RU2795731C1 - Rotating rocket projectile launched from a tubular guide - Google Patents

Abstract

FIELD: rocket technology.

SUBSTANCE: invention can be used in the development of rockets launched from tubular guides. A rotating missile projectile launched from a tubular guide contains a head part (1), a stabilizer (4) with opening arcuate blades (5), convex surfaces (7) oriented in the direction of projectile rotation, having one-sided bevels on the leading edges from the side of their convex surfaces with an angleβ_blade =5…15° in a plane perpendicular to the edges, and installed at an angle to the longitudinal axis of the projectile, a jet engine (2) with one central nozzle, including a device for generating torque using a jet engine jet (2), made in the form of evenly spaced in the circumferential direction on the side surface plate nozzles with a constant thickness in height and the same angle of elevation of the helix of their side surfaces to the longitudinal axis of the projectile, for projectile rotation in the same direction as from the torque generated by the blades (5) of the stabilizer (4). The surface of each plate of the rotation device, facing the longitudinal axis of the nozzle, is formed by elements of a cylindrical surface with an axis coinciding with the longitudinal axis of the nozzle, and the angle of elevation of the helix of the side surfaces of the plates of the rotation device is made within the limits determined by the dependence:

_pl = (0.8 ... 2.4)

_blade * S_blade / S_pl * r_blade / r_pl * n_blade / n_pl, where S_pl is the projection area of the side surface of one plate of the rotation device in a plane passing through the longitudinal axis of the projectile; S_blade - the projection area of one convex stabilizer blade in a plane passing through the longitudinal axis of the missile; r_pl - the distance from the axis of the missile to the centre of pressure of the plate of the rotation device;

- the distance from the axis of the missile to the centre of pressure of the projection of the convex blade of the stabilizer; H_st - the span of the convex blades of the stabilizer; d_fair - the diameter of the fairing on which the convex blades of the stabilizer are installed; n_pl, n_blade - the number of plates of the rotation device and the arcuate blades of the stabilizer, respectively; δ_blade - the angle of installation of the convex blades of the stabilizer to the longitudinal axis of the rocket; δ_pl - the angle of elevation of the helix of the side surfaces of the plates of the rotation device.

EFFECT: creation of a rotating projectile launched from a tubular guide, with a significantly increased firing range and increased operational reliability, with improved aeroballistic characteristics by reducing the resistance of the rotation device and stabilizer blades, reducing initial disturbances and the spread of aeroballistic characteristics in flight, optimizing the rotation speed and eliminating resonant phenomena both during departure from the guides and in all parts of the trajectory.

1 cl, 1 dwg

Description

The invention relates to the field of rocketry, and in particular to rotating rockets (PC) launched from a tubular guide MLRS of various bases.

The object of the invention is a rotating PC with an increased flight range, increased reliability of operation, improved aeroballistic characteristics.

The experience of designing and operating the MLRS has shown that the most rational layout solution is the placement and launch of the PC from tubular guides. In this case, the greatest number of PCs can be placed on the combat vehicle.

Known PC multiple launch rocket system M-210F (see Combat vehicle BM-21. Technical description and operating instructions. - M: Military publishing house of the USSR Ministry of Defense, 1977, p. 74-75), containing the warhead, a jet engine with nozzles, stabilizer with opening arcuate blades mounted at an angle to the longitudinal axis of the engine and oriented convex surfaces in the direction of its rotation. The leading edges of the blades are symmetrical.

Installing the stabilizer blades in the open state at a certain angle to the longitudinal axis of the PC ensures its rotation in flight. Rotation is given to compensate for eccentric disturbances and, as a result, improve accuracy, and in salvo fire, improve accuracy.

For each type of PC, there is an allowable range of rotation speed changes based on the conditions of normal operation, strength and flight with minimum angles of attack.

The upper limit is determined by the frequency of bending vibrations of the PC case, and the lower limit is determined by the frequency of natural vibrations.

The range of change in the rotation speed for the PC is the greater, the greater the flight speed at the end of the active trajectory segment (OUT). Therefore, for the M21OF design with the indicated shape of the blade edges, due to the peculiarities of the change in the roll torque from the Mach number, there are restrictions on the maximum flight speed, and, consequently, on increasing the maximum firing range.

The task of this technical solution was to place on the combat vehicle the largest number of multiple launch rocket launchers while ensuring stable flight, a significant increase in range compared to known multiple launch rocket launchers, for example, PC M8, M13.

Common features with the design of the rotating PC proposed by the authors is the presence in the analogue of: the head part, a jet engine, a stabilizer with opening arcuate blades installed at an angle to the longitudinal axis of the PC and oriented convex surfaces in the direction of its rotation.

Also known is a rotating PC according to the patent of the Russian Federation No. 2166178, IPC F42B 15/00. It contains a head part, a jet engine and an aerodynamic stabilizer with opening arcuate blades installed at an angle to the longitudinal axis PC. The arcuate blades are mounted with convex surfaces in the direction of rotation of the projectile, the front and rear edges of each blade are made with one-sided sharpening with a bevel located on the convex surface of the blade, and the ratio of the average angle of installation of the stabilizer blades to the angle of the beveled edges is in the range (0.02 ... 0, 03) H / d, where H is the span of the stabilizer blades, d is the caliber of the projectile.

The task of this technical solution was to create a rotating supersonic PC multiple launch rocket systems with increased flight speed and firing range, increase its combat effectiveness and operational reliability by reducing the range of rotation speed change on the trajectory and eliminating resonance phenomena.

Common features with the design of the rotating PC proposed by the authors is the presence in the analog of: the head part, a jet engine, a stabilizer with opening arcuate blades and having an asymmetric leading edge shape with a bevel on their convex surfaces, installed at an angle to the longitudinal axis of the PC and oriented convex surfaces in the direction its rotation.

The initial value of the rotation speed of the PC M21OF, as well as according to patent No. 2166178 when taking off from the launcher, was provided due to the presence of a screw groove inside the tubular guide and a drive pin in the rear of the jet engine housing.

In connection with the development and practical application of more technologically advanced and economical, often disposable containers with smoothbore tubular guides, it became necessary to create a new design of a rotating PC.

A rotating PC is known, launched from a smoothbore tubular guide, according to the patent of the Russian Federation No. It contains a head part, a jet engine with one central nozzle, including a device for generating torque using a jet of a jet engine, a stabilizer with opening arcuate blades installed at an angle to the longitudinal axis PC. The arcuate blades are installed with convex surfaces in the direction of projectile rotation, the leading edges of each blade are made with one-sided sharpening with a bevel located on the convex surface of the blade, with an angle ρ _lop =5°...15° in the plane perpendicular to the edges

A device for generating torque using a jet engine jet to rotate the projectile in the same direction as from the moment created by the stabilizer blades is located on the inner surface of the nozzle behind its critical one and contains plates uniformly installed in the circumferential direction at the same angle of elevation of their helix side surfaces to the longitudinal axis of the rocket, the thickness of the plates is constant in height and is (0.05 ... 0.15) d _cr , and the center of pressure of each plate is removed from the outlet section of the jet engine nozzle at a distance of (1.5 ... 3.0) d _cr. , where d _cr - the diameter of the critical section of the jet engine nozzle.

Further improvement of PCs, similar to the prototype, in order to significantly increase the range and increase the reliability of operation at higher flight speeds, led to the need to improve the shape of the plates and optimize the ratio of the geometric parameters of the plates of the rotation device and stabilizer blades, their installation angles.

,Unlike the prototype, in the proposed rotating projectile launched from a tubular guide, the surface of each plate of the rotation device, facing the longitudinal axis of the nozzle, is formed by elements of a cylindrical surface with an axis coinciding with the longitudinal axis of the nozzle, and the angle of elevation of the helical line of the side surfaces of the plates of the rotation device performed within the limits determined by the dependence:

,

where S _pl is the projection area of the side surface of one plate of the rotation device in a plane passing through the longitudinal axis of the projectile;

S _lop - the projection area of one arcuate stabilizer blade in a plane passing through the longitudinal axis of the missile;

r _pl - distance from the axis of the missile to the center of pressure of the plate of the rotation device;

- расстояние от оси реактивного снаряда до центра давления проекции дугообразной лопасти стабилизатора;

- distance from the axis of the missile to the center of pressure of the projection of the arcuate blade of the stabilizer;

H _st - the span of the arcuate blades of the stabilizer;

d _obt - the diameter of the fairing on which the arcuate blades of the stabilizer are installed;

n _pl , n _lop - the number of plates of the rotation device and the arcuate blades of the stabilizer, respectively;

δ _lop - installation angle of the arcuate blades of the stabilizer to the longitudinal axis of the missile;

δ _pl - the angle of elevation of the helix of the side surfaces of the plates of the rotation device.

This allows us to conclude that there is a causal relationship between the set of essential features of the proposed technical solution and the achieved technical result.

The said features, which are different from the prototype and which are covered by the claimed scope of legal protection, are in all cases sufficient.

The objective of the invention is to create a rotating missile launched from a tubular guide, with a significantly increased firing range and increased operational reliability, with improved aeroballistic characteristics by reducing the resistance of the rotation device and stabilizer blades, reducing initial disturbances and the spread of aeroballistic characteristics in flight, optimizing speed rotation and exclusion of resonance phenomena both during departure from the guides and in all parts of the trajectory.

This technical result is achieved by the fact that in a rotating projectile launched from a tubular guide, containing a warhead, a jet engine with one central nozzle, including a device for creating torque using a jet engine jet to rotate the projectile in the same direction as from the rotating moment created by the stabilizer blades, in the form of plates evenly spaced in the circumferential direction on the side surface of the nozzle with a constant thickness in height and the same angle of elevation of the helix of their side surfaces to the longitudinal axis of the projectile, a stabilizer with opening arcuate blades oriented by convex surfaces in the direction of rotation of the projectile , having one-sided bevels on the leading edges from the side of their convex surfaces with an angle β _lop = 5° ... 15° in a plane perpendicular to the edges, and installed at an angle to the longitudinal axis of the projectile, according to the invention, the surface of each plate of the rotation device facing the longitudinal axis nozzle, formed by elements of a cylindrical surface with an axis coinciding with the longitudinal axis of the nozzle, and the angle of elevation of the helix of the side surfaces of the plates of the rotation device is made within the limits determined by the dependence:

where S _pl is the projection area of the side surface of one plate of the rotation device in a plane passing through the longitudinal axis of the projectile;

S _lop - the projection area of one arcuate stabilizer blade in a plane passing through the longitudinal axis of the missile;

r _pl - distance from the axis of the missile to the center of pressure of the plate of the rotation device;

- расстояние от оси реактивного снаряда до центра давления проекции дугообразной лопасти стабилизатора;

- distance from the axis of the missile to the center of pressure of the projection of the arcuate blade of the stabilizer;

H _st - the span of the arcuate blades of the stabilizer;

d _obt - the diameter of the fairing on which the arcuate blades of the stabilizer are installed;

n _pl , n _lop - the number of plates of the rotation device and the arcuate blades of the stabilizer, respectively;

δ _lop - installation angle of the arcuate blades of the stabilizer to the longitudinal axis of the missile;

δ _pl - the angle of elevation of the helix of the side surfaces of the plates of the rotation device.

The authors of the proposed invention conducted research in wind tunnels, bench and flight tests of PC prototypes with rotation devices located behind the critical section of the jet engine nozzle, aimed at finding technical solutions to ensure stable resonance-free flight with zero angles of attack in the allowable range of angular velocity of rotation of PC , increase the reliability of the rotating PC and its combat effectiveness, reduce the range of changes in the angular velocity of rotation of the projectile when moving in a tubular guide and in all parts of the flight path by choosing the shape of the plates of the rotation device, the shape of the edges of the stabilizer blades and the optimal ratios of their geometric parameters, reduce resistance rotation devices and stabilizer blades.

A new set of structural elements, as well as the presence of relationships between the parameters of the inventive rotating missile launched from a tubular guide, made it possible, in particular, by performing:

- the surface of each plate facing the longitudinal axis of the nozzle, by elements of a cylindrical surface with an axis coinciding with the longitudinal axis of the nozzle,

- reduce the resistance of the plates of the rotation device, reduce the loss of jet thrust and thereby increase the flight range of the PC;

- the angle of elevation of the helix of the side surfaces of the plates of the rotation device within the limits determined by the dependence:

- повысить надежность функционирования, улучшить характеристики точности и кучности за счет уменьшения сопротивления устройства вращения и лопастей стабилизатора, снижения начальных возмущений и разброса аэробаллистических характеристик в полете, оптимизации скорости вращения и исключения резонансных явлений как при вылете из трубчатой направляющей, так и на всех участках траектории полета. При увеличении угла подъема винтовой линии боковых поверхностей пластин свыше

- происходит увеличение сопротивления реактивного снаряда за счет увеличения сопротивления пластин устройства вращения, потере тяги и как следствие к уменьшению дальности стрельбы. Выполнение угла подъема винтовой линии боковых поверхностей пластин менее

приводит к снижению начальной угловой скорости вращения при вылете из трубчатой направляющей, повышается вероятность раскачки PC и попаданию в зону резонансной неустойчивости, снижается надежность функционирования, увеличиваются начальные возмущения, влияющие на точность и кучность стрельбы.

- increase the reliability of operation, improve the accuracy and accuracy characteristics by reducing the resistance of the rotation device and stabilizer blades, reducing the initial disturbances and the spread of aeroballistic characteristics in flight, optimizing the rotation speed and eliminating resonance phenomena both when leaving the tubular guide and in all parts of the trajectory flight. With an increase in the angle of elevation of the helix of the side surfaces of the plates over

- there is an increase in the resistance of the rocket due to an increase in the resistance of the plates of the rotation device, loss of thrust and, as a result, a decrease in the firing range. Implementation of the angle of elevation of the helix of the side surfaces of the plates is less than

leads to a decrease in the initial angular velocity of rotation when leaving the tubular guide, increases the likelihood of PC buildup and getting into the zone of resonant instability, reduces the reliability of operation, increases the initial disturbances that affect the accuracy and accuracy of fire.

The essence of the invention is illustrated by the drawing figure 1, which shows a General view of a rotating rocket projectile with a view D from the side of the nozzle of the rocket projectile, which shows the location of the drop-down arcuate blades, section A-A - the axial section of the nozzle, which shows the elements of the device for creating torque in in the form of plates, view C on one of the plates located in the circumferential direction of the nozzle and section B-B of one of the arcuate blades made with a one-sided bevel.

The rotating PC consists of a head part 1, a jet engine 2 with one central nozzle 3, a stabilizer 4 with opening arcuate blades 5 with asymmetrical leading edges 6 and oriented convex surfaces 7 in the direction of PC rotation. The leading edges 6 of the arcuate blades 5 are made with one-sided bevels 8, made on their convex surfaces 7 with an angle β _lop =5°...15° in a plane perpendicular to the edges. The blades 5 are set at an angle δ _lop to the longitudinal axis PC.

On the inner side surface of the nozzle 3 behind its critical section 9 there is a device 10 for creating a torque using a jet of a jet engine 2. The device 10 contains plates 11 uniformly spaced in the circumferential direction of the nozzle 3 at the same angle _δpl of the helix of their side surfaces 12 to longitudinal axis PC and thickness t constant in height.

The surface 13 of each plate 11 of the rotation device 10, facing the longitudinal axis of the nozzle 3, is formed by elements of a cylindrical surface with an axis coinciding with the longitudinal axis of the nozzle 3, and the angle _{δpl of} the helix of the side surfaces of the plates of the rotation device is made within the limits determined by the dependence:

The functioning of the proposed rotary PC is as follows. After starting the jet engine 2, due to the reactive force of the gas jet flowing from the central nozzle 3, the PC with the head part 1 moves along the tubular guide of the launcher, the arcuate blades 5 of the stabilizer 4 are in the folded position. The gas jet of the jet engine 2 acts on the side surfaces 12 of the plates 11 of the rotation device 10 located behind the critical section 9 of the nozzle 3, creates a torque about the longitudinal axis PC, which starts rotation.

After the PC leaves the tubular guide of the launcher, the blades 5 open, providing a stable movement of the projectile along the trajectory. Due to the installation of the blades 5 at an angle δ _lop to the longitudinal axis of the PC is supported by its further rotation. By providing the required rotation speed, the influence of initial disturbances during the departure of PC, geometric, gas-dynamic eccentricities on the main characteristics of firing is excluded. The presence of one-sided bevels 8 of the leading edges 6, made on the convex surfaces 7 of the blades in combination with the angle m δ _lop of their installation, creates an optimal aerodynamic torque of the stabilizer 4, directed in the same direction as the gas-dynamic moment from the plates 11.

Due to the choice of shapes, installation angles, geometric parameters of the stabilizer blades and plates of the rotation device, their rational relationships between themselves and those indicated in the above description formula, a stable resonance-free flight of the PC is ensured without buildups and destructions in the permissible range of the angular velocity of rotation in all sections of the trajectory, a decrease in resistance device plates and stabilizer blades, when driving at high speeds, reduce the loss of engine thrust.

The proposed technical solution made it possible to develop a rotating rocket with increased operational reliability, a significantly increased firing range, and improved aeroballistic characteristics.

The specified positive effect is confirmed by flight design tests of samples of rotating PC multiple launch rocket systems, made in accordance with the proposed invention.

Claims (11)

A rotating missile launched from a tubular guide, containing a warhead, a stabilizer with opening arcuate blades oriented by convex surfaces in the direction of rotation of the projectile, having one-sided bevels on the leading edges from the side of their convex surfaces with an angle β _lop = 5 ... 15 ° in the plane, perpendicular to the edges, and mounted at an angle to the longitudinal axis of the projectile, a jet engine with one central nozzle, including a device for generating torque using a jet engine jet, made in the form of plates evenly spaced in the circumferential direction on the side surface of the nozzle with plates of constant height and the same the angle of elevation of the helix of their side surfaces to the longitudinal axis of the projectile, for projectile rotation in the same direction as from the torque generated by the stabilizer blades, characterized in that the surface of each plate of the rotation device, facing the longitudinal axis of the nozzle, is formed by elements of a cylindrical surface with an axis coinciding with the longitudinal axis of the nozzle, and the angle of elevation of the helix of the side surfaces of the plates of the rotation device is made within the limits determined by the dependence

_pl \u003d (0.8 ... 2.4) *

_lop *S _lop / S _pl * r _lop / r _pl * n _lop / n _pl , where S _pl is the projection area of the side surface of one plate of the rotation device in a plane passing through the longitudinal axis of the projectile; S _lop - the projection area of one arcuate stabilizer blade in a plane passing through the longitudinal axis of the missile; r _pl - distance from the axis of the missile to the center of pressure of the plate of the rotation device;

- distance from the axis of the missile to the center of pressure of the projection of the arcuate blade of the stabilizer; H _st - the span of the arcuate blades of the stabilizer; d _obt - the diameter of the fairing on which the arcuate blades of the stabilizer are installed; n _pl , n _lop - the number of plates of the rotation device and the arcuate blades of the stabilizer, respectively; δ _lop - installation angle of the arcuate blades of the stabilizer to the longitudinal axis of the missile; δ _pl - the angle of elevation of the helix of the side surfaces of the plates of the rotation device.

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