RU2100760C1 - Nozzle assembly - Google Patents

Abstract

FIELD: rocketry, in particular, nozzle assemblies with a jet projectile flight stabilizing device, can find a jet projectile flight stabilizing device, can find a wide application in development of new prototype jet projectiles, mainly rocket projectiles. SUBSTANCE: the known nozzle assembly has the nose and tail cones located in the free space bent fins with locking surfaces, torsion - compression springs, axles and a fairing. Each blade of the fins, in the root section, is furnished with local bosses with locking surfaces, and the tail cone of the nozzle assembly is furnished with bosses with mating locking surfaces; the locking surfaces of the bosses, for instance the tail ones, are parallel to the assembly longitudinal axis, and the nose surfaces are positioned at an angle to the assembly longitudinal axis; in the folded position the blades are located with a partial overlapping of each other, and the concave surface of each blade is made in a radius, whose center lies on intersection of the perpendiculars constructed from the center of two straight lines connecting in pairs the reference points of this surface in the cross-section of the blade in the folded position, and the fairing is made in the form of several plates bent in an arc of circumference, secured between the blades. EFFECT: improved design. 3 dwg

Description

 The invention relates to the field of rocketry, and more specifically, to nozzle blocks with a device for stabilizing the flight of rockets (RS) and can be widely used in the development of new models of RS, mainly uncontrollable.

 As is known, in order to successfully defeat targets in flight, the RS should not deviate from the calculated flight path, and random disturbances (gust of wind, local drop in air density, etc.) should not cause the RS to leave the trajectory with an ever-increasing deviation from the original direction flight that is, the RS must be stabilized on the trajectory, and its flight must be stable.

 It should be noted that the RS will be stable on the trajectory only if the center of pressure (the point of application of all aerodynamic forces) is shifted back to the tail and lies behind its center of gravity, while the distance between these points determines the degree of stability.

 To shift the RS pressure center back, stabilizers are placed in the tail region, which are thin plates (blades) protruding beyond the caliber of the projectile.

 Known RS, (Vinitsky AM Solid propellant rocket engines. M. Engineering 1973, s, 13 and 14) to stabilize the flight which uses a blade stabilizer located on the nozzle block of the engine. The nozzle block consists of a nozzle, stabilizer and fairing.

 The stabilizer consists of blades fixedly mounted on the fairing, which in turn is rigidly mounted on the nozzle. The blades significantly favor the caliber of the PC.

 The considered stabilizer is simple in design, provides the necessary stability of the PC, is highly technological.

 It is known that when placing several RSs on a launcher (launcher), the distance between them should ensure the free launch of any of the RSs, while neighboring RSs should not interfere with the movement of the RS along the PU guide during its launch.

 Given the above, the placement on the control panel of the required number of PCs with the described stabilizer, which protrudes significantly over the caliber, significantly increases the dimensions and mass of the control panel, and when the overall dimensions and mass characteristics of the control panel are limited, the number of control panels placed on the control panel decreases, which is a significant drawback of the described nozzle block design with stabilizer.

 Thus, the objective of this technical solution was to develop a nozzle block with a stabilizing device, simple in design and high-tech, but not providing the maximum density of the PC placement on the control panel.

 The common features with the nozzle block proposed by the authors are the blades and the fairing.

 The optimal design of the nozzle block that meets the requirements for the maximum density of PC placement on the launcher would be the block design with the plumage folding into the caliber of the projectile, which allowed launching from tubular guides.

 The closest in technical essence and the achieved technical effect is the nozzle block described in (Combat vehicle 9P138. Technical description and instruction manual. M. Voenizdat, 1986, part 3, book 1, p. 15-21), accepted by the authors for the prototype.

 The nozzle block contains a front and rear cone, a cylindrical thin-walled fairing with grooves and bends, which is installed in the free volume between the cones, four rigid curved feathering blades freely rotating on the axes installed in the bends of the breeder and torsion-compression springs mounted on the axes in the grooves fairing.

 The blades are thin plates, curved along the radius of the baker and in the closed position completely enclose its outer surface without any overlap of one blade of the other.

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

The disadvantages of the known block are:
the implementation of the plumage blades along the radius of the fairing does not allow partial overlap of one blade of the other to increase their span to increase the plumage efficiency at elevated speeds associated with increasing firing range;
the use of limited sections of the end face of the root part of the blade as locking surfaces significantly increases the stress in these areas from the action of aerodynamic forces on the blade and does not ensure the strength of the blade when they increase, for example, with an increase in flight speed to increase the firing range;
the use of separate, adjacent to the grooves, sections of the breeder as reciprocal locking surfaces does not provide local strength of the fairing with increasing aerodynamic loads acting on the blade.

 All this leads to low efficiency and stability of the stabilizer as a whole and does not allow the use of this technical solution in long-range RS with high flight speeds.

 Thus, the objective of this technical solution (prototype) was to develop a nozzle block that provides the maximum density of the RS in the launcher and can only be used in shells with low technical characteristics.

 When the PC leaves the guide vane, mounted on the nozzle block, under the action of the springs, they open and move backward along the axes until the local recesses are jammed on the end surface of the blade with the end of the groove in the cowl.

 Aerodynamic loads acting in flight on the blades are perceived by the surfaces of the recesses and sections of their ends, abutting the recesses and transmitted by them to the fairing.

 Common features with the nozzle block proposed by the authors are the presence of front and rear cones, fairings, rigid curved blades with locking surfaces, axes and torsion-compression springs.

 Unlike the prototype, in the proposed nozzle block, each of the plumage blades in its root part is provided with local tides with locking surfaces, and the rear cone of the nozzle block is equipped with protrusions with mating locking surfaces, while the locking surfaces of the tides, for example, rear, are parallel to the longitudinal axis of the block, and the front at an angle to the longitudinal axis of the block, while the blades in the closed position are partially overlapped relative to each other, and the concave surface of each of the blades is Nena radially, whose center lies on the intersection of the perpendiculars drawn from the middle of two lines connecting pairwise the characteristic points of this surface in the cross section of the blade in the closed position and the fairing is in the form of several curved along a circular arc plates secured between the blades.

 This will allow us to conclude that there is a causal relationship between the totality of the essential features of the proposed technical solution and the achieved technical results.

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

 The objective of the proposed technical solution is to create a nozzle block design with an increased range of plumage and operable at high aerodynamic loads, characteristic of long-range RS.

 The execution of the blades along a different radius than in the prototype, allows to partially overlap one blade of the other and increases the range of plumage while maintaining the same dimensions of the folded plumage, which is very important.

 The implementation of the blades and the rear cone with local tides and locking surfaces on them allows you to sharply increase their area and reduce stress in these areas from the action of aerodynamic forces, which allows you to increase the load perceived without destruction by these surfaces, while the mass of the structure practically does not increase.

 The implementation of one of the supporting surfaces on the blades and the counter surface on the cone at an angle to the longitudinal axis of the block allows to obtain a clearance-free "blade-cone" connection, which reduces random disturbances associated with backlash in this connection.

 The performance of the fairing in the form of plates bent along an arc of a circle and fixed between the blades allows you to maximize the diametrical dimensions of the cavity between the cones to accommodate the tides of the cone without reducing the free volume for the placement of the blades.

 The essence of the invention lies in the fact that the nozzle block containing the front and rear cones, placed in a free volume between the outer surfaces of the cones, has a rigid, curved plumage with locking surfaces, torsion-compression springs, axes and fairing, in contrast to the prototype, according to the invention, each of the blades the plumage is provided with local tides with locking surfaces, and the rear cone of the nozzle block is equipped with protrusions with mating locking surfaces, while the locking surfaces of the tides, such as the rear e, made parallel to the longitudinal axis of the block, and the front at an angle to the longitudinal axis of the block, while the blades in the closed position are partially overlapped relative to each other, and the concave surface of each of the blades is made along a radius whose center lies at the intersection of perpendiculars drawn from the midpoints of two straight lines pairwise connecting the characteristic points of this surface on the cross section of the blade in the closed position, and the fairing is made in the form of several plates bent along an arc of a circle, fixed between the blades.

 In FIG. 1 shows a longitudinal section of a nozzle block with folded blades, FIG. 2 is a longitudinal section through a nozzle block with open blades; FIG. 3 is a diagram for determining centers of bending radii of two adjacent blades. The centers of the bending radii of the two blades are defined similarly.

 The nozzle block (Fig. 1) contains the front 1 and rear 2 cones, a rigid, blade-like plumage 3, axles 4, compression-torsion springs 5 and fairing 6 located between them.

 In the root part 7 (figure 2) of each blade, local tides 9 and 10 are made with locking surfaces 11 and 12.

On the rear cone 2 (Fig. 1) there are made local protrusions 13 and 14 with mating locking surfaces 15 and 16. The locking surfaces 16 of the rear protrusions 14 are parallel to the longitudinal axis of the block, and the locking surfaces 15 of the front protrusions 13 are at an angle of 9-11 ^o to the longitudinal block axis.

The locking surface 11 (Fig. 2) of the blades 8 is made at an angle of 6-8 ^o to the longitudinal axis of the block, and the locking surface 12 parallel to the longitudinal axis of the block.

 The axis 4 (Fig. 1) is installed in the holes of the protrusions 13 and 14 of the rear cone 2. On the axles 4 with the possibility of their free rotation are installed blades 8 (Fig. 2); springs 5 (Fig. 1) are mounted on axes 4 between the rear end face of the protrusion 13 and the rear tide 10 (Fig. 2) of the blade 8. In this case, one of the ends of the spring 5 (Fig. 1) abuts against the surface of the rear cone 2, and the other the inner surface of the blade 8 (Fig. 2), Fairing 6 (Fig. 1 and 2), is installed between the blades 8 (Fig. 2) and is made in the form of four plates curved in an arc of a circle, which are mounted on the annular thickenings 17, 18 of the front 1 and rear 2 (Fig. 1) cones, respectively. From the opening of the blade holds the ring 19 (Fig. 1).

In the diagram (Fig. 3) is indicated:
⌀ _shell diameter of the PC;
⌀ _fairing outer diameter of the fairing;
α the angle of overlap of one blade of the other;
I, II cross sections of adjacent blades;
segments 1-2 and 2-3 are straight, connecting the characteristic points of the concave surface of the blade;
segments ac and bc are perpendicular, drawn from the middle of segments 1-2 and 2-3;
point with the center of the radius of the inner surface;
point o the center of rotation of the blade when opening;
R _{l - the} radius of the bend of the inner surface of the blade.

As characteristic points of the inner surface of the blade used:
1 point corresponding to the upper end of the blade, which overlaps the previous blade;
2 point lying on the upper end of the blade;
3 point lying on the axis connecting the center of symmetry of the block with the center of rotation of the blade at opening.

The determination of the position of the center of the bend of the blade and the value of the radius of the bend is as follows:
knowing the necessary range of plumage find the value of the angle a of the overlap of one blade of the other;
based on the diameter of the PC on a certain scale build a circle corresponding to the diameter of the PC;
on this circle, the overlap angles a of one blade of the other are noted;
on the segments connecting the points of the angles a lying on a circle with its center, mark points 1 and 2 lying at a distance of 2d and d, respectively, to the center of the circle (d blade thickness);
determine the turning points of the blade at its opening and connect these points with the center of the circle; on these segments mark points 3 lying at a distance d to the center of the circle;
segments are drawn through points 1-2 and 2-3, from the middle of which the perpendiculars ac and bc are lowered, respectively;
point c (the point of intersection of the perpendiculars) is the center of the radius of the bend of the blade, and the distance from this point for any characteristic point (1, 2 and 3) will determine the radius.

 The operation of the unit is as follows.

 When an electric pulse is applied to the electric igniter of a rocket engine, the latter is triggered and ignites the charge of solid fuel. The outflow of gas through the nozzle begins. When the engine enters the mode, the PC overcomes the force of the locking device PU and begins to move along the guide pipe PU. Ring 19 (Fig. 1) is discharged by the rear end of the pipe and the blades are kept from opening by the walls of the pipe PU.

 When exiting the pipe, the blades 8 (Fig. 2) under the action of the springs 5 (Fig. 1), turning on the axes 4, open and move back until the locking surfaces 10 are jammed by the mating locking surfaces 15 (Fig. 1), made on the protrusions 13 of the rear cone 2.

 Aerodynamic loads acting on the blade during the flight of the RS are perceived by the locking surfaces 11 and 12 of the blade (Fig. 2) and transmitted to the mating locking surfaces 15 and 16 (Fig. 1) made on local tides 13 and 14 of the rear cone 2 (Fig. 1) .

 The RS starts flying along the trajectory.

 According to the alleged invention, design documentation was developed (Fig. Inv. N I-2405, I-2431), according to which prototypes of nozzle blocks are currently manufactured.

 Their tests confirmed the unit's operability under conditions of increased loads characteristic of long-range RS.

The test results (report N 19-232 from 12/27/95) showed that, compared with the prototype:
the breaking load increased by 4-5 times, while the safety factor was 2.5-3;
plumage range increased by 25%
the mass of the nozzle block remained unchanged.

 According to the test results, the proposed design was recognized as promising and an experimental batch of RS is being manufactured using the proposed design for acceptance tests and further serial production with the prospect of export deliveries.

Claims (1)

 A nozzle block containing front and rear cones, placed in a free volume between the outer surfaces of the cones, rigid curved plumage with locking surfaces, torsion-compression springs, axes and fairing, characterized in that each of the plumage blades in its root part is provided with local tides with locking surfaces, and the rear cone of the nozzle block is provided with protrusions with mating locking surfaces, while the locking surface of the tides, for example, the rear, are made parallel to the longitudinal axis block, and the front ones at an angle to the longitudinal axis of the block, while the blades in the closed position are partially overlapped relative to each other, and the concave surface of each of the blades is made along a radius, the center of which lies at the intersection of perpendiculars drawn from the middle of two straight lines connecting in pairs the characteristic points of this surface on the cross section of the blade in the closed position, and the fairing is made in the form of several plates bent along an arc of a circle, fixed between the blades.

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