CN119288707A - Rigid-flexible coupled heat shield for reusable rocket engine nozzle load reduction - Google Patents
Rigid-flexible coupled heat shield for reusable rocket engine nozzle load reduction Download PDFInfo
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- CN119288707A CN119288707A CN202411512723.XA CN202411512723A CN119288707A CN 119288707 A CN119288707 A CN 119288707A CN 202411512723 A CN202411512723 A CN 202411512723A CN 119288707 A CN119288707 A CN 119288707A
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- 238000003825 pressing Methods 0.000 claims description 71
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- 235000015842 Hesperis Nutrition 0.000 description 1
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Classifications
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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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Abstract
本发明公开了面向重复使用火箭发动机喷管降载的刚柔耦合防热裙，包括：套筒、防热裙压板、上压板、下压板和柔性防热裙带；其中，套筒与火箭尾段连接；所述柔性防热裙带置于套筒中；防热裙压板将柔性防热裙带的外边沿压紧在套筒上；防热裙压板、柔性防热裙带和套筒层叠压紧连接；上压板与火箭发动机的防火板连接；下压板将柔性防热裙带的内边沿压紧在上压板上；下压板、柔性防热裙带和上压板层叠压紧连接。实现发动机喷管横向载荷大幅减小。
The invention discloses a rigid-flexible coupling heat-resistant skirt for reducing the load of a reusable rocket engine nozzle, comprising: a sleeve, a heat-resistant skirt pressure plate, an upper pressure plate, a lower pressure plate and a flexible heat-resistant skirt belt; wherein the sleeve is connected to the rocket tail section; the flexible heat-resistant skirt belt is placed in the sleeve; the heat-resistant skirt pressure plate presses the outer edge of the flexible heat-resistant skirt belt onto the sleeve; the heat-resistant skirt pressure plate, the flexible heat-resistant skirt belt and the sleeve are stacked and pressed tightly; the upper pressure plate is connected to the fireproof plate of the rocket engine; the lower pressure plate presses the inner edge of the flexible heat-resistant skirt belt onto the upper pressure plate; the lower pressure plate, the flexible heat-resistant skirt belt and the upper pressure plate are stacked and pressed tightly. The lateral load of the engine nozzle is greatly reduced.
Description
Technical Field
The invention relates to a rigid-flexible coupling heat-resistant skirt for load reduction of a reusable rocket engine nozzle, and belongs to the technical field of aerospace systems.
Background
The repeated use rocket is decelerated by utilizing aerodynamic resistance generated by high-speed incoming flow impacting the rocket body in the reentry aerodynamic deceleration section. The rocket body bottom plate and the engine spray pipe face to the incoming flow, are equivalent to a blunt body windward structure, generate a split shock wave after being impacted by the incoming flow and form local high pressure in the central area of the rocket body heat-proof bottom, and the pressure acts on the bottom plate and the engine, so that the rocket body spray pipe is caused to have extremely large radial outward expansion force and axial force. Meanwhile, the heat-proof skirt needs to bear larger external pressure load, and local radial force and axial force are generated when the heat-proof skirt deforms to act on the connection part of the heat-proof skirt and the engine. Under the combined action, the load of the return section exceeds the bearing capacity of the engine and the servo mechanism. In order to reduce the load requirements on a servo mechanism and an engine, load optimization design is required to be developed, and on the basis, the heat-proof skirt is adaptively designed according to a load optimization scheme, so that the rigid-flexible coupling heat-proof skirt is formed.
The current domestic heat-proof skirt is only suitable for a disposable rocket, does not need to bear force and heat load brought by high-speed incoming flow of a return section, is generally of a flexible structure, is made of materials only suitable for the heat flow environment of a rising section, and is only required to meet the swinging requirement of an engine in shape and size.
The rocket repeatedly used abroad adopts a pure rigid structure, and when the engine swings, the rigid structure swinging along with the engine has larger requirement on movement space and heavier structure.
The rigid-flexible coupling heat-proof skirt structure has the functions of heat protection at the return section, bearing and reducing the load of the engine spray pipe, and has small space requirement and greatly reduced mass compared with the rigid heat-proof skirt.
According to the characteristics of the reusable rocket flight profile and the load requirements, the heat-resistant skirt functions comprise:
1) The heat insulation is characterized in that the heat insulation function is maintained in the ignition and pneumatic heating environment of the engine at the return section besides the heat insulation at the rising section;
2) The flexible part of the heat-proof skirt swings with the engine, and the relaxation length of the flexible part is suitable for the coordination requirement of the swinging space of the engine;
3) The bearing is characterized in that besides bearing the load of the rising section and the return Duan Lire, the bearing needs of the engine and the servo mechanism are required to be met, and the needs are mainly met through the dimension of the rigid structure of the heat-proof skirt and the deformation shape under the dynamic pressure of the flexible structure.
The design index requirements include:
1) The heat insulating capacity meets the highest temperature constraint of the space of the tail cabin.
2) The length of the heat-proof skirt is adapted to the maximum swing angle requirement of the engine.
3) The method is suitable for the ultimate transverse bearing capacity of the primary engine.
4) The method is suitable for the limit output force of the primary servo mechanism.
5) Bearing the load of the external pressure of the return section.
6) And the load of the cross section of the connecting surface between the heat-resistant skirt and the tail section and the engine is born.
Disclosure of Invention
The invention solves the problems of overcoming the defects of the prior art, providing the rigid-flexible coupling heat-resistant skirt for reducing load of the reusable rocket engine nozzle, and realizing the great reduction of the transverse load of the engine nozzle.
The technical scheme of the invention is as follows:
The invention discloses a rigid-flexible coupling heat-proof skirt for reducing load of a reusable rocket engine nozzle, which comprises a sleeve, a heat-proof skirt pressing plate, an upper pressing plate, a lower pressing plate and a flexible heat-proof skirt belt, wherein,
The sleeve is connected with the rocket tail section;
the flexible heat-resistant skirt band is arranged in the sleeve;
The outer edge of the flexible heat-proof skirt band is tightly pressed on the sleeve by the heat-proof skirt pressing plate;
the heat-proof skirt pressing plate, the flexible heat-proof skirt and the sleeve are in laminated and pressed connection;
the upper pressing plate is connected with a fireproof plate of the rocket engine;
the lower pressing plate presses the inner edge of the flexible heat-proof skirt band on the upper pressing plate;
A lower pressing plate the flexible heat-proof skirt and the upper pressing plate are in laminated and pressed connection.
Further, in the heat-proof skirt, the sleeve comprises an upper end frame, a sleeve section, a sleeve heat-proof layer and a lower end frame, wherein,
The upper end frame is connected with the rocket tail section;
The cylinder section is in a beveled cylindrical shape, the upper end face is horizontal, and the lower end face is inclined;
The inner surfaces of the upper edge and the lower edge of the cylinder section are respectively connected with the upper end frame and the lower end frame;
the lower end frame is connected with the outer edge of the flexible heat-resistant skirt;
the sleeve heat-proof layer is adhered and solidified on the outer surface of the barrel section.
Further, in the heat-proof skirt, the flexible heat-proof skirt is formed by laminating a silicon rubber coated glass cloth, a flexible heat-insulating felt and a silicon rubber coated Kevlar, and the number of layers and the lamination sequence are determined according to the heat-proof and bearing performances of the materials.
In the heat-proof skirt, the upper pressure plate, the lower pressure plate and the heat-proof skirt pressure plate are all of a double-layer design, wherein the upper layer is of a stainless steel metal structure and is responsible for bearing, and the lower layer is of a glass fiber reinforced plastic heating heat-proof coating and is responsible for heat prevention and heat insulation.
Further, in the heat-proof skirt, the flexible heat-proof skirt is a 360-degree variable cross-section rotary body.
Further, in the heat-proof skirt, the length of the inner and outer side sections of the flexible heat-proof skirt is calculated by the following formula:
Wherein, The method is characterized in that the length of the inner side section of the flexible heat-resistant skirt is the radius of the inner side compression deformation state, ri is the height of the inner side compression deformation state, li is the length of the inner side compression deformation state, and Hi is the inner side length of the sleeve at the inner side of the flexible heat-resistant skirt; the flexible heat-proof skirt is characterized in that the length of the outer cross section of the flexible heat-proof skirt is Ro, ho, lo, di and do are the radius of the outer compression deformation state, ho, lo, and do are the length of the outer compression deformation state, ho is the length of the inner side of the sleeve at the outer side of the flexible heat-proof skirt, di is the height difference of the connecting point of the inner side flexible heat-proof skirt, and do is the height difference of the connecting point of the outer side flexible heat-proof skirt.
Further, in the heat-resistant skirt, the inclination angle of the lower end surface of the sleeve is designed according to the pneumatic pressure difference, the bus of the sleeve at one side with high pressure is long, the inclination angle is larger as the pressure difference is larger, the heat-resistant skirt is suitable for a peripheral swing engine in a high internal and external pressure difference environment, the inclination angle is zero when the pressure difference is not present, the sleeve is in a straight cylinder shape, and the heat-resistant skirt is suitable for a central engine in a high-pressure area as a whole.
Further, in the heat-proof skirt, the sleeve, the heat-proof skirt pressing plate, the upper pressing plate and the lower pressing plate are of a rigid structure, and the flexible heat-proof skirt belt is of a flexible structure.
Further, in the heat-proof skirt, the heat-proof skirt pressing plate, the upper pressing plate and the lower pressing plate are all connected in a multi-block lap joint mode.
The beneficial effects of the invention compared with the prior art are as follows:
(1) The invention provides a design scheme and a structural form for optimizing the load of the heat-proof skirt, which utilize the flexible structure of the heat-proof skirt to change the length along the circumferential direction and the appearance difference after being pressed, increase the lateral bending moment of the outside and reduce the lateral bending moment of the inside, thereby realizing the great reduction of the lateral load of an engine spray pipe;
(2) The invention provides a design that the height of the rigid structure of the heat-proof skirt is changed along the circumferential direction, so that the pneumatic pressure difference of the inner space of the rigid structure is reduced, the deformable length of the flexible heat-proof skirt is adjusted, and the adjustment of load distribution in the rigid structure is realized, thereby reducing the radial outward expansion force and the axial force acting on the engine spray pipe and the load transferred to the servo mechanism;
(3) According to the invention, through the complex force-heat load analysis at the bottom of the reusable rocket return section and the combined load shedding technology of structural design, a novel heat-proof skirt structure which is suitable for the continuous force-heat environment of the reusable rocket ascending section and the reusable rocket return section and is combined with rigid sleeve and flexible heat-insulation design is designed;
(4) The invention provides a rigid-flexible coupling heat-proof skirt structure, which realizes the functional requirements of heat prevention, bearing and engine nozzle load reduction of a reused rocket ascending section and a return section with lower space and weight cost, and promotes the low-cost quick realization of converting a disposable rocket into a reusable rocket;
(5) The invention can be popularized and applied to the design of the heat-resistant skirt with high reliability and the transverse load reduction of the engine of various reusable rockets.
Drawings
FIG. 1 is a flow chart of the load optimization of the heat shield skirt of the present invention;
FIG. 2 shows a schematic view of the heat-resistant skirt structure of the peripheral swing engine, wherein (a) is a schematic view of a sleeve with an inclined section, and (b) is a schematic view of the heat-resistant skirt structure of the peripheral swing engine;
FIG. 3 is a schematic view of the heat-proof skirt structure of the central engine of the invention, (a) is a schematic view of a sleeve with a flat section, and (b) is a schematic view of the heat-proof skirt structure of the central engine;
FIG. 4 is a schematic view of the construction of the heat shield skirt of the present invention;
FIG. 5 is a schematic illustration of the connection of the heat shield skirt of the present invention to the tail section;
FIG. 6 is a schematic illustration of the attachment of the heat shield skirt of the present invention to an engine;
FIG. 7 is a schematic view of the connection of the lower platen, the flexible heat resistant skirt and the upper platen of the present invention;
FIG. 8 is a schematic view of the attachment of the heat shield skirt platen, flexible heat shield skirt and sleeve of the present invention;
FIG. 9 is a schematic view of the upper platen structure of the present invention;
FIG. 10 is a schematic view of the structure of the lower platen of the present invention;
FIG. 11 shows a flexible heat-resistant skirt of the present invention in various variations, (a) a constant-section flexible heat-resistant skirt, and (b) a variable-section flexible heat-resistant skirt;
FIG. 12 is a drawing showing the relationship between the design dimensions of the heat-proof skirt of the present invention, (a) the trace dimensions of the flexible heat-proof skirt and the force diagram, and (b) the relationship between the length of the inner and outer cross-sections of the flexible heat-proof skirt and the length of the inner and outer cross-sections of the sleeve.
Detailed Description
The present invention is described in further detail below with reference to the drawings and detailed description.
As shown in fig. 4, the invention discloses a rigid-flexible coupling heat-proof skirt for load reduction of a reusable rocket engine nozzle, which comprises a sleeve, a heat-proof skirt pressing plate 5, an upper pressing plate 6, a lower pressing plate 7 and a flexible heat-proof skirt belt 8;
Wherein,
The sleeve is connected with the rocket tail section;
The flexible heat-proof skirt band 8 is arranged in the sleeve;
The outer edge of the flexible heat-proof skirt band 8 is tightly pressed on the sleeve by the heat-proof skirt pressing plate 5;
The heat-proof skirt pressing plate 5, the flexible heat-proof skirt belt 8 and the sleeve are in laminated, pressed and connected;
The upper pressing plate 6 is connected with a fireproof plate of the rocket engine;
the lower pressing plate 7 presses the inner edge of the flexible heat-proof skirt 8 on the upper pressing plate 6;
the lower pressing plate 7, the flexible heat-proof skirt 8 and the upper pressing plate 6 are connected in a laminated and pressed mode.
Preferably, the sleeve comprises an upper end frame 1, a sleeve section 2, a sleeve heat protection layer 3 and a lower end frame 4, wherein,
The upper end frame 1 is connected with the rocket tail section;
the cylinder section 2 is in a beveling cylinder shape, the upper end face is horizontal, and the lower end face is inclined;
the inner surfaces of the upper edge and the lower edge of the cylinder section 2 are respectively connected with an upper end frame 1 and a lower end frame 4;
The lower end frame 4 is connected with the outer edge of the flexible heat-proof skirt band 8;
the sleeve heat-proof layer 3 is adhered and solidified on the outer surface of the barrel section 2.
Preferably, the flexible heat-proof skirt 8 is formed by laminating a silicon rubber coated glass cloth, a flexible heat-insulating felt and a silicon rubber coated Kevlar, and the number of layers and the lamination sequence are determined according to the heat-proof and bearing performance of the materials.
The upper pressing plate 6, the lower pressing plate 7 and the heat-proof skirt pressing plate 5 are all of double-layer design, wherein the upper layer is of a stainless steel metal structure and is responsible for bearing, and the lower layer is of glass fiber reinforced plastic heat-proof coating and is responsible for heat prevention and heat insulation.
Preferably, the flexible heat-proof skirt 8 is a 360-degree variable-section rotary body, the section length is designed according to the pneumatic pressure difference, and the section length of one side with high pressure is short.
The rigid-flexible coupling heat-resistant skirt for reducing load of a reusable rocket engine nozzle according to claim 1, wherein the length of the inner and outer side cross sections of the flexible heat-resistant skirt 8 is calculated by the following formula:
Wherein, The method is characterized in that the length of the inner side section of the flexible heat-resistant skirt is the radius of the inner side compression deformation state, ri is the height of the inner side compression deformation state, li is the length of the inner side compression deformation state, and Hi is the inner side length of the sleeve at the inner side of the flexible heat-resistant skirt; the flexible heat-proof skirt is characterized in that the length of the outer cross section of the flexible heat-proof skirt is Ro, ho, lo, di and do are the radius of the outer compression deformation state, ho, lo, and do are the length of the outer compression deformation state, ho is the length of the inner side of the sleeve at the outer side of the flexible heat-proof skirt, di is the height difference of the connecting point of the inner side flexible heat-proof skirt, and do is the height difference of the connecting point of the outer side flexible heat-proof skirt.
Preferably, the inclination angle of the lower end surface of the sleeve is designed according to the pneumatic differential pressure, the bus bar of the sleeve at one side with high pressure is long, the larger the differential pressure is, the larger the inclination angle is, the sleeve is suitable for a peripheral swing engine in a high internal and external differential pressure environment, the inclination angle is zero when the differential pressure is not present, the sleeve is in a straight cylinder shape, and the sleeve is suitable for a central engine in a high-pressure area as a whole.
The sleeve, the heat-proof skirt pressing plate 5, the upper pressing plate 6 and the lower pressing plate 7 are preferably rigid structures, the flexible heat-proof skirt 8 is of a flexible structure, the rigid structures bear complex force heat load of a reusable rocket return section, pneumatic pressure difference of the inner space is reduced through design of a sleeve section inclined angle, the deformable length of the flexible heat-proof skirt is adjusted, the flexible structures bear complex force heat load, the shape of the flexible structures under the effect of incoming flow is influenced through design of the section length of the flexible structures, and further radial outward expansion force on a part of engine spray pipes is balanced, so that the purpose of reducing the load on the engine spray pipes is achieved.
The flexible heat-resistant skirt 8 is designed to adapt to the thermal environment of the flight section, the outer layers are alternately paved with flexible heat-insulating felts with high heat insulation performance and silicone rubber coated glass cloth with high heat resistance performance, the heat flows of the ascending section and the return section can be born, a good temperature environment is created for the inner layer materials, the inner layers are alternately paved with the silicone rubber coated glass cloth with high heat resistance performance and Kevlar with high bearing capacity, and the flexible heat-resistant skirt has the capability of bearing the load of Duan Lire after the damage function loss of the outer layer materials.
Preferably, the heat-proof skirt pressing plate 5, the upper pressing plate 6 and the lower pressing plate 7 are connected in a multi-block lap joint mode, so that the heat-proof skirt pressing plate is convenient to process and install on a fireproof plate in the middle of an engine spray pipe, the structural thickness of a lap joint part is halved and then overlapped, and the heat-proof skirt pressing plate is connected by bolts, the overall thickness is unchanged, and the heat-proof skirt pressing plate has good continuity.
Examples
The load reduction of the rocket engine nozzle for reuse is realized by adopting a mode of optimizing the high length ratio of the heat-resistant skirt, and the load optimization idea of the heat-resistant skirt is shown in figure 1.
The load adaptability design of the heights of the upper connecting surface and the lower connecting surface of the flexible heat-proof skirt 8 is realized by utilizing the design that the height of the rigid sleeve is changed along the circumferential direction, and the load adaptability design of the length of the flexible heat-proof skirt is realized by utilizing the design that the length of the flexible heat-proof skirt is changed along the circumferential direction between the upper pressing plate 7 and the lower pressing plate 7. According to the load optimization result, the load optimization schemes of the heat-protection skirt of the peripheral swing engine and the central engine are different, and the structural form of the heat-protection skirt is shown in fig. 2-3.
The heat-proof skirt is composed of a sleeve, a heat-proof skirt pressing plate 5, an upper pressing plate 6, a lower pressing plate 7, a flexible heat-proof skirt belt 8 and the like, wherein the sleeve comprises an upper end frame 1, a barrel section 2, a sleeve heat-proof layer 3 and a lower end frame 4, and is a connecting and heat-proof product between a tail section and an engine as shown in fig. 4.
The connection of the heat-proof skirt and the tail section is realized through the connection of the upper end frame 1 of the heat-proof skirt sleeve and the tail section bottom plate 52, and the connection of the heat-proof skirt and the engine is realized through the connection of the upper pressure plate 6 and the engine fireproof plate 61, as shown in fig. 5-6.
As shown in fig. 5, the upper end frame 1 of the sleeve is connected with the tail section bottom plate 52 of the rocket through bolts 53, washers 54 and self-locking nuts 55.
As shown in fig. 6, the engine fireproof plate 61 is connected to the upper platen upper layer 62 (metal bearing layer), and the upper platen lower layer 63 (nonmetallic heat shield layer) by bolts 64, washers 65, and self-locking nuts 66.
The heat-proof skirt pressing plate 5, the flexible heat-proof skirt strip 8 and the sleeve are in laminated pressing connection, the outer edge of the flexible heat-proof skirt strip 8 is pressed on the sleeve by the heat skirt pressing plate, the lower pressing plate 7, the flexible heat-proof skirt strip 8 and the upper pressing plate 6 are in laminated pressing connection, and the inner edge of the flexible heat-proof skirt strip 8 is pressed on the upper pressing plate 6 by the lower pressing plate 7, as shown in figures 7-8.
As shown in fig. 7, the upper platen upper layer 71, the upper platen lower layer 72, the lower platen upper layer 73, the lower platen lower layer 74 and the flexible heat-resistant skirt 8 are connected by bolts 76, washers 77 and self-locking nuts 78.
As shown in fig. 8, the sleeve lower end frame 4, the flexible heat-proof skirt 8, the heat-proof skirt platen upper layer 83 and the heat-proof skirt platen lower layer 84 are connected by bolts 87, washers 88 and self-locking nuts 89.
The clamp plate is used for pressing flexible heat protection skirt 8 on connection structure, all clamp plates, including top board 6, holding down plate 7 and heat protection skirt clamp plate 5 all adopt bilayer design, the upper strata is stainless steel metal construction, be responsible for bearing, the lower floor is glass steel heating protection coating, be responsible for heat protection and thermal-insulated, the top and bottom clamp plate 7 all adopt polylith overlap joint mode to connect, be convenient for process and install on engine nozzle middle part PLASTIC LAMINATED, overlap again and use bolted connection overlap in overlap position structure thickness, whole thickness is unchangeable, and have better continuity, as shown in fig. 9-10.
The flexible heat-proof skirt 8 is formed by laminating a silicon rubber coated glass cloth, a flexible heat-insulating felt and a silicon rubber coated Kevlar, and is subjected to adaptive design of layering materials and layers according to thermal environment and load conditions. Because the heat-proof skirt is required to bear larger pneumatic external pressure load during return on the basis of bearing the heat flow environment condition, the bearing adaptability and air tightness of the heat-proof skirt after high-temperature ablation are required to be considered. The high strength performance of Kevlar and the air impermeability of the silicone rubber coated fabric are utilized. The shape of the heat-resistant skirt considers the deformation characteristics of the flexible body under the action of static pressure, as shown in fig. 11, the shape change is related to the connecting force transmission direction of the flexible body, so that the load optimization result is influenced, and the purpose of further load reduction is realized.
The ratio of the height H to the length L of the flexible heat-resistant skirt 8 is determined according to the load design requirements, and as shown in fig. 12a, the stress relation diagram of the heat-resistant skirt elements shows that the height and the length influence the pressure Ps, the tension T, the transverse force F x1 and the axial force F y1 acting on the heat-resistant skirt. The length of the inner and outer side sections of the flexible heat-proof skirt 8 and the length of the inner and outer sides of the sleeve are determined according to the dimensional relation chart of fig. 12 b. Length of inner cross section of flexible heat-proof skirt 8The radius Ri, the height Hi, the length Li, the length Hi of the inner side of the sleeve and the corresponding outer side dimensions of the sleeve are respectivelyRo, ho, length Lo, length Ho inside the sleeve. The height difference of the connecting point of the inner flexible heat-proof skirt 8 is di, the height difference do of the connecting point of the outer flexible heat-proof skirt 8 is determined according to the lengths hi and ho of the inner side and the outer side of the sleeve and the installation position of the engine on an arrow. The distance from the engine swing center to the heat-proof skirt mounting plate is L, and the engine swing angle is alpha. From the dimensional relationship diagram, the length of the inner and outer side sections of the flexible heat-proof skirt 8 is as follows:
Finally checking the flexible heat protection inner and outer side cross-sectional length of skirt 8 AndThe total value of the engine swinging motion quantity Lalpha and the initial distance of the connecting point of the flexible heat-proof skirt 8 is not smaller than, the length of the heat-proof skirt is ensured to meet the requirement of the maximum swing angle of the engine.
While the present invention has been described in detail through the foregoing description of the preferred embodiment, it should be understood that the foregoing description is not to be considered as limiting the invention. Many modifications and substitutions of the present invention will become apparent to those of ordinary skill in the art upon reading the foregoing. Accordingly, the scope of the invention should be limited only by the attached claims.
What is not described in detail in the present specification belongs to the known technology of those skilled in the art.
Claims (9)
1. The rigid-flexible coupling heat-proof skirt for reducing load of the reusable rocket engine jet pipe is characterized by comprising a sleeve, a heat-proof skirt pressing plate (5), an upper pressing plate (6), a lower pressing plate (7) and a flexible heat-proof skirt (8),
The sleeve is connected with the rocket tail section;
The flexible heat-proof skirt band (8) is arranged in the sleeve;
The outer edge of the flexible heat-proof skirt band (8) is tightly pressed on the sleeve by the heat-proof skirt pressing plate (5);
The heat-proof skirt pressing plate (5), the flexible heat-proof skirt (8) and the sleeve are in laminated and pressed connection;
The upper pressing plate (6) is connected with a fireproof plate of the rocket engine;
the lower pressing plate (7) presses the inner edge of the flexible heat-proof skirt band (8) on the upper pressing plate (6);
the lower pressing plate (7), the flexible heat-proof skirt band (8) and the upper pressing plate (6) are connected in a laminated and pressed mode.
2. The rigid-flexible coupling heat shield skirt for load reduction of a reusable rocket engine nozzle according to claim 1, wherein the sleeve comprises an upper end frame (1), a sleeve section (2), a sleeve heat shield (3) and a lower end frame (4), wherein,
The upper end frame (1) is connected with the rocket tail section;
The cylinder section (2) is in a beveling cylinder shape, the upper end face is horizontal, and the lower end face is inclined;
the inner surfaces of the upper edge and the lower edge of the cylinder section (2) are respectively connected with an upper end frame (1) and a lower end frame (4);
the lower end frame (4) is connected with the outer edge of the flexible heat-proof skirt (8);
the sleeve heat-proof layer (3) is adhered and solidified on the outer surface of the barrel section (2).
3. The rigid-flexible coupling heat-resistant skirt for reducing load of the reusable rocket engine nozzle according to claim 1, wherein the flexible heat-resistant skirt (8) is formed by laminating a silicon rubber coated glass cloth, a flexible heat-resistant felt and a silicon rubber coated Kevlar, and the number of layers and the lamination sequence are determined according to the heat resistance and the bearing performance of the materials.
4. The rigid-flexible coupling heat-resistant skirt for load reduction of the reusable rocket engine nozzle according to claim 1 is characterized in that the upper pressing plate (6), the lower pressing plate (7) and the heat-resistant skirt pressing plate (5) are all of a double-layer design, the upper layer is of a stainless steel metal structure and is responsible for bearing, and the lower layer is of a glass fiber reinforced plastic heating heat-resistant coating and is responsible for heat resistance and heat insulation.
5. The rigid-flexible coupling heat-resistant skirt for reducing load of the reusable rocket engine nozzle according to claim 1, wherein the flexible heat-resistant skirt (8) is a 360-degree variable cross-section rotary body.
6. The rigid-flexible coupling heat-resistant skirt for reducing load of a reusable rocket engine nozzle according to claim 5, wherein the length of the inner and outer side cross sections of the flexible heat-resistant skirt (8) is calculated by the following formula:
Wherein, The method is characterized in that the length of the inner side section of the flexible heat-resistant skirt is the radius of the inner side compression deformation state, ri is the height of the inner side compression deformation state, li is the length of the inner side compression deformation state, and Hi is the inner side length of the sleeve at the inner side of the flexible heat-resistant skirt; the flexible heat-proof skirt is characterized in that the length of the outer cross section of the flexible heat-proof skirt is Ro, ho, lo, di and do are the radius of the outer compression deformation state, ho, lo, and do are the length of the outer compression deformation state, ho is the length of the inner side of the sleeve at the outer side of the flexible heat-proof skirt, di is the height difference of the connecting point of the inner side flexible heat-proof skirt, and do is the height difference of the connecting point of the outer side flexible heat-proof skirt.
7. The rigid-flexible coupling heat-resistant skirt for reducing load of the spray pipe of the reusable rocket engine according to claim 1 is characterized in that the inclination angle of the lower end face of the sleeve is designed according to pneumatic pressure difference, the larger the pressure difference is, the larger the inclination angle is, the periphery swinging engine in the environment with high internal and external pressure difference is, the inclination angle is zero when the pressure difference is not present, the sleeve is in the shape of a straight cylinder, and the sleeve is suitable for a central engine in a high-pressure area as a whole.
8. The rigid-flexible coupling heat-resistant skirt for reducing load of the reusable rocket engine nozzle according to claim 1 is characterized in that the sleeve, the heat-resistant skirt pressing plate (5), the upper pressing plate (6) and the lower pressing plate (7) are of rigid structures, and the flexible heat-resistant skirt (8) is of flexible structures.
9. The rigid-flexible coupling heat-resistant skirt for load reduction of the reusable rocket engine nozzle according to claim 1 is characterized in that a heat-resistant skirt pressing plate (5), an upper pressing plate (6) and a lower pressing plate (7) are connected in a multi-piece lap joint mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411512723.XA CN119288707A (en) | 2024-10-28 | 2024-10-28 | Rigid-flexible coupled heat shield for reusable rocket engine nozzle load reduction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411512723.XA CN119288707A (en) | 2024-10-28 | 2024-10-28 | Rigid-flexible coupled heat shield for reusable rocket engine nozzle load reduction |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN119288707A true CN119288707A (en) | 2025-01-10 |
Family
ID=94156748
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202411512723.XA Pending CN119288707A (en) | 2024-10-28 | 2024-10-28 | Rigid-flexible coupled heat shield for reusable rocket engine nozzle load reduction |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN119288707A (en) |
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2024
- 2024-10-28 CN CN202411512723.XA patent/CN119288707A/en active Pending
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