CN112857154A - Solid power instrument cabin of carrier rocket - Google Patents
Solid power instrument cabin of carrier rocket Download PDFInfo
- Publication number
- CN112857154A CN112857154A CN202110153365.8A CN202110153365A CN112857154A CN 112857154 A CN112857154 A CN 112857154A CN 202110153365 A CN202110153365 A CN 202110153365A CN 112857154 A CN112857154 A CN 112857154A
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- CN
- China
- Prior art keywords
- end frame
- mounting plate
- instrument
- instrument mounting
- skin
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
Abstract
The application discloses a solid power instrument cabin of a carrier rocket, which comprises an upper end frame, a lower end frame, a skin, a plurality of outer stringers and an instrument mounting plate, wherein the upper end frame is provided with a plurality of outer stringers; the upper end frame and the lower end frame are both annular, the diameter of the lower end frame is smaller than that of the upper end frame, the upper end surface of the upper end frame is connected with the satellite support adapter frame, and the bottom surface of the lower end frame is connected with the rear-stage section; the outer stringers are fixed on the outer surface of the skin, and the skin is fixed between the upper end frame and the lower end frame through the outer stringers; the instrument mounting plate is horizontally fixed in the middle of the inner side of the skin, a circular through hole is formed in the center of the instrument mounting plate, and the final-stage solid engine penetrates through the circular through hole; the inside of instrument mounting panel is equipped with the installation and buries the piece. The layout has good adjustability, a larger elastic space can be provided for the mass center balance, the installation difficulty and the installation and launching cost are reduced, and the working environment is improved; in addition, the whole instrument cabin is not provided with a large beam structure and is mainly made of aluminum alloy materials, so that the weight of the instrument cabin is greatly reduced.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a solid power instrument cabin of a carrier rocket.
Background
The instrument capsule is a core section of the carrier rocket and is used as a brain of the rocket, and most important electrical equipment and final-stage correction systems for positioning, controlling, measuring, attitude controlling, networking, power supplying and the like are installed on the instrument capsule. Therefore, the structure of the instrument pod directly affects the success or failure of the launch vehicle. In a common launch vehicle, the instrument pod is located at the top end of the final power section and is provided in the form of a separate pod section.
The solid final stage of a conventional launch vehicle, the solid engine is typically contained within the instrument bay, and the engine mounting structure is typically a multi-beam structure that connects the final stage solid engine to the instrument bay shell section. The diameters of the carrier rocket, the diameter of the final-stage engine and the size of the large beam are large, and the instrument is arranged on one side of the engine, and a special mass center balancing device is needed, so that the installation space reserved for instrument equipment and the final-stage attitude control system is extremely limited, the layout and installation difficulty of the instrument equipment, the cable and the final-stage attitude control system is increased, and the working environment of the content is poor. In addition, the beam structure and the shell section structure corresponding to the beam structure have higher design, manufacturing and total assembly cost, heavier structure weight and invisibly increased emission cost.
Disclosure of Invention
An object of the application is to provide a solid power instrument cabin of carrier rocket for solve instrument installation degree of difficulty in current instrument cabin big, operational environment is poor, installation and launch cost are high and the big technical problem of weight.
The application provides a solid power instrument cabin of a carrier rocket, which comprises an upper end frame, a lower end frame, a skin, a plurality of outer stringers and an instrument mounting plate; the upper end frame and the lower end frame are both annular, the diameter of the lower end frame is smaller than that of the upper end frame, the upper end surface of the upper end frame is connected with the satellite support adapter frame, and the bottom surface of the lower end frame is connected with the rear-stage section; the outer stringers are fixed on the outer surface of the skin, and the skin is fixed between the upper end frame and the lower end frame through the outer stringers; the instrument mounting plate is horizontally fixed in the middle of the inner side of the skin, a circular through hole is formed in the center of the instrument mounting plate, and the final-stage solid engine penetrates through the circular through hole; the inside of instrument mounting panel is equipped with the installation and buries the piece, and the instrument installation buries the piece and is connected with the instrument in the solid power instrument cabin.
Preferably, the solid power instrument pod further comprises an inner middle frame, the inner middle frame being secured to the bottom surface of the instrument mounting plate and the inner middle frame being secured to the inner side surface of the skin.
Preferably, interior center includes first instrument mounting panel connection plane, connects the face and the turn-ups of extending downwards from first instrument mounting panel connection plane from the covering that first instrument mounting panel connection plane upwards extends, and covering is connected the face and is pasted and with covering fixed connection, first instrument mounting panel connection plane and instrument mounting panel fixed connection with the covering.
Preferably, the solid power instrument cabin further comprises an inner ring frame, the inner ring frame is fixedly connected with the edge of the circular through hole in the instrument mounting plate, and the inner ring frame is fixedly connected with the lower end frame through a plurality of inner stringers.
Preferably, the cross section of the lower end frame is a U-shaped groove, the bottom surface of the U-shaped groove is a plane, the bottom surface is connected with the rear-stage section of the solid power instrument cabin, the first side edge of the U-shaped groove is attached to the skin and fixedly connected with the skin, and the second side edge of the U-shaped groove is attached to the inner stringer and fixedly connected with the inner stringer.
Preferably, the inner ring frame comprises an annular second instrument mounting plate connecting plane and an annular inner stringer connecting plane, the second instrument mounting plate connecting plane and the inner stringer connecting plane form a T-shaped structure, the second instrument mounting plate connecting plane is fixedly connected with the edge of the circular through hole in the instrument mounting plate, and the inner stringer connecting plane is fixedly connected with the end portion of the inner stringer.
Preferably, on the second instrument mounting plate connecting plane, the annular end part close to the skin is a second instrument mounting plate connecting part, the annular end part close to the engine is an engine mounting part, the second instrument mounting plate connecting part is fixedly connected with the instrument mounting plate, and the engine mounting part is fixedly connected with the engine.
Preferably, the instrument mounting plate is an annular body with a radial indentation.
Preferably, the instrument mounting plate comprises an upper layer, an interlayer and a lower layer, wherein the upper layer and the lower layer are made of carbon fiber composite materials, and the interlayer is a honeycomb plate.
Preferably, the inner stringer comprises a first connecting surface and a first reinforcing surface, two ends of the first connecting surface are fixedly connected with the inner ring frame and the lower end frame respectively, and the first reinforcing surface and the first connecting surface form a T-shaped structure.
Preferably, the outer stringer includes a second connection surface and a second reinforcement surface, two ends of the second connection surface are respectively and fixedly connected with the upper end frame and the lower end frame, and the second reinforcement surface and the second connection surface form a T-shaped structure.
Preferably, the upper end frame and the lower end frame are made of aluminum alloy materials.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings can be obtained by those skilled in the art according to the drawings.
FIG. 1 is a block diagram of a solid state power instrument pod of a launch vehicle provided herein;
FIG. 2 is a cross-sectional view of a solid state power instrument pod of a launch vehicle provided herein.
Detailed Description
The technical solutions in the embodiments of the present application are clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, embodiments of the present application. 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 application.
FIG. 1 is a block diagram of a solid power instrument pod of a launch vehicle provided herein, and FIG. 2 is a cross-sectional view of FIG. 1.
As shown in fig. 1 and 2, the solid power instrument pod of the launch vehicle includes an upper end frame 110, a lower end frame 120, a skin 130, a plurality of outer stringers 140, and an instrument mounting plate 180.
The upper end frame 110 and the lower end frame 120 are both aluminum alloy material adding structures, the upper end frame 110 and the lower end frame 120 are both annular, and the diameter of the lower end frame 120 is smaller than that of the upper end frame 110, so that the solid power instrument cabin is in an inverted cone shape. The upper end surface of the upper end frame 110 is connected with the satellite support adapter frame, and the bottom surface of the lower end frame 120 is connected with the rear-stage section. The skin 130 is an outer skin structure formed by splicing a plurality of aluminum thin plates. The skin 130 is crimped between the upper end frame 110 and the lower end frame 120 by a plurality of outer stringers 140. Specifically, a plurality of outer stringers 140 are fixed on the outer surface of the skin 130, and both ends of the outer stringers 140 are fixedly connected to the upper and lower end frames 110 and 120. Specifically, the outer stringer 140 includes a connecting surface and a reinforcing surface, wherein two ends of the connecting surface are fixedly connected to the upper end frame 110 and the lower end frame 120, respectively, and the reinforcing surface and the connecting surface form a T-shaped structure. The outer stringers 140 act to transmit forces throughout the structure, bearing external operating loads and internal solid engine operating loads. The mounting position of the outer stringer 140 on the skin 130 is determined from the load input data.
The instrument mounting plate 180 comprises an upper layer, an interlayer and a lower layer, wherein the upper layer and the lower layer are both made of carbon fiber composite materials, and the interlayer is a honeycomb plate. According to the using conditions in the instrument cabin, the instrument mounting plate mainly bears the axial bending moment of the rocket body, the mechanical property and the mechanical environment of the carbon fiber composite material sandwich honeycomb plate structure material are very good, and the requirements of the instrument mounting plate can be met. As shown in fig. 1, the instrument mounting plate 180 is horizontally fixed to the inside center of the skin 130. The instrument mounting plate 180 is an annular body with a radial gap 1801, and the radial gap is used for providing a mounting space for an inertial unit of a launch vehicle, so that the complex mechanical environment of the instrument mounting plate is prevented from being superposed on the inertial unit, which is a device with high precision and high requirements on mechanical performance and mechanical environment, and an elastic space is also provided for vibration, deformation, force transmission and other factors. The instrument mounting plate 180 is provided with a circular through hole 1803 at the center, and the diameter of the circular through hole 1803 is smaller than the inner diameter of the lower end frame 120. The inside of the instrument mounting plate 180 is provided with a mounting embedded part which is connected with instrument equipment and other systems in the solid power instrument cabin. The instrument mounting plate 180 is provided with a plurality of mounting holes 1802.
As shown in fig. 1 and 2, the instrument mounting plate 180 is secured to the inner side of the skin 130 by the inner center frame 150. The inner center frame 150 is riveted to the skin 130 and the outer stringers 140 (if there are outer stringers at the attachment locations). Inner center 150 is an aluminum alloy material machined structure, and inner center 150 includes a first instrument-mounting-plate attachment plane 1502, a skin attachment plane 1501 extending upwardly from first instrument-mounting-plate attachment plane 1502, and a flange 1503 extending downwardly from first instrument-mounting-plate attachment plane 1502, such that the cross-section of the inner center is Z-shaped. Skin attachment surface 1501 is attached to skin 130 and riveted to skin 130 and outer stringers 140 (if attached) and first instrument mounting plate attachment plane 1502 is horizontal and is fixedly attached to instrument mounting plate 180 and contacts the bottom surface of instrument mounting plate 180. Flanges 1503 are used to stabilize the structure, acting against bending and twisting, and flanges 1503 are used for auxiliary support structures for the tube set bracket and for the bracket of the conduit cable.
The solid power instrument chamber further comprises an inner ring frame 170, and the inner ring frame 170 is an aluminum alloy material machining structure. The inner ring frame 170 is fixedly connected to the edge of the circular through hole of the instrument mounting plate 180, and the inner ring frame 170 is fixedly connected to the lower end frame 120 by a plurality of inner stringers 160.
Preferably, the inner ring frame 170 comprises a second annular instrument mounting plate connection plane 1701 and an annular inner stringer connection plane 1702, the second instrument mounting plate connection plane 1701 and the inner stringer connection plane 1702 form a T-shaped structure, the second instrument mounting plate connection plane 1701 is fixedly connected with the edge of the circular through hole on the instrument mounting plate 180, and the inner stringer connection plane 1702 is fixedly connected with the end of the inner stringer 160.
On the second instrument-mounting-plate attachment plane 1701, an annular end portion near the skin 130 is a second instrument-mounting-plate attachment portion (an annular region formed by screw holes for attachment to the instrument mounting plate as shown in fig. 1 on the outer side), and an annular end portion near the engine is an engine attachment portion (an annular region formed by screw holes as shown in fig. 1 on the inner side), and the second instrument-mounting-plate attachment portion is fixedly attached to the instrument mounting plate and the engine attachment portion is fixedly attached to the engine.
Preferably, the cross section of the lower end frame 120 is a U-shaped groove, the bottom surface of the U-shaped groove is a plane, the bottom surface is connected with the rear section of the solid power instrument cabin, the first side edge of the U-shaped groove is attached to the skin 130 and fixedly connected with the skin 130, and the second side edge of the U-shaped groove is attached to the inner stringer 160 and fixedly connected with the inner stringer 160. Wherein the diameter of the first side is larger than the diameter of the second side.
Specifically, the inner stringer 160 includes a connecting surface and a reinforcing surface, two ends of the connecting surface are respectively and fixedly connected to the inner ring frame 170 and the lower end frame 120, and the reinforcing surface and the connecting surface form a T-shaped structure. The inner stringers 160 act to transmit forces throughout the structure, bearing external operating loads and internal solid engine operating loads.
The beneficial effects obtained by the application are as follows:
1. according to the solid engine, the solid engine is arranged at the central position, the periphery of the engine provides an annular installation space for the instrument equipment, the final attitude control system, the cable and the pipeline, the traditional structure with a single-side layout and a mass center balancing device is abandoned, the mass center balance can be achieved by adjusting the position relation of the instrument equipment, the final attitude control system, the cable and the pipeline, the layout adjustability is good, a larger elastic space can be provided for the mass center balance, the installation difficulty and the installation and emission cost are reduced, and the working environment is improved; in addition, the whole instrument cabin is not provided with a large beam structure and is mainly made of aluminum alloy materials, so that the weight of the instrument cabin is greatly reduced.
2. The instrument mounting plate is an annular body with a radial opening, the radial opening provides a mounting space for an inertial unit of a carrier rocket, and the complex mechanical environment of the instrument mounting plate is prevented from being superposed on the equipment which is precise and has higher requirements on mechanical performance and mechanical environment and is used for the inertial unit.
3. The instrument chamber is stable in conical structure and stable in structure, and provides a stable operation environment for the instrument chamber.
4. In the application, the U-shaped lower end frame not only can complete the bearing and transmission of the working load of the instrument cabin and the rear-stage section, but also can complete the bearing and transmission of the working load of the last-stage solid engine of the instrument cabin.
5. The T-shaped inner ring frame in the application not only can complete the bearing and transmission of the working load of the final-stage solid engine of the instrument chamber, but also provides support for the instrument mounting plate.
6. The instrument mounting plate combines the carbon fiber composite material and the honeycomb material, the panel material is high in strength and rigidity, the honeycomb core is in an orthotropic structure along the plate surface, excellent structural mechanical properties and a good mechanical environment are provided for the instrument mounting plate, the plate density is small, and the final-stage weight reduction effect is achieved.
7. The skin-stringer structure is adopted between the upper end frame and the lower end frame, and main working condition loads of the instrument cabin are borne.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all alterations and modifications as fall within the scope of the application. It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. A solid power instrument cabin of a carrier rocket is characterized by comprising an upper end frame, a lower end frame, a skin, a plurality of outer stringers and an instrument mounting plate;
the upper end frame and the lower end frame are both annular, the diameter of the lower end frame is smaller than that of the upper end frame, the upper end surface of the upper end frame is connected with the satellite support adapter frame, and the bottom surface of the lower end frame is connected with the rear-stage section;
the plurality of outer stringers are secured to an outer surface of the skin, the skin being secured between the upper end frame and the lower end frame by the plurality of outer stringers;
the instrument mounting plate is horizontally fixed in the middle of the inner side of the skin, a circular through hole is formed in the center of the instrument mounting plate, and a final-stage solid engine penetrates through the circular through hole; the inside of instrument mounting panel is equipped with the installation and buries the piece.
2. The solid power instrument pod of a launch vehicle of claim 1, further comprising an inner mid-frame secured to a bottom surface of the instrument mounting plate and secured to an inner side surface of the skin.
3. The solid power equipment bay of a launch vehicle of claim 2, wherein the solid power equipment bay further comprises an inner ring frame fixedly attached to an edge of the circular through hole in the equipment mounting plate, and wherein the inner ring frame is fixedly attached to the lower end frame by a plurality of inner stringers.
4. The solid power pod of a launch vehicle of claim 3, wherein the cross-section of the lower end frame is a U-shaped channel, wherein a bottom surface of the U-shaped channel is planar, wherein the bottom surface is attached to a rear section of the solid power pod, wherein a first side of the U-shaped channel engages and is fixedly attached to the skin, and wherein a second side of the U-shaped channel engages and is fixedly attached to the inner stringer.
5. The solid power instrument pod of a launch vehicle of claim 3, wherein the inner annular frame comprises an annular second instrument mounting plate attachment plane and an annular inner stringer attachment plane, the second instrument mounting plate attachment plane and the inner stringer attachment plane forming a T-shaped structure, the second instrument mounting plate attachment plane fixedly attached to an edge of the circular through hole in the instrument mounting plate, the inner stringer attachment plane fixedly attached to an end of the inner stringer.
6. The solid power instrument pod of a launch vehicle of claim 5, wherein a second instrument mounting plate attachment plane is defined by an annular end portion adjacent to the skin being a second instrument mounting plate attachment portion and an annular end portion adjacent to the engine being an engine mount portion, the second instrument mounting plate attachment portion being fixedly attached to the instrument mounting plate and the engine mount portion being fixedly attached to the engine.
7. The solid state power instrument pod of a launch vehicle of claim 1, wherein the instrument mounting plate comprises an upper layer, an interlayer, and a lower layer, the upper and lower layers being carbon fiber composite material, the interlayer being a honeycomb panel.
8. The solid state power pod of a launch vehicle of claim 3, wherein the inner stringer comprises a first attachment surface and a first reinforcement surface, wherein both ends of the first attachment surface are fixedly attached to the inner ring frame and the lower end frame, respectively, and wherein the first reinforcement surface and the first attachment surface form a T-shaped structure.
9. The solid state power pod of a launch vehicle of claim 1, wherein the outer stringer comprises a second attachment surface and a second reinforcement surface, wherein both ends of the second attachment surface are fixedly attached to the upper end frame and the lower end frame, respectively, and the second reinforcement surface and the second attachment surface form a T-shaped structure.
10. The solid state power pod of a launch vehicle of claim 1, wherein said upper end frame and said lower end frame are of aluminum alloy material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110153365.8A CN112857154A (en) | 2021-02-04 | 2021-02-04 | Solid power instrument cabin of carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110153365.8A CN112857154A (en) | 2021-02-04 | 2021-02-04 | Solid power instrument cabin of carrier rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112857154A true CN112857154A (en) | 2021-05-28 |
Family
ID=75986675
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110153365.8A Withdrawn CN112857154A (en) | 2021-02-04 | 2021-02-04 | Solid power instrument cabin of carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112857154A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114061379A (en) * | 2021-11-16 | 2022-02-18 | 天津爱思达新材料科技有限公司 | Front cabin T-shaped frame reinforcing structure |
| CN116518795A (en) * | 2023-07-03 | 2023-08-01 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
-
2021
- 2021-02-04 CN CN202110153365.8A patent/CN112857154A/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114061379A (en) * | 2021-11-16 | 2022-02-18 | 天津爱思达新材料科技有限公司 | Front cabin T-shaped frame reinforcing structure |
| CN116518795A (en) * | 2023-07-03 | 2023-08-01 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
| CN116518795B (en) * | 2023-07-03 | 2023-09-15 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
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Application publication date: 20210528 |