CN115408780B - Core-level arrow body structure design method for directional decoupling of force and moment and core-level arrow body - Google Patents
Core-level arrow body structure design method for directional decoupling of force and moment and core-level arrow body Download PDFInfo
- Publication number
- CN115408780B CN115408780B CN202211352812.3A CN202211352812A CN115408780B CN 115408780 B CN115408780 B CN 115408780B CN 202211352812 A CN202211352812 A CN 202211352812A CN 115408780 B CN115408780 B CN 115408780B
- Authority
- CN
- China
- Prior art keywords
- longitudinal
- plate
- core
- designing
- housing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000013461 design Methods 0.000 title claims abstract description 44
- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000005452 bending Methods 0.000 claims abstract description 85
- 230000005540 biological transmission Effects 0.000 claims description 40
- 239000007788 liquid Substances 0.000 claims description 24
- 230000008878 coupling Effects 0.000 claims description 17
- 238000010168 coupling process Methods 0.000 claims description 17
- 238000005859 coupling reaction Methods 0.000 claims description 17
- 238000009434 installation Methods 0.000 claims description 6
- 238000012546 transfer Methods 0.000 claims description 2
- 230000009471 action Effects 0.000 description 7
- 238000010586 diagram Methods 0.000 description 5
- 238000009792 diffusion process Methods 0.000 description 3
- 239000002828 fuel tank Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 206010066054 Dysmorphism Diseases 0.000 description 1
- 229910000746 Structural steel Inorganic materials 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- General Engineering & Computer Science (AREA)
- Evolutionary Computation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Automation & Control Theory (AREA)
- General Details Of Gearings (AREA)
Abstract
The application provides a core-level arrow body structure design method for directional decoupling of force and moment and a core-level arrow body. The method is used for the connection design of the front binding joint and the core-level arrow body, and comprises the following steps: designing the first housing (20) of the core-stage arrow body to carry an equivalent longitudinal thrust of the thrust provided by the booster engine (100); designing an equivalent additional bending moment for carrying thrust provided by the boost engine (100) by a second housing (30) of the core-stage arrow body, wherein the first housing (20) is disposed above the second housing (30), and the central axis of the first housing (20) is aligned with the central axis of the second housing (30); the front binding joint (40) is arranged on the outer side of the second shell (30), wherein the front binding joint (40) is also used for being connected with the boosting engine (100) to bear the thrust provided by the boosting engine (100). So, optimized structural strength, satisfied structure lightweight design requirement.
Description
Technical Field
The invention belongs to the technical field of structural design, and particularly relates to a core-level arrow body structural design method for directional decoupling of force and moment and a core-level arrow body.
Background
The load of a large-sized binding type liquid carrier rocket is in the kiloton level, and the configuration of the large-sized binding type liquid carrier rocket has multiple stages, such as a boosting stage, a core first stage, a core second stage and the like. Wherein, the oblique head cone at the top end of each boosting engine is respectively connected with the core-level arrow body through the front binding joint. In the flying process, the centralized thrust generated by each boosting engine (hereinafter referred to as boosting engine) is transmitted to the core-stage rocket body through the front binding joint, and the whole carrier rocket is pushed to fly.
To increase the payload of the launch vehicle, the overall structure of the rocket body (including the core-stage rocket body) needs to meet the design requirements for light weight.
According to the traditional rocket structure design method, in order to ensure the connection strength, the structural strength and the structural integrity of binding points, the connection bolts need to be densely distributed in groups. Accordingly, the front binding joints and the housing of the core stage arrow body require dense openings. After the holes are densely opened, the opened regions need to be locally reinforced. Therefore, the core-level arrow body and the front binding joint are difficult to simultaneously meet the bearing requirement and the light-weight design requirement.
Disclosure of Invention
Aiming at the problems, the application provides a core-level arrow body structure design method for directionally decoupling force and torque and a core-level arrow body, so as to solve the technical problem that the core-level arrow body and a front binding joint in the prior art are difficult to meet the bearing requirements and the light weight design requirements at the same time.
In a first aspect, the present application provides a method for designing a core-level arrow body structure with directional decoupling of force and moment, which is used for designing connection between a front binding joint and a core-level arrow body, and the method includes:
designing the first housing (20) of the core-stage arrow body to carry an equivalent longitudinal thrust of the thrust provided by the booster engine (100);
designing an equivalent additional bending moment for carrying thrust provided by the boost engine (100) by a second housing (30) of the core-stage arrow body, wherein the first housing (20) is disposed above the second housing (30), and the central axis of the first housing (20) is aligned with the central axis of the second housing (30);
it is designed to dispose the front binding joint 40 at the outside of the second housing (30), wherein the front binding joint 40 is also used for connecting with the boosting engine (100) to carry the thrust provided by the boosting engine (100).
Further, designing the first housing (20) of the core stage arrow body to carry an equivalent longitudinal thrust of the thrust provided by the booster engine (100) comprises:
designing a first connecting portion 21 and a first bearing shell wall 22 of the first shell 20, and connecting the first bearing shell wall 22 with the first connecting portion 21;
designing a second connecting part 31 and a second bearing shell wall 32 of the second shell 30, and connecting the second connecting part 31 and the second bearing shell wall 32;
designing a third connecting part 41 and a third force transmission wall plate 42 of the front binding joint 40, wherein the third connecting part 41 is connected with the third force transmission wall plate 42;
the first connecting portion 21, the second connecting portion 31, and the third connecting portion 41 are connected in this order in the longitudinal direction;
the second carrier housing wall 32 is connected in a transverse direction to a third force transmission wall 42.
Further, the equivalent additional bending moment of the thrust provided by the booster engine 100 is designed to be carried by the second housing 30 of the core stage arrow body, including:
designing a bending moment bearing part 33 of the second shell 30, and connecting the bending moment bearing part 33 with the second bearing shell wall 32;
designing a bending moment transmission part 43 of the front binding joint 40, and connecting the bending moment transmission part 43 with the third force transmission wall plate 42;
the bending moment bearing part 33 is connected to the bending moment transmitting part 43 in the transverse direction.
Further, designing the second housing 30 of the core-stage arrow body to carry the equivalent additional bending moment of the thrust provided by the booster engine 100, further includes:
the designed bending moment bearing part 33 comprises a bearing longitudinal plate 33C extending along the longitudinal direction, and an upper long circular hole group and a lower long circular hole group are longitudinally distributed on the bearing longitudinal plate 33C, wherein the upper long circular hole group is positioned above the lower long circular hole group, the central lines of all long circular holes are overlapped, and the size of each long circular hole in the length direction is larger than that in the width direction;
connecting the upper part of the bearing longitudinal plate 33C with the second bearing shell wall 32 along the transverse direction;
at least two rows of threaded holes are distributed in the bending moment transmission part 43 along the longitudinal direction;
the upper connecting screw column group 60A is designed to pass through the upper long circular hole group;
the lower set of attachment screws 60B are designed to pass through the lower set of oblong holes.
Further, designing the second housing 30 of the core-stage arrow body to carry the equivalent additional bending moment of the thrust provided by the booster engine 100, further includes:
the design load-bearing longitudinal plate 33C includes an upper side portion and a lower side portion divided in the longitudinal direction;
designing the upper side part to comprise a longitudinal part and a transverse part, wherein the longitudinal part and the transverse part are combined into an L shape;
the longitudinal and transverse portions of the upper section are brought into abutment with the inner side and bottom surfaces of the second bearing housing wall 32, respectively.
Further, designing the second housing 30 of the core-stage arrow body to carry the equivalent additional bending moment of the thrust provided by the booster engine 100, further includes:
the designed bending moment bearing part 33 comprises at least two longitudinal beams, each longitudinal beam comprises an inner longitudinal narrow plate 33B, an outer special-shaped narrow plate and a transverse narrow plate 33A which are arranged oppositely, and the outer special-shaped narrow plates are used as bearing longitudinal plates 33C;
designing a second bearing shell wall 32 as an outer longitudinal arc-shaped plate 32B, designing the second bearing shell wall 32 to further comprise an annular transverse plate 32A and an inner longitudinal arc-shaped plate 32C, and sequentially connecting the outer longitudinal arc-shaped plate 32B, the annular transverse plate 32A and the inner longitudinal arc-shaped plate 32C;
designing an annular chamber formed by enclosing and combining at least two longitudinal beams in an outer longitudinal arc-shaped plate 32B, an annular transverse plate 32A and an inner longitudinal arc-shaped plate 32C;
accordingly, the third force-transmitting wall plate 42 is designed to abut and be connected to the outer longitudinal arc 32B.
Further, it is designed to dispose the front binding joint 40 at the outside of the second housing 30, further including:
the binding joint 40 further comprises a boosting installation fin plate 44 and a boosting installation bottom plate 45 before design, and a preset included angle is formed between the boosting installation bottom plate 45 and the transverse direction;
it is designed to provide a through hole 46 in the assist mounting plate 45 so that the assist engine 100 passes through the through hole 46.
Further, the number of the threaded holes in each row of threaded holes is not less than the sum of the number of the oblong holes in the upper oblong hole group and the number of the oblong holes in the lower oblong hole group.
Further, still include:
the longitudinal beam with an integrated structure is designed by combining an inner longitudinal narrow plate 33B, a transverse narrow plate 33A and an outer special-shaped narrow plate which are sequentially connected.
In a second aspect, the application provides a core-level rocket body of a large-scale bundled liquid carrier rocket, which is designed by adopting the structural design method of the core-level rocket body with the directional decoupling of force and moment explained above.
The core-level arrow body structure design method and the core-level arrow body for directional decoupling of force and moment, which are provided by the embodiment of the application, aim at the connection of a front binding joint and a core-level arrow body of a large binding type liquid carrier rocket, and carry out optimized structural design in a binding point region, so that the core-level arrow body with light weight design is realized, the structural strength is optimized, and the structural light weight design requirement is met.
Drawings
FIG. 1 is a schematic flow diagram of a core-level arrow structure design method for directionally decoupling force and torque according to an embodiment of the present application;
FIG. 2A is a schematic view of the connection and force application between the core-stage rocket body and the front binding joint of a certain type of binding type liquid carrier rocket according to the embodiment of the present application;
FIG. 2B is a schematic view of a core rocket body and a front binding joint of a certain type of bound liquid carrier rocket in the area of a binding point according to an embodiment of the present application;
FIG. 2C is a force diagram illustrating directional decoupling of force and moment at a tie point region between a core-stage rocket body and a front tie joint of a certain type of bundled liquid launch vehicle according to an embodiment of the present application;
FIG. 3 is a schematic view of the core rocket body and front binding joint of a certain type of bound liquid launch vehicle according to an embodiment of the present application in the area of the binding points;
FIG. 4 is a schematic illustration of a stringer of a core-stage rocket body of a bundled liquid launch vehicle according to an embodiment of the present application;
FIG. 5A is a schematic view of a first configuration of a front binding joint of a bundled liquid launch vehicle of an embodiment of the present application;
FIG. 5B is a second schematic diagram of a front binding joint of a certain type of bundled liquid launch vehicles according to embodiments of the present application;
FIG. 6 is a schematic force diagram of a bundled liquid launch vehicle of an embodiment of the present application; wherein the content of the first and second substances,
10. an upper housing; 20. a first housing; 21. a first connection portion; 22. a first carrier wall; 30. a second housing; 31. a second connecting portion; 32. a second carrier wall; 32A, an annular transverse plate; 32B, an outer longitudinal arc plate; 32C, an inner longitudinal arc plate; 33. a bending moment bearing part; 33A, transverse narrow plates; 33B, an inner longitudinal narrow plate; 33C, bearing the longitudinal plates and the outer special-shaped narrow plates; 40. a front binding joint; 41. a third connecting portion; 42. a third force transfer wall plate; 43. a bending moment transmission part; 44. mounting a fin plate in a boosting manner; 44A, a left side fin plate; 44B, a right wing plate; 45. mounting a bottom plate; 46. a through hole; 47. the special-shaped hole at the lower part, the special-shaped hole at the upper part, the threaded holes at 49A in the first row, the threaded holes at 49B in the second row, the threaded holes at 60A in the upper side and the threaded holes at the lower side; 60B, connecting a screw column group at the lower side; 70. a liquid fuel storage tank; 100. the engine is boosted.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. In addition, technical features of various embodiments or individual embodiments provided by the present invention may be arbitrarily combined with each other to form a feasible technical solution, and such combination is not limited by the sequence of steps and/or the structural composition mode, but must be realized by a person skilled in the art, and when the technical solution combination is contradictory or cannot be realized, such a technical solution combination should not be considered to exist and is not within the protection scope of the present invention.
To describe the technical contents of the present application accurately and to understand the present application accurately, the terms used in the present specification are explained or defined as follows before describing the embodiments.
As shown in FIGS. 6 and 3, the core-stage rocket body of the large-sized bundled liquid carrier rocket and the booster engine 100 are connected by using a bundling joint at the tapered end portion thereof, so that the large thrust of the booster engine is transmitted to the thrust Fa in the longitudinal direction through the front bundling joint 40 * To the core level arrow body. For example, the core-level rocket body of a large binding type liquid carrier rocket is connected with 4 booster engines at 4 binding points respectively by adopting binding joints, and the huge thrust of the booster engines is transmitted to the core-level rocket body through the binding joints.
As shown in fig. 6 and 2A, the boosting thrust F provided by the boosting engine through the front binding joint 40 is inclined upward along the axis of the oblique-headed cone and forms a predetermined angle with the central axis of the core-stage arrow body. At each binding point, the line of action of the thrust Fa of the booster engine in the longitudinal direction is at a certain distance from the wall of the core-stage arrow body in the vicinity thereof. For example, FIG. 2A shows a generatrix JJ of the wall of the core-stage arrow body around the central axis of the core-stage arrow body, when the line of action of the thrust force Fa in the longitudinal direction of the booster engine is aligned with the wall of the core-stage arrow bodyThe distance between the walls is marked L, the additional bending moment M = L Fa acting in the region of the binding points # The equivalent longitudinal thrust acting on the second housing and the second housing is denoted as Fa.
It should be understood that the respective thin-walled housings (for housing walls having a thickness on the order of millimeters, such as liquid fuel tanks) that the front binding joints and the core-stage arrows comprise may each be considered a structure. Each of these areas on the structure may be subjected to a specific force load or moment load and need to withstand a predetermined load without buckling or breaking.
Since the line of action of the thrust of the booster engine is at a non-negligible distance from the wall of the core-stage arrow body, as shown in fig. 2A and 3, the large boost thrust is transmitted to the core-stage arrow body through the binding joint at the binding point, and at the same time, the eccentric boost thrust also generates a large additional bending moment M and is transmitted to the core-stage arrow body through the binding joint in a coupling manner. Aiming at the phenomenon that the force and the moment are entangled and coupled to be transmitted, the following two design problems can be generated according to the traditional rocket structure design method: (1) the thrust and the additional bending moment act on the upper part of the binding point area of the core-level arrow body, so that the structure of the area, such as the upper shell 10 being an oxygen box barrel section, the first shell 20 being an oxygen box rear short shell and the second shell 30 being a box interval shell, generates compression instability and is damaged. In order to make the region capable of bearing the thrust force and the additional bending moment without instability, the structure is inevitably very thick, and the finally designed core-level arrow body is difficult to meet the design requirement of light structure. (2) The force and the moment are entangled and coupled for transmission, the connecting bolt needs to bear the force and the moment at the same time, the bearing is very bad, the nominal diameter of the connecting bolt is increased, correspondingly, the diameter of the connecting bolt hole arranged on the shell needs to be increased, and the corresponding hole opening area needs to be further reinforced. On the other hand, in consideration of concentrated transmission of force and additional bending moment, the connection bolts must be densely distributed to bear the severe load, after the connection bolts are densely distributed, dense holes are also required on the shell, the hole areas of the dense holes are more difficult to reinforce, and the final design is difficult to meet the design requirements of load bearing and light weight.
As shown in fig. 2A, in the rocket flight phase, the boosting thrust F provided by the boosting engine 100 at the concentrated force application point Q includes a thrust Fa in the longitudinal direction. The line of action of the thrust Fa of the booster engine in the longitudinal direction is at a distance from the wall of the core stage.
As shown in fig. 2C, the design method of the core-level arrow body structure with directional decoupling of force and moment according to the embodiment of the present invention realizes directional decoupling of the longitudinal thrust Fa provided by the boost engine 100 at the concentrated force action point Q into the equivalent longitudinal thrust Fa carried by the first housing 20 * Thrust additional bending moment M borne by the second shell 30 * . Thus, the equivalent longitudinal thrust Fa * For sequentially pushing the front binding joint 40, the second housing 30, and the first housing 20 to move upward in the longitudinal direction. Thus, thrust additional bending moment M * Is carried by the front binding joint 40, the second housing 30, and is not transferred to the first housing 20. By blocking thrust additional bending moment M * Transmits the thrust to the first casing 20 and the upper casing 10 to apply a bending moment M * The limitation to the binding point region improves the load bearing condition of the first housing 20 and the upper housing 10.
As shown in fig. 1, the method for designing a core-level arrow structure with directional decoupling of force and moment, provided by the embodiment of the invention, is used for designing connection between a front binding joint and a core-level arrow, and comprises the following steps:
s10: designing the first housing of the core-stage arrow body to carry an equivalent longitudinal thrust of the thrust provided by the boost engine;
s20: the second housing of the core stage arrow body is designed to carry the equivalent additional bending moment of the thrust provided by the boost engine,
wherein the first housing is disposed above the second housing, the first housing being aligned with a central axis of the second housing;
s30: the front binding joint is designed to be arranged on the outer side of the second shell, for example, in the circumferential direction of the outer wall of the second shell, and is used for being connected with the boosting engine and bearing the thrust provided by the boosting engine.
Therefore, in the flying stage, the thrust provided by the plurality of boosting engines uniformly arranged along the circumferential direction of the second shell is respectively transmitted to the second shell and the first shell in sequence through the front binding joints so as to push the core-level arrow body to fly. The thrust provided by the boosting engines is directionally decoupled between force and torque at the core-level arrow body, the first shell bears equivalent longitudinal thrust, the second shell bears equivalent additional bending moment, the structural strength is optimized, and the structural lightweight design requirement is met.
Specifically, in step S10, designing an equivalent longitudinal thrust to be carried by the first housing of the core stage arrow body to carry the thrust provided by the booster engine includes:
designing a first connecting part 21 and a first bearing shell wall 22 of the first shell 20, wherein the first bearing shell wall 22 is connected with the first connecting part 21;
designing a second connecting part 31 and a second bearing shell wall 32 of the second shell 30, wherein the second connecting part 31 is connected with the second bearing shell wall 32;
designing a third connecting part 41 and a third force transmission wall plate 42 of the front binding joint 40, wherein the third connecting part 41 is connected with the third force transmission wall plate 42;
the first connecting portion 21, the second connecting portion 31, and the third connecting portion 41 are connected in this order in the longitudinal direction;
the second bearing housing wall 32 is connected to the third force-transmitting wall plate 42 in the transverse direction such that an equivalent longitudinal thrust of the thrust provided by the booster engine 100 is transmitted longitudinally upward through the third force-transmitting wall plate 42 and the second bearing housing wall 32.
In this way, in the flight phase, the thrust provided by the booster engine is sequentially transmitted to the second connection portion 31, the first connection portion 21, and the first bearing housing wall 22 through the third force transmission wall plate 42, the third connection portion 41, and the second bearing housing wall 32, so that the equivalent longitudinal thrust pushes the core-stage arrow body to fly in the longitudinal direction.
Specifically, the first connecting portion 21 includes an upper flange body; the second connecting portion 31 includes a middle flange body, and the third connecting portion 41 includes a lower flange body. Correspondingly, connecting the first connecting portion 21, the second connecting portion 31, and the third connecting portion 41 in sequence includes: the upper flange body, the middle flange body and the lower flange body are connected in sequence by utilizing the connecting bolt group.
In this way, the upper, middle and lower flanges respectively connected to the wall plates and the walls of the revolving structure are sequentially aligned, so that the outer wall of the first housing is aligned with the outer wall of the second housing, for example, the outer edges of the wall plates are aligned, and the first housing and the second housing are connected in series in the longitudinal direction.
In this way, as shown in fig. 3, the thrust of the booster engine is distributively transmitted in the longitudinal direction from the front binding joint 40, the second housing 30, and the first housing 20 in this order to push the liquid fuel tank 70 contained in the upper housing 10 connected to the first bearing housing wall 22 of the first housing 20, and the above respective structures are realized to bear the thrust without being destabilized or destroyed.
In particular, the second bearing housing wall 32 is connected to the third force transmission wall 42 in the transverse direction by riveting, which is not described in detail.
Specifically, in step S20, designing an equivalent additional bending moment for the second housing of the core-stage arrow body to bear the thrust provided by the boosting engine includes:
designing a bending moment bearing part 33 of the second shell 30, and connecting, such as riveting, the bending moment bearing part 33 with the second bearing shell wall 32;
designing a bending moment transmission part 43 of the front binding joint 40, and connecting the bending moment transmission part 43 with the third force transmission wall plate 42;
the bending moment bearing part 33 is connected to the bending moment transmission part 43 in the transverse direction, so that the equivalent additional bending moment of the thrust force provided by the booster engine (100) is transmitted to the bending moment bearing part 33 through the bending moment transmission part 43, and the equivalent additional bending moment is blocked from being continuously transmitted to the first bearing shell wall 22 of the first shell 20 through the second bearing shell wall 32.
Thus, the second bearing housing wall 32 and the bending moment bearing portion 33 together correspond to the binding point of the front binding joint on the core stage arrow body. In this way, the front binding joints are bound to the core-stage arrow body through the third connecting portion 41, the third force-transmitting wall plate 42, and the bending moment transmitting portion 43, respectively.
As shown in fig. 3, 5A, 5B and 6, in the radial direction of the front binding joint 40 and the second housing 30, the thrust provided by the booster engine is distributed and transmitted sequentially through the bending moment transmission part 43 and the bending moment bearing part 33, and the bending moment bearing part 33 bears the equivalent additional bending moment, and the additional bending moment is borne by the above structures without instability or damage.
Specifically, as shown in fig. 2C and 2B, in step S20, designing the second housing of the core-stage arrow body to carry the equivalent additional bending moment of the thrust provided by the boosting engine may further include:
the designed bending moment bearing part 33 comprises a bearing longitudinal plate 33C extending along the longitudinal direction, and an upper long circular hole group and a lower long circular hole group are longitudinally distributed on the bearing longitudinal plate 33C, wherein the upper long circular hole group is positioned above the lower long circular hole group, the central lines of all the long circular holes are overlapped, and the size of the long circular holes in the length direction is larger than that in the width direction; if the upper long circular hole group is positioned in the middle of the bearing longitudinal plate, the lower long circular hole group is positioned at the lower part of the bearing longitudinal plate 33C;
accordingly, in the transverse direction, the upper part of the load-bearing longitudinal plate 33C is designed to be connected, e.g. riveted, to the second load-bearing housing wall 32;
the bending moment transmission part 43 is designed to be longitudinally distributed with at least two rows of threaded holes, such as a first row of threaded holes 49A and a second row of threaded holes 49B shown in FIG. 5B;
passing the upper tie screw set 60A through the upper long circular hole set, the upper part of the first row of threaded holes 49A or the upper part of the second row of threaded holes 49B;
the lower set of attachment screws 60B is passed through the lower set of oblong holes, the lower portion of the first row of threaded holes 49A or the lower portion of the second row of threaded holes 49B.
In this way, in the flight phase, as shown in fig. 2C, two sets of the lower coupling screw group and the upper coupling screw group are provided, and are transmitted in the horizontal direction through the lower coupling screw group, the lower long circular hole group, and two rows of threaded holes (the lower coupling screw group is compressed), and transmitted through the upper coupling screw group, the upper long circular hole group, and two rows of threaded holes (the upper coupling screw group is pulled), so that the upper portion of the vertical carrier plate 33C tends to be separated from the second carrier housing wall 32, and the second carrier housing wall 32 does not carry the equivalent additional bending moment. In this way, the load bearing vertical plate 33C as a whole bears an equivalent additional bending moment generated by the thrust force provided by the booster engine.
Thus, in the transverse direction, and carryingThe second bearing shell wall 32 closely attached to the upper part of the vertical plate 33C does not bear the bending moment M * And further, the equivalent additional bending moment M generated by the thrust provided by the boosting engine is prevented from being continuously transmitted to the first shell through the second bearing shell wall 32, and the directional decoupling of the force and the moment is realized.
Referring to fig. 2A, 2B and 2C, the design method for directionally decoupling thrust and additional bending moment between the core-stage arrow body and the binding joint is described as follows:
as shown in the schematic diagram of fig. 2C, the bolt connection holes matched with the respective connecting screw groups are all oblong holes in the longitudinal bearing plate 33C, so that slidable contact assembly of the respective connecting screw groups and the longitudinal bearing plate in the longitudinal direction can be realized. It is thereby achieved that the middle and lower portions of the load-bearing longitudinal plate 33C transmit only a lateral tensile load (e.g., f in the drawing) or a compressive load (e.g., -f in the drawing) in the horizontal direction, i.e., in the lateral direction, and do not transmit the thrust force Fa from the booster engine transmitted through the bending moment transmitting portion 43 of the front binding joint so that the bolt bears a shear load (in the vertical direction, i.e., in the longitudinal direction) in the radial direction thereof. After the thrust additional bending moment M is transmitted through the area, the bending moment M * Is converted into a tensile force (transmitted by the connecting stud) borne by the rear end of the longitudinal beam, namely the lower part of the longitudinal load bearing plate 33C, and a compressive force (transmitted by the connecting stud) borne by the front end of the longitudinal beam, namely the middle part of the longitudinal load bearing plate 33C. In this way, the tensile and compressive forces of the two regions form a couple moment M along the couple line of action K, which is absorbed by the load-bearing longitudinal plate 33C or the longitudinal beam described below.
Due to the slidable fit formed by the oblong holes, the connecting stud can be made not to withstand the bolt shear force formed by the equivalent longitudinal thrust force as described above. The second bearing shell wall of the second shell corresponding to the binding point of the front binding joint does not bear additional bending moment, and the longitudinal thrust is continuously transmitted forwards and upwards through the third force transmission wall plate and the second bearing shell wall.
In this way, the moment transmitting portion 43, the load-bearing longitudinal plate 33C, the upper coupling stud group, and the lower coupling stud group form a couple moment, thereby decoupling the force and the moment, and finally decoupling the boosting thrust and the additional bending moment thereof, and transmitting them separately, and receiving them in a distributed manner on the housing of the core-stage arrow body, so that the design of the thin-walled housing in the region near the binding point and the load environment of the coupling bolt can be greatly relaxed.
In this way, in the flight phase, as shown in fig. 2C, the upper coupling screw group can slide in the longitudinal direction in the upper long circular hole group, and the lower coupling screw group can slide in the longitudinal direction in the lower long circular hole group, so that even under the action of a flight random load or a vibration load, the upper coupling screw group does not contact with the lower edge or the upper edge of the long circular hole and does not bear the longitudinal thrust.
Specifically, the number of threaded holes in each row of threaded holes is not less than the sum of the number of oblong holes in the upper oblong hole group and the number of oblong holes in the lower oblong hole group.
Specifically, in step S20, designing an equivalent additional bending moment for the second housing of the core-stage arrow body to bear the thrust provided by the boosting engine may further include:
designing the bearing longitudinal plate 33C to include an upper side portion and a lower side portion divided in the longitudinal direction;
the upper side part comprises a longitudinal part and a transverse part which are combined into an L shape;
the longitudinal and transverse portions of the upper section abut against the inner side and bottom surfaces of the second carrier housing wall 32, respectively.
In this way, in the longitudinal direction, the equivalent longitudinal thrust can be further transmitted and borne through the upper portion of the L-shape of the bearing longitudinal plate 33C, which is beneficial for the third force transmission wall plate 42, the second bearing shell wall 32, and the first bearing shell wall 22 to respectively bear the equivalent longitudinal thrust without instability.
Thus, during the flight phase, as shown in fig. 2C, the thrust provided by the booster engine is transmitted in the longitudinal direction through the third force transmission wall plate 42, the load-bearing longitudinal plate 33C and the second load-bearing shell wall 32, and finally the first shell bears the equivalent longitudinal thrust generated by the thrust provided by the booster engine, and pushes the upper shell 10 connected to the first load-bearing shell wall 22 of the first shell 20 and the liquid fuel tank 70 contained and connected thereto.
Specifically, in step S20, designing an equivalent additional bending moment for the second housing of the core-stage arrow body to bear the thrust provided by the boosting engine may further include:
the designed bending moment bearing part 33 comprises at least two longitudinal beams, each longitudinal beam comprises an inner longitudinal narrow plate 33B, an outer special-shaped narrow plate and a transverse narrow plate 33A which are arranged oppositely, and the outer special-shaped narrow plates are used as bearing longitudinal plates 33C;
the second bearing shell wall 32 is designed to serve as an outer longitudinal arc-shaped plate 32B, the second bearing shell wall 32 further comprises an annular transverse plate 32A and an inner longitudinal arc-shaped plate 32C, and the outer longitudinal arc-shaped plate 32B, the annular transverse plate 32A and the inner longitudinal arc-shaped plate 32C are sequentially connected;
designing an annular chamber formed by enclosing and combining at least two longitudinal beams in an outer longitudinal arc-shaped plate 32B, an annular transverse plate 32A and an inner longitudinal arc-shaped plate 32C;
accordingly, the third force-transmitting wall 42 is designed to abut against the outer longitudinal arc 32B and be connected, e.g. riveted.
So, horizontal narrow plate 33A leans on in annular diaphragm 32A, and inboard vertical narrow plate 33B, outside dysmorphism narrow plate respectively with the vertical arc 32B of outside, the vertical arc 32C gomphosis of inboard, are favorable to improving the rigidity and the intensity of structure.
In specific implementation, as shown in fig. 4, the longitudinal beam with an integrated structure is designed by combining the inner longitudinal narrow plate 33B, the transverse narrow plate 33A and the outer special-shaped narrow plate which are sequentially connected, so that the mechanical processing is facilitated, and the rigidity and the strength of the structure are improved. For example, the I-shaped structural steel section is adopted to process each narrow plate of the longitudinal beam.
In specific implementation, as shown in fig. 2B, the front frame of the integrated structure is formed by combining the outer longitudinal arc-shaped plate 32B, the annular transverse plate 32A, the inner longitudinal arc-shaped plate 32C and the second connecting portion 31 which are sequentially connected, so that the mechanical processing is facilitated, and the rigidity and the strength of the structure are improved. It should be understood that the front frame is a solid of revolution structure.
In this way, the thrust force provided by the booster engine is distributed and transmitted sequentially along the bending moment transmitting portion 43 of the front binding joint and the at least two longitudinal beams. As shown in fig. 2C, the longitudinal beams have a moment M of couple * Form of carrying the equivalent addition of thrust Fa generationThe bending moment M, the second bearing housing wall 32 does not carry the equivalent additional bending moment that occurs.
Thus, the transverse narrow plate 33A abuts against the annular transverse plate 32A, the upper part of the outer special-shaped narrow plate abuts against the outer longitudinal arc-shaped plate 32B, and the inner longitudinal narrow plate 33B abuts against the inner longitudinal arc-shaped plate 32C.
In this way, in the flight phase, the thrust provided by the booster engine is transmitted in the longitudinal direction in a distributed manner through the third force transmission wall plate 42, the longitudinal beam and the second bearing shell wall 32 in sequence, and the first shell bears and bears the equivalent longitudinal thrust generated by the thrust provided by the booster engine.
Specifically, step S30 is designed to dispose the front binding joint at the outer side of the second housing, and may further include:
as shown in fig. 5A and 5B, a boost mounting fin plate 44 and a boost mounting base plate 45 of the binding joint 40 before design, wherein the boost mounting fin plate 44 includes a left side fin plate 44A and a right side fin plate 44B extending along the longitudinal direction, and the boost mounting base plate 45 forms a preset included angle with the transverse direction; the assist mount base plate 45 is provided with a through hole 46 so that the assist engine is positioned in a space surrounded by the left and right fin plates 44A, 44B after passing through the through hole.
Specifically, in order to further reduce weight, it may be further designed to provide a weight reduction hole in the boost mounting fin 44, which is implemented with reference to the prior art and will not be described again.
Specifically, in order to further prolong the thrust of the boost engine, the thrust has a longer circumferential diffusion and transmission path along the front binding joint and avoid stress concentration, a larger-area hole may be formed in the portion of the bending moment transmission part 43 located inside the boost mounting fin 44, and the area and size of the portion of the bending moment transmission part 43 located outside the boost mounting fin 44 may be enlarged, which is implemented with reference to the prior art and is not described again.
Specifically, in order to further prolong the thrust of the boost engine, the thrust has a longer circumferential diffusion and transmission path along the front binding joint and avoid stress concentration, a larger-area hole may be formed in the region of the third force transmission wall plate 42 located above the boost mounting fin plate 44, and the area and size of the portion of the third force transmission wall plate 42 located above and outside the boost mounting fin plate 44 may be enlarged, which is implemented with reference to the prior art and is not described again.
In this way, since the front binding joint 40 is disposed on the outer side of the second housing in the circumferential direction, the front binding joint 40 is formed in a dustpan shape as shown in fig. 5A and is engaged with the outer side of the second housing.
In this way, after the light weight design, the front binding joint 40 is provided with an upper profile hole 48 and a lower profile hole 47, wherein the upper profile hole 48 is located above the lower profile hole 47.
The core-level rocket body of the large-scale binding type liquid carrier rocket is designed by adopting any one of the structural design methods, as shown in fig. 3, fig. 2B, fig. 4, fig. 5A and fig. 5B, so that the core-level rocket body of the binding type liquid carrier rocket is connected with 4 booster engines at 4 binding points by adopting binding joints respectively, the huge thrust of the booster engines is transmitted to the core-level rocket body through the binding joints, directional decoupling is realized due to the force and the moment of the booster engines, the structural strength of the core-level rocket body is optimized, and the structure is lightened.
When the core-level rocket body of the large-scale binding-type liquid carrier rocket in the embodiment of the application is assembled, the connection mode among all the parts shown in the structural design method is referred, and the details are not repeated.
As shown in fig. 2C and 3, after assembly, the core-grade arrow body includes three sets of connectors in sequence from top to bottom. The first set of connectors is used to distributively connect the first housing 20 and the second housing 30 for distributively carrying in the longitudinal direction. The second set of connectors 80 are used to distributively connect the front binding joints 40 and the second load bearing housing wall 32 for distributively bearing in the lateral direction. A third set of connecting members, such as upper set of coupling screws 60A and lower set of coupling screws 60B, are used to distributively connect the front lashing joints and stringers to distributively carry loads in the transverse direction and create a couple moment.
As shown in fig. 3, the diffusion rib plate, the stringer, and the like, which connect the rear frame and the front frame of the second housing 30, are implemented with reference to the prior art, and are not described again.
The directional decoupling method for the force and the moment of the core-level rocket body of the large-scale binding-type liquid carrier rocket, which is provided by the embodiment of the application, decouples the force and the additional bending moment through actively carrying out decoupling design of the force and the force coupling, diffuses and transmits the force and the additional bending moment respectively according to preset paths in binding point regions of the core-level rocket, so that the force and the additional bending moment are borne by different structural members in different regions, centralized transmission and bearing of the force and the additional bending moment are avoided, more moderate load conditions are provided for structural design, and lightweight design of the structure is facilitated.
The directional decoupling method for the force and the moment of the core-level rocket body of the large-scale binding type liquid carrier rocket is applied to the design of the force bearing, force transmission and force spreading of the front binding point of the core-level rocket body of a certain type of rocket, and the structural weight reduction is more than 500 kg.
In the description of the present invention, it should be understood that the aforementioned fitting, centering or fitting respectively has fitting accuracy, dimensional tolerance, shape error, contour error, and/or form and position error, etc. known to those skilled in the art, and will not be described in detail. The aforementioned blocks, plates, rods, frames, and sheets have the known ratio of the transverse dimension to the longitudinal dimension, dimensional tolerance, shape error, contour error, and/or form and position error, fitting precision, etc. and will not be described in detail.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; either mechanically (e.g., welding, adhesives, threads, screws, pins, rivets, etc.) or electrically; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature "under," "beneath," and "under" a second feature may be directly under or obliquely under the second feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
The foregoing description is intended to be illustrative rather than limiting, and it will be appreciated by those skilled in the art that many modifications, variations or equivalents may be made without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (8)
1. A method for designing a core-level arrow body structure with directional decoupling of force and moment, which is used for designing connection of a front binding joint and a core-level arrow body, and comprises the following steps:
-designing an equivalent longitudinal thrust of the thrust provided by the booster engine (100) to be carried by the first housing (20) of the core-stage arrow body;
designing an equivalent additional bending moment to carry thrust provided by a boost engine (100) by a second housing (30) of the core-stage arrow body, wherein the first housing (20) is disposed above the second housing (30), the first housing (20) being aligned with a central axis of the second housing (30);
-arranging a front binding joint (40) outside the second casing (30), wherein the front binding joint (40) is also intended to be connected to the booster engine (100) for carrying the thrust provided by the booster engine (100);
the design is such that the first housing (20) of the core stage arrow body carries the equivalent longitudinal thrust of the thrust provided by a booster engine (100), comprising:
designing a first connection portion (21), a first carrying shell wall (22) of the first housing (20), connecting the first carrying shell wall (22) with the first connection portion (21);
designing a second connection part (31) and a second bearing shell wall (32) of the second shell (30), and connecting the second connection part (31) and the second bearing shell wall (32);
designing a third connecting part (41) and a third force transmission wall plate (42) of the front binding joint (40), wherein the third connecting part (41) is connected with the third force transmission wall plate (42);
connecting the first connecting portion (21), the second connecting portion (31), and the third connecting portion (41) in this order in a longitudinal direction;
-connecting the second carrier wall (32) to the third force transfer wall (42) in a transverse direction;
said design carrying the equivalent additional bending moment of thrust provided by a booster engine (100) by the second housing (30) of the core stage arrow body, comprising:
designing a bending moment bearing part (33) of the second shell (30), and connecting the bending moment bearing part (33) with the second bearing shell wall (32);
designing a bending moment transmission part (43) of the front binding joint (40), and connecting the bending moment transmission part (43) with the third force transmission wall plate (42);
the bending moment bearing part (33) is connected with the bending moment transmission part (43) along the transverse direction.
2. The method of claim 1,
said design carrying an equivalent additional bending moment of thrust provided by a booster engine (100) by a second housing (30) of said core stage arrow body, further comprising:
designing the bending moment bearing part (33) to comprise a longitudinal bearing plate (33C) extending along the longitudinal direction, wherein the longitudinal bearing plate (33C) is longitudinally distributed with an upper long circular hole group and a lower long circular hole group, the upper long circular hole group is positioned above the lower long circular hole group, and the central lines of all the long circular holes are overlapped;
connecting the upper part of the bearing longitudinal plate (33C) with the second bearing shell wall (32) along the transverse direction;
designing at least two rows of threaded holes distributed in the bending moment transmission part (43) along the longitudinal direction;
designing an upper coupling screw set (60A) to pass through the upper slotted hole set;
a lower set of attachment screws (60B) is designed to pass through the lower set of oblong holes.
3. The method of claim 2,
the design carries the equivalent additional bending moment of thrust provided by a boost engine (100) by the second housing (30) of the core stage arrow body, further comprising:
designing the bearing longitudinal plate (33C) to comprise an upper side part and a lower side part which are divided along the longitudinal direction;
designing the upper side part to comprise a longitudinal part and a transverse part, wherein the longitudinal part and the transverse part are combined into an L shape;
-abutting the longitudinal and transverse parts of the upper section against the inner side and bottom surface of the second carrying shell wall (32), respectively.
4. The method of claim 3,
the design carries the equivalent additional bending moment of thrust provided by a boost engine (100) by the second housing (30) of the core stage arrow body, further comprising:
designing the bending moment bearing part (33) to comprise at least two longitudinal beams, wherein each longitudinal beam comprises an inner side longitudinal narrow plate (33B), an outer side special-shaped narrow plate and a transverse narrow plate (33A) which are arranged oppositely, and the outer side special-shaped narrow plates are used as bearing longitudinal plates (33C);
designing the second bearing shell wall (32) to be used as an outer longitudinal arc-shaped plate (32B), designing the second bearing shell wall (32) to further comprise an annular transverse plate (32A) and an inner longitudinal arc-shaped plate (32C), and sequentially connecting the outer longitudinal arc-shaped plate (32B), the annular transverse plate (32A) and the inner longitudinal arc-shaped plate (32C);
designing an annular chamber formed by embedding the at least two longitudinal beams into the outer longitudinal arc-shaped plate (32B), the annular transverse plate (32A) and the inner longitudinal arc-shaped plate (32C) in a surrounding manner;
accordingly, the third force-transmitting wall (42) is designed to abut against and be connected to the outer longitudinal arc (32B).
5. The method of claim 1,
the design disposes the front binding joint (40) outside the second housing (30), further comprising:
designing the front binding joint (40) to further comprise a boosting installation fin plate (44) and a boosting installation bottom plate (45), wherein a preset included angle is formed between the boosting installation bottom plate (45) and the transverse direction;
a through hole (46) is provided in a booster mounting base plate (45) so that the booster engine (100) passes through the through hole (46).
6. The method of claim 2,
the number of the threaded holes in each row of threaded holes is not less than the sum of the number of the oblong holes in the upper oblong hole group and the number of the oblong holes in the lower oblong hole group.
7. The method of claim 4, further comprising:
and designing a longitudinal beam which combines the inner side longitudinal narrow plate (33B), the transverse narrow plate (33A) and the outer side special-shaped narrow plate which are sequentially connected into an integrated structure.
8. A core-stage rocket body of a large-scale bundled liquid carrier rocket is characterized by being designed by adopting the core-stage rocket body structure design method for directionally decoupling force and moment according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211352812.3A CN115408780B (en) | 2022-11-01 | 2022-11-01 | Core-level arrow body structure design method for directional decoupling of force and moment and core-level arrow body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211352812.3A CN115408780B (en) | 2022-11-01 | 2022-11-01 | Core-level arrow body structure design method for directional decoupling of force and moment and core-level arrow body |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115408780A CN115408780A (en) | 2022-11-29 |
| CN115408780B true CN115408780B (en) | 2023-03-28 |
Family
ID=84167025
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211352812.3A Active CN115408780B (en) | 2022-11-01 | 2022-11-01 | Core-level arrow body structure design method for directional decoupling of force and moment and core-level arrow body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115408780B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19856670B4 (en) * | 1998-12-09 | 2004-12-02 | Eads Space Transportation Gmbh | Satellite launching device |
| US6761335B2 (en) * | 2001-11-29 | 2004-07-13 | Alliant Techsystems Inc. | Apparatus for load transfer between aerospace vehicle components, aerospace vehicles including same, and method of attachment of aerospace vehicle components |
| CN106777613A (en) * | 2016-12-05 | 2017-05-31 | 大连理工大学 | A kind of light titanium alloy rapid shaping carrier rocket of optimization bundlees the preparation method of bearing |
| CN107121028B (en) * | 2017-05-22 | 2019-04-05 | 上海宇航系统工程研究所 | It is a kind of to hold the boost motor plagiocephaly wimble structure for biasing big concentrated force |
| CN109325256B (en) * | 2018-08-16 | 2023-01-17 | 上海宇航系统工程研究所 | Design method of primary and secondary connection section structure with uniform bias load boosting stress |
| CN113865821B (en) * | 2021-08-23 | 2023-06-23 | 北京强度环境研究所 | Bulb connection simulation assembly and wind load test device for bundled rocket scaling model |
-
2022
- 2022-11-01 CN CN202211352812.3A patent/CN115408780B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN115408780A (en) | 2022-11-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101959753B (en) | Transverse butt connection between two fuselage sections | |
| JP6423621B2 (en) | Apparatus and method for joining aircraft composite structures | |
| US8371532B2 (en) | Aircraft joint | |
| US7093470B2 (en) | Methods of making integrally stiffened axial load carrying skin panels for primary aircraft structure and fuel tank structures | |
| US8608110B2 (en) | Cargo aircraft system | |
| CN109050989B (en) | Double-star point type adapter | |
| EP3725677A1 (en) | Aircraft landing gear forward trunnion support assemblies and related methods | |
| CN112977789A (en) | Compression chord of fuselage | |
| CN111196343A (en) | Frame assembly for an aft section of an aircraft and aft section of an aircraft | |
| US20220026022A1 (en) | Composite inner frame multi-bonded barrel, shell-integrated projectile propellant tank including same, and method for manufacturing those | |
| CN108116650B (en) | Fuselage skin panel connection system and method of connecting skin panels | |
| EP3228534A1 (en) | Pressure bulkhead apparatus | |
| EP3725674B1 (en) | Aircraft main landing gear drag brace backup fitting assemblies and related methods | |
| CN115408780B (en) | Core-level arrow body structure design method for directional decoupling of force and moment and core-level arrow body | |
| US20210179249A1 (en) | Longitudinal beam joint for a pressure deck assembly | |
| EP3604119A1 (en) | Frame for fuselage shells of an aircraft and fuselage shell | |
| US11420718B2 (en) | Aircraft tail assembly | |
| US10703420B2 (en) | Vehicle joint | |
| US10138627B2 (en) | Method of assembly of composite core sandwich edge joint | |
| US20200122816A1 (en) | Bulkhead joint assembly | |
| EP3360801B1 (en) | Method of assembly of composite core sandwich edge joint | |
| US10279550B2 (en) | Method of assembly of composite core sandwich edge joint | |
| US20230159179A1 (en) | Engine pylon for coupling a jet engine to a wing of an aircraft | |
| CN218617223U (en) | Satellite connecting ring and satellite | |
| US10173406B2 (en) | Fluted core sandwich shell edge joint |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |