阅读说明：本技术 一种含超音速分离线摆动喷管的固体火箭发动机 (Solid rocket engine containing supersonic separation line swinging spray pipe ) 是由 王革 程靖懿 李德坚 何定鹏 苏成志 周凌 杨海威 关奔 于 2020-11-24 设计创作，主要内容包括：本发明提供一种含超音速分离线摆动喷管的固体火箭发动机,包括点火器、发动机主体和超音速分离线摆动喷管；所述点火器包括点火头、点火头压盖、点火器密封圈、点火头定位部件、点火药筒、点火器与发动机主体连接件；所述点火器与发动机主体连接件通过螺纹与发动机前封头、点火药筒、点火头定位部件连接,点火头压盖通过螺纹与点火头定位部件连接,将点火头压紧定位；本发明点火成功率高、药柱不易撕裂、密封性好、能够进行全轴推力矢量,通过电机伺服机构,使摆动喷管能够全轴摆动,且在分离线扩张比较小和后开口小的情况下实现较大摆动,提高发动机的推力矢量性能。(The invention provides a solid rocket engine containing a supersonic separation line swinging spray pipe, which comprises an igniter, an engine main body and the supersonic separation line swinging spray pipe, wherein the engine main body is provided with a plurality of supersonic separation line swinging spray pipes; the igniter comprises an ignition head, an ignition head gland, an igniter sealing ring, an ignition head positioning part, an ignition cartridge, an igniter and an engine main body connecting piece; the igniter and the engine main body connecting piece are connected with the engine front end socket, the ignition cartridge and the ignition head positioning part through threads, and the ignition head gland is connected with the ignition head positioning part through threads to tightly press and position the ignition head; the invention has high ignition success rate, difficult tearing of the explosive column, good sealing performance and capability of carrying out full-axis thrust vector, the swinging spray pipe can swing in a full-axis manner through the motor servo mechanism, and the swinging spray pipe can realize larger swinging under the conditions of smaller separation line expansion and small rear opening, thereby improving the thrust vector performance of the engine.)

1. A solid rocket engine containing supersonic separation line swinging jet pipes is characterized in that: comprises an igniter, an engine body and a supersonic separation line swinging nozzle.

2. A solid rocket engine incorporating a supersonic separation line oscillating nozzle in accordance with claim 1, wherein: the igniter comprises an ignition head, an ignition head gland, an igniter sealing ring, an ignition head positioning part, an ignition cartridge, an igniter and an engine main body connecting piece; the igniter and the engine body connecting piece are connected with the engine front end socket, the ignition cartridge and the ignition head positioning part through threads, and the ignition head gland is connected with the ignition head positioning part through threads to compress and position the ignition head.

3. A solid rocket engine incorporating a supersonic separation line oscillating nozzle in accordance with claim 2, wherein: the igniter sealing rings are four, the igniter sealing ring I and the igniter sealing ring IV and the igniter sealing ring III are located between the igniter and the engine main body connecting piece and the ignition cartridge, and the igniter sealing ring II is located between the igniter and the engine main body connecting piece and the engine front end socket.

4. A solid rocket engine incorporating a supersonic separation line oscillating nozzle in accordance with claim 1, wherein: the engine main body comprises an engine shell, a front end enclosure, a rear end enclosure, a heat insulation layer, a coating layer and a grain, wherein the front end enclosure and the rear end enclosure are connected with the front and the rear of the engine shell, the heat insulation layer, the coating layer and the grain are arranged in the engine shell from outside to inside, and the front end enclosure and the rear end enclosure are also provided with a debonding sheet and a sealing ring.

5. A solid rocket engine incorporating a supersonic separation line oscillating nozzle in accordance with claim 1, wherein: the supersonic separation line spray pipe is integrally divided into a movable section and a fixed section, and the fixed section of the swing spray pipe is connected with a rear end socket of the engine main body through a flange plate and a bolt; a separation line thermal protection block is arranged near a separation line gap between the movable section and the fixed section and the throat part of the spray pipe, a plurality of sealing rings are arranged in the separation line gap, and 4 symmetrical motor base mounting grooves which are distributed annularly are arranged on the flange plate and used for mounting a motor.

6. A solid rocket engine incorporating a supersonic separation line oscillating nozzle in accordance with claim 5, wherein: the motor on the flange plate is connected with the spherical groove base on the movable section through a connecting rod device to form a servo mechanism of the swinging spray pipe.

7. The solid rocket engine with supersonic separation line oscillating nozzle of claim 5, wherein: the connecting rod device is driven by a motor rotating shaft by adopting a motor driving cylinder.

8. The solid rocket engine with supersonic separation line oscillating nozzle of claim 5, wherein: four servo mechanisms consisting of motors, connecting rods and spherical groove bases are arranged on the fixed section in an annular symmetrical mode, and the movable section of the swinging spray pipe is driven to swing in a full-axis mode.

Technical Field

The invention relates to a solid rocket engine, in particular to a solid rocket engine with a supersonic separation line swinging nozzle, and belongs to the technical field of thrust vectors of solid rocket engines.

Background

The solid rocket engine is a preferred power device of missile weapons of all countries because of the advantages of high reliability, good maintainability, simple structure and the like; meanwhile, the thrust vectoring nozzle can greatly improve the maneuverability of a missile weapon, so that the missile weapon with the thrust vector can have more advantages in confrontation, and the solid rocket engine containing the thrust vectoring nozzle becomes an important direction for the power development of tactical missiles.

A vectoring nozzle in which the boundary between the fixed and movable portions of the supersonic separation line oscillating nozzle is located in the supersonic region of the nozzle. Compared with other thrust vectoring nozzle, the thrust vectoring nozzle has the advantages of simple structure, high deflection efficiency, thrust vectoring deflection angle larger than a geometric swing angle and the like.

Thus, to better exploit the above advantages, the combination of supersonic split-line nozzles with thrust vectoring solid rocket engines is imperative. The traditional thrust vector solid rocket engine nozzle is overstaffed and complex in structure, the overall redundant quality of the engine is increased, and the overall performance and reliability of the engine are reduced; meanwhile, due to low deflection efficiency, a larger geometric pivot angle is often needed to achieve a sufficient vector angle, and compared with an engine with a supersonic separation line spray pipe, the engine needs a larger mechanical motion stroke and longer time to achieve the same vector angle, which is often fatal in the event of a transient battle.

Disclosure of Invention

Aiming at the complete scheme that a supersonic separation line thrust vectoring nozzle solid rocket engine is lacked at present, the invention aims to provide a set of design scheme containing an igniter, a combustion chamber shell, a grain, a supersonic separation line swinging nozzle and a swinging nozzle servo mechanism, and the practical application of the supersonic separation line nozzle on the solid rocket engine is realized. Meanwhile, the engine is high in ignition success rate, the explosive column is not easy to tear, the sealing performance is good, the swinging spray pipe can carry out omnidirectional thrust vector, the spray pipe can swing greatly under the conditions that the separation line expansion is small and the rear opening is small, the limited space in the engine can be effectively saved, and the redundancy quality is reduced.

The purpose of the invention is realized as follows:

a solid rocket engine containing supersonic separation line swinging jet pipes is characterized in that: comprises an igniter, an engine body and a supersonic separation line swinging nozzle;

the igniter comprises an ignition head, an ignition head gland, an igniter sealing ring, an ignition head positioning part, an ignition cartridge, an igniter and an engine main body connecting piece; the igniter and the engine main body connecting piece are connected with the engine front end socket, the ignition cartridge and the ignition head positioning part through threads, and the ignition head gland is connected with the ignition head positioning part through threads to tightly press and position the ignition head;

the number of the igniter sealing rings is four, the first igniter sealing ring and the fourth igniter sealing ring and the third igniter sealing ring are positioned between the igniter and the engine main body connecting piece and the ignition cartridge, and the second igniter sealing ring is positioned between the igniter and the engine main body connecting piece and the engine front end socket;

the engine main body comprises an engine shell, a front end enclosure, a rear end enclosure, a heat insulation layer, a coating layer and a grain, wherein the front end enclosure and the rear end enclosure are connected with the front and the rear of the engine shell, and the heat insulation layer, the coating layer and the grain are arranged in the engine shell from outside to inside;

the supersonic separation line spray pipe is integrally divided into a movable section and a fixed section, and the fixed section of the swing spray pipe is connected with a rear end socket of the engine main body through a flange plate and a bolt; a separation line thermal protection block is arranged near a separation line gap between the movable section and the fixed section and near the throat part of the spray pipe, a plurality of sealing rings are arranged in the separation line gap, and 4 symmetrical motor base mounting grooves which are distributed annularly are arranged on the flange plate and used for mounting a motor;

the motor on the flange plate is connected with the spherical groove base on the movable section through a connecting rod device to form a servo mechanism of the swinging spray pipe;

a motor driving cylinder is adopted, and a motor rotating shaft is used for driving the connecting rod device;

four servo mechanisms consisting of motors, connecting rods and spherical groove bases are arranged on the fixed section in an annular symmetrical mode, and the movable section of the swinging spray pipe is driven to swing in a full-axis mode.

Compared with the prior art, the invention has the beneficial effects that:

the invention provides a complete scheme of a solid rocket engine with a sound velocity separation line swinging spray pipe, so that the solid rocket engine has full-axis thrust vector capacity, the maneuvering capacity of a missile weapon where the solid rocket engine is positioned is greatly improved, and the combat efficiency is obviously improved.

1. The ignition wire in the ignition head is directly connected with the ignition powder with higher ignition success rate, and the ignition powder ignites the ignition powder, so that the ignition success rate is effectively improved.

2. The explosive column in the engine main body is connected with the inner wall of the heat insulating layer of the cylinder body at the front and rear end sockets by the artificial debonding sheet, so that the explosive column tearing phenomenon caused by stress concentration at the front and rear ends of the explosive column in the high-speed flying process of the engine can be effectively prevented.

3. The inner wall part of the swinging spray pipe is made of high-temperature-resistant and ablation-resistant materials, so that the manufacturing cost of the spray pipe is reduced, and the molded surface of the inner wall surface of the spray pipe is effectively protected from being damaged by high-temperature and high-speed gas scouring when an engine works.

4. The supersonic speed separating line nozzle is adopted as the swinging nozzle, the separating line and the swinging movable part of the nozzle are arranged at the expansion section of the nozzle, the shock wave generated by the airflow passing through the step at the gap of the separating line generates larger deflection, and a larger thrust vector angle can be provided under the condition that the swinging geometric angle of the nozzle is smaller.

5. The spray pipe adopts four sets of motors, connecting rods and spherical groove base servo mechanisms which are circumferentially and uniformly distributed, so that the swinging spray pipe can swing in a full axis manner, and thrust vector capacity in any direction is provided.

6. The motor of swing spray tube is connected with the spray tube fixed section, does not move along with the swing of spray tube, can effectively reduce the wiring degree of difficulty of motor.

7. In the past, hydraulic devices are often used as servos to drive the movable section of the nozzle to oscillate. The invention uses the motor to replace the traditional actuating cylinder and the hydraulic system thereof, and compared with the traditional actuating cylinder, the invention can effectively reduce the space of the servo mechanism in the engine and reduce the redundant mass.

Drawings

FIG. 1 is an isometric view of a solid rocket engine incorporating a supersonic parting line pendulum nozzle of the present invention;

FIG. 2 is an overall semi-sectional view of a solid rocket engine incorporating a supersonic split-line pendulum nozzle of the present invention;

FIG. 3 is an isometric view of an ignition device of a solid rocket engine incorporating a supersonic parting line pendulum nozzle of the present invention;

FIG. 4 is a semi-sectional view of an ignition device of a solid rocket engine incorporating a supersonic split-line swinging nozzle of the present invention;

FIG. 5 is an isometric view of a swing nozzle of a solid rocket engine incorporating a supersonic parting line swing nozzle of the present invention;

FIG. 6 is a semi-sectional view of a swing nozzle of a solid rocket engine incorporating a supersonic split-line swing nozzle of the present invention;

FIG. 7 is an isometric view of a body portion of a solid rocket engine incorporating a supersonic parting line pendulum nozzle of the present invention;

FIG. 8 is an enlarged fragmentary view of the main body of a solid rocket engine incorporating a supersonic split-line oscillating nozzle in accordance with the present invention.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.

A solid rocket engine with supersonic separation line swinging jet pipes comprises an igniter, an engine main body, the supersonic separation line swinging jet pipes and a solid rocket engine design scheme of a swinging jet pipe servo mechanism. The igniter comprises an ignition head, an igniter sealing ring for isolating the engine combustion chamber from the outside, a powder charging barrel for charging ignition powder and ignition powder, an igniter positioning part for fixing the ignition head and other parts. The engine main body comprises an engine shell, a front end socket, a rear end socket, a heat insulation layer, a manual de-sticking sheet and a solid propellant grain, wherein the front end socket and the rear end socket are connected with the shell. The supersonic separation line spray pipe is integrally divided into a movable section and a fixed section, and the fixed section of the swing spray pipe is connected with the rear end enclosure through a flange plate and a bolt; a thermal protection part is added near the separation line gap between the movable section and the fixed section and the throat part of the spray pipe, and a high-temperature resistant and ablation resistant material is adopted; a plurality of sealing rings are adopted in the separation line gaps to isolate fuel gas; in addition, 4 symmetrical motor base installation grooves which are distributed annularly are arranged on the flange plate and used for installing the motor. The motor on the flange plate is connected with the spherical groove base on the movable section through a connecting rod device to form a servo mechanism of the swinging spray pipe. A plurality of thermal protection components are added beside the throat part and the separation line of the fixed section of the swinging spray pipe, and the inner molded surface of the spray pipe is formed by adopting high-temperature-resistant and ablation-resistant materials and the main component of the spray pipe. And a plurality of sealing rings are adopted to insulate the movable section near the separation line gap. The linkage is driven by the motor rotating shaft, rather than by a hydraulic ram. Four servo mechanisms consisting of motors, connecting rods and spherical groove bases are arranged on the fixed section in an annular symmetrical mode, and the movable section of the swinging spray pipe is driven to swing in a full-axis mode.

The object of the invention is achieved in that: the integral rocket engine comprises an igniter, a combustion chamber shell, a grain, a supersonic separation line swinging spray pipe and a swinging spray pipe servo mechanism, wherein the igniter comprises an ignition head, an igniter sealing ring for isolating the combustion chamber of the engine from the outside, an ignition powder charging cartridge for charging ignition powder, a fixed point ignition head and igniter positioning parts of other parts; the engine main body comprises a cylinder body, a front end socket, a rear end socket, a heat insulation layer, an artificial debonding layer and a solid propellant, wherein the front end socket and the rear end socket are connected with the cylinder body; the spray pipe is integrally divided into a movable section and a fixed section, and the fixed section of the swinging spray pipe is connected with the rear seal head through a flange plate and a bolt; three heat-radiating components are added at the main body of the spray pipe near the separation line gap between the movable section and the fixed section and the throat part of the spray pipe, and the heat-radiating components are made of high-temperature-resistant and ablation-resistant materials; in the separation line gap, a plurality of sealing rings are adopted in the movable section part to isolate fuel gas; in addition, 4 symmetrical motor base installation grooves which are distributed annularly are arranged on the flange plate and used for installing a motor, and a servo mechanism consisting of four motors, connecting rods and a spherical groove base can drive the movable section of the swinging spray pipe to swing in a full-axis mode.

The invention also includes such structural features:

1. the ignition head of the igniter adopts an electric ignition device, and an ignition wire is directly connected with ignition powder in an ignition powder cartridge through a hollow inner cavity of the ignition head.

2. Ignition powder cartridge case passes through the screw thread and is connected with some firearm fixed part, and the direct and ignition powder direct contact of the priming charge of ignition powder cartridge is through the direct ignition of priming charge.

3. The inner surface of the cylinder is attached with a heat insulating layer to prevent the combustion of the explosive column in the engine main body from damaging the cylinder structure.

4. The explosive columns in the engine cylinder body are connected with the front and rear seal heads of the engine main body through artificial de-sticking pieces.

5. The front and the rear seal heads are in threaded connection with the cylinder body.

6. The spray pipe is connected with the rear end socket of the engine main body by a flange plate.

7. The connecting rod swinging devices are four sets in total, and comprise four motors, connecting rods and spherical groove parts which are circumferentially and uniformly distributed, so that a servo mechanism of the swinging spray pipe is formed together.

Referring to fig. 1 and 2, the invention provides a solid rocket engine comprising a supersonic separation line swinging nozzle, which comprises an ignition device, an engine body and the supersonic separation line swinging nozzle. FIG. 1 shows the overall appearance of an engine; FIGS. 2(a), (b) show a half-sectional view of the entire engine, in which FIG. 2(b)2-1 is an igniter, 2-2 is an engine body, and 2-3 is a supersonic split-line oscillating nozzle.

Referring to fig. 3 and 4, fig. 3 shows a specific structure of an engine ignition device.

Fig. 4 is a half sectional view of an engine ignition device, 4-1 is an ignition head gland, 4-2 is an ignition head positioning part, 4-3 is an igniter seal ring I, 4-4 is an igniter seal ring II, 4-5 is an igniter and engine body connecting piece, 4-6 is an igniter seal ring III, 4-7 is an ignition cartridge, 4-8 is an ignition charge column and a primer, 4-9 is an igniter seal ring IV, and 4-10 is an ignition head.

4-10 ignition head connects ignition lead with ignition powder and ignition powder column directly through its cavity, after electrifying, ignition lead directly ignites ignition powder loaded in 4-7 ignition powder cartridge, then ignition point 4-8 ignition powder column and ignition powder, start engine. The 4-3 igniter sealing ring I, the 4-9 igniter sealing ring IV and the 4-6 igniter sealing ring III prevent 4-8 ignition powder columns in the 4-7 ignition powder cartridge and fuel gas generated by ignition powder from overflowing from the front end and are positioned between the 4-5 igniter and engine main body connecting piece and the 4-7 ignition powder cartridge; the 4-5 igniter and the engine main body connecting piece are connected with the 4-7 ignition cartridge, the engine front end socket and the 4-2 ignition head positioning part through threads, and the 4-4 igniter sealing ring II is positioned between the 4-5 igniter and the engine main body connecting piece and the engine front end socket to isolate fuel gas in the engine; the 4-1 ignition head gland is connected with the 4-2 ignition head positioning part through threads to tightly press and position the 4-10 ignition head.

With reference to fig. 5 and 6, fig. 5 shows an isometric view of the oscillating nozzle, in which 1 is a servo mechanism consisting of a motor-connecting rod-ball groove distributed uniformly in a circumferential direction.

FIG. 6 is a half-sectional view of the swing nozzle, 6-1 is a main body part of a contraction section of the swing nozzle, 6-2 is a rear head, 6-3 is a seal ring of an engine main body and the swing nozzle, 6-4 is a nozzle rear head connecting piece, 6-5 is a motor, 6-6 is a connecting rod connected with the motor, 6-7 is a connecting rod device connecting pin, 6-8 is a spherical connecting rod, 6-9 is a spherical groove base, 6-10 is a movable section sealing and swinging part, 6-11 is a nozzle expansion section main body, 6-12 is a nozzle expansion section profile part, 6-13 is a separation line thermal protection block III, 6-14 is a separation line sealing ring group, 6-15 is a nozzle fixed section spherical part, 6-16 is a separation line thermal protection block II, and 6-17 is a separation line thermal protection block I.

The main body component of the contraction section of the 6-1 swinging nozzle is a base body of the contraction section and the fixed part of the swinging nozzle, two heat protection blocks 6-16 separation line heat protection blocks II and 6-17 separation line heat protection blocks are directly bonded on the main body component, and the two heat protection blocks are made of high-temperature-resistant and ablation-resistant tungsten copper infiltration materials and play a role in protecting the inner wall surface of the nozzle from being flushed by high-temperature gas; the 6-4 spray pipe rear end socket connecting piece is connected with the 6-2 rear end socket through a bolt, the swing spray pipe is fixed on the engine main body, and the 6-3 engine main body and a swing spray pipe sealing ring prevent hot gas in the engine main body from overflowing from a gap between the connection; the 6-15 spray pipe fixed section spherical part is a main part for keeping the 6-10 movable section sealing and swinging part motion track and positioning of the fixed section; the main body of the expansion section of the 6-11 spray pipe is connected with the 6-10 movable section seal and swing part through screw threads, and then is connected with the profile part of the expansion section of the 6-12 spray pipe through screw threads, and the thermal protection block III at the separation line of 6-13 is bonded to form the movable section of the spray pipe, wherein the thermal protection block 3 at the separation line of 6-13, the main body of the expansion section of the 6-11 spray pipe and the profile part of the expansion section of the 6-12 spray pipe jointly form an inner profile of the expansion section of the spray pipe, and the thermal protection block III at the separation line of 6-13 is made of high-temperature and ablation resistant tungsten copper-infiltrated material, so that the wall surface near the separation line is protected from; the sealing ring group at the 6-14 separation line isolates high-temperature and high-pressure fuel gas in the separation line, and the fuel gas in the spray pipe is prevented from seeping out.

The 6-9 spherical groove base is connected with the 6-10 movable section seal and swing part through bolts, 4 sets of 6-7 connecting rods and 6-8 spherical connecting rod devices are directly driven to rotate by 4 circularly and uniformly distributed 6-5 motors, and a servo mechanism of the swing spray pipe is formed; meanwhile, the 6-8 spherical connecting rods are connected with 4 annular 6-9 spherical groove bases which are uniformly distributed, so that the movable section at the rear part of the spray pipe is driven to move;

referring to fig. 7 and 8, fig. 7 shows the overall structure of the engine main body portion.

FIG. 8 shows the detailed construction of the front, rear and casing of the engine body in three parts A, B, C: 8-1 is front part explosive column de-sticking piece, 8-2 is front end enclosure, 8-3 is heat insulation layer, 8-4 is coating layer, 8-5 is engine shell, 8-6 is explosive column, 8-7 is rear end enclosure, 8-8 is rear part explosive column de-sticking piece, 8-9 is rear end enclosure and shell sealing ring, 8-10 is front end enclosure and shell sealing ring.

The 8-2 front end socket, the 8-5 engine shell and the 8-7 rear end socket jointly form the appearance of an engine main body, wherein the 8-2 front end socket and the 8-7 rear end socket simultaneously play a role in connecting with other engine components; in the process of high-speed movement of an engine, the 8-6 explosive column is directly bonded with the 8-2 front end socket and the 8-7 rear end socket, so that the 8-6 explosive column is torn due to stress concentration, and therefore the 8-1 front explosive column debonding piece and the 8-8 rear explosive column debonding piece play a role in reducing stress concentration and protecting the 8-6 explosive column structure; the 8-4 coating layer can prevent the 8-6 grains from burning on the surface which is not supposed to burn; the 8-9 rear end socket and the shell sealing ring play a role in sealing between the 8-7 rear end socket and the 8-5 engine shell, so that gas in the engine is prevented from leaking; the 8-10 front end socket and the shell sealing ring play a role in sealing between the 8-2 front end socket and the 8-5 engine shell, and gas in the engine is prevented from leaking.

In summary, the following steps: the invention provides a design scheme of a solid rocket engine with a supersonic separation line swinging nozzle, and the rocket engine has the advantages of high ignition success rate, difficult tearing of explosive columns, good sealing performance, capability of carrying out full-axis thrust vector and the like.

The invention provides a design scheme of a solid rocket engine comprising an igniter, a combustion chamber shell, a grain, a supersonic separation line swinging nozzle and a swinging nozzle servo mechanism. The ignition powder is ignited by using the ignition powder in the igniter, so that the ignition success rate is improved; a thermal protection layer is arranged in the shell to protect the shell from erosion of high-temperature gas; the manual de-sticking piece can effectively protect the structure of the explosive column; the sealing performance of the engine shell and the spray pipe is effectively ensured through the design of a plurality of sealing rings; high-temperature-resistant and ablation-resistant materials are adopted at the throat part and the separation line of the spray pipe to protect the molded surface of the spray pipe; through the motor servo mechanism, the swinging spray pipe can swing in a full-axis mode, large swinging is achieved under the conditions that the expansion of a separation line is small and a rear opening is small, and the thrust vector performance of the engine is improved.