CN111114834A - Light side wall suspension vertical force transmission rack and primary engine - Google Patents
Light side wall suspension vertical force transmission rack and primary engine Download PDFInfo
- Publication number
- CN111114834A CN111114834A CN201911303993.9A CN201911303993A CN111114834A CN 111114834 A CN111114834 A CN 111114834A CN 201911303993 A CN201911303993 A CN 201911303993A CN 111114834 A CN111114834 A CN 111114834A
- Authority
- CN
- China
- Prior art keywords
- joint
- main
- frame
- mounting
- main joint
- 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.)
- Granted
Links
- 230000005540 biological transmission Effects 0.000 title claims abstract description 67
- 239000000725 suspension Substances 0.000 title claims abstract description 14
- 230000007246 mechanism Effects 0.000 claims description 42
- 238000009434 installation Methods 0.000 claims description 35
- 238000012546 transfer Methods 0.000 claims description 19
- 238000003466 welding Methods 0.000 claims description 12
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 229910000851 Alloy steel Inorganic materials 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 210000001503 joint Anatomy 0.000 description 17
- 238000013461 design Methods 0.000 description 9
- 241000239290 Araneae Species 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000011295 pitch Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 230000005570 vertical transmission Effects 0.000 description 1
- 201000009482 yaws Diseases 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The invention provides a light-weight side wall suspension vertical force transmission rack and a primary engine, which solve the problems that the existing primary engine has a long rack and a complicated support assembly due to the large difference between the height dimensions of a large engine and a small engine; or take up space in the cabin. The rack comprises a cross joint, 4 main joints, 4 connecting rods, a first I-shaped beam, a second I-shaped beam and 2 dowel bars; the 4 connecting rods are connected through 4 main joints to form a rectangular frame; the 4 main joints are respectively a first main joint, a second main joint, a third main joint and a fourth main joint; two ends of the first I-beam are respectively connected with the third main joint and the first interface of the cross joint; two ends of the second I-beam are respectively connected with the fourth main joint and the second interface of the cross joint; the connecting rod and the 2I-beams form a first isosceles right-angle triangular frame, and the included angle between the plane of the frame and the plane of the rectangular frame is 93 degrees; one end of each of the 2 dowel bars is connected with the first main joint and the second main joint respectively, and the other end of each dowel bar is connected with the cross joint.
Description
Technical Field
The invention relates to a technology for vertically taking off and landing and repeatedly using a primary engine in a rocket, in particular to a light side wall suspension vertical force transmission rack and a primary engine.
Background
The frame is the foundation of the primary engine assembly layout, is a component for bearing the connection, support and transmission thrust between the engine and the arrow body, and is required to bear bending moment and torque when the arrow body pitches, yaws and rolls. The frame design principle of the primary engine requires simple structure, good manufacturability, open structure and strong bearing capacity. The frame skeleton is usually a truss beam type structure, the upper joint and the lower joint transmit force in parallel through a main bearing beam, and the auxiliary structure relieves stress concentration or is supported by adopting a forge piece or a rod piece to be integrally assembled and welded.
As a first-stage engine of a type of vertical take-off and landing reusable carrier rocket, two large single engines and two small single engines (engines) are adopted, four single engines are arranged in the arrow diameter of 3350mm, when the rocket takes off, the four engines are simultaneously ignited to work, fuel and oxidant in a rocket storage tank enter a combustion chamber through a supply system and a control system, the fuel and the oxidant are combusted into high-temperature and high-pressure fuel gas, the high-temperature and high-pressure fuel gas is ejected at high speed through a thrust chamber nozzle to form a recoil action to generate thrust, and the thrust is transmitted to the rocket through a thrust chamber head, a.
Because the height sizes of the large engine and the small engine are different greatly, the height of the small engine is half of that of the large engine, generally speaking, the lower end of the rack is connected with the engine, the lower sections of the four engine thrust chambers are on the same plane, the upper ends of the four engine thrust chambers are flush with the rocket body, if the four-engine parallel rack is designed, a long force transmission structure needs to be designed, the thrust of the small engine is transmitted to the rocket body, the four-engine rack transmits force to the same tail section butt joint face, and for the small engine, the rack is long and the supporting assembly is complicated; if the arrow body sets up suspension structure, reduce the butt joint face of little engine, then occupy cabin section space, the structure utilization efficiency is low. Therefore, a rack structure of the primary engine needs to be reasonably designed, so that the engine and the rocket body are coordinated and optimized, and the occupied cabin space is reduced.
Disclosure of Invention
The engine aims to solve the problems that the existing primary engine has a long frame and a complicated supporting assembly due to the large and small engine height size difference; or the space of the cabin section is occupied, and the structural utilization efficiency is low.
In order to achieve the purpose, the technical scheme provided by the invention is as follows:
a light side wall suspension vertical force transmission frame is characterized in that: the connecting device comprises a cross joint, 4 main joints, 4 connecting rods, 2I-beams and 2 dowel bars;
the 4 connecting rods are sequentially and respectively connected end to end through 4 main joints to form a rectangular frame;
the 4 main joints are respectively a first main joint, a second main joint, a third main joint and a fourth main joint;
the 2I-beams are respectively a first I-beam and a second I-beam, one end of the first I-beam is connected with the third main joint, and the other end of the first I-beam is connected with a first interface of the cross joint;
one end of the second I-beam is connected with the fourth main joint, the other end of the second I-beam is connected with a second interface of the cross joint, and the second interface is adjacent to the first interface; a connecting rod between the third main joint and the fourth main joint and the 2I-beams form a first isosceles right angle triangular frame, and the included angle between the plane of the first isosceles right angle triangular frame and the plane of the rectangular frame is 93 degrees;
one end of each of the 2 dowel bars is connected with the first main joint and the second main joint respectively, and the other end of each of the 2 dowel bars is connected with the upper surface, parallel to the first isosceles right-angle triangular frame, of the cross joint;
the lower surface of the cross joint is used for mounting a small engine.
The device further comprises a first servo mechanism mounting joint, a first connecting rod, a second connecting rod, a supporting rod and a second servo mechanism mounting joint;
one end of the first connecting rod is connected with a third interface of the cross joint, the third interface is adjacent to the second interface, and the other end of the first connecting rod is connected with the first servo mechanism mounting joint;
one end of the second connecting rod is connected with one end of the second I-beam, the other end of the second connecting rod is connected with the first servo mechanism mounting joint, the first connecting rod, the second connecting rod and the second I-beam form a second isosceles right triangular frame, and the second isosceles right triangular frame and the first isosceles right triangular frame are positioned on the same plane;
one end of the supporting rod is connected with the first main joint, and the other end of the supporting rod is connected with the upper surface of the first servo mechanism mounting joint;
the second servo mechanism mounting joint is arranged on the lower surface of one end of the second I-shaped beam;
and the lower surface of the first servo mechanism mounting joint and the lower surface of the second servo mechanism mounting joint are used for mounting an external servo mechanism.
Furthermore, a first mounting pipe for mounting a dowel bar is arranged on the first main joint;
the first installation pipe is connected with a second installation pipe used for installing the supporting rod, and the second installation pipe is communicated with the first installation pipe.
Furthermore, a third mounting pipe for mounting the dowel bar is arranged on the second main joint.
Furthermore, the cross joint upper surface is equipped with the V type cavity installation pipe that is used for installing the dowel steel, the other end of 2 dowel steels all passes through V type cavity installation pipe and cross joint and goes up the upper surface that is on a parallel with first isosceles right angle triangular frame and be connected.
Furthermore, the joint of the first installation pipe and the first main joint and the joint of the second installation pipe and the first installation pipe adopt butt weld seams;
the joint of the third installation pipe and the second main joint adopts butt welding;
the joint of the V-shaped hollow installation pipe and the upper surface of the cross joint adopts butt welding.
Further, the first main joint, the first installation pipe and the second installation pipe are integrally arranged;
the second main joint and the third mounting pipe are integrally arranged;
the cross joint and the V-shaped hollow installation pipe are integrally arranged.
Furthermore, the distance from the center of the second main joint to the center of the third main joint is set as the height of the force transmission rack, and the distance from the center of the cross joint to the connecting rod between the third main joint and the fourth main joint is set as the cantilever length of the force transmission rack;
the ratio of the height of the force transmission rack to the length of the cantilever of the force transmission rack is 1.6: 1.
furthermore, the cross joint, the main joint, the connecting rod, the I-beam, the dowel bar, the first servo mechanism mounting joint, the first connecting rod, the second connecting rod, the supporting rod and the second servo mechanism mounting joint are all made of alloy steel 30CrMnSiA materials.
Meanwhile, the invention provides a primary engine, which comprises an arrow body, 2 small engines, 2 large engines and a first frame, wherein the 2 small engines, the 2 large engines and the first frame are arranged in the arrow body, and the primary engine is characterized in that: the device also comprises 2 light side wall suspension vertical force transmission frames;
4 main joints of each light side wall suspension vertical force transmission rack are arranged on the inner wall of the arrow body;
the 2 small engines are respectively arranged on the lower surfaces of the cross joints of the 2 light side walls suspended vertical force transmission racks.
Compared with the prior art, the invention has the advantages that:
1. the vertical force transmission rack is independently designed for the installation mode of small engines with low height and small thrust, so that the low-efficiency structure and the inconsistent deformation of the whole rack with four parallel machines are avoided, the length of a propellant supply conduit of the small engine is shortened, and the small conduit is short and stable; the small engine is connected with the rocket body wall through the force transmission rack, the force transmission rack is small in overall size, particularly the height size is greatly reduced, the whole weight is light, the force transmission path is short, and the thrust transmission efficiency is high; and the force transmission frame has low processing cost, the small engine is independently installed, the maintenance is convenient, the reserved space in the rocket body cabin section is large, and the operation is convenient.
The included angle between the plane where the first isosceles right-angle triangular frame is located and the plane where the rectangular frame is located is designed to be 93 degrees, so that the whole small engine inclines outwards for 3 degrees after being installed, the large engine and the small engine can both realize cycloidal motion, and the operation between the large engine and the small engine cannot be influenced.
2. The vertical force transmission rack is provided with the servo mechanism mounting joint, and the external servo mechanism is mounted on the force transmission rack through the mounting joint, so that the force transmission of the external servo mechanism to the rack can be realized.
3. According to the vertical force transmission machine frame, the mounting pipe is connected to the main joint, the mounting pipe and the main joint are integrally designed, and the butt welding seam is adopted at the connecting part, so that the local stress concentration is reduced, and the structural stability of the force transmission machine frame is improved.
Drawings
FIG. 1 is a schematic view of a lightweight sidewall suspended vertical force transfer frame according to the present invention;
FIG. 2 is a first schematic view of the first primary connection of the lightweight sidewall suspended vertical force transfer housing of the present invention;
FIG. 3 is a second schematic structural view of the first primary connection of the lightweight sidewall suspended vertical force transfer housing of the present invention;
FIG. 4 is a cross-sectional view of a first primary connection in a lightweight sidewall suspended vertical force transfer housing according to the invention;
FIG. 5 is a schematic view of the construction of the V-shaped hollow mounting tube in the lightweight sidewall suspended vertical force transfer housing of the present invention;
FIG. 6 is a top view of FIG. 5;
FIG. 7 is a sectional view A-A of FIG. 6;
FIG. 8 is a schematic perspective view of a cross joint in a lightweight sidewall suspended vertical force transfer frame according to the present invention;
FIG. 9 is a top view of a cross joint in a lightweight sidewall suspended vertical force transfer frame according to the present invention;
FIG. 10 is a transverse cross-sectional view of a cross joint in a lightweight sidewall suspended vertical force transfer frame according to the present invention;
FIG. 11 is a plan expanded view of a four-engine layout of the one-stage engine of the present invention;
wherein the reference numbers are as follows:
1-connecting rod, 2-first main joint, 21-first mounting pipe, 22-second mounting pipe, 3-second main joint, 31-third mounting pipe, 4-third main joint, 5-fourth main joint, 6-first I-beam, 7-second I-beam, 8-cross joint, 81-first interface, 82-second interface, 83-third interface, 84-fourth interface, 85-V type hollow mounting pipe, 9-force transmission rod, 10-first servo mechanism mounting joint, 11-first connecting rod, 12-second connecting rod, 13-supporting rod, 14-component supporting frame, 15-light side wall suspension vertical force transmission frame, 16-first frame, 17-arrow body, 18-small engine, 19-large engine, 20-second servo mechanism mounting joint.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
The force transmission device is based on four-machine assembly layout, has certain strength and rigidity, can bear wide-range load change, is light and efficient, and is simple and reliable in structure in a limited space.
As a first-stage engine of the carrier rocket capable of being repeatedly used in vertical take-off and landing, the carrier rocket adopts four engines, namely two large engines and two small engines, to form combined power, and is used as the main power of the rocket, and because the large engine and the small engine have large height and large appearance difference, the two large engines are installed and designed into a split type frame, the two large engines are fixed by adopting the existing frame structure, and the two small engines with small height and small thrust in the four engines are independently designed into a force transmission frame; because the radial distance of the small engines is large, each small engine is closer to the rocket wall, and therefore the thrust of the small engines can be transmitted to the rocket through vertical force transmission by utilizing the supporting structure of the rocket body.
As shown in fig. 1 to 10, a lightweight side wall suspended vertical force transfer frame for connecting a small engine comprises a cross joint 8, 4 main joints, 4 connecting rods 1, 2 i-beams and 2 force transfer rods 9; the 4 connecting rods 1 are sequentially and respectively connected end to end through 4 main joints to form a rectangular frame; the 4 main joints are respectively a first main joint 2, a second main joint 3, a third main joint 4 and a fourth main joint 5, the 2I-beams are respectively a first I-beam 6 and a second I-beam 7, one end of the first I-beam 6 is connected with the third main joint 4, and the other end of the first I-beam is connected with a first interface 81 of the cross joint 8; one end of the second i-beam 7 is connected with the fourth main joint 5, and the other end is connected with the second interface 82 of the cross joint 8; the second port 82 is adjacent to the first port 81; a connecting rod 1 between a third main joint 4 and a fourth main joint 5 and 2I-beams form a first isosceles right angle triangular frame, one end of each of 2 dowel bars 9 is respectively connected with the first main joint 2 and the second main joint 3, and the other end of each of 2 dowel bars 9 is connected with the upper surface, parallel to the first isosceles right angle triangular frame, of a cross joint 8; the lower surface of the spider 8 is used for mounting a small engine 18. The specific structural form of the butt joint of the frame, the engine and the inner wall of the arrow body can be designed according to the requirements of the engine interface and the arrow body interface. In order to coordinate the distances between the engines and the arrow bodies, the included angle between the plane where the first isosceles right-angle triangular frame is located and the plane where the rectangular frame is located is designed to be 93 degrees, namely the included angles between the four joint planes butted with the arrow walls and the engine butting plane are 93 degrees, so that the whole small engine inclines outwards for 3 degrees after being installed, the large engine and the small engine can realize cycloidal motion, and the work between the large engine and the small engine cannot influence the operation between the large engine and the small engine.
The 4 connecting rods comprise two vertical connecting rods arranged in parallel and two horizontal connecting rods arranged in parallel; the first main joint 2, the second main joint 3, the third main joint 4 and the fourth main joint 5 are symmetrically distributed in the same plane, the four main joints are respectively connected with the I-beam and the dowel bar, the vertical connecting rod coordinates the deformation of the upper main joint (the first main joint 2, the second main joint 3) and the lower main joint (the third main joint 4 and the fourth main joint 5), and the transverse connecting rod seals the joints, so that the force transmission rack is stable in structure and welding deformation is reduced. The lower end of the cross joint 8 is connected with a small engine, and the cross joint 8 is a force transmission central point of the rack. The main joint and the cross joint 8 are designed in a topological way, only the bearing framework is reserved, and the internal low-efficiency structure is removed, so that the force transmission rack is light in weight.
The force transmission rack of the embodiment further comprises a first servo mechanism mounting joint 10, a first connecting rod 11, a second connecting rod 12, a supporting rod 13 and a second servo mechanism mounting joint 20; one end of the first connecting rod 11 is connected with the third interface 83 of the cross joint 8, the third interface 83 is adjacent to the second interface 82, and the other end is connected with the first servo mechanism mounting joint 10; one end of a second connecting rod 12 is connected with one end of a second I-beam 7, the other end of the second connecting rod 12 is connected with a first servo mechanism mounting joint 10, a second isosceles right-angle triangular frame is formed by the first connecting rod 11, the second connecting rod 12 and the second I-beam 7, and the second isosceles right-angle triangular frame and the first isosceles right-angle triangular frame are located on the same plane; one end of the support rod 13 is connected with the first main joint 2, and the other end thereof is connected with the upper surface of the first servo mechanism mounting joint 10; the second servo mechanism mounting joint 20 is arranged on the lower surface of one end of the second I-shaped beam 7, the lower surface of the first servo mechanism mounting joint 10 and the lower surface of the second servo mechanism mounting joint 20 are both used for mounting an external servo mechanism, and the servo mechanism is mounted on the rack through the servo mechanism mounting joints to realize the force transmission of the external servo mechanism to the parallel rack. The second servo mechanism mounting joint is directly arranged on the second I-beam, so that the deformation is reduced, the first-order frequency of the frame torsion is improved, the first servo mechanism mounting joint is stabilized by the first connecting rod 11, the second connecting rod 12 and the supporting rod 13, and the design is the simplest supporting mode and the supporting structure on the premise of meeting the requirements on strength and rigidity.
A first mounting pipe 21 for mounting the dowel bar 9 is arranged on the first main joint 2, a second mounting pipe 22 for mounting the support rod 13 is connected to the first mounting pipe 21, the second mounting pipe 22 is communicated with the first mounting pipe 21, and the second mounting pipe 22 and the first mounting pipe 21 are arranged in a V-shaped manner; a third mounting pipe 31 for mounting the dowel bar 9 is arranged on the second main joint 3; each main joint and the installation pipe connected with the main joint are designed integrally, the position of a welding seam avoids the stress concentration position of the installation pipe, the welding seam of the joint of the first installation pipe 21 and the first main joint 2, the joint of the third installation pipe 31 and the second main joint 3, and the welding seam of the upper surface joint of the V-shaped hollow installation pipe 85 and the cross joint 8 is changed into a butt welding seam from a fillet welding seam through interface optimization, the whole main joint and the installation pipe are forged piece machining processes, the middle low-efficiency position is empty, the structural utilization rate is improved, and the joint is light and efficient.
The intersection of two dowel bars 9 on the upper surface of the cross joint 8 is provided with a center joint, the center joint is a V-shaped hollow installation pipe 85, the center joint is simplified into a Y-shaped component according to a force transmission path, the split welding of slope openings at the joints of multiple bars is avoided, and the center joint is made into a hollow structure through topological optimization, so that the joint is light and efficient. The cross joint 8 is the force center of the whole force transmission frame, the lower end surface is butted with an engine, an I-shaped interface structure coordinated with a bearing beam extends outwards from the cross, a framework is reserved along the main bearing direction, the material of the middle part is removed, and the cross joint 8 is provided with a connecting bolt hole for connecting a small engine; the connecting bolt holes are uniformly distributed at four corners with open space, so that the installation is convenient; the fourth interface 84 of the spider 8 is connected to the assembly support frame 14, the assembly support frame 14 being adapted to support an external servomechanism.
The width of the force transmission frame is determined by the cross beam and the distribution circle of the engine. The engine is 3 erection angles that lean out, establishes the second main joint 3 center and establishes the distance to the third main joint 4 center for the height of biography power frame, and the distance of cross joint 8 center to connecting rod 1 between third main joint 4 and the fourth main joint 5 is the cantilever of biography power frame, and the height of biography power frame and the cantilever length proportion of biography power frame are 1.6: 1, the stress concentration of the joint and the installation pipe is greatly relieved under the condition of meeting the requirements of the strength and the rigidity of the rack, and meanwhile, the main bearing structure of the rack has the lightest weight.
All parts of the force transmission rack (the cross joint 8, the main joint, the connecting rod 1, the I-beam, the force transmission rod 9, the first servo mechanism mounting joint 10, the first connecting rod 11, the second connecting rod 12 and the supporting rod 13) of the embodiment are made of high-strength alloy steel 30CrMnSiA, and basic guarantee is provided for designing the rack with excellent strength and rigidity. By optimizing the force transmission path, the thrust of the engine is vertically transmitted to the wall of the rocket cabin, and the overall size of the frame is reduced. The worst load is taken as an input condition, and an optimal combination is screened out through multi-scheme calculation and comparison according to an equal-strength design principle, so that the strength, the rigidity and the stability of the rack meet the requirements.
The force transmission rack of the embodiment can be popularized and applied to the fields of solid rocket engines, other military systems and civil use with similar force transmission requirements.
The small engine frame of the embodiment has the advantages that the small engine frame is independently designed with low height and small thrust, so that the low-efficiency structure and inconsistent deformation of the four parallel-connected frames are avoided, the length of a propellant supply guide pipe of the small engine is shortened, the small guide pipe is short and stable, and the supporting structure is simplified; the force transmission rack provided with the small engine and the rocket body force transmission structure are integrally designed, the overall size of the rack is small, particularly, the height is greatly reduced, the overall weight is light, the force transmission path is short, and the thrust transmission efficiency is high. The force transmission rack has low processing cost, a small engine is independently installed, the maintenance is convenient, the reserved space in the rocket body cabin section is large, and the operation is convenient; the scheme of hanging the frame on the side wall realizes the vertical transmission of the thrust between the engine and the rocket body on the vertical joint surface for the first time, improves the utilization rate of the structure, and solves the problem that the quality of the engine is reduced and the first-order low frequency of a small loop is improved; the scheme of the side wall frame follows the equal-strength design principle, the joint adopts the integral design, the fillet weld of the existing root (the joint of the dowel bar and the supporting rod) is eliminated, and the local stress concentration is reduced. The hollow design of the joint and the mounting pipe simplifies the structure with low efficiency, lightens the weight of the frame and improves the engine thrust-mass ratio.
The force transmission frame is used for a reusable rocket return main power device for vertical take-off and landing to transmit thrust. The operation of the engines with different thrust forces, which form combined power by switching, is one of the ways of realizing the large-range thrust adjustment of takeoff and landing of the recoverable rocket. The combined power system is complex, the thrust-mass ratio is sensitive, the layout space is limited, and the integrated machine frame is difficult to match different thrusts and is not adaptive any more. The invention breaks through the traditional design idea of integral parallel force transmission, arranges a vertical force transmission path along the supporting structure of the rocket tail section, fully utilizes the layout space between the large-thrust engine and the rocket wall, and realizes the integrated design of connection and force transmission of the small engine and the rocket body. The invention has simple and reliable structure, portability and flexibility, ensures that the combined power is coordinated and matched in the arrow body, has compact layout and meets the requirement of cycloidal motion in the respective working process.
Based on the force transmission rack, the embodiment provides a first-stage engine for a vertical take-off and landing reusable carrier rocket, a plane development view of a four-engine layout is shown in fig. 11, and two large engines and two small engines form combined power to serve as the main power of the rocket. The engine comprises an arrow body 17, 2 small engines 18 arranged in the arrow body 17, 2 large engines 19, a first frame 16 for mounting the 2 large engines 19, and 2 light-weight side wall suspension vertical force transmission frames 15; 4 main joints of each light side wall suspension vertical force transmission frame 15 are arranged on the inner wall of the arrow body 17; 2 small engines 18 are respectively arranged on the lower surfaces of the cross joints 8 of the 2 light side wall suspension vertical force transmission racks; because the two types of engines have larger height and appearance difference, the split type frame is designed to be an optimal structural scheme, the small engine 18 with small appearance and height is independently designed to be the split type small frame, the characteristic that the thrust of the small engine is small is coordinated and matched, the small engine is hung on the existing supporting rocket body framework structure on the inner wall of the rocket body, and the fixed installation and the thrust transmission of the small engine are realized. Compared with the existing parallel force transmission rack, the vertical force transmission realizes the integrated collaborative design of the rocket body force transmission structure and the engine rack, avoids unnecessary superposition of the rocket body structure and the rack safety coefficient, reduces the structure weight, shortens the force transmission path and optimizes the rocket body space.
The above description is only for the purpose of describing the preferred embodiments of the present invention and does not limit the technical solutions of the present invention, and any known modifications made by those skilled in the art based on the main technical concepts of the present invention fall within the technical scope of the present invention.
Claims (10)
1. The utility model provides a vertical power frame that passes that hangs of light lateral wall which characterized in that: comprises a cross joint (8), 4 main joints, 4 connecting rods (1), 2I-beams and 2 dowel bars (9);
the 4 connecting rods (1) are sequentially and respectively connected end to end through 4 main joints to form a rectangular frame;
the 4 main joints are respectively a first main joint (2), a second main joint (3), a third main joint (4) and a fourth main joint (5);
the 2I-beams are respectively a first I-beam (6) and a second I-beam (7), one end of the first I-beam (6) is connected with the third main joint (4), and the other end of the first I-beam is connected with a first interface (81) of the cross joint (8);
one end of the second I-shaped beam (7) is connected with the fourth main joint (5), the other end of the second I-shaped beam is connected with a second interface (82) of the cross joint (8), and the second interface (82) is adjacent to the first interface (81); a connecting rod (1) between the third main joint (4) and the fourth main joint (5) and the 2I-beams form a first isosceles right-angle triangular frame, and the included angle between the plane of the first isosceles right-angle triangular frame and the plane of the rectangular frame is 93 degrees;
one end of each of the 2 dowel bars (9) is connected with the first main joint (2) and the second main joint (3) respectively, and the other end of each of the 2 dowel bars (9) is connected with the upper surface, parallel to the first isosceles right-angle triangular frame, of the cross joint (8);
the lower surface of the cross joint (8) is used for mounting a small engine (18).
2. The lightweight sidewall suspended vertical force transfer frame of claim 1, wherein: the device also comprises a first servo mechanism mounting joint (10), a first connecting rod (11), a second connecting rod (12), a supporting rod (13) and a second servo mechanism mounting joint (20);
one end of the first connecting rod (11) is connected with a third interface (83) of the cross joint (8), the third interface (83) is adjacent to the second interface (82), and the other end of the third interface is connected with the first servo mechanism mounting joint (10);
one end of the second connecting rod (12) is connected with one end of the second I-shaped beam (7), the other end of the second connecting rod (12) is connected with the first servo mechanism mounting joint (10), the first connecting rod (11), the second connecting rod (12) and the second I-shaped beam (7) form a second isosceles right triangular frame, and the second isosceles right triangular frame and the first isosceles right triangular frame are located on the same plane;
one end of the supporting rod (13) is connected with the first main joint (2), and the other end of the supporting rod is connected with the upper surface of the first servo mechanism mounting joint (10);
the second servo mechanism mounting joint (20) is arranged on the lower surface of one end of the second I-shaped beam (7);
the lower surface of the first servo mechanism mounting joint (10) and the lower surface of the second servo mechanism mounting joint (20) are used for mounting external servo mechanisms.
3. The lightweight sidewall suspended vertical force transfer frame of claim 2, wherein: a first mounting pipe (21) for mounting a dowel bar (9) is arranged on the first main joint (2);
the first installation pipe (21) is connected with a second installation pipe (22) used for installing the support rod (13), and the second installation pipe (22) is communicated with the first installation pipe (21).
4. The lightweight sidewall suspended vertical force transfer frame of claim 3, wherein: and a third mounting pipe (31) for mounting the dowel bar (9) is arranged on the second main joint (3).
5. The lightweight sidewall suspended vertical force transfer frame of claim 4, wherein: the cross joint (8) upper surface is equipped with V type cavity installation pipe (85) that are used for installing dowel steel (9), the other end of 2 dowel steel (9) all is on a parallel with through V type cavity installation pipe (85) and cross joint (8) first isosceles right angle triangular frame's upper surface is connected.
6. The lightweight sidewall suspended vertical force transfer frame of claim 5, wherein: the joint of the first mounting pipe (21) and the first main joint (2) and the joint of the second mounting pipe (22) and the first mounting pipe (21) adopt butt weld seams;
the joint of the third mounting pipe (31) and the second main joint (3) adopts butt welding;
the joint of the V-shaped hollow installation pipe (85) and the upper surface of the cross joint (8) adopts butt welding.
7. The lightweight sidewall suspended vertical force transfer frame of claim 5, wherein: the first main joint (2) is integrally arranged with the first installation pipe (21) and the second installation pipe (22);
the second main joint (3) and the third mounting pipe (31) are integrally arranged;
the cross joint (8) and the V-shaped hollow installation pipe (85) are integrally arranged.
8. A lightweight sidewall suspended vertical force transfer frame as claimed in any one of claims 1 to 7, wherein: setting the distance from the center of the second main joint (3) to the center of the third main joint (4) as the height of the force transmission rack, and setting the vertical distance from the center of the cross joint (8) to the connecting rod (1) between the third main joint (4) and the fourth main joint (5) as the cantilever length of the force transmission rack;
the ratio of the height of the force transmission rack to the length of the cantilever of the force transmission rack is 1.6: 1.
9. the lightweight sidewall suspended vertical force transfer frame of claim 8, wherein: the cross joint (8), the main joint, the connecting rod (1), the I-shaped beam, the dowel steel (9), the first servo mechanism mounting joint (10), the first connecting rod (11), the second connecting rod (12), the supporting rod (13) and the second servo mechanism mounting joint (20) are all made of alloy steel 30CrMnSiA materials.
10. A one-level engine comprises an arrow body (17), 2 small engines (18) arranged in the arrow body (17), 2 large engines (19) and a first frame (16) used for installing the 2 large engines (19), and is characterized in that: -further comprising 2 lightweight sidewall suspended vertical force transfer housings (15) according to any of claims 1 to 8;
4 main joints of each light side wall suspension vertical force transmission rack (15) are arranged on the inner wall of the arrow body (17);
2 small engines (18) are respectively arranged on the lower surfaces of the cross joints (8) of the 2 light side wall suspension vertical force transmission racks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911303993.9A CN111114834B (en) | 2019-12-17 | 2019-12-17 | Light side wall suspension vertical force transmission rack and primary engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911303993.9A CN111114834B (en) | 2019-12-17 | 2019-12-17 | Light side wall suspension vertical force transmission rack and primary engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111114834A true CN111114834A (en) | 2020-05-08 |
| CN111114834B CN111114834B (en) | 2021-05-04 |
Family
ID=70499460
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911303993.9A Active CN111114834B (en) | 2019-12-17 | 2019-12-17 | Light side wall suspension vertical force transmission rack and primary engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111114834B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111810317A (en) * | 2020-08-11 | 2020-10-23 | 安徽九州云箭航天技术有限公司 | Rocket engine frame |
| CN112943482A (en) * | 2021-01-26 | 2021-06-11 | 西安航天动力研究所 | Integral frame of liquid rocket engine |
| CN114056603A (en) * | 2021-11-16 | 2022-02-18 | 哈尔滨工业大学 | Space high folding-unfolding ratio dragging-unfolding type high-rigidity stretching arm |
| CN116447043A (en) * | 2023-03-16 | 2023-07-18 | 大连理工大学 | Main frame structure of carrier rocket engine with box-type section load beam |
| CN117249019A (en) * | 2023-09-25 | 2023-12-19 | 江苏天兵航天科技有限公司 | Three-engine parallel structure of rocket engine and rocket |
| CN118423565A (en) * | 2024-07-03 | 2024-08-02 | 西安航天动力研究所 | Force transmission frame of rocket engine |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2557674A1 (en) * | 1975-01-03 | 1976-07-08 | List Hans | Testbed for internal combustion engines - with easily attachable supply and exhaust facilities is designed for rapid removal and replacement of engine |
| US4452412A (en) * | 1982-09-15 | 1984-06-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Space shuttle with rail system and aft thrust structure securing solid rocket boosters to external tank |
| CN87107285A (en) * | 1986-12-04 | 1988-06-15 | 克莱因香林及贝克尔股份公司 | The chassis bracket of turbo machine |
| JPH09193899A (en) * | 1996-01-18 | 1997-07-29 | Mitsubishi Heavy Ind Ltd | Retaining device for elastic remote center |
| JPH109056A (en) * | 1996-06-27 | 1998-01-13 | Nippon Yuso Eng Kk | Hangar type aircraft engine testing facilities and method |
| JP2002156311A (en) * | 2000-11-21 | 2002-05-31 | Kawasaki Heavy Ind Ltd | Hangar type aircraft ground test equipment |
| CN2839997Y (en) * | 2005-10-24 | 2006-11-22 | 成都发动机（集团）有限公司 | Suspension type engine test run rack |
| US7540145B2 (en) * | 2003-03-28 | 2009-06-02 | Mojave Aerospace Ventures, Llc | Unitized hybrid rocket system |
| CN101907041A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
| CN103742768A (en) * | 2013-10-10 | 2014-04-23 | 国家电网公司 | Automatic leveling device for suspension equipment |
| CN205138790U (en) * | 2015-10-12 | 2016-04-06 | 桂林电子科技大学 | Ware is put to six gestures in engine |
| US20170036782A1 (en) * | 2013-11-19 | 2017-02-09 | Arthur Dula | Launch apparatus |
| CN106628266A (en) * | 2017-01-13 | 2017-05-10 | 哈尔滨工业大学 | Suspension type composite storage box structure |
| CN106644488A (en) * | 2016-09-20 | 2017-05-10 | 天津航天瑞莱科技有限公司 | Large rocket engine and support integral overturn fixture |
| CN109780541A (en) * | 2018-12-21 | 2019-05-21 | 西安航天动力研究所 | The pneumatic nebulization liquid liquid jet method and ejector filler of a wide range of variable working condition can be achieved |
-
2019
- 2019-12-17 CN CN201911303993.9A patent/CN111114834B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2557674A1 (en) * | 1975-01-03 | 1976-07-08 | List Hans | Testbed for internal combustion engines - with easily attachable supply and exhaust facilities is designed for rapid removal and replacement of engine |
| US4452412A (en) * | 1982-09-15 | 1984-06-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Space shuttle with rail system and aft thrust structure securing solid rocket boosters to external tank |
| CN87107285A (en) * | 1986-12-04 | 1988-06-15 | 克莱因香林及贝克尔股份公司 | The chassis bracket of turbo machine |
| JPH09193899A (en) * | 1996-01-18 | 1997-07-29 | Mitsubishi Heavy Ind Ltd | Retaining device for elastic remote center |
| JPH109056A (en) * | 1996-06-27 | 1998-01-13 | Nippon Yuso Eng Kk | Hangar type aircraft engine testing facilities and method |
| JP2002156311A (en) * | 2000-11-21 | 2002-05-31 | Kawasaki Heavy Ind Ltd | Hangar type aircraft ground test equipment |
| US7540145B2 (en) * | 2003-03-28 | 2009-06-02 | Mojave Aerospace Ventures, Llc | Unitized hybrid rocket system |
| CN2839997Y (en) * | 2005-10-24 | 2006-11-22 | 成都发动机（集团）有限公司 | Suspension type engine test run rack |
| CN101907041A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
| CN103742768A (en) * | 2013-10-10 | 2014-04-23 | 国家电网公司 | Automatic leveling device for suspension equipment |
| US20170036782A1 (en) * | 2013-11-19 | 2017-02-09 | Arthur Dula | Launch apparatus |
| CN205138790U (en) * | 2015-10-12 | 2016-04-06 | 桂林电子科技大学 | Ware is put to six gestures in engine |
| CN106644488A (en) * | 2016-09-20 | 2017-05-10 | 天津航天瑞莱科技有限公司 | Large rocket engine and support integral overturn fixture |
| CN106628266A (en) * | 2017-01-13 | 2017-05-10 | 哈尔滨工业大学 | Suspension type composite storage box structure |
| CN109780541A (en) * | 2018-12-21 | 2019-05-21 | 西安航天动力研究所 | The pneumatic nebulization liquid liquid jet method and ejector filler of a wide range of variable working condition can be achieved |
Non-Patent Citations (1)
| Title |
|---|
| 王文龙: "应变测试技术应用于发动机质心偏移研究", 《火箭推进》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111810317A (en) * | 2020-08-11 | 2020-10-23 | 安徽九州云箭航天技术有限公司 | Rocket engine frame |
| CN112943482A (en) * | 2021-01-26 | 2021-06-11 | 西安航天动力研究所 | Integral frame of liquid rocket engine |
| CN112943482B (en) * | 2021-01-26 | 2022-08-12 | 西安航天动力研究所 | Integral frame of liquid rocket engine |
| CN114056603A (en) * | 2021-11-16 | 2022-02-18 | 哈尔滨工业大学 | Space high folding-unfolding ratio dragging-unfolding type high-rigidity stretching arm |
| CN116447043A (en) * | 2023-03-16 | 2023-07-18 | 大连理工大学 | Main frame structure of carrier rocket engine with box-type section load beam |
| CN116447043B (en) * | 2023-03-16 | 2023-09-01 | 大连理工大学 | Main frame structure of carrier rocket engine with box-type section load beam |
| CN117249019A (en) * | 2023-09-25 | 2023-12-19 | 江苏天兵航天科技有限公司 | Three-engine parallel structure of rocket engine and rocket |
| CN117249019B (en) * | 2023-09-25 | 2024-06-11 | 江苏天兵航天科技有限公司 | Three-engine parallel structure of rocket engine and rocket |
| CN118423565A (en) * | 2024-07-03 | 2024-08-02 | 西安航天动力研究所 | Force transmission frame of rocket engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111114834B (en) | 2021-05-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111114834B (en) | Light side wall suspension vertical force transmission rack and primary engine | |
| CN101824905B (en) | Assembly type variable steel girder platform, distribution method and assembly method thereof | |
| CN214272390U (en) | Rigid reinforced connection node of H-shaped steel column and I-shaped steel beam | |
| CN115929507A (en) | Light three-engine parallel engine frame | |
| TW202142777A (en) | Assembly of a jacket structure | |
| CN203145482U (en) | Steel structural member assembling and aligning device | |
| CN210507344U (en) | Series-type surge-chamber for hydropower station | |
| CN207959499U (en) | A kind of steel construction | |
| CN106368322A (en) | Installing method of bidirectional symmetric oblique steel posts used between super high-rise building transfer stories | |
| CN215802266U (en) | Direct-insertion type bolt-free connecting joint of closed cavity column and steel beam | |
| CN214994605U (en) | Modularization steel structure spare | |
| CN206681165U (en) | A kind of full bolt beam-column connection of assembled | |
| CN113463754A (en) | Assembled branch type cable support prestressed column suitable for multi-angle connection | |
| CN105021404A (en) | Curved-type heavy loading force structure for liquid rocket propulsion system test | |
| CN112726375A (en) | Sectional type steel truss bridge and construction method thereof | |
| CN220150515U (en) | Assembled beam column node | |
| CN217299283U (en) | Steel construction node is with reinforceing component | |
| CN216810279U (en) | Connecting structure of beam and vertical supporting member | |
| CN113606058B (en) | Force transmission device of boosting rocket | |
| CN2075255U (en) | Ordinary h shaped steel derrick | |
| CN212534514U (en) | Folding steel structure | |
| CN205399663U (en) | Connection structure of pipe post and H type roof beam | |
| CN217651601U (en) | Adjustable steel pipe column joint | |
| CN219491064U (en) | Variable-inclination offshore wind turbine jacket foundation structure suitable for deep open sea | |
| CN109779016A (en) | A kind of Self-resetting frame center support system with end plate connecting node |
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 |