RU2773057C1 - Rotating projectile launched from a smoothbore tubular rail - Google Patents

Abstract

FIELD: weaponry.

SUBSTANCE: rotating projectile launched from a smooth-bore tubular guide contains, on the inner surface of the nozzle behind its critical section, a device for generating torque using a jet of a jet engine. The rotation of the projectile is made in the same direction as from the torque created by the stabilizer blades. The rotation device contains plates uniformly installed in the circumferential direction at the same angle of elevation of the helix of their side surfaces to the longitudinal axis of the rocket.

EFFECT: increase in firing range, increase in reliability, optimization of rotation speed, exclusion of resonant phenomena during departure from guides and in all parts of the trajectory.

1 cl, 1 dwg

Description

The invention relates to the field of rocketry, namely to rotating rockets (PC) launched from a smooth-bore tubular guide of multiple rocket launchers of various bases.

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

Experience in the design and operation of multiple launch rocket systems has shown that the most rational layout solution is to place the PC before launch and launch them from tubular guides.

In this case, the greatest number of PCs can be placed on the combat vehicle. The arcuate blades of the stabilizer are in the folded position before launch, and after leaving the guide they open.

Known for 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 a 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 stabilizer blades are symmetrical.

Due to the installation of the stabilizer blades in the open state at a certain angle to the longitudinal axis of the PC, its rotation in flight is ensured.

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

The upper limit is due to the frequency of bending vibrations of the body PC, and the lower limit is 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 edges of the blades, due to the peculiarities of the change in the roll torque from the Mach number, which affect the range of rotation speed, there are restrictions on the maximum flight speed, and, consequently, on increasing the maximum firing range.

The objective of this technical solution was to place on the combat vehicle the largest number of multiple launch rocket launchers while ensuring their 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 are 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 rocket 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 and adopted by the authors as a prototype. It contains a warhead (pointed nose, combat compartment), a jet engine and an aerodynamic stabilizer with opening arcuate blades mounted at an angle to the longitudinal axis PC. 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 installation angle 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 an increased flight speed and, consequently, a firing range, to increase the reliability of operation by reducing the range of rotation speed changes on the trajectory and eliminating resonance phenomena.

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

The initial value of the angular velocity of rotation 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.

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.

Unlike the prototype, in the proposed rotating projectile launched from a smoothbore tubular guide, on the inner surface of the nozzle behind its critical section there is a device for generating torque using a jet engine jet to rotate the projectile in the same direction as from the torque generated by the blades stabilizer, the rotation device contains plates uniformly installed in the circumferential direction at the same angle of elevation of the helix of their 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 plates are removed from the outlet section of the jet engine nozzle at a distance of (1.5 ... 3.0) d _cr , while the front edges of the arcuate stabilizer blades are made of an asymmetric shape with one-sided bevels made on their convex surfaces with an angle β _lop = 5 ° ... 15 ° in the plane perpendicular to the edges, and the angle under removal of the helix of the side surfaces of the plates of the rotation device is made within δ _pl =(1.2…2.4)β _lop ,

where d _cr - the diameter of the critical section of the jet engine nozzle;

β _lop - the angle of the bevel of the leading edges of the arcuate blades of the stabilizer;

δ _pl - the angle of elevation of the helical line of the side surfaces of the plates of the rotation device to the longitudinal axis of the rocket.

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 proposed invention is to create a rotating projectile launched from a smooth-bore tubular rail, with an increased firing range and increased operational reliability, by reducing the dispersion of aeroballistic characteristics in flight, optimizing the rotation speed and eliminating resonance phenomena both when taking off from the rails and at all sections of the trajectory.

The specified technical result is achieved by the fact that in a rotating projectile launched from a smooth-bore tubular guide, containing a warhead, a jet engine with one central nozzle, a stabilizer with opening arcuate blades and having an asymmetric shape of the leading edges, installed at an angle to the longitudinal axis of the projectile and oriented convex surfaces in the direction of its rotation, according to the invention, on the inner surface of the nozzle behind its critical section there is a device for creating torque using a jet engine jet to rotate the projectile in the same direction as from the torque generated by the stabilizer blades, the rotation device contains plates uniformly installed in the circumferential direction at the same angle of elevation of the helix of their side surfaces to the longitudinal axis of the rocket, the thickness of the plates is constant in height and amounts to (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 , while the front edges of the arcuate blades of the stabilizer are made of an asymmetric shape with one-sided bevels made on their convex surfaces with an angle β _lop =5°…15° in the plane perpendicular to the edges, and the angle of elevation of the helix of the side surfaces of the plates of the rotation device is made within δ _pl =(1.2…2.4)β _lop ,

where d _cr - the diameter of the critical section of the jet engine nozzle;

β _lop - the angle of the bevel of the leading edges of the arcuate blades of the stabilizer;

δ _pl - the angle of elevation of the helical line of the side surfaces of the plates of the rotation device to the longitudinal axis of the rocket.

The authors of the alleged invention conducted research in wind tunnels on models and models with full-scale stabilizers with arcuate blades, 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 the angular velocity of rotation of the PC, to increase the reliability of the functioning of the rotating PC to reduce the range of change in the angular velocity of the projectile when moving in a smooth-bore tubular guide and in all sections of the flight path by selecting the geometric parameters of the arcuate blades of the stabilizer and the rotation device located on the inner nozzle surface, rational ratios of the shape of the edges and geometric parameters of the rotation device.

A new set of structural elements, as well as the presence of links between the parameters of the inventive rotating projectile launched from a smooth-bore tubular guide, made it possible, in particular, due to the following:

- on the inner surface of the nozzle behind its critical section of a device for generating torque using a jet of a jet engine, containing plates uniformly installed in the circumferential direction at the same angle of elevation of the helix of their side surfaces to the longitudinal axis of the rocket with a constant height equal to (0, 05 ... 0.15)d _cr - ensure reliable creation of torque in the same direction as from a stabilizer with arcuate blades with minimal values of the resistance force of the plates. When the thickness of the plates is more than 0.15 d _cr , there is a significant increase in the resistance of the plates and the loss of engine thrust. If the thickness of the plates is less than 0.05d _kr , due to the high temperature and the aggressive effect of the gas jet of a jet engine, the plates burn out, the creation of the required torque is not ensured, the reliability of the operation of the rotation device and the PC as a whole is not ensured;

- the center of pressure of each plate, remote from the outlet section of the nozzle of a jet engine at a distance of (1.5 ... 3.0) d _cr , - to ensure the creation of a torque at the minimum values of the geometric parameters of the plates of the rotation device. Increasing the distance over 3d _cr leads to a decrease in torque due to a decrease in the shoulder of the transverse force on the plate, as well as a decrease in the dynamic pressure of the gas jet of a jet engine. Making the distance less than 1.5d _cr leads to a decrease in torque due to a decrease in pressure and velocity head of the gas jet as it approaches the outlet section of the nozzle;

- the front edges of the arcuate blades of the stabilizer of an asymmetric shape with one-sided bevels made on their convex surfaces with an angle β _lop = 5° ... 15° in a plane perpendicular to the edges, and the angle of helix of the side surfaces of the plates of the rotation device within δ _{pl =} (1 ,2…2,4)β _lop - to ensure the creation of torque PC when moving in a smooth-bore tubular guide, on the OUT and maintain its rotation in the passive section (PUT) in the allowable range of angular velocity of rotation at the minimum geometric values of the rotation device and arcuate stabilizer blades . The fulfillment of the angle of one-sided bevel of the leading edges of less than 5° leads to a violation of the specified shape of the edges in the conditions of flight PC at high speeds and the effect of aerodynamic heating, an increase in the spread of torque and angular velocity of rotation, an increase in the probability of reaching unacceptable values of the roll torque PC. When β _lop >15° there is an increase in the frontal resistance of the blades, the resistance of the PC as a whole and a decrease in the range of its flight. When the angle δ _pl >2,4β _lop increases the resistance of the plates of the rotation device and increases the loss of thrust of the jet engine. In addition, gas flow separations and flow instability are possible, leading to a spread in the intra-ballistic characteristics of a jet engine. The fulfillment of the angle δ _pl <1.2β _lop leads to the creation of insufficient torque relative to the longitudinal axis of the PC to parry the initial perturbations when it leaves the smooth-bore tubular guides of the launcher, leading to a decrease in range and a deterioration in the main characteristics.

The essence of the invention is illustrated by the drawing of Fig. 1, which shows a general view of a rotating projectile.

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 presented design is illustrated by the section B-B in Fig. one.

On the inner 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 δ _pl =(1.2...2.4 )β _lop of lifting the helix of their side surfaces 12 to the longitudinal axis PC. The thickness of the plates 11 is constant in height and amounts to t=(0.05...0.15) d _kr , and the center of pressure of each plate is removed from the outlet section of the nozzle 3 by a distance L=(1.5...3.0) d _kp , where d _kp - diameter of the critical section 9 of the nozzle 3. In section A-A of Fig. 1 shows in detail the device 10 for generating torque, as well as the side surface 12 of the plate 11, indicating the point of the center of pressure. In view C of FIG. 1 the structure of the plate 11 with an indication of its thickness t

The functioning of the proposed rotary PC is as follows. After starting the jet engine 2, due to the reactive force of the gas jets flowing from the central nozzle 3, the projectile with the head part 1 moves along the smooth-bore 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 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 its rotation.

After the PC leaves the guide launcher, the blades 5 open, providing a stable movement of the projectile along the trajectory. Due to the required angular velocity of rotation, the influence of the initial disturbances during the departure of PC, geometric, gas-dynamic eccentricities on the main characteristics of the shooting is excluded. Due to one-sided bevels 8 of the leading edges 6, made on the convex surfaces 7 of the blades, an aerodynamic torque of the stabilizer 4 is created, directed in the same direction as the gas-dynamic moment from the plates 11. This moment ensures the rotation of the PC after the end of the operation of the jet engine 2.

Due to the choice of the geometrical parameters of the arcuate blades of the stabilizer and the rotation device located on the inner surface of the nozzle, the rational ratios of the shape of the edges and the geometric parameters of the rotation device, a stable resonance-free flight of the PC is ensured in the permissible range of the angular velocity of rotation when moving at high speeds, which makes it possible to increase the firing range, operational reliability.

The specified positive effect is confirmed by flight design tests of prototypes of the rotating multiple launch rocket system made in accordance with the proposed invention.

At present, design documentation has been developed, and it is planned to manufacture an experimental batch of rotating PCs.

Claims (4)

Rotating rocket projectile launched from a smooth-bore tubular guide, containing a warhead, a jet engine with one central nozzle, a stabilizer with opening arcuate blades and having an asymmetric leading edge shape, installed at an angle to the longitudinal axis of the projectile and oriented convex surfaces in the direction of its rotation, characterized by the fact that on the inner surface of the nozzle behind its critical section there is a device for creating a torque using a jet engine jet to rotate the projectile in the same direction as from the torque generated by the stabilizer blades, the rotation device contains plates uniformly installed in the circumferential direction under the same angle of elevation of the helix of their lateral 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 nozzles and a jet engine at a distance of (1.5…3.0)d _cr , while the leading edges of the arcuate stabilizer blades are made of an asymmetric shape with one-sided bevels made on their convex surfaces with an angle β _lop =5°…15° in a plane perpendicular to edges, and the angle of elevation of the helix of the side surfaces of the plates of the rotation device is made within δ _pl =(1.2...2.4)β _lop , where d _cr - the diameter of the critical section of the jet engine nozzle; β _lop - the angle of the bevel of the leading edges of the arcuate blades of the stabilizer; δ _pl - the angle of elevation of the helical line of the side surfaces of the plates of the rotation device to the longitudinal axis of the rocket.

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