CN115900454A - Honeycomb type integrated engine cabin structure - Google Patents
Honeycomb type integrated engine cabin structure Download PDFInfo
- Publication number
- CN115900454A CN115900454A CN202211280328.4A CN202211280328A CN115900454A CN 115900454 A CN115900454 A CN 115900454A CN 202211280328 A CN202211280328 A CN 202211280328A CN 115900454 A CN115900454 A CN 115900454A
- Authority
- CN
- China
- Prior art keywords
- end frame
- heat
- proof
- supporting
- honeycomb
- 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.)
- Pending
Links
Images
Landscapes
- Body Structure For Vehicles (AREA)
Abstract
The honeycomb type integrated engine cabin structure comprises an upper end frame, a wall plate, a web plate, a lower end frame, a bearing beam, a heat-proof plate, a heat-proof beam, a supporting beam and a supporting block; the bearing beam is arranged in the upper end frame and fixedly connected with the upper end frame; the heat-proof beam is arranged in the lower end frame and fixedly connected with the lower end frame; a web is detachably arranged between the bearing beam and the heat-proof beam; the supporting beam is connected with the supporting block and then arranged between the upper end frame and the lower end frame; the heat-proof plate is fixedly connected with the lower end frame and the heat-proof beam; the wall plate is connected with the upper end frame and the lower end frame. The invention provides a frame and web structure, realizes integrated force transfer, is used as force transfer of a rocket ascending section and force transfer of a return section, greatly improves the force transfer efficiency, reduces the height of a frame, compresses the size of the rocket, and makes a contribution to the layout of other systems and the performance improvement of the rocket; meanwhile, the wall plate and the web plate can be assembled and disassembled, so that the convenience of ground operation maintenance of equipment such as an engine and a servo mechanism and maintenance after the rocket returns is improved.
Description
Technical Field
The invention relates to a functional structure design of a vehicle, in particular to an engine compartment structure of the vehicle.
Background
One substage of the carrier rocket which is repeatedly used in vertical take-off and landing is generally used by 5, 7 or 9 engines in parallel, and the requirement on the thrust adjusting capacity of the engine is reduced by utilizing the middle engine to ignite for a plurality of times for work and speed reduction. The arrangement of a plurality of engines ensures that the heat-proof beam and the heat-proof plate at the bottom of the engine compartment of the carrier rocket are designed to be cracked, the carrier rocket is influenced by atmospheric resistance in the return stage, and the heat-proof beam and the heat-proof plate at the bottom of the engine compartment need to have enough rigidity and strength.
The carrier rocket engine cabin repeatedly used in vertical take-off and landing needs to bear loads such as rocket vertical bearing, drag release, landing buffer mechanism, airflow impact when the rocket returns and the like, and the stress is severe and complex. The traditional engine room in a rod system frame mode cannot give consideration to loads such as airflow impact and the like when the carrier rocket is vertically lifted and repeatedly used and returns, the overall force transfer efficiency of the structure is low, and meanwhile, the space height is large, and the performance of the rocket is influenced.
Disclosure of Invention
The invention aims to provide a honeycomb type integrated engine cabin structure, which realizes integrated force transfer, is used for transferring force at a rising section of a carrier rocket and also used for transferring force at a return section of the carrier rocket, and greatly improves the force transfer efficiency; the height of the frame is reduced, and the carrier rocket makes contributions to the layout of other systems and the performance improvement of the rocket; meanwhile, the tail section wall plate and the web plate are of detachable structures, and convenience in ground operation maintenance of equipment such as an engine and a servo mechanism and maintenance after the carrier rocket returns is improved.
In order to achieve the purpose, the invention provides a honeycomb type integrated engine cabin structure, which comprises an upper end frame, a wall plate, a web plate, a lower end frame, a bearing beam, a heat-proof plate, a heat-proof beam, a supporting beam and a supporting block, wherein the upper end frame is provided with a first end plate and a second end plate; the bearing beam is arranged in the upper end frame and fixedly connected with the upper end frame; the heat-proof beam is arranged in the lower end frame and is fixedly connected with the lower end frame; the web plate is detachably arranged between the bearing beam and the heat-proof beam; the supporting beam is connected with the supporting block and then arranged between the upper end frame and the lower end frame; the heat-proof plate is fixedly connected with the lower end frame and the heat-proof beam; the wall plate is connected with the upper end frame and the lower end frame to form an engine compartment wall.
The honeycomb type integrated engine compartment structure is characterized in that the web plate adopts a honeycomb type bionic structure.
Above-mentioned honeycomb formula integration engine compartment structure, wherein, the web is removable structure.
The honeycomb type integrated engine cabin structure comprises an upper end frame, a lower end frame, a bearing beam, a heat-proof beam, a supporting beam and a supporting block which form a frame structure, and the whole engine cabin adopts a frame and web structure.
Above-mentioned honeycomb formula integration engine compartment structure, wherein, the force bearing roof beam is connected as an organic wholely through polylith dismantled and assembled web and heat-proof roof beam, realizes integration biography power.
In the honeycomb type integrated engine cabin structure, the bearing beam is provided with an engine mounting interface; the supporting block is provided with a landing buffer mechanism mounting interface, and the heat-proof plate is provided with an engine spray pipe opening.
The honeycomb type integrated engine cabin structure is characterized in that the supporting block is connected to one end of the supporting beam, the other end of the supporting beam is connected with the outer side wall of the annular upper end frame, the supporting block is connected with the outer side wall of the annular lower end frame, and the end face, which is not connected with the supporting beam, of the supporting block is provided with a landing buffer mechanism mounting interface.
In the honeycomb integrated engine room structure, a plurality of support beam and support block combinations are arranged between the upper end frame and the lower end frame, and the plurality of support beam and support block combinations are uniformly arranged along a cylinder.
In the honeycomb type integrated engine compartment structure, the wall plate is provided with a plurality of wall plates, and one wall plate is arranged between any two adjacent support beams and the support block; the wallboard with upper end frame with lower end frame detachable connections.
The bearing beam is a plane beam structure
Compared with the prior art, the invention has the beneficial technical effects that:
1) The honeycomb type integrated engine cabin structure adopts a frame and web structure, realizes integrated force transfer, is used for force transfer of a carrier rocket ascending section and force transfer of a carrier rocket returning section, and greatly improves the force transfer efficiency;
2) The honeycomb type integrated engine cabin structure adopts a frame and web structure, so that the bearing capacity of the combination of the bearing beam and the heat-proof plate is greatly enhanced, and therefore, the bearing beam can adopt a plane beam structure, compared with the traditional conical beam structure, the height of the engine cabin frame structure is reduced, the size of a carrier rocket is compressed, and the honeycomb type integrated engine cabin structure contributes to the layout of other systems of the carrier rocket and the performance improvement of the carrier rocket;
3) According to the honeycomb type integrated engine compartment structure, the web plate is detachably mounted, and the wall plate and the engine compartment frame structure are detachably mounted, so that the convenience of ground operation maintenance and maintenance after return of equipment such as an engine and a servo mechanism is improved; the web also can be used as an explosion-proof clapboard, thereby improving the safety.
Drawings
The honeycomb type integrated engine room structure of the present invention is given by the following embodiments and the accompanying drawings.
Fig. 1 is a schematic structural diagram of a honeycomb type integrated engine room according to a preferred embodiment of the present invention.
Detailed Description
The honeycomb-integrated engine compartment structure of the present invention will be described in further detail below with reference to fig. 1.
FIG. 1 is a schematic view of a honeycomb-type integrated engine room according to a preferred embodiment of the present invention.
Referring to fig. 1, the honeycomb type integrated engine room structure of the present embodiment includes an upper end frame 1, a wall plate 2, a web 3, a lower end frame 4, a bearing beam 5, a heat-proof plate 6, a heat-proof beam 7, a support beam 8 and a support block 9;
the bearing beam 5 is arranged in the upper end frame 1, and the bearing beam 5 is fixedly connected with the upper end frame 1;
the heat-proof beam 7 is arranged in the lower end frame 4, and the heat-proof beam 7 is fixedly connected with the lower end frame 4;
the web 3 is arranged between the bearing beam 5 and the heat-proof beam 7 in a detachable mode;
the supporting beam 8 is connected with the supporting block 9 and then arranged between the upper end frame 1 and the lower end frame 4;
the heat-proof plate 6 is fixedly connected with the lower end frame 4 and the heat-proof beam 7;
the wall plate 2 is positioned at the periphery of the upper end frame 1 and the lower end frame 4, and the wall plate 2 is connected with the upper end frame 1 and the lower end frame 4;
the bearing beam 5 is provided with an engine mounting interface; the supporting block 9 is provided with a landing buffer mechanism mounting interface, and the heat-proof plate 6 is provided with an engine jet pipe opening.
The web 3 adopts a honeycomb bionic structure; and a plurality of webs 3 are arranged between the bearing beam 5 and the heat-proof beam 7.
The honeycomb type integrated engine cabin structure of the embodiment is characterized in that a bearing beam 5 is arranged in an upper end frame 1, a heat-proof beam 7 is arranged in a lower end frame 4, the bearing beam 5 is connected with the heat-proof beam 7 into a whole through a plurality of detachable webs 3, a supporting beam 8 and a supporting block 9 are arranged between the upper end frame 1 and the lower end frame 4, wherein the upper end frame 1, the lower end frame 4, the bearing beam 5, the heat-proof beam 7, the supporting beam 8 and the supporting block 9 form a frame structure, and the whole engine cabin adopts a frame + web (honeycomb type bionic structure) structure.
The honeycomb type integrated engine compartment structure of the embodiment adopts the web 3 to connect the supporting beam 5 and the heat-proof beam 7, so that integrated force transmission is realized, the force transmission efficiency is greatly improved, and the engine compartment can bear airflow impact when a carrier rocket returns.
In this embodiment, the upper end frame 1 and the lower end frame 4 are both circular ring frames, the force-bearing beam 5 is arranged in the circular ring frame of the upper end frame 1, and the heat-proof beam 7 is arranged in the circular ring frame of the lower end frame 4; the end face of the bearing beam 5 facing the heat-proof beam is provided with an engine mounting interface;
the supporting block 9 is connected to one end of the supporting beam 8, the other end of the supporting beam 8 is connected with the outer side wall of the annular upper end frame 1, the supporting block 9 is connected with the outer side wall of the annular lower end frame 4, and a landing buffer mechanism mounting interface is arranged on the end face, not connected with the supporting beam 8, of the supporting block 9; a plurality of supporting beam 8 and supporting block 9 combinations are arranged between the upper end frame 1 and the lower end frame 4, and the plurality of supporting beam 8 and supporting block 9 combinations are uniformly distributed along a cylinder;
the wall plate 2 is connected with the outer side wall of the annular upper end frame 1 and the outer side wall of the annular lower end frame 4 through screws to form a bulkhead of the engine compartment; the wall plate 2 is provided with a plurality of wall plates, and one wall plate 2 is arranged between the combination of any two adjacent supporting beams 8 and supporting blocks 9;
the bearing beam 5 is a plane beam structure.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. The honeycomb type integrated engine cabin structure is characterized by comprising an upper end frame, a wall plate, a web plate, a lower end frame, a bearing beam, a heat-proof plate, a heat-proof beam, a supporting beam and a supporting block;
the bearing beam is arranged in the upper end frame and fixedly connected with the upper end frame;
the heat-proof beam is arranged in the lower end frame and is fixedly connected with the lower end frame;
the web plate is installed between the bearing beam and the heat-proof beam in a detachable mode;
the supporting beam is connected with the supporting block and then arranged between the upper end frame and the lower end frame;
the heat-proof plate is fixedly connected with the lower end frame and the heat-proof beam;
the wall plate is connected with the upper end frame and the lower end frame to form an engine compartment bulkhead.
2. The honeycomb integrated engine compartment structure of claim 1 wherein said web is of a honeycomb biomimetic configuration.
3. The honeycomb integrated engine compartment structure of claim 2 wherein said web is a multi-piece removable structure.
4. The honeycomb type integrated engine room structure of claim 1 or 2, wherein the upper end frame, the lower end frame, the bearing beam, the heat-proof beam, the supporting beam and the supporting blocks form a frame structure, and the whole engine room adopts a frame + web structure.
5. The honeycomb type integrated engine room structure of claim 1, wherein the bearing beam is connected with the heat-proof beam into a whole through a plurality of detachable webs so as to realize integrated force transmission.
6. The honeycomb type integrated engine room structure as recited in claim 1, wherein the bearing beam is provided with an engine mounting interface; the supporting block is provided with a landing buffer mechanism mounting interface, and the heat-proof plate is provided with an engine jet pipe opening.
7. The honeycomb integrated engine room structure of claim 1, wherein the supporting block is connected to one end of the supporting beam, the other end of the supporting beam is connected to the outer side wall of the circular upper end frame, the supporting block is connected to the outer side wall of the circular lower end frame, and the end surface of the supporting block, which is not connected to the supporting beam, is provided with a landing buffer mechanism mounting interface.
8. The honeycomb integrated engine compartment structure of claim 7 wherein a plurality of support beam and block combinations are provided between said upper end frame and said lower end frame, the plurality of support beam and block combinations being uniformly arranged along a cylinder.
9. The honeycomb integrated engine compartment structure of claim 8 wherein said wall panel is a plurality of panels, one of said wall panels being disposed between any two adjacent support beam and support block combinations; the wallboard is detachably connected with the upper end frame and the lower end frame.
10. The honeycomb integrated engine room structure of claim 1 wherein said load-bearing beam is a planar beam structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211280328.4A CN115900454A (en) | 2022-10-19 | 2022-10-19 | Honeycomb type integrated engine cabin structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211280328.4A CN115900454A (en) | 2022-10-19 | 2022-10-19 | Honeycomb type integrated engine cabin structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115900454A true CN115900454A (en) | 2023-04-04 |
Family
ID=86478491
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211280328.4A Pending CN115900454A (en) | 2022-10-19 | 2022-10-19 | Honeycomb type integrated engine cabin structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115900454A (en) |
-
2022
- 2022-10-19 CN CN202211280328.4A patent/CN115900454A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103863577B (en) | The board-like satellite configuration of frame surface and modularization satellite | |
| CN100575191C (en) | A kind of main load-carrying structure of spacecraft | |
| CN109850186B (en) | Plate frame type satellite structure for one-rocket multi-satellite parallel transmission and assembly method | |
| CN111703592B (en) | Large commercial remote sensing satellite platform configuration and assembly method | |
| CN112319851B (en) | Large-scale boxboard formula communication cabin structure | |
| CN105539878A (en) | Large truss type vibration isolation platform structure facing various effective loads | |
| CN111891156B (en) | Corridor vehicle body structure in novel diesel locomotive | |
| CN111029968B (en) | Multilayer modularization spanning frame that does not have a power failure suitable for intensive block construction | |
| US20100132378A1 (en) | Hydraulic system for transmission of forces between an aircraft turboprop and an attachment device | |
| CN115900454A (en) | Honeycomb type integrated engine cabin structure | |
| CN212605879U (en) | Rocket ejection type thrust cone connecting angle box structure | |
| CN108238261B (en) | Main structure for a support for an aircraft propeller group comprising a pyramidal section with convergent struts | |
| CN102417017B (en) | Ship building molding bed combination method and ship building combined molding bed | |
| CN210719610U (en) | Mechanical test device of load transfer mechanism | |
| WO2017000528A1 (en) | Driving device assembly including multiple driving devices and application thereof | |
| CN113277121A (en) | Constellation deployment-oriented minisatellite configuration and modular assembly method | |
| CN209739314U (en) | Unmanned helicopter non-bearing type fuselage structure | |
| CN207072445U (en) | A kind of high rigidity combined type suitable for high resolution camera installs framework | |
| CN220054120U (en) | Civil aircraft floor support, floor structure and aircraft | |
| RU94209U1 (en) | MULTI-SYSTEM AIRCRAFT MODULE | |
| CN212897498U (en) | Hanging basket for construction and installation of air-cooled wind-shield wall panel | |
| CN113044239A (en) | Supporting structure of two-degree-of-freedom test bed | |
| CN205294546U (en) | Elevator steel frame hoistway | |
| CN116002073A (en) | Plate-shell-beam combined type large-bearing satellite cabin section connecting structure | |
| CN114857129A (en) | Large-scale aircraft hydraulic system test bed body capable of realizing nondestructive deconstruction and recombination |
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 |