CN113606056A - Heat-proof tail cabin structure of rocket engine - Google Patents
Heat-proof tail cabin structure of rocket engine Download PDFInfo
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- CN113606056A CN113606056A CN202111098213.9A CN202111098213A CN113606056A CN 113606056 A CN113606056 A CN 113606056A CN 202111098213 A CN202111098213 A CN 202111098213A CN 113606056 A CN113606056 A CN 113606056A
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- fire
- ring
- packing
- tail
- heat
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Thermal Insulation (AREA)
Abstract
The invention provides a rocket engine heat-proof tail cabin structure which comprises a tail cabin body, wherein an assembling hole for assembling an engine spray pipe is formed in the tail cabin body, a pressing ring is arranged on the tail cabin body corresponding to the assembling hole, one side, facing the center of the assembling hole, of the pressing ring is provided with a joint part for filling a gap between the engine spray pipe and the tail cabin body, the other side of the pressing ring is arranged on the tail cabin body, heat-proof rings are arranged on the tail cabin body corresponding to the periphery of the assembling hole, fire-blocking rings are arranged on the heat-proof rings corresponding to the pressing ring, a filling gap is formed between the fire-blocking rings and the joint part of the pressing ring, and a filler assembly is arranged in the filling gap. The invention provides a rocket engine heat-proof tail cabin structure which has good fireproof and heat-proof performance, can effectively prevent tail flame of a rocket engine spray pipe from influencing equipment in an engine tail cabin, ensures that the tail cabin can keep continuous and stable operation, and is beneficial to improving the overall safety and reliability of a rocket.
Description
Technical Field
The invention belongs to the field of rocket tail cabins, and particularly relates to a heat-proof tail cabin structure of a rocket engine.
Background
The rocket body structure is an important component of the rocket and has the function of connecting various subsystems on the rocket, such as an effective load, a control system, a power system, a measuring system and the like into a whole, providing a reliable working environment for the subsystems, bearing external force in ground operation and flight, maintaining a good aerodynamic shape and keeping the integrity of the rocket. The rocket body structure generally comprises a payload fairing, a propellant storage box, a conveying system element, an instrument cabin, a stage section, an engine frame, a tail cabin and the like, wherein the tail cabin is used as an important component of the rocket, a control surface control mechanism is generally integrated inside the tail cabin, and the control mechanism has certain requirements on the working environment, so that the fire prevention and heat protection of the tail cabin in the operation process are very important, and particularly the tail flame of an engine nozzle needs to be prevented from entering or influencing the tail cabin. The existing tail cabin structure is generally provided with a heat-proof layer structure corresponding to one side of an engine spray pipe, but the joint of the engine spray pipe and the tail cabin body is lack of an effective fireproof sealing structure, the single fireproof sealing structure is greatly influenced by temperature change, the reliability of the single fireproof sealing structure in the running process of the tail cabin is poor, the tail flame is very easy to enter or influence the tail cabin through the joint of the engine spray pipe and the tail cabin body, the tail cabin is damaged or the temperature is increased, and the stability of the tail cabin in the running process is greatly influenced.
Disclosure of Invention
In view of the above, the present invention is directed to a heat-proof tail tank structure of a rocket engine, so as to solve the fire and heat protection problem of the tail tank during operation.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the utility model provides a rocket engine heat protection tail cabin structure, includes the tail cabin body, is equipped with the pilot hole that is used for assembling the engine spray tube on the tail cabin body, the position that corresponds the pilot hole on the tail cabin body is equipped with the clamping ring, and the clamping ring is equipped with the laminating portion that is used for filling engine spray tube and tail cabin body junction clearance towards one side at pilot hole center, and the opposite side sets up on the tail cabin body, it is equipped with heat proof ring to correspond pilot hole position all around on the tail cabin body, and the position that corresponds the clamping ring on the heat proof ring is equipped with the fender fire ring, has the packing clearance between fender fire ring and the clamping ring laminating portion, is equipped with the filler subassembly that can extend laminating portion volume in the packing clearance.
Further, be equipped with the filling groove with filling clearance intercommunication in the laminating portion, laminating portion corresponds one side of filling groove open-ended and sets up towards keeping off the fire ring, and the opposite side is equipped with the bending of the laminating portion deformation laminating engine nozzle of being convenient for.
Further, the packing assembly comprises fireproof packing, one end of the fireproof packing is provided with a bending part matched with the filling groove, the other end of the fireproof packing is provided with a filling part matched with the filling gap, a protruding part is arranged at the position, extending out of the filling gap, of the fireproof packing, and the protruding part corresponds to the joint of the attaching part and the engine spray pipe.
Furthermore, an assembly groove matched with the compression ring is arranged on the tail cabin body corresponding to the compression ring, the assembly groove is communicated with the assembly hole, one end, extending into the assembly groove, of the fire blocking ring abuts against the compression ring, and a protruding portion used for limiting the fireproof filler is arranged at the other end of the fire blocking ring; the bellying corresponds laminating portion and sets up, is equipped with the constant head tank with the cooperation of fire prevention filler protruding portion on the bellying.
Furthermore, the position of the fire-blocking ring corresponding to the filling groove of the attaching part is provided with a pressing part, and one end of the pressing part extending into the filling groove presses the fireproof filler towards the center of the assembling hole.
Furthermore, the packing component further comprises a fireproof packing used for filling the fireproof packing gap in the packing groove, one end of the fireproof packing props against the bending part of the fireproof packing, and the other end of the fireproof packing props against the fire blocking ring.
Furthermore, the position of the fire-proof ring corresponding to the periphery of the fire-proof ring is provided with a fire-proof cover, the position of the tail cabin body corresponding to the fire-proof cover is provided with a supporting block for installing the fire-proof cover, the heat-proof ring is provided with a through hole for the supporting block to pass through, and a heat-insulating cavity is arranged in the supporting block.
Furthermore, keep off the fire ring salient in heat protection ring surface, the one side towards the pilot hole on the fire prevention cover is equipped with the bulge that is used for sheltering from fire prevention cover and keeps off the fire ring clearance, has thermal-insulated clearance between the position that corresponds the bulge on the fire prevention cover and the supporting shoe.
Furthermore, the fireproof covers and the supporting blocks are C-shaped structural members, the tail cabin body is correspondingly provided with two fireproof covers, the two fireproof covers form an annular structure outside the fire blocking ring, and a heat dissipation gap exists between the end parts of the two fireproof covers.
Compared with the prior art, the heat-proof tail cabin structure of the rocket engine has the following advantages:
the invention provides a thermal-protection tail cabin structure of a rocket engine, which has good fireproof and thermal-protection performance, can effectively prevent tail flame of a nozzle of the rocket engine from influencing equipment in the tail cabin of the rocket engine, ensures that the tail cabin can keep continuous and stable operation, and is beneficial to improving the overall safety and reliability of the rocket; the compression ring is arranged on the tail cabin body, so that a gap between the tail cabin body and the engine spray pipe can be effectively sealed, and after the bonding part on the compression ring is combined with the packing assembly, the fireproof sealing performance at the bonding part of the compression ring can be ensured, tail flames are prevented from entering the tail cabin body, and the fireproof performance of the tail cabin body is improved; through setting up fire prevention heat-proof structure such as heat-proof ring and fire prevention cover on the tail cabin body, can realize the thermal-insulated protection to the tail cabin body, avoid heat conduction to this internally of tail cabin, ensure that the heat of engine spray tube tail flame can not destroy tail cabin body internal plant, improved this kind of holistic fire prevention heat resistance in tail cabin.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic structural view of a rocket engine heat-proof tail capsule structure according to an embodiment of the present invention;
FIG. 2 is an exploded view of a rocket engine heat shielding tail capsule structure according to an embodiment of the present invention;
FIG. 3 is a schematic structural view of a heat-shielding ring on a tail capsule body in a rocket engine heat-shielding tail capsule structure according to an embodiment of the present invention;
FIG. 4 is a rear view of FIG. 3;
FIG. 5 is a schematic view of the structure in the direction A-A in FIG. 3;
FIG. 6 is a schematic structural view of a joint of a compression ring and a fire blocking ring in a rocket engine heat-proof tail cabin structure according to an embodiment of the invention;
FIG. 7 is an enlarged view of a portion of FIG. 6 at B;
FIG. 8 is a schematic structural view of a rocket engine thermal runaway tail capsule structure with an engine nozzle mounted on a tail capsule body according to an embodiment of the invention.
Description of reference numerals:
1. a tail capsule body; 2. a heat-proof ring; 3. a fire-blocking ring; 4. a fire-proof cover; 5. a boss portion; 6. pressing a ring; 7. a bonding section; 8. a protrusion; 9. a support block; 10. a thermally insulating cavity; 11. assembling a groove; 12. an assembly hole; 13. a heat shield; 14. an engine nozzle; 15. filling the groove; 16. a fire-resistant filler; 17. positioning a groove; 18. a refractory filler; 19. a pressing part; 20. accommodating grooves; 21. a projection; 22. a filling section; 21. a bending section; 22. the gas rudder avoids the groove.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The utility model provides a rocket engine heat protection tail cabin structure, as shown in fig. 1 to 8, including tail cabin body 1, be equipped with the pilot hole 12 that is used for assembling engine spray tube 14 on the tail cabin body 1, it is equipped with clamping ring 6 to correspond the position on the pilot hole 12 body on the tail cabin body 1, one side that clamping ring 6 is towards pilot hole 12 center is equipped with the laminating portion 7 that is used for filling engine spray tube 14 and tail cabin body 1 junction clearance, the opposite side sets up on tail cabin body 1, it is equipped with heat protection ring 2 to correspond pilot hole 12 position all around on the tail cabin body 1, heat protection ring 2, clamping ring 6, and the coaxial setting of pilot hole 12, the position that corresponds clamping ring 6 on heat protection ring 2 is equipped with fire blocking ring 3, there is the packing clearance between fire blocking ring 3 and the 6 laminating portion 7 of clamping ring, be equipped with the packing assembly in the packing clearance.
When the engine nozzle 14 is assembled, after the engine nozzle 14 is inserted into the assembling hole 12, the press ring 6 can be sleeved on the engine nozzle 14, and the press ring 6 can be installed and fixed on the tail cabin body 1 through screws, so that the press ring 6 can block a gap at the joint of the engine nozzle 14 and the tail cabin body 1, the tail flame of the engine nozzle 14 is prevented from flowing back into the tail cabin body 1, the equipment in the tail cabin body 1 is prevented from being damaged, and the safety and the reliability of the tail cabin structure in the operation process are improved; after the compression ring 6 is installed, the heat-proof ring 2 can be installed again, the fire-blocking ring 3 on the heat-proof ring 2 is pressed against the compression ring 6, the compression ring 6 is further fixed, the heat-proof ring 2 and the fire-blocking ring 3 can be integrally formed with the heat-proof ring 2 on the screw tail cabin body 1, and the heat-proof ring 2 and the fire-blocking ring 3 are fixed on the tail cabin body 1.
A filling groove 15 communicated with the filling gap can be formed in the attaching part 7, one side, corresponding to the opening of the filling groove 15, of the attaching part 7 faces the fire blocking ring 3, and the other side of the attaching part 7 is provided with a bend facilitating the attaching part 7 to deform and attach to the engine spray pipe 14; laminating portion 7 can increase the area of contact between clamping ring 6 and the engine spray tube 14, be favorable to improving the leakproofness of clamping ring 6 and the 14 junctions of engine spray tube, through set up filling groove 15 on laminating portion 7, and set up filler assembly in filling groove 15, filler assembly not only can play thermal-insulated effect, avoid the heat to transmit to tail-room body 1 from engine spray tube 14, and through setting up filler assembly, can also fill filling groove 15 of laminating portion 7, enlarge the sectional area of laminating portion 7, make one side of laminating portion 7 can be inseparabler and the laminating of 14 outer walls of engine spray tube, under filler assembly's the tight effect in packing top, can effectively solve clamping ring 6 thermal deformation and cause the problem that sealing performance descends, be favorable to improving the fire prevention sealing performance of laminating portion 7 and 14 junctions of engine spray tube.
Optionally, the whole attaching portion 7 is of a U-shaped structure, and the bending can be V-shaped or arc-shaped, so that the attaching portion 7 has better deformation performance due to the V-shaped or arc-shaped bending, and the attaching portion 7 can deform adaptively along with the diameter of the engine nozzle 14, which is beneficial to improving the sealing performance of the compression ring 6; after the V-shaped or arc-shaped bend is further bent, the V-shaped or arc-shaped bend also has larger reset elasticity, and can support one side of the attaching part 7 to be attached to the engine spray pipe 14 more tightly; through set up the flexible construction of bending (laminating portion 7 promptly) that the deformation of laminating portion 7 was laminated engine spray tube 14 of being convenient for on clamping ring 6 for laminating portion 7 can take place certain deformation along with engine spray tube 14, and can keep laminating sealed with engine spray tube 14 all the time in the deformation process laminating portion 7.
The packing assembly comprises fireproof packing 16 capable of expanding under heat so as to fill the filling groove 15 and ensure that the compression ring 6 is stably attached to the engine spray pipe; one end of the fireproof filler 16 is provided with a bending part 21 matched with the filling groove 15, the other end of the fireproof filler 16 is provided with a filling part 22 matched with the filling gap, a protruding part 8 is arranged at the position of the fireproof filler 16 extending out of the filling gap, and the protruding part 8 is arranged corresponding to the connection position of the tail cabin body 1 and the engine nozzle; the position that corresponds clamping ring 6 on the tail cabin body 1 is equipped with clamping ring 6 complex assembly groove 11, assembly groove 11 and pilot hole 12 intercommunication, and the one end that keeps off fire ring 3 and stretch into assembly groove 11 withstands clamping ring 6, and the other end is equipped with the bellying 5 that is used for spacing fire prevention to pack 16.
Optionally, the fireproof filler 16 may be an asbestos rope, which has good heat insulation and fireproof performance and can expand to a certain extent after being heated to fill and expand the joint part 7; the bending part 21 arranged on the fireproof filler 16 can extend into the filling groove 15 and fill the filling groove 15 to a certain degree, so that the fireproof sealing effect is achieved; the fireproof filler 16 filled in the filling groove 15 can also expand the joint portion 7 to a certain extent, so that the sectional area of the joint portion 7 is increased, and the sealing performance of the joint portion 7 and the engine nozzle 14 is further improved.
One horizontal sealing section, kink 21 can be to filling and extend laminating portion 7 promptly to press ring 6 to laminating portion 7 department plays good fire prevention sealing effect, avoids the tail flame to damage press ring 6 through fire prevention packing 16, can prevent effectively that the tail flame from getting into in the tail cabin body 1 through press ring 6 and tail cabin body 1 junction.
A vertical line seal section, filling portion 22 then can be used for the shutoff to fill the clearance promptly, and then realizes sealed the fire prevention in clearance between ring 3 and the laminating portion 7 of keeping off the fire, avoids the tail flame to get into clamping ring 6 or tail cabin body 1 through filling the clearance in, can play the effect of isolated tail flame jointly with kink 21, and the tail flame that the subtend clamping ring 6 removed plays the effect of two-stage isolation.
The other transverse sealing section, namely the protruding part 8, can extend the fireproof packing 16, so that the fireproof packing 16 can extend to shield the joint of the joint part 7 and the engine spray pipe 14 and the joint of the end part of the compression ring 6 and the fire blocking ring 3, and further fireproof shielding effect is achieved on the two positions, so that tail flames are prevented from entering a filling gap, and the compression ring 6 is prevented from being damaged or entering the tail cabin body 1 through the gap between the compression ring 6 and the engine spray pipe 14; because laminating portion 7 can be sealed with the laminating of engine spray tube 14 under the filler subassembly expands the effect, consequently further through the fire prevention filler 16 to carry out the fire prevention to laminating portion 7 and engine spray tube 14 laminating department and shelter from, can form multiple protection to tail cabin body 1, avoid the tail flame to get into and damage tail cabin body 1.
Keep off and can set up bellying 5 on the fire ring 3, bellying 5 can correspond laminating portion 7 and set up, and bellying 5 can set up and pack 16 protruding 8 complex constant head tank 17 with the fire prevention towards one side of clamping ring 6, and the opposite side can set up the gas vane and dodge groove 22, and gas vane dodges groove 22 can be for with gas vane complex notch cuttype groove, can effectively prevent that the engine jet from ablating the gas vane pivot. Through set up the bellying 5 that is used for spacing 16 protruding portions 8 of fire prevention packing on keeping off fire ring 3, 16 protruding portions 8 of fire prevention packing are withstood through compressing tightly to bellying 5, can compress tightly protruding portion 8 and fix the tip at engine spray tube 14 and clamping ring 6, improve the fire prevention and the thermal-insulated effect of 16 protruding portions 8 of fire prevention packing to the clearance between clamping ring 6 and the engine spray tube 14.
Optionally, the locating slot 17 can adopt the dovetail, after the fire prevention filler 16 inserts the dovetail, under the effect of compressing tightly of bellying 5, can promote the deformation of fire prevention filler 16 tip or diffusion, make the fire prevention filler 16 tip can fill the dovetail, in order to realize the fire prevention to fire prevention filler 16 and bellying 5 junction sealed, avoid the tail flame to get into from fire prevention filler 16 and bellying 5 junction and fill the clearance and damage clamping ring 6, consequently, utilize the protruding portion 8 and the cooperation of the bellying 5 of fire prevention filler 16, also can realize the protection to clamping ring 6, three-section structure on the fire prevention filler 16 all can play good fire prevention separation effect to clamping ring 6, avoid the tail flame to get into tail cabin body 1 through clamping ring 6 and tail cabin body 1 junction.
Through set up constant head tank 17 on bellying 5, can realize the spacing fixed to 16 protruding portions 8 of fire prevention filler, prevent that 16 protruding portions 8 of fire prevention filler from taking place to remove, bellying 5 can compress tightly fire prevention filler 16 and fix on clamping ring 6 surface through propping against 16 protruding portions 8 of fire prevention filler, improves the fire prevention sealed effect of 16 to the contact department of clamping ring 6 and engine spray pipe 14 of fire prevention filler.
Optionally, one side of the boss 5 facing the center of the fire-blocking ring 3 may also be provided with an inclined surface in smooth transition with the side surface of the fireproof packing 16, and the inclined surface may guide the tail flame to be ejected towards the axial direction of the assembly hole 12 through the boss 5, so that the influence of the boss 5 on the airflow ejected from the engine nozzle 14 may be reduced, the occurrence of turbulence is prevented, and meanwhile, most of the tail flame may be far away from the connection between the fireproof packing 16 and the boss 5, thereby reducing the possibility of the tail flame entering the tail cabin body 1; after the fireproof packing 16 is inserted into the dovetail groove, under the pressing and guiding action of the inner wall of one side of the dovetail groove, the fireproof packing 16 can be pushed to be more tightly attached to the boss 5, so that smooth transition between the surface of the fireproof packing 16 and the inclined surface of the boss 5 is realized, and the condition that the jet air flow cannot enter a gap between the boss 5 and the fireproof packing 16 is ensured.
A pressing part 19 can be further arranged on the position, corresponding to the filling groove 15 of the attaching part 7, of the fire-blocking ring 3, and one end, extending into the filling groove 15, of the pressing part 19 presses the fireproof packing 16 towards the center of the assembling hole 12; one side at 19 orientation pilot hole 12 centers of portion that compresses tightly can set up the inclined plane that is used for promoting fire prevention filler 16, compresses tightly clamping ring 6 along with keeping off fire ring 3, and portion 19 that compresses tightly also can last deeply to fill groove 15 to promote the laminating of fire prevention filler 16 and the 15 inner walls in filling groove, realize the fire prevention sealed, be favorable to improving the fire prevention effect that 16 kink 21 departments of fire prevention filler were packed.
Optionally, the packing assembly further comprises a fire-resistant packing 18 filled in the gap of the fire-resistant packing 16 in the filling groove 15, one end of the fire-resistant packing 18 abuts against the bending part 21 of the fire-resistant packing 16, and the other end abuts against the fire-stopping ring 3; the fireproof filler 18 can be used for filling gaps between the fireproof filler 16 and the pressure ring 6 and between the fireproof filler 16 and the fire-blocking ring 3, so that the fireproof filler 16 is pushed to better fill and expand the joint part 7, and meanwhile, the fireproof sealing effect of the fireproof filler 16 is improved; through setting up fire-resistant filler 18, operating personnel can fill as required when the assembly, is favorable to reducing the degree of difficulty that fire prevention packed 16 assembled, improves fire prevention packed 16 in the operation of tail-room your reliability.
Optionally, the whole pressing portion 19 is of an annular structure, the cross section of the pressing portion 19 can be of a conical structure or an arc structure, the pressing portion 19 can be matched with the fireproof filler 18 for use, the pressing portion 19 can further compress and reduce gaps between the fireproof filler 16 and each component by pressing the fireproof filler 18 downwards, and meanwhile, gaps between the fireproof filler 18 and each component can also be reduced, so that the fireproof filler 18 and the fireproof filler 16 can be attached to the attaching portion 7 more tightly, and a fireproof sealing effect is achieved; for example, when the pressing portion 19 is of a conical structure, the fire-resistant packing 18 may be disposed inside and outside the pressing portion 19 and between the pressing portion 19 and the attaching portion 7, along with the pressing portion 19 extending into the filling groove 15, the pressing portion 19 may push the fire-resistant packing 18 outside thereof to abut against the fire-resistant packing 16, and the pressing portion 19 may push the fire-resistant packing 18 below thereof to press the fire-resistant packing 16 downward, so that the fire-resistant packing 16 may be subjected to downward acting force toward the center of the assembling hole 12 to limit the fire-resistant packing 16, and when the fire-resistant packing 16 is prevented from moving, a gap between the fire-resistant packing 16 and the attaching portion 7 may be further eliminated.
Optionally, the fireproof filler 18 is arranged on one side of the fireproof filler 16 far away from the engine nozzle 14, so that the fireproof filler 16 can effectively block the tail flame and prevent the tail flame from directly burning the fireproof filler 18, the influence of the tail flame on the fireproof filler 18 is small, and the fireproof material mainly has the function of isolating heat; therefore, the fire-resistant filler 18 can also be made of a thermal expansion type fire-resistant material, such as a thermal expansion ceramic fiber or an expansion rope, which has the thermal expansion performance, and the thermal expansion type fire-resistant material has the characteristics of high temperature resistance, heat insulation, sealing, large expansion coefficient and the like, and can expand to a certain extent after being heated, and by adopting the thermal expansion type fire-resistant material, the fire-resistant filler 18 can expand to a certain extent after being heated by the heat of the tail flame of the engine nozzle 14, so that the gap can be further filled and sealed, the limit effect of the fire-resistant filler 18 on the fire-resistant filler 16 is improved, and the fire-resistant filler 16 can always play a stable fire-resistant sealing effect in the operation process of the tail cabin.
However, in the actual use process of the tail cabin, due to the influence of multiple factors such as the heat of the engine nozzle 14 and the air flow vibration of the tail cabin, the compression action of the fire-blocking ring 3 on the fireproof filler 16 may be slightly loosened, even the body of the fireproof filler 16 may be deformed due to the heat caused by the quality problem, etc., so that the overall fireproof sealing performance of the fireproof filler 16 may be problematic, meanwhile, due to the compression action of the fireproof filler 18 on the fireproof filler 16, the fireproof filler 16 may be kept in a tight state to achieve the optimal fireproof sealing effect, but any slight change of the fireproof filler 16 (the compression force of the fire-blocking ring 3 is loosened or the fireproof filler 16 is deformed) may cause the sealing performance of the filling portion 22 of the fireproof filler 16 to be reduced, the filling portion 22 of the fireproof filler 16 may slightly leak, so that the overall fireproof sealing effect of the fireproof filler 16 is affected, therefore, a structure is preferably arranged at the filling portion 22 of the fireproof filler 16, the multi-point compression and fixation of the fireproof packing 16 are realized, so that the fireproof sealing effect of the fireproof packing 16 is further improved.
In an optional embodiment, the fire-blocking ring 3 may also be provided with a fire-resistant filler 18 at a position corresponding to the filling gap, the fire-resistant filler 18 may also be made of a thermal expansion type fire-resistant material, the fire-blocking ring 3 may be provided with an accommodating groove 20 for assembling the fire-resistant filler 18, one side of an opening of the accommodating groove 20 is disposed toward the filling gap and is communicated with the filling gap, and the cross section of the opening of the accommodating groove 20 may be of a horn-shaped structure, so that after the thermal expansion type fire-resistant material is heated, the opening of the accommodating groove 20 of the horn-shaped structure may guide the thermal expansion type fire-resistant material to directionally expand and expand, so that the thermal expansion type fire-resistant material can further compress and fix the filling portion 22 of the fire-resistant filler 16 after being heated, thereby ensuring fire-resistant sealing at the filling portion 22 of the fire-resistant filler 16; the fireproof packing 16 can be restrained by the fireproof packing 18 in the accommodating groove 20 and the fireproof material in the filling groove 15, and even if the fire-stopping ring 3 is slightly loosened, the fireproof packing 16 can be well restrained.
Through setting up multiple structure on ring 3 keeps off the fire, and set up fire-resistant filler 18 in packing groove 15 and holding tank 20, can realize filling 16 by outer fixed in proper order and compressing tightly to interior to the fire prevention, make 16 whole pressing ring 6 of pressing close to all the time of fire prevention filler, ensure that 16 plays the fire prevention sealed effect to clamping ring 6 of fire prevention filler, even keep off fire ring 3 and become flexible, 16 deformation of fire prevention filler even, can not lead to 16 leakproofness of fire prevention filler to descend yet, can effectively avoid in tail flame damage crushing or the tail cabin body 1 of getting into through clamping ring 6, ensure the safety of tail cabin body 1.
The fire-proof cover 4 can be arranged on the heat-proof ring 2 corresponding to the position around the fire-proof ring 3, the supporting block 9 for installing the fire-proof cover 4 is arranged on the tail cabin body 1 corresponding to the position of the fire-proof cover 4, the heat-proof ring 2 is provided with a through hole for the supporting block 9 to pass through, and the supporting block 9 is internally provided with a heat-insulating cavity 10; the fireproof cover 4 and the supporting block 9 can be fixedly arranged on the tail cabin body 1 through screws, and mounting holes for mounting the screws can be formed in the fireproof cover 4 and the supporting block 9; the supporting shoe 9 and the fire-proof cover 4 can limit the tail flame sprayed out by the engine nozzle 14 together, and the tail flame is prevented from moving to the outer side of the tail cabin body 1, so that the all-round fire prevention and heat prevention of the tail cabin body 1 are realized.
The assembly of supporting shoe 9 can be convenient for to the through-hole that sets up on heat-proof ring 2, through with supporting shoe 9 direct assembly on tail-room body 1, is favorable to improving supporting shoe 9 and the stability of fire prevention cover 4 on tail-room body 1, and heat-proof ring 2 can also realize heat-proof ring 2's spacing through-hole and supporting shoe 9 cooperation in addition, is favorable to improving the stability of multiple heat-proof structure on tail-room body 1.
The fire-blocking ring 3 can protrude out of the surface of the heat-proof ring 2, one side of the fire-proof cover 4 facing the assembly hole 12 is provided with a convex part 21 for shielding the gap between the fire-proof cover 4 and the fire-blocking ring 3, and a heat insulation gap is formed between the position of the fire-proof cover 4 corresponding to the convex part 21 and the supporting block 9; the heat insulation gap can be matched with the heat insulation cavity 10, so that the fire protection cover 4 and the supporting block 9 form more heat insulation layer structures, and the overall heat insulation effect of the fire protection cover 4 and the supporting block 9 is further improved; wherein the fire prevention cover 4 can effectively avoid the tail flame to damage supporting shoe 9, and the bulge 21 on the fire prevention cover 4 can cooperate with fender fire ring 3, realizes fire prevention cover 4 and the smooth transition between fender fire ring 3, avoids the tail flame to get into the clearance between fire prevention cover 4 and the fender fire ring 3, reduces the thermal-insulated pressure of clamping ring 6 department, is favorable to reducing the holistic temperature of clamping ring 6, improves the stability of the 6 department's of clamping ring fire packing 16.
Optionally, the fire-proof covers 4 and the supporting blocks 9 can be C-shaped structural members, two fire-proof covers 4 are correspondingly arranged on the tail cabin body 1, the two fire-proof covers 4 form an annular structure outside the fire-blocking ring 3, and a heat dissipation gap exists between the end parts of the two fire-proof covers 4; the C-shaped fireproof cover 4 can be better attached to the fire-blocking ring 3, and the possibility that tail flames enter a gap between the fireproof cover 4 and the fire-blocking ring 3 is further reduced; the heat dissipation clearance is favorable to cold air to get into the tail flame, forms the air current that flows in heat dissipation clearance department, plays certain cooling action to heat protection ring 2 and fire prevention cover 4, and 4 tip of fire prevention cover of two C types can form the structure of similar laval spray tube, and the speed on cold air process heat protection ring 2 surfaces is favorable to reducing heat protection ring 2's temperature with higher speed.
Optionally, the heat-proof ring 2 may also be fixed on the tail cabin body 1 by screws, a thread groove for mounting the screws is provided on the tail cabin body 1, a heat insulation cover 13 may be provided at a position corresponding to the thread groove in the tail cabin body 1, and the heat insulation cover 13 is provided corresponding to the heat dissipation gap; the heat shield 13 can play a good heat insulation role for the heat-proof ring 2 at the position of the heat dissipation gap, and avoid the conduction of redundant heat to the tail cabin body 1 through the heat-proof ring 2, and the heat shield 13 can also play a good heat insulation role for the tail cabin body 1 at the position of the thread groove.
A specific assembly method of such a tail tank structure can be referred to as follows:
an operator can assemble the fireproof filler 16 on the attaching portion 7 of the pressing ring 6, and uses the fireproof filler 18 to fill a gap between the fireproof filler 16 and the attaching portion 7, and at the moment, the fireproof filler 16 can be bent by using a tool, so that the fireproof filler 16 is bent into a Z shape, and after the fireproof filler 16 is bent, the fireproof filler 16 can be shaped by using a shaping tool, so that the fireproof filler 16 is prevented from deforming in the subsequent component assembling process, and the subsequent component assembling is facilitated.
Then, the compression ring 6 can be assembled on the heat-proof ring 2, the fire-proof ring 3 on the heat-proof ring 2 is matched with the joint part 7 of the compression ring 6, the limit fixation of the fire-proof filler 16 is realized, the fire-proof filler 16 is convenient to play a fire-proof sealing role, and the fire-proof filler 18 can be assembled in the fire-proof ring 3 accommodating groove 20 before the compression ring 6 is assembled; wherein, when pressing ring 6 when assembling on keeping off fire ring 3, can align to insert constant head tank 17 with protruding portion 8 on the fire prevention packs 16, realize the spacing back to fire prevention packs 16, can demolish the forming tool.
And finally, the supporting block 9 and the fireproof cover 4 can be sequentially assembled on the heat-proof ring 2, and the finally assembled structure is installed and fixed on the tail cabin body 1, so that the operation is simple and convenient.
The invention provides a thermal-protection tail cabin structure of a rocket engine, which has good fireproof and thermal-protection performance, can effectively prevent tail flame of a nozzle of the rocket engine from influencing equipment in the tail cabin of the rocket engine, ensures that the tail cabin can keep continuous and stable operation, and is beneficial to improving the overall safety and reliability of the rocket; the compression ring is arranged on the tail cabin body, so that a gap between the tail cabin body and the engine spray pipe can be effectively sealed, and after the bonding part on the compression ring is combined with the packing assembly, the fireproof sealing performance at the bonding part of the compression ring can be ensured, tail flames are prevented from entering the tail cabin body, and the fireproof performance of the tail cabin body is improved; through setting up fire prevention heat-proof structure such as heat-proof ring and fire prevention cover on the tail cabin body, can realize the thermal-insulated protection to the tail cabin body, avoid heat conduction to this internally of tail cabin, ensure that the heat of engine spray tube tail flame can not destroy tail cabin body internal plant, improved this kind of holistic fire prevention heat resistance in tail cabin.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (9)
1. The utility model provides a rocket engine heat protection tail cabin structure, includes the tail cabin body, is equipped with the pilot hole that is used for assembling the engine nozzle on the tail cabin body, its characterized in that: the position that corresponds the pilot hole on the tail cabin body is equipped with the clamping ring, and the clamping ring is equipped with the laminating portion that is used for filling engine spray tube and tail cabin body junction clearance towards one side at pilot hole center, and the opposite side setting is on the tail cabin body, it is equipped with the heat proof ring to correspond pilot hole position all around on the tail cabin body, and the position that corresponds the clamping ring on the heat proof ring is equipped with keeps off the fire ring, has the packing clearance between fender fire ring and the clamping ring laminating portion, is equipped with the filler subassembly that can expand laminating portion volume in the packing clearance.
2. A rocket engine heat shield aft tank structure according to claim 1, wherein: the laminating portion is provided with a filling groove communicated with the filling gap, one side, corresponding to the opening of the filling groove, of the laminating portion faces the fire blocking ring, and the other side of the laminating portion is provided with a bend facilitating deformation of the laminating portion to be laminated on the engine spray pipe.
3. A rocket engine heat shield aft tank structure according to claim 2, wherein: the packing assembly comprises fireproof packing, one end of the fireproof packing is provided with a bending part matched with the packing groove, the other end of the fireproof packing is provided with a packing part matched with the packing gap, a protruding part is arranged at the position, extending out of the packing gap, of the fireproof packing, and the protruding part corresponds to the joint of the attaching part and the engine spray pipe.
4. A rocket engine heat shield aft tank structure according to claim 3, wherein: an assembly groove matched with the compression ring is formed in the position, corresponding to the compression ring, of the tail cabin body, the assembly groove is communicated with the assembly hole, one end, extending into the assembly groove, of the fire blocking ring abuts against the compression ring, and a protruding portion used for limiting the fireproof filler is arranged at the other end of the fire blocking ring; the bellying corresponds laminating portion and sets up, is equipped with the constant head tank with the cooperation of fire prevention filler protruding portion on the bellying.
5. A rocket engine heat shield aft tank structure according to claim 3, wherein: the position that corresponds laminating portion filling groove on keeping off the fire ring is equipped with the portion of compressing tightly, and the one end that the portion of compressing tightly stretched into filling groove compresses tightly the fire prevention filler to the direction at pilot hole center.
6. A rocket engine heat shield tail tank structure according to claim 3 or 5, wherein: the packing assembly further comprises a fireproof packing used for filling the fireproof packing gap in the packing groove, one end of the fireproof packing abuts against the bent part of the fireproof packing, and the other end of the fireproof packing abuts against the fire blocking ring.
7. A rocket engine heat shield aft tank structure according to claim 1, wherein: the fire-proof cover is arranged on the heat-proof ring corresponding to the position around the fire-proof ring, the supporting block for installing the fire-proof cover is arranged on the position, corresponding to the fire-proof cover, of the tail cabin body, the through hole for the supporting block to pass through is formed in the heat-proof ring, and the heat-insulating cavity is formed in the supporting block.
8. A rocket engine heat shield aft tank structure according to claim 7, wherein: the fire-blocking ring protrudes out of the surface of the heat-proof ring, a protruding portion used for shielding a gap between the fire-blocking cover and the fire-blocking ring is arranged on one side, facing the assembly hole, of the fire-blocking cover, and a heat insulation gap exists between the position, corresponding to the protruding portion, of the fire-blocking cover and the supporting block.
9. A rocket engine heat shield aft tank structure according to claim 7, wherein: the fire prevention cover and the supporting shoe are C type structures, and the tail cabin body is correspondingly provided with two fire prevention covers which form an annular structure outside the fire blocking ring, and a heat dissipation gap exists between the end parts of the two fire prevention covers.
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| CN202111098213.9A CN113606056B (en) | 2021-09-18 | 2021-09-18 | Heat-proof tail cabin structure of rocket engine |
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| CN202111098213.9A CN113606056B (en) | 2021-09-18 | 2021-09-18 | Heat-proof tail cabin structure of rocket engine |
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| CN113606056B CN113606056B (en) | 2022-07-12 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115900454A (en) * | 2022-10-19 | 2023-04-04 | 上海宇航系统工程研究所 | Honeycomb type integrated engine cabin structure |
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| CN113606056B (en) | 2022-07-12 |
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Address after: 300000 No.2 workshop of high power bulldozer, No.18 Yingchun Road, Huaming hi tech Industrial Zone, Dongli District, Tianjin Patentee after: Tianjin istar-space Technology Co.,Ltd. Address before: 300000 No.2 workshop of high power bulldozer, No.18 Yingchun Road, Huaming hi tech Industrial Zone, Dongli District, Tianjin Patentee before: SUZHOU ISTAR AVIATION TECHNOLOGY Co.,Ltd. |