RU2542650C2 - Rocket engine nozzle and its expansion gear - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry and can be used in production of rocket engine with expansion nozzle. Rocket engine nozzle comprises bell and folding adapter composed by tabs articulated with said bell by expander for changing of tabs from folded position to working position. Folded tab generatrix drawn through the plane of tab mirror plane is parallel with bell generatrix drawn through the same plane. Another invention of the set relates to rocket engine expansion gear including elements of articulation of tabs with nozzle bell that make the pantographs interconnecting the adjacent tabs. Every pantograph comprises lengthwise beam connected with each of two adjacent tabs by two articulated plates while every tab is connected with bell by guide elements.

EFFECT: simplified design of nozzle and its drive, decreased weight, higher reliability.

3 cl, 11 dwg

Description

The invention relates to rocket technology and can be used to create a rocket engine with a sliding nozzle.

It is known that an increase in the specific impulse of thrust due to the high degree of expansion of the nozzle with limited dimensions of the rocket and rocket engine is realized through the use of a nozzle with telescopic sliding nozzles and a mechanism for their expansion [Fakhrutdinov I.Kh., Kotelnikov A.V. Design and Design of Solid Fuel Rocket Engines: A Textbook for Engineering Universities. - M.: Mechanical Engineering, 1987. - 328 s: ill., Page 142, Fig. 6.14]. This design is used in the presence of free volume between the nozzle cut of the nozzle and the bottom of the rocket engine. In the indicated free volume there are sliding telescopic nozzles and a mechanism for their sliding. The design under consideration is not applicable in the absence (deficit) of free volume before the nozzle nozzle cut (or when this volume is occupied by any rocket engine units).

The closest in technical essence and the achieved positive effect to the proposed invention is the flap nozzle and the mechanism of its expansion [Fakhrutdinov I.Kh., Kotelnikov A.V. Design and Design of Solid Fuel Rocket Engines: A Textbook for Engineering Universities. - M .: Mechanical Engineering, 1987. - 328 s: ill., Page 145, Fig. 6.20]. The nozzle of the rocket engine contains a bell and a folding nozzle formed by petals kinematically connected with the bell by a sliding mechanism, providing the transfer of the petals from the folded position to the working one. The folded position of the petals may be their vertical (radial) location, which requires a minimum free volume before cutting the nozzle socket. The disadvantages of this design are:

- the relatively large dimensions of the nozzle in the folded position, as a result of which there is a need for free volume before cutting the nozzle nozzle when folding the petals by turning forward (by almost 180 °), or free space in the radial direction (increasing the missile’s midship) when folding the petals is turned vertically ( radial) position (90 °). The large dimensions of the nozzle in the folded position are also due to the fact that the curvature of the rotary lobes is directed in the opposite direction relative to the curvature of adjacent elements (for example, the bottom of the previous stage, the shell of the interstage compartment),

- a large number of petals, leading both to structural complexity of the design, and to a large number of joints between the petals, which also reduces the reliability of the nozzle during operation. A large (8 or more) number of rotary petals is explained by the fact that the curvature of the petals increases the size of the folded nozzle (the more petals, the less curvature (the ratio of the deflection of the cross section to its chord) of one petal),

- the complexity of the sliding mechanism containing a synchronization system for turning the petals, the complexity of the sliding mechanism leads to its low reliability,

- a large mass of the structure, due to the complexity of the design of the sliding mechanism and the nozzle and a large number of petals, each of which contains a node for attaching the petal to the sliding mechanism.

The technical task of the present invention is to simplify the design of the nozzle and its sliding mechanism, reducing the mass of the structure, increasing its reliability, reducing the size of the nozzle in the folded position.

The essence of the invention “rocket engine nozzle” is that in the nozzle of a rocket engine containing a bell and a folding nozzle formed by petals kinematically connected with the bell by a sliding mechanism, providing the transfer of the petals from the folded position to the working, forming the petal in the folded position, drawn through the plane of its symmetry, parallel to the generatrix of the bell, drawn through the same plane.

The essence of the invention, “the mechanism for extending the nozzle of the rocket engine” is that in the mechanism for extending the nozzle of the rocket engine according to the previous paragraph, containing elements of the kinematic connection of the petals with the bell of the nozzle of the rocket engine, the elements of the kinematic connection of the petals with the bell form pantographs connecting adjacent petals to each other . Each pantograph contains a longitudinal beam connected to each of two adjacent petals by two pivotally fixed strips. Each petal is connected with a bell by guide elements. A rod located perpendicular to the longitudinal axis of the nozzle can be installed in adjacent petals with the possibility of longitudinal movement, and a rod mounted with the possibility of longitudinal movement in the glass and forming a piston cavity with which the squib is connected can be connected with the rod. The glass may form a longitudinal beam.

The technical result in the nozzle of a rocket engine is achieved by the fact that when the generatrix of the lobe is parallel in the folded position, drawn through its symmetry plane, which forms the socket drawn through the same plane, the folded position of the petals is formed by a plane-parallel movement in the radial-axial direction of each petal relative to its working position. The configuration of the folded position of the petal, in which any face is parallel to the same face of the petal in its working position, provides both the kinematic simplicity of folding the nozzle and its compactness. The kinematic simplicity of folding is due to the fact that for folding - sliding, plane-parallel movement of the petals is used - the simplest type of movement in nature. At the same time, folding is ensured at the same time due to the fact that when the petals radially move upward due to the curvature of the bottom of the previous stage, the free space for the petal increases towards this bottom. With the radial-axial movement of the petals up and down, the indicated free space for the petal becomes even greater. Thus, the proposed layout of the folded nozzle (equal to the degree of expansion) is provided in such radial and axial dimensions that it is impossible to accommodate either a telescopically movable nozzle or a rotary lobe. When moving the petals of the proposed design, their adjacent longitudinal edges move towards each other, and the end edges move “in passing” (with a small approximation due to the parallelism of the edge to the direction of movement) relative to the edges of the socket. This ensures reliable mating of the edges of the petals in the working position. The number of petals required for the proposed fold, the curvature of which is directed in the same direction with adjacent elements (for example, the bottom of the previous stage, the shell of the interstage compartment), is minimal (the nozzle with rotary petals contains 8 or more petals due to the curvature of the petals (depending on their quantities) increases the dimensions of the folded nozzle). The minimum number of petals not only structurally simplifies the design, but also reduces the number of joints between the petals, which increases the reliability of the design. The kinematic simplicity of folding the nozzle creates the prerequisites for simplifying the mechanism of sliding the nozzle.

The technical result in the mechanism of sliding the nozzle of the rocket engine is achieved both by the simplest (plane-parallel) nature of the movement of the petals for their folding - sliding, and by the fact that in the sliding mechanism of the sliding system of the petals and the synchronization system of their movement are combined into a single unit. The sliding drive is also included in the same assembly. Plane-parallel movement of the petals relative to each other is provided by pantographs containing a longitudinal beam connected to each of two adjacent petals by two pivotally fixed strips. When the distance between the petals connected by pantographs to the ring system changes, the radial position of each petal automatically changes. The axial position of each petal when changing its radial position is governed by guiding elements connecting each petal with a bell. The inclusion of the power drive in the sliding mechanism is achieved by the fact that a rod located perpendicular to the longitudinal axis of the nozzle is mounted with the possibility of longitudinal movement in adjacent petals, and a power drive is connected to the rod. The power drive forms a rod, mounted with the possibility of longitudinal movement in the glass and forming a piston cavity with the glass, with which the squib is connected. The combination of the glass with the longitudinal beam simplifies the design and reduces its weight.

This technical solution is not known from the patent and technical literature.

The invention is illustrated by the following graphic material:

figure 1 shows a side view of the nozzle in the folded position;

figure 2 shows the leader And figure 1 in the form of a longitudinal section of the nozzle in the folded position;

figure 3 shows a rear view of the nozzle (on its slice) in the folded position;

figure 4 shows the nozzle in the folded position in the plane of the guide element (the lower half of the figure without cutouts, the upper half is a longitudinal section of the nozzle BB of Fig.3);

figure 5 shows the nozzle in the folded position in isometric view (front-side view);

figure 6 shows the nozzle in the folded position in isometric view (rear-side view);

7 shows a side view of the nozzle in the operating position;

on Fig shows the leader In Fig.7 in the form of a longitudinal section of the nozzle in the working position;

figure 9 shows the nozzle in the working position in the plane of the guide element (the lower half of the figure without cuts, the upper half is a longitudinal section of the nozzle BB of Fig.3 (taking into account the working position));

figure 10 shows the nozzle in the working position in isometric view (front-side view);

figure 11 shows the nozzle in the working position in isometric view (rear-side view).

The nozzle of the rocket engine contains a bell 1 and a folding nozzle formed by the petals 2 (figure 1). The petals 2 are kinematically connected with the bell 1 by a sliding mechanism, providing the transfer of the petals 2 from the folded position L to the working position N (figure 2). Generating Y of the petal 2 (Fig. 4) in the folded position L, drawn through the plane Z of its symmetry (Fig. 3), parallel to the generatrix F of the socket 1 (Fig. 4), drawn through the same plane Z (Fig. 3). In Fig.2, the operating position of the N petals 2 is shown by a dashed line intersecting the bottom 3 of the previous stage, shown by a thin line. The folded position L of the petals 2 does not intersect either the bottom 3 of the previous stage, nor the units 4 of the rocket engine. The folded position L of the petals 2 is formed by a plane-parallel movement in the radial-axial direction of each petal 2 relative to its working position N. The petals 2 contain longitudinal edges 5 and end edges 6. The longitudinal edges 5 in any position of the petals 2 are parallel to each other.

The mechanism for extending the nozzle of a rocket engine according to the previous paragraph contains elements of the kinematic connection of the petals 2 with the bell 1. Elements of the kinematic connection of the petals 2 with the bell 1 form pantographs 7 connecting adjacent petals 2 to each other. Each pantograph 7 contains a longitudinal beam 8 connected to each of two adjacent petals 2 by two pivotally fixed strips 9. The strips 9 are mounted on the longitudinal beam 8 by means of beam hinges 10 and are connected to the petals 2 by means of petal hinges 11. The indicated design of the pantographs 7 ensures that that in any position, the petals 2 are parallel to each other, i.e. determines the plane - parallel nature of the possible movement of the petals 2, causing a change in their radial position. The axial position of each petal 2 when changing its radial position is regulated by the guiding elements 12, connecting each petal 2 with the bell 1. The simplest guiding element 12 is a rod along which the eye 13 can slide, rigidly connected to the petal 2. The guiding elements 12 are located in the plane of symmetry Z petals 2 (figure 4). In adjacent petals 2 can be installed with the possibility of longitudinal movement of the rod 14 located perpendicular to the longitudinal axis of the nozzle. The rod 14 not only provides centering of the adjacent petals 2 relative to each other, but also is an emphasis for the power drive sliding. The sliding actuator is made in the form of a rod 15 connected with the rod 14 and mounted with the possibility of longitudinal movement in the glass 16. The rod 15 forms a piston cavity 17 with the glass 16, with which the squib 18 is connected. In order to simplify the design and reduce its weight, the glass 16 can form longitudinal beam 8 (to be combined with it).

The device operates as follows. In the folded position L of the petals 2, the ring formed by the petals 2 and pantographs 7 with the fixed radial position of the petals 2 by means of the pantographs 7 is held and centered relative to the socket 1 by the guide elements 12. In the folded position L, the petals 2 are located between the units 4 of the rocket engine and the bottom 3 of the previous one steps (moreover, the bell 1 practically abuts against the bottom 3). After separation of the bottom 3 of the previous stage, the petals 2 are transferred to the operating position N by applying an electric impulse to the squib 18. In the sub-piston cavity 17 pressure arises that acts on the rod 15 and the glass 16, pushing them apart. When the rod 15 rests on the rod 14, the cup 16 and, accordingly, the longitudinal beam 8 are pushed forward. Moving the longitudinal beam 8 forward relative to the petals 2 causes a synchronous rotation of the strips 9. With the synchronous rotation of the strips 9 there is a mutual approach of the petals 2. The mutual approach of the petals 2 leads to compression (reduction of the radius) of the ring formed by the petals 2 and pantographs 7, i.e. to the centripetal radial movement of the petals 2. In the process of centripetal radial movement of the petals 2 along the guide elements 12 (rods), the eyes 13 slide, each of which is rigidly connected to its petal 2. This regulates the axial position of each petal 2 when changing its radial position in the process centripetal radial movement of the petals 2. As a result of the radial-axial movement of the petals 2, their longitudinal edges 5 are joined together, and the end edges 6 of the prima ayut to the funnel 1, ensuring the tightness of the nozzle in the working position N, the pitch 2 as the working position N. Petals 2 are fixed relative to each other known mechanisms, for example, collet latch. Next, a rocket engine is launched, and the nozzle works as a unit.

Feasibility study of the present invention, in comparison with the prototype, which selected the petal nozzle and the mechanism of its expansion [Fakhrutdinov I.Kh., Kotelnikov A.V. Design and Design of Solid Fuel Rocket Engines: A Textbook for Engineering Universities. - M .: Mechanical Engineering, 1987. - 328 s: ill., Page 145, Fig. 6.20], consists in simplifying the design of the nozzle and its sliding mechanism, reducing the mass of the structure, increasing its reliability, reducing the size of the nozzle in the folded position.

Claims (3)

1. The nozzle of a rocket engine containing a bell and collapsible nozzles formed by petals kinematically connected to the bell by a sliding mechanism, providing the transfer of the petals from the folded position to the working one, characterized in that the generatrix of the petal in the folded position, drawn through its plane of symmetry, is parallel to the generatrix of the bell drawn through the same plane. 2. The mechanism for extending the nozzle of a rocket engine according to claim 1, containing elements of the kinematic connection of the petals with the bell of the nozzle of the rocket engine, characterized in that the elements of the kinematic connection of the petals with the bell form pantographs connecting adjacent petals to each other, each pantograph containing a longitudinal beam, connected to each of two adjacent petals by two pivotally fixed strips, and each petal is connected with a bell by guide elements. 3. The sliding mechanism of the nozzle of a rocket engine according to claim 2, characterized in that a rod located perpendicular to the longitudinal axis of the nozzle is mounted in adjacent petals, and a rod mounted with the possibility of longitudinal movement in the glass and forming a piston with the glass is connected to the rod the cavity with which the squib is connected, and the glass forms a longitudinal beam.

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