) * 2009-12-15 2013-09-30 Александр Александрович ЗВОНОВ Antiaircraft guided missile

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
КАРПЕНКО А.В. Российское ракетное оружие 1943...1993 г. - СПб.: ПИКА, 1993, с.83, 84, 98. *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EA018694B1 (en) * 2009-12-15 2013-09-30 Александр Александрович ЗВОНОВ Antiaircraft guided missile
RU2478907C1 (en) * 2011-12-14 2013-04-10 Открытое акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Unfolding wing of two-stage rocket

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