CN112429280A - External camera mounting structure of carrier rocket - Google Patents
External camera mounting structure of carrier rocket Download PDFInfo
- Publication number
- CN112429280A CN112429280A CN202011462138.5A CN202011462138A CN112429280A CN 112429280 A CN112429280 A CN 112429280A CN 202011462138 A CN202011462138 A CN 202011462138A CN 112429280 A CN112429280 A CN 112429280A
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- CN
- China
- Prior art keywords
- camera
- mounting
- mounting structure
- carrier rocket
- hole
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- 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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
-
- 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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
Abstract
The invention relates to the technical field of camera installation and fixation, in particular to an external camera installation structure of a carrier rocket, which comprises: the mounting plate is provided with a first mounting surface which is matched and fixed with the outer wall of the cabin body of the carrier rocket and a second mounting surface which is matched and fixed with the camera; and the shell covers the periphery of the mounting plate and covers the camera. The invention provides an external camera mounting structure of a carrier rocket, which is not easy to damage a camera and is firm and convenient to mount.
Description
Technical Field
The invention relates to the technical field of camera installation and fixation, in particular to an external camera installation structure of a carrier rocket.
Background
The carrier rocket is subjected to severe force and thermal environment tests in the whole flight process from launching to entering space. The speed of the carrier rocket after being launched can reach thousands of meters per second, and the rocket body moving at high speed not only is acted by aerodynamic force when passing through a dense atmospheric layer, but also generates a large amount of heat when being violently rubbed with air. The camera is as sensitive electrical equipment, has strict requirement to installation, service environment, directly exposes can lead to the camera to destroy in external environment, influences the use.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defects that the externally arranged camera of the carrier rocket in the prior art is easy to damage and inconvenient to install, thereby providing the externally arranged camera installation structure of the carrier rocket, which has the advantages of difficult damage of the camera and firm and convenient installation.
In order to solve the technical problem, the invention provides an external camera mounting structure of a carrier rocket, which comprises:
the mounting plate is provided with a first mounting surface which is matched and fixed with the outer wall of the cabin body of the carrier rocket and a second mounting surface which is matched and fixed with the camera;
and the shell covers the periphery of the mounting plate and covers the camera.
Optionally, the first mounting surface of the mounting plate is an arc surface, and the second mounting surface is a plane.
Optionally, the mounting plate is provided with a first through hole for allowing the first fastening member to pass through.
Optionally, the first fastening member sequentially penetrates through a second through hole formed in the camera, a first through hole formed in the mounting plate and a first mounting hole formed in the outer wall of the cabin of the launch vehicle and then is fixed to the outer wall of the cabin.
Optionally, the housing is streamlined, and the mounting plate is disposed near a large end of the housing.
Optionally, the large head end of the housing is provided as an opening.
Optionally, the outer surface of the casing is coated with a heat protection layer.
Optionally, the edge of the housing is further formed with a mounting portion, and the mounting portion is provided with a third through hole allowing the second fastening member to penetrate through.
Optionally, the second fastening member penetrates through the third through hole and then is fastened with a third fastening member mounted on the outer wall of the cabin body.
Optionally, the second fastener is a screw and the third fastener is a pallet nut.
The technical scheme of the invention has the following advantages:
1. according to the external camera mounting structure of the carrier rocket, the camera is fixed with the outer wall of the cabin body of the carrier rocket through the mounting plate, and the first mounting surface of the mounting plate is matched with the outer wall of the cabin body, so that the mounting reliability is ensured, the structure of the outer wall of the cabin body does not need to be changed, and the mounting is convenient; in addition, the arrangement of the outer periphery shell of the mounting plate enables the camera to be completely arranged in the shell, so that the camera has a good protection effect, avoids damage of external force heat to the camera, and prolongs the service life of the camera.
2. The mounting structure of the externally arranged camera of the carrier rocket, provided by the invention, has the advantages that the streamlined shell is arranged, the force and heat load in the flight process of the carrier rocket can be borne, and the damage of external force and heat flow to the camera is relieved.
3. According to the external camera mounting structure of the carrier rocket, the heat-proof layer is arranged on the outer surface of the shell, so that the heat insulation effect of the mounting structure is further improved.
4. According to the mounting structure of the external camera of the carrier rocket, the edge mounting part of the shell and the second fastening piece are arranged, so that the load borne by the shell can be diffused, the pressure borne by the shell is reduced, and the service life is prolonged.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic view of an external camera mounting structure of a carrier rocket provided by the invention;
FIG. 2 is a schematic view of the outer wall of the cabin of the carrier rocket without a camera mounting structure;
FIG. 3 is a schematic view of the housing;
FIG. 4 is an enlarged partial schematic view of FIG. 2;
fig. 5 is a partially enlarged schematic view of fig. 1 when the housing is not mounted.
Description of reference numerals:
1. mounting a plate; 2. a housing; 3. a camera; 4. a first fastener; 5. a cabin body; 6. a first mounting hole; 7. an installation part; 8. a third through hole; 9. a second mounting hole; 10. a third fastener; 11. and a third mounting hole.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
As shown in fig. 1 to 5, the external camera mounting structure of the carrier rocket is mounted on the outer wall of the second-stage rear-section cabin of the carrier rocket, and the outer surface of the second-stage rear-section cabin is cylindrical and is located at the lowest end of the second-stage rear section of the carrier rocket for supporting components and maintaining the appearance of the rocket body. The diameter of the second-stage rear-section cabin body is 1.4m, the height is 1.1m, the wall thickness is 4mm, the thickness of the end frame is 10mm, and the height and the width of the internal grid ribs are 12mm and 3 mm. The second-stage rear-section cabin body is made of an aluminum alloy 2A14 forge piece and is machined and formed. The external camera mounting structure comprises a mounting plate 1 and a shell 2 covering the periphery of the mounting plate 1.
The mounting plate 1 is a rectangular plate made of aluminum alloy 2A14, is machined and molded, has the length of 60mm and the width of 50mm, and is provided with a first mounting surface and a second mounting surface, wherein the first mounting surface is matched and fixed with the outer wall of a cabin body 5 of the carrier rocket, and the second mounting surface is matched and fixed with the camera 3. Specifically, the first installation face of mounting panel 1 is the cambered surface, and the radian size is unanimous with the cylindrical surface of the second grade back end cabin body, and the second installation face is the plane to with the camera 3 towards the laminating fastening of the one side of the second grade back end cabin body.
For the convenience of installation, the four corners of the installation plate 1 are respectively provided with a first through hole for allowing the first fastening piece 4 to penetrate through. As shown in fig. 2 and 4, four first mounting holes 6 with internal threads corresponding to the first through holes are formed in the outer wall of the cabin 5 of the launch vehicle, and screws serving as the first fasteners 4 sequentially penetrate through the second through holes formed in the camera 3, the first through holes formed in the mounting plate 1 and the first mounting holes 6 formed in the outer wall of the cabin 5 of the launch vehicle and then are fixed to the outer wall of the cabin 5. The first mounting hole 6 may be a through hole or a blind hole.
As shown in fig. 1 and 3, the housing 2 is streamlined, the base material is a 304 stainless steel plate material with a thickness of 1.5mm, the outer surface of the housing is coated with a TL-5 heat-proof layer with a thickness of 3mm, and the housing covers the camera 3. The big head end of the shell 2 is arranged in an opening mode, the small head end is arranged in a closed mode, the mounting plate 1 is close to the big head end of the shell 2, and therefore the camera 3 can conduct shooting operation through the opening of the big head end. The edge of casing 2 still outwards extends the shaping and has installation department 7, be equipped with the third through-hole 8 that allows the second fastener to run through on the installation department 7, the interval symmetric distribution of third through-hole 8 has a plurality ofly, and is corresponding, as shown in fig. 2 and 5, the corresponding distribution has a plurality of second mounting holes 9 on the second grade back end cabin body outer wall. As shown in fig. 4, the screw as the second fastening member is inserted through the third through hole 8 and then fastened to a pallet nut as a third fastening member 10 mounted on the outer wall of the cabin 5. The pallet nuts are pre-mounted in corresponding positions on the outer wall of the cabin 5, so that the fixing screws of the housing 2 can be installed from the outside on one side, further simplifying the assembly operation.
In order to facilitate the connection of the camera 3 and the equipment inside the second-stage rear-stage cabin body, a third mounting hole 11 is further formed in the corresponding position of the second-stage rear-stage cabin body, and a cable of the camera 3 penetrates through the third mounting hole 11 to be electrically connected with the equipment inside the cabin body 5.
When the camera 3 is installed, at first, 7 independent supporting plate nuts are installed in the second installation hole 9 of the second-stage rear-section cabin body, rivets can be used for riveting, and sunk screws can also be used for screwing. Then, four screws sequentially penetrate through a second through hole in the camera 3 and a first through hole in the mounting plate 1, and are screwed in a first mounting hole 6 of the second-stage rear-section cabin body, so that the camera 3 is mounted. And finally, sequentially penetrating 7 screws through a third through hole 8 on the mounting part 7 of the shell 2 and then screwing the screws with a support plate nut on the outer wall of the cabin body 5 to finish assembly.
The installation structure of the external camera of the carrier rocket has the characteristics of simple structure, convenience and quickness in assembly, safety, reliability, high installation precision and the like, improves the protection reliability of the camera, reduces the processing cost, lightens the weight of a structural system, and meets the protection requirement of an electrical system of the carrier rocket.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (10)
1. The utility model provides an external camera mounting structure of carrier rocket which characterized in that includes:
the mounting plate (1) is provided with a first mounting surface which is matched and fixed with the outer wall of the cabin body (5) of the carrier rocket and a second mounting surface which is matched and fixed with the camera (3);
and the shell (2) covers the periphery of the mounting plate (1) and covers the camera (3).
2. The mounting structure of the outboard camera of the carrier rocket according to claim 1, wherein the first mounting surface of the mounting plate (1) is a cambered surface, and the second mounting surface is a plane.
3. The outboard camera mounting structure of a launch vehicle according to claim 1 or 2, characterized in that the mounting plate (1) is provided with a first through hole allowing a first fastening member (4) to pass through.
4. The vehicle rocket external camera mounting structure according to claim 3, wherein the first fastener (4) sequentially penetrates through the second through hole formed on the camera (3), the first through hole formed on the mounting plate (1) and the first mounting hole (6) formed on the outer wall of the cabin (5) of the vehicle rocket and then is fixed with the outer wall of the cabin (5).
5. The outboard camera mounting structure of a launch vehicle according to any one of claims 1-4, wherein the housing (2) is streamlined, and the mounting plate (1) is disposed near the large end of the housing (2).
6. The outboard camera mounting structure of a launch vehicle according to claim 5, wherein the large end of the case (2) is open.
7. The externally mounted camera mounting structure of a launch vehicle according to claim 6, characterised in that the outer surface of the casing (2) is coated with a heat-proof layer.
8. The outboard camera mounting structure of a launch vehicle according to any one of claims 5-7, wherein the housing (2) is further formed with a mounting portion (7) at an edge thereof, and the mounting portion (7) is provided with a third through hole (8) for allowing a second fastening member to pass therethrough.
9. The outboard camera mounting structure of the launch vehicle according to claim 8, wherein the second fastening member is fastened to a third fastening member (10) mounted on the outer wall of the nacelle (5) after penetrating through the third through hole (8).
10. The externally mounted camera mounting structure of a launch vehicle according to claim 9, characterised in that the second fasteners are screws and the third fasteners (10) are pallet nuts.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011462138.5A CN112429280A (en) | 2020-12-09 | 2020-12-09 | External camera mounting structure of carrier rocket |
| CN202110445499.7A CN113022899A (en) | 2020-12-09 | 2021-04-23 | External camera mounting structure of carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011462138.5A CN112429280A (en) | 2020-12-09 | 2020-12-09 | External camera mounting structure of carrier rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112429280A true CN112429280A (en) | 2021-03-02 |
Family
ID=74692496
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011462138.5A Pending CN112429280A (en) | 2020-12-09 | 2020-12-09 | External camera mounting structure of carrier rocket |
| CN202110445499.7A Pending CN113022899A (en) | 2020-12-09 | 2021-04-23 | External camera mounting structure of carrier rocket |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110445499.7A Pending CN113022899A (en) | 2020-12-09 | 2021-04-23 | External camera mounting structure of carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN112429280A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114993119A (en) * | 2022-06-21 | 2022-09-02 | 北京凌空天行科技有限责任公司 | Shooting system on carrier rocket cabin section |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3362291A (en) * | 1965-09-03 | 1968-01-09 | Hawley Products Co | Fairing |
| US7036773B2 (en) * | 2003-08-28 | 2006-05-02 | Ecliptic Enterprises Corporation | Compact external launcher for small space payloads |
| US9108747B2 (en) * | 2011-12-05 | 2015-08-18 | Macdonald, Dettwiler And Associates Inc. | Tool for accessing satellite fill/drain valves during propellant resupply |
| CN106428631A (en) * | 2016-11-03 | 2017-02-22 | 王德龙 | Electric rocket |
| CN207518687U (en) * | 2017-08-22 | 2018-06-19 | 肇庆市广应科通用航空研究院 | A kind of aerospace camera |
| CN209455019U (en) * | 2019-01-29 | 2019-10-01 | 深圳市惠尔智控技术有限公司 | A kind of camera protection device for surveying and drawing unmanned plane |
| CN109854411B (en) * | 2019-02-25 | 2024-03-26 | 蓝箭航天空间科技股份有限公司 | Propellant sinking energy and fairing separation energy combined supply system |
| CN111023913A (en) * | 2019-12-27 | 2020-04-17 | 北京星际荣耀空间科技有限公司 | Carrier rocket final-stage structure |
-
2020
- 2020-12-09 CN CN202011462138.5A patent/CN112429280A/en active Pending
-
2021
- 2021-04-23 CN CN202110445499.7A patent/CN113022899A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| CN113022899A (en) | 2021-06-25 |
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Application publication date: 20210302 |