RU2288433C1 - Rocket projectile - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the rocket projectile has a fuse, nose section, solid propellant jet engine with a nozzle unit of inlet and outlet cones, cylindrical fin with fastening assemblies and blade fixing fastened to them, folding blade fin, axles and springs located on the fin assembly. The fin assembly is made in the form of stressed panels, interconnected by cylindrical panels, rectangular in plan, with the assemblies for fastening and fixation of blades, it is installed on the inlet cone with radial and end clearances, and on the outlet cone with a radial clearance with a support of its rear end on the surface of the outlet cone. The fastening assemblies of the fin are located in the lines passing through the stressed panels, the thickness and width of each cylindrical panel makes up 0.4 to 0.6 and 0.6 to 0.7 of the thickness and width of the stressed panel respectively. The values of the radial and end clearances make up 0.0008 to 0.0003 and 0.0004 to 0.012 of the projectile caliber respectively.

EFFECT: enhanced range of fire and close grouping of shots.

5 dwg

Description

The present invention relates to rocket technology, namely to unguided rockets (NURS) and may find application in the development of new samples of NURS.

As is known, to stabilize the NURS in flight, vane stabilizers are widely used located in the region of the tail part of the NURS and are a series of plates (blades) that protrude beyond the caliber of the projectile.

To average the influence of shape errors, gas-dynamic and aerodynamic eccentricities, and other disturbing factors on the flight of the NURS, they are given rotation around the longitudinal axis due to the installation of the tail unit at an angle to the longitudinal axis of the NURS.

At the same time, increased requirements are imposed on the accuracy of the angular location, reliability and strength of the mounting of the blades, as failure to fulfill these requirements significantly affects the stability of the aerodynamic and external ballistic characteristics of the NURS, and consequently, the firing range and dispersion parameters.

Known NURS (Vinitsky A.M. Solid propellant rocket engines. M: Mechanical Engineering, 1973, p.13.14), consisting of a fuse, a head part, a rocket engine with a solid fuel charge and a nozzle block. On the nozzle block, consisting of inlet and outlet cones, a fairing with fixed blades fixed on its surface is rigidly fixed. The design of the NURS is extremely simple and technologically advanced, while ensuring the reliability and strength of the mounting of the blades and compliance with the requirements for their angular location.

The launch of the well-known NURS is made from the launcher (PU) with rail guides, while the distance between adjacent shells ensures the free launch of any of the shells, and neighboring NURS do not interfere with the starting projectile.

Given the above, the placement on the launcher of the required number of known NURSs significantly increases the overall mass characteristics of the installation, and, while limiting its dimensions and mass, significantly reduces the number of NURSs placed on the launchers, which is a significant drawback.

Thus, the objective of this technical solution (prototype) was the development of a simple and technological design of the NURS, but not providing the maximum density of their location on the PU.

Common signs with the proposed NURS authors are the presence of a fuse, a warhead, a solid propellant rocket engine (RDTT) with a nozzle block, a fairing, and a plumage.

The optimal design of the NURS, satisfying the requirements for the maximum density of their placement on the launcher, would be the design of the projectile with the plumage folding in its caliber, which would allow launching the NURS from tubular guides having the maximum density on the installation.

The closest in technical essence and the achieved technical effect is NURS, described in "BM-21 combat vehicle. Technical description and instruction manual". M .: Military Publishing, 1982. p. 89-92 and accepted by the authors for the prototype.

The projectile consists of a fuse, a warhead, a solid propellant rocket engine with a nozzle block, and an oblique-shaped plumage folding into its caliber.

The nozzle block consists of inlet and outlet cones, between which is placed an equally thick cylindrical fairing with attachment and fixing units for the blades in the open position.

The fairing is rigidly fixed to the cones. The blades are plates curved along the radius of the fairing and in the closed position surrounding its surface without protruding beyond the caliber of the NURS.

On the fairing, the blades are mounted on the axes passing through the nodes of fastening and fixing the blades. On the axes are also springs, with the help of which the blades open and fix.

In the open position, the blades are fixed on the fairing with the help of locking surfaces made on their root ends and counter surfaces of the fairing.

When an electrical impulse is applied to the solid propellant igniter, the latter fires and ignites the charge of solid fuel. The outflow of gases through the nozzle block begins, the engine enters the mode. Upon reaching the engine thrust value equal to the magnitude of the force of forcing, begins the movement of the NURS along the guide.

When leaving the guide, under the action of the springs, the blades open and fix, while the blades rotate on the axes and move back to the end of the ends of their supporting surfaces in the counter surfaces on the fairing. The flight of the projectile begins along the trajectory.

During the operation of the solid propellant rocket engine, the flight speed increases from almost zero to a maximum value, which leads to an increase in alternating aerodynamic loads acting on the blades, and also vibrations of the shell of the shell caused by static and dynamic imbalance, vibrations of the shell of a working engine, etc.

Flight (aerodynamic) loads acting on the blades are perceived by the end sections of their locking surfaces and transmitted by them to the counter sections of the fairing.

It should be noted that the rigid mount of the fairing on the nozzle block facilitates both the transmission of the vibrations of the NURS body to the blades and the transmission of the vibrations of the blades from flight loads to the shell of the shell.

If it is necessary to increase the maximum flight speed (for example, to increase the firing range), the flight and vibration loads on the blades increase sharply, and the combined action on the blades of increased loads significantly increases the stresses on the locking surfaces of the fairing, leading to their bending and the appearance of play in the connection "blade - cowl".

Backlash in this connection increases the reaction time of the blade to the appearance of the angle of attack (when the sign of the aerodynamic load changes), which leads to fluctuations in the angles of attack of the NURS, causing it to "swing", and adversely affects its external ballistic and aerodynamic characteristics, reducing the firing range and worsening parameters its dispersion.

In addition, when the vibration frequency of the NURS case coincides with the frequency of the natural vibrations of the blades, resonance phenomena can occur, characterized by the loss of mechanical strength by the blades and their breakage.

Thus, the well-known NURS (prototype) has significant disadvantages:

- the use of fairing surfaces as perceiving loads from the blades affects the external ballistic and aerodynamic characteristics by increasing the reaction time of the blade to the appearance of the angle of attack (when the sign of the aerodynamic load changes), which leads to fluctuations in the angles of attack of the NURS, causing it to "swing" due to the raising of these surfaces and an increase in play in the blade-fairing joint at higher flight speeds;

- the rigid mount of the fairing on the nozzle block also affects the external ballistic and aerodynamic characteristics of the NURS due to:

- transmission of vibrations of the shell to the blades, which leads to their additional loading, causing additional "buildup" or breakage of the blades;

- transmission of the vibrations of the blades from alternating flight loads to the shell of the projectile, which leads to off-design fluctuations in the angle of attack of the NURS.

Thus, the objective of this technical solution (prototype) was the development of NURS, providing the maximum density of their placement on launchers, but not intended for use in long-range MLRS systems with increased flight speeds.

Common signs with the proposed NURS authors are the presence of a fuse, a head part, a solid propellant rocket engine with a nozzle block, a fairing with attachment and fixation units for the blades, rigid obliquely placed curved blades, axles and springs.

In contrast to the prototype, in the NURS proposed by the authors, the fairing is made in the form of power panels connected with each other by cylindrical rectangular panels with fastening and fixing nodes for the blades and mounted on the inlet cone with radial and end gaps and in the outlet cone with a radial clearance with support for its rear end on the surface of the outlet cone, while the fairing mounts are located on the lines passing through the power panels, the thickness and width of each cylindrical panel is respectively 0.4 ... 0.6 and 0.6 ... 0.7 of the thickness and width of the power panel, and the magnitude of the radial and end gaps are 0.0008 ... 0.003 and 0.0004 ... 0.012 caliber projectiles, respectively.

It is this that allows us to conclude that there is a causal relationship between the totality of the essential features of the claimed technical solution and the achieved technical results.

These signs, distinctive from the prototype and to which the requested amount of legal protection applies, are sufficient in all cases.

The objective of the invention is to increase the combat effectiveness of the NURS by improving its external ballistic and aerodynamic characteristics by reducing the impact on the projectile of disturbing factors from vibrations of its body.

A new set of structural elements, as well as the presence of connections between the details of the claimed NURS allow:

- due to the performance of the fairing in the form of power panels, connected in relation to each other with rectangular cylindrical power planes with fastening and fixing units for the blades, increase the local stiffness of the fastening and fixing units, reduce the impact of additional loads on the blades and reduce the amplitude of the deflection of the blades from these forces;

- due to the installation of a fairing with radial and end gaps with a value of 0.0008 ... 0.003 and 0.0004 ... 0.012 projectile caliber, respectively:

a) - reduce the transmission of vibration of the housing NURS to the fairing and the blades associated with it;

b) - reduce the transmission of the vibration of the blades from alternating flight loads to the NURS case;

- due to the support of the rear end of the fairing on the surface of the output cone to ensure a uniform distribution and transfer to the nozzle block (and further to the shell of the projectile) of the loads from the blades;

- and due to the implementation of cylindrical panels with a thickness and width that are respectively 0.4 ... 0.6 and 0.6 ... 0.7 of the thickness and width of the power panel, and the location of the fairing attachment points on the lines passing through the power panels , to exclude or significantly reduce the transmission of vibration loads to the blades with frequencies close to their own frequencies of bending and torsional vibrations (the cowl is a mechanical filter).

A change in the claimed ratios (values of radial and end gaps, thickness and width of cylindrical panels) leads to a deterioration of characteristics:

- making a radial clearance of less than 0.0008 and an end gap of less than 0.0004 caliber of the projectile leads to an increase in the transmission of body vibrations to the blades and an increase in the amplitude of their vibrations;

- the implementation of a radial clearance of more than 0.003 and an end gap of more than 0.012 caliber of the projectile leads to a decrease in the stability of the NURS in the air flow due to the skew of the fairing and changes in the flow around the blades;

- the implementation of cylindrical panels with a thickness and width of less than 0.4 and 0.6, respectively, of the thickness and width of the power panels leads to a decrease in the natural frequency of the fairing, due to which resonant phenomena of the blades from external (aerodynamic) influences may occur;

- the implementation of cylindrical panels with a thickness and width of more than 0.6 and 0.7, respectively, of the thickness and width of the power panels leads to an increase in the natural frequency of the fairing, due to which resonant phenomena of the blades from vibration effects from the side of the NURS can occur.

The essence of the invention lies in the fact that in an uncontrolled rocket containing a fuse, a head part, a solid fuel rocket engine with a nozzle block from the inlet and outlet cones, a cylindrical cowl fastened with them with attachment and fixing units for the blades, a folding shovel is placed on the cowl, axes and springs, in contrast to the prototype, according to the invention, the fairing is made in the form of power panels, connected in the form of cylindrical panels, rectangular in terms of power, with crepe assemblies blades and fixation and mounted on the inlet cone with radial and end gaps and on the outlet cone with a radial gap with the support of its rear end on the surface of the outlet cone, while the fairing mounts are located on the lines passing through the power panels, the thickness and width of each cylindrical panels are respectively 0.4 ... 0.6 and 0.6 ... 0.7 of the thickness and width of the power panel, and the radial and end clearances are 0.0008 ... 0.003 and 0.0004 ... 0.012 projectile caliber, respectively.

The invention is illustrated by drawings, where figure 1 shows a General view of the NURS with open plumage, figure 2 and 3 are local views of the nozzle block in the places of its mounting on the output (figure 2; view A of figure 1) and input (figure .3; view B of Fig. 1) cones, in Fig. 4 is a local view of a nozzle block with a cowl (view In Fig. 1), in Fig. 5 is a local section along the fastening points of the cowl (section G-G of Fig. 4) .

NURS (figure 1) contains a fuse 1, the head part 2, a jet engine of solid fuel 3, a nozzle block 4 of the input 5 and output 6 cones, a fairing 7 installed between the cones 5 and 6, the blades 8, axis 9 and the spring 10.

The fairing 7 (Fig. 1) is made in the form of power rectangular panels 11 with nodes 12 (Fig. 4) for fastening and fixing the blades 8 (Fig. 1), interconnected by cylindrical panels 13 (Fig. 4) with a thickness of δ ( 5), equal to 0.4 ... 0.6 of the thickness δ ₁ (Fig. 5) of the power panels 11 (Fig. 4).

Fairing 7 (Fig. 1) is mounted on the inlet cone 5 with a radial clearance Δ (Fig. 2, 3) equal to 0.0008 ... 0.003 caliber of the projectile and an end clearance Δ ₁ (Fig. 3) equal to 0.0004 ... 0.012 caliber; and on the output cone 6 (FIG. 1) with a radial clearance Δ, with the support of its rear end 14 on the surface 15 (FIG. 2) of the output cone 6.

The attachment points 16 (Fig. 4) of the fairing 7 on the cones 5 and 6 (Fig. 1) are located on the lines D (Fig. 4) passing through the power panels 11 (Fig. 4).

The projectile operates as follows.

Electric voltage through the contacts 17 of the cover 18 and the connecting conductors 19 is transmitted to the igniter 20, which ignites the charge of solid fuel 21 (Fig. 1).

Upon reaching a certain pressure in the engine, the cover 18 (Fig. 1) is reset and gas outflow through the nozzle block 4 (Fig. 1) begins, the engine enters the mode.

When the engine thrust reaches a value equal to the magnitude of the force, the projectile begins to move along the guide. The blades are kept from opening by the walls of the guide.

When leaving the guide, under the action of the springs 10 (Fig. 1), the blades open and are fixed in the fixation nodes 12 (Fig. 4) of the fairing 7 (Fig. 1). NURS begins flight along the trajectory.

Due to the radial Δ (Fig. 2, 3) and the end Δ ₁ (Fig. 3), the gaps between the fairing 7 and the nozzle block 4 (Fig. 1), the vibrations of the blades from the vibrations of the housing that occur during flight are reduced, which ensures their design location in air flow, and flight loads acting on the blades are perceived by the power panels of the fairing, which ensures the local strength of its supporting surfaces.

The proposed design of the NURS allowed to increase the firing range by ~ 10% and increase accuracy by ~ 15%.

Using the proposed invention, design documentation was developed, a batch of shells for flight tests was made.

Currently, flight tests have been carried out, which confirmed the indicated positive effect; production is being prepared for serial production of the proposed NURS.

Claims (1)

An uncontrolled missile containing a fuse, a head part, a solid fuel rocket engine with a nozzle block from the inlet and outlet cones, a cylindrical cowl fastened with them with attachment and fixing units for the blades, a folding blade unit, axles and springs placed on the cowl, characterized in that the fairing is made in the form of power panels connected with each other by cylindrical panels in plan view with the blades fastening and fixing units and mounted on the inlet cone with a radial and end gaps and on the exit cone with a radial clearance with support of its rear end on the surface of the output cone, while the fairing attachment points are located on the lines passing through the power panels, the thickness and width of each cylindrical panel is 0.4 ... 0, respectively 6 and 0.6 ... 0.7 of the thickness and width of the power panel, and the magnitude of the radial and end gaps are 0.0008 ... 0.003 and 0.0004 ... 0.012 caliber shells, respectively.

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