CN114993119A - Shooting system on carrier rocket cabin section - Google Patents
Shooting system on carrier rocket cabin section Download PDFInfo
- Publication number
- CN114993119A CN114993119A CN202210701872.5A CN202210701872A CN114993119A CN 114993119 A CN114993119 A CN 114993119A CN 202210701872 A CN202210701872 A CN 202210701872A CN 114993119 A CN114993119 A CN 114993119A
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- camera
- rocket
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- wall
- assembly
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- 230000005540 biological transmission Effects 0.000 claims abstract description 39
- 230000001681 protective effect Effects 0.000 claims abstract description 15
- 210000004907 gland Anatomy 0.000 claims description 11
- 239000002775 capsule Substances 0.000 claims 2
- 238000009434 installation Methods 0.000 abstract description 9
- 238000000034 method Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 208000032370 Secondary transmission Diseases 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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Classifications
-
- 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
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M13/00—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles
- F16M13/02—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Accessories Of Cameras (AREA)
Abstract
The application provides a shooting system on a carrier rocket cabin section, which comprises a camera mounting assembly, a camera mounting assembly and a shooting assembly, wherein the camera mounting assembly is exposed outside the rocket cabin section and is used for mounting a shooting camera; the transparent protective cover covers the camera mounting assembly, and the edge of the transparent protective cover is fixed on the rocket cabin section wall; the transmission assembly penetrates through the rocket cabin section wall and is fixedly connected with the camera mounting assembly; the driving assembly is arranged in the rocket cabin section and used for driving the transmission assembly to rotate along a first axis; the first axis is arranged perpendicular to a rocket cabin segment wall; the positive light emitting direction of a lens of the camera is perpendicular to the first axis; this application drives transmission assembly by drive element through setting up drive element and rotates to drive the camera installation component that links to each other with transmission assembly and rotate, so that realize the rotation of camera, the direction of the first axis of light-emitting direction perpendicular to of camera lens, so when the camera rotates, the camera lens can carry out the omnidirectional observation to the environment around the arrow body.
Description
Technical Field
The application relates to the technical field of motion trail shooting of carrier rocket launching, in particular to a shooting system on a carrier rocket cabin section
Background
In the whole flight process from launching to entering space of the carrier rocket, ground staff need to record the conditions of the surrounding environment of the rocket in the process of launching, the existing shooting direction can only be unidirectional shooting, unidirectional shooting cannot be carried out on the rocket in the process of launching, and the environment around the rocket body cannot be observed.
Disclosure of Invention
The application aims to solve the problems and provides a shooting system on a cabin section of a carrier rocket.
The application provides a shooting system on a carrier rocket cabin section, which comprises a camera mounting component, a camera module and a shooting module, wherein the camera mounting component is exposed out of the wall of the rocket cabin section and used for mounting a shooting camera; the transparent protective cover covers the camera mounting assembly, and the edge of the transparent protective cover is fixed on the rocket cabin section wall; the transmission assembly penetrates through the rocket cabin section wall and is fixedly connected with the camera mounting assembly; the driving assembly is arranged in the rocket cabin section wall and used for driving the transmission assembly to rotate along a first axis; the first axis is disposed perpendicular to the rocket pod segment wall; the positive light emitting direction of a lens of the camera is perpendicular to the first axis.
According to the technical scheme that this application embodiment provided, drive assembly is including the switching axle, the switching axle is close to the terminal surface of camera installation component is equipped with the locating hole, camera installation component is equipped with and inserts locating pin in the locating hole, camera installation component passes through the bolt fastening and is in the terminal surface of switching axle.
According to the technical scheme provided by the embodiment of the application, the rocket cabin segment wall is provided with a through hole, and the transmission assembly further comprises:
the mounting plate is positioned in the rocket cabin section wall, covers the through hole and is fixed on the rocket cabin section wall, and the adapter shaft is matched and connected with the mounting plate through a first bearing;
the bearing gland is positioned outside the rocket cabin section wall, and the adapter shaft extends out of the bearing gland and is connected with the camera mounting plate;
the adapter shaft is matched and connected with the bearing gland through a second bearing.
According to the technical scheme provided by the embodiment of the application, the driving assembly comprises:
a drive element having an output shaft disposed parallel to the rocket pod segment wall;
the output shaft is in transmission connection with one end, far away from the camera mounting assembly, of the adapter shaft through a bevel gear set.
According to the technical scheme provided by the embodiment of the application, the driving element is fixedly connected with the mounting plate.
According to the technical scheme provided by the embodiment of the application, the rocket cabin section wall is provided with a mounting hole, the camera mounting assembly comprises a hollow annular mounting block, and the annular side wall of the mounting block is provided with an annular mounting groove; the edge of the mounting hole is embedded into the mounting groove and is matched and connected with the mounting groove through a third bearing.
According to the technical scheme provided by the embodiment of the application, a circle of annular tooth surface is arranged at the end part of the mounting block positioned in the rocket cabin section wall; a gear meshed with the annular tooth surface is rotatably arranged in the rocket cabin section wall; the gear is driven to rotate by the driving assembly; the diameter of the annular tooth surface is larger than that of the gear.
According to the technical scheme provided by the embodiment of the application, the transmission assembly comprises a driving element arranged on the wall of the rocket cabin segment, an output shaft of the driving element is arranged in parallel to the wall of the rocket cabin segment, and the output shaft is in secondary transmission connection with the gear through a bevel gear set.
According to the technical scheme provided by the embodiment of the application, the middle part of the end face of the mounting block, which is positioned outside the rocket cabin, is fixedly provided with an L-shaped supporting plate, and the camera is fixed on the L-shaped supporting plate.
Compared with the prior art, the beneficial effect of this application: the camera mounting component is arranged outside the rocket cabin section, the transparent protective cover is fixed outside the camera mounting component, the positive light emitting direction of the camera lens is vertical to the direction of the first axis, the transmission component which penetrates through the wall of the rocket cabin section and is fixedly connected with the camera mounting component is also arranged, the driving component for driving the transmission component to rotate along the first axis is also arranged, the direction of the first axis is vertical to the wall of the rocket cabin section, when the rocket is used, the driving component provides power to drive the transmission component to rotate, the camera mounting component fixedly connected with the transmission component can rotate along with the transmission component, and the positive light emitting direction of the camera lens is vertical to the direction of the first axis, so when the camera is driven to rotate by the camera mounting component, the observation of the environment around the rocket body can be realized by using one camera, and on one hand, the space occupied by the camera can be reduced, on the other hand, the weight of the rocket is reduced.
Drawings
Fig. 1 is an overall schematic view of a shooting system on a launch vehicle cabin section provided in embodiment 1 of the present application;
fig. 2 is a schematic structural diagram of a shooting system on a launch vehicle cabin section provided in embodiment 1 of the present application;
FIG. 3 is a schematic view of a configuration of a transfer shaft on a launch vehicle bay section as provided in embodiment 1 of the present application;
FIG. 4 is a schematic structural diagram of a first bevel gear set of the shooting system on a launch vehicle cabin section provided in embodiment 1 of the present application;
fig. 5 is a schematic structural diagram of a shooting system on a launch vehicle cabin section provided in embodiment 2 of the present application;
fig. 6 is a schematic structural diagram of a mounting block of a shooting system on a launch vehicle cabin section according to embodiment 2 of the present application.
The text labels in the figures are represented as:
1. a drive element; 2. a transfer shaft; 3. a first bearing; 4. mounting a plate; 5-1, rocket cabin section walls; 6. a bearing gland; 7. a transparent protective cover; 8. a second bearing; 10. a camera; 11. mounting holes; 12. mounting blocks; 13. mounting grooves; 14. a third bearing; 15. an annular tooth surface; 16. a gear; 17. a third bevel gear; 18. an L-shaped support plate; 19. a fourth bevel gear; 20. a first bevel gear; 22. a second bevel gear.
Detailed Description
The following detailed description of the present application is given in conjunction with the accompanying drawings for the purpose of enabling those skilled in the art to better understand the technical solution of the present application, and the description in this section is only exemplary and explanatory, and should not be taken as limiting the scope of the present application in any way.
Example 1
Referring to fig. 1 to 4, the present embodiment provides a shooting system on a launch vehicle cabin, including: the camera mounting assembly is exposed out of the rocket cabin section wall 5-1 and used for mounting a shooting camera 10;
the transparent protective cover 7 covers the camera mounting component, and the edge of the transparent protective cover is fixed on the rocket cabin section wall 5-1;
the transmission assembly penetrates through the rocket cabin section wall 5-1 and is fixedly connected with the camera mounting assembly;
the driving assembly is arranged in the rocket cabin section wall 5-1 and used for driving the transmission assembly to rotate along a first axis; the first axis is disposed perpendicular to the rocket tank segment wall 5-1;
the positive light emitting direction of the lens of the camera 10 is perpendicular to the first axis.
Specifically, in this embodiment, the camera mounting assembly is fixedly mounted on the rocket cabin segment, the camera mounting assembly is mounted outside the wall 5-1 of the rocket cabin segment, and the camera mounting assembly is used for mounting a camera 10 which needs to shoot the environment around the rocket body; a transparent protective cover 7 is further mounted outside the camera mounting assembly, the transparent protective cover 7 is used for protecting the camera 10 from being damaged in the use process, the edge of the transparent protective cover 7 is fixedly connected to the outer wall of the rocket cabin segment wall 5-1, the transparent protective cover 7 can be fixed to the outer wall of the rocket cabin segment wall 5-1 in a welding mode for keeping the stability of the transparent protective cover 7 in the use process, a transmission assembly is further mounted inside the rocket cabin segment wall 5-1, the camera mounting assembly is provided with a first end and a second end, the first end is connected with the transmission assembly, the second end is located outside the rocket cabin segment and is connected with the camera 10, for example, the transmission assembly can be welded, and a driving assembly is further arranged inside the rocket cabin segment wall 5-1 and is used for providing rotating force for the transmission assembly, the rocket pod driving device is used for driving the transmission assembly to rotate along the direction of a first axis, the direction of the first axis is perpendicular to the extending direction of the rocket pod section wall 5-1, the camera 10 is fixedly installed on the second end of the camera installation assembly, and the positive light emitting direction of the lens of the camera 10 is perpendicular to the direction of the first axis, so that when the camera 10 rotates, the omnibearing recording of the environment around the rocket body can be realized.
In the use, open drive assembly's switch, drive assembly can provide power and drive transmission assembly and rotate, and the camera installation component who is connected with transmission assembly can rotate along with it to drive the camera and rotate, the camera can observe the environment around the arrow body at the pivoted in-process, the record.
The application provides a can realize camera in the course of the work, can rotate on the arrow body is originally up to under the condition that does not need other cameras, observe the environment around the arrow body.
Furthermore, the transmission assembly comprises a transfer shaft 2, the transfer shaft 2 is close to the end face of the camera mounting assembly and is provided with a positioning hole, the camera mounting assembly is provided with a positioning pin inserted into the positioning hole, and the camera mounting assembly is fixed on the end face of the transfer shaft 2 through a bolt.
Specifically, in this embodiment, the transmission assembly includes a connecting shaft 2, the connecting shaft 2 is close to a positioning hole is embedded in the end face of the first end of the camera mounting assembly, a positioning pin is arranged at the first end of the camera mounting assembly, the positioning pin can be inserted into the positioning hole, a first group of threaded holes are respectively arranged at two sides of the positioning hole, a second group of threaded holes corresponding to the first group of threaded holes are arranged at the first end of the camera mounting assembly, the inner diameters of the first group of threaded holes and the second group of threaded holes are consistent, and in the using process, the positioning pin is inserted into the positioning hole, the first group of threaded holes are aligned with the second group of threaded holes, and the connecting shaft is tightly connected with the camera mounting assembly through bolts.
Furthermore, a through hole is formed in the rocket cabin section wall 5-1, and the transmission assembly further comprises:
the mounting plate 4 is positioned in the rocket cabin section wall 5-1, covers the through hole and is fixed on the rocket cabin section wall 5-1, and the transfer shaft 2 is matched and connected with the mounting plate 4 through a first bearing 3;
the bearing gland 6 is positioned outside the rocket cabin section wall 5-1, and the transfer shaft 2 extends out of the bearing gland 6 and is connected with the camera mounting plate 4;
the adapter shaft 2 is matched and connected with the bearing gland 6 through a second bearing 8.
Specifically, in this embodiment, a circular through hole is formed in the rocket cabin segment wall 5-1, the transmission assembly further includes a mounting plate 4, the mounting plate 4 is fixedly connected in the rocket cabin segment wall 5-1, and the mounting plate 4 covers the through hole, a first bearing 3 is installed inside the through hole, the first bearing 3 is an angular contact ball bearing, the first bearing 3 is fixedly connected between the transfer shaft 2 and the mounting plate 4, a bearing cover 6 is further disposed outside the rocket cabin segment wall 5-1, a protrusion is disposed on the mounting plate 4, a notch is formed between one side of the protrusion and the transfer shaft 2, the first bearing 3 is embedded inside the notch, the bearing cover 6 simultaneously compresses the mounting plate 4 and the first bearing 3, and one end of the transfer shaft 2, which is far away from the through hole, extends outward to the outside of the bearing cover 6, a second bearing 8 is connected between the switching shaft 2 and the bearing gland 6, and the second bearing 8 is a plane bearing.
Further, the drive assembly includes; a drive element 1 having an output shaft arranged parallel to the rocket cabin segment wall 5-1;
the output shaft is in transmission connection with one end, far away from the camera mounting assembly, of the transfer shaft 2 through a bevel gear set.
Specifically, in this embodiment, the driving assembly includes a driving element 1, the driving element 1 is a motor, the driving element 1 has an output shaft, the direction of the output shaft is parallel to the rocket cabin segment, the output shaft and an end of the transfer shaft 2 away from the camera mounting assembly are connected by the first bevel gear set, the first bevel gear set includes a first bevel gear 20 and a second bevel gear 21, and the first bevel gear 20 is in meshed connection with the second bevel gear 21.
Further, the driving element 1 is fixedly connected with the mounting plate 4.
Specifically, in the present embodiment, the driving element 1 and the mounting plate 4 are fixedly connected, for example, by riveting.
Example 2
The embodiment provides a shooting system on a carrier rocket cabin section, which is further improved on the basis of embodiment 1, and the same points as those in embodiment 1 are not repeated, except that a mounting hole 11 is formed in a wall 5-1 of the rocket cabin section, the camera mounting assembly comprises a hollow annular mounting block 12, and an annular mounting groove 13 is formed in an annular side wall of the mounting block 12; the edge of the mounting hole 11 is inserted into the mounting groove 13 and is coupled to the mounting groove 13 through a third bearing 14.
Specifically, in this embodiment, a mounting hole 11 is formed in a side wall of the rocket cabin segment wall 5-1, the mounting hole 11 is circular, the camera mounting assembly includes an annular mounting block 12, the mounting block 12 is in a hollow cylindrical shape, a mounting groove 13 is embedded in the annular side wall of the mounting block 12, the mounting groove 13 is circular, the mounting groove 13 and the mounting block 12 can be used in a mutually matched manner, a third bearing 14 is further installed between the mounting groove 13 and the mounting block 12, and the third bearing 14 can be a flat bearing.
Further, the end part of the mounting block 12 positioned in the rocket cabin segment wall 5-1 is provided with a circle of annular tooth surface 15; a gear 16 meshed and connected with the annular tooth surface 15 is rotatably arranged in the rocket cabin section wall 5-1; the gear 16 is driven to rotate by the drive assembly; the diameter of the annular tooth surface 15 is larger than the gear 16.
Specifically, in this embodiment, the mounting block 12 includes a first end, the first end is located inside the rocket cabin section, a circle of tooth surface is arranged outside the first end, the tooth surface forms an annular tooth surface 15 around the first end of the mounting block, a gear 16 is further mounted on the inner wall of the rocket cabin section, the gear 16 is in meshing connection with the annular tooth surface 15, the gear 16 is mounted on the inner wall of the rocket cabin section wall 5-1, and the gear 16 is rotatably connected with the inner wall of the rocket cabin section wall 5-1; the gear 16 is connected with an extending shaft of the driving assembly, the driving assembly is used for driving the gear 16 to rotate, the gear 16 rotates correspondingly to the annular tooth surface 15 on the mounting block 12 in meshed connection with the gear 16 in the rotating process, and the diameter of the annular tooth surface 15 is larger than that of the gear 16.
Further, the transmission assembly comprises a driving element 1 installed on the rocket cabin section wall 5-1, an output shaft of the driving element 1 is arranged in parallel to the rocket cabin section wall 5-1, and the output shaft is in transmission connection with the gear 16 through a bevel gear set II.
Specifically, in this embodiment, the driving element includes an output shaft, the direction of the output shaft is parallel to the rocket cabin segment wall 5-1, that is, the driving element is parallel to the rocket cabin segment wall 5-1, one end of the output shaft is further connected with a third bevel gear 17 and a fourth bevel gear 19, the third bevel gear 17 and the fourth bevel gear 19 are in meshing connection, and the fourth bevel gear 19 and the gear 16 are in meshing connection.
Furthermore, an L-shaped support plate 18 is fixed in the middle of the end face of the mounting block 12 located outside the rocket cabin, and the camera 10 is fixed on the L-shaped support plate 18.
The mounting block 12 has a second end extending outside the rocket pod section, an L-shaped support plate 18 is fixedly connected to the second end, for example, the L-shaped support plate 18 may be fixed by using bolts, and the camera 10 may be fixed to the L-shaped support plate 18 by riveting.
The shooting system on carrier rocket cabin section that this application embodiment provided starts drive element, drive element's output shaft can drive transmission assembly and rotate, and is corresponding, and transmission assembly can drive camera installation component and rotate, and the camera that is connected with camera installation component simultaneously also can rotate, and the direction that the camera lens is just giving vent to anger is the first axis of perpendicular to, so carry out the pivoted in-process at camera installation component, and the camera can carry out the omnidirectional observation to the environment around the arrow body.
The principles and embodiments of the present application are explained herein using specific examples, which are provided only to help understand the method and the core idea of the present application. The foregoing is only a preferred embodiment of the present application, and it should be noted that there are no specific structures which are objectively limitless due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes can be made without departing from the principle of the present invention, and the technical features mentioned above can be combined in a suitable manner; such modifications, variations, combinations, or adaptations of the invention using its teachings or may be resorted to without departing from the scope of the invention as set forth in the claims that follow.
Claims (9)
1. A camera system on a launch vehicle bay, comprising:
the camera mounting component is exposed out of the rocket cabin section wall (5-1) and used for mounting a shooting camera (10);
the transparent protective cover (7) covers the camera mounting assembly, and the edge of the transparent protective cover is fixed on the rocket cabin section wall (5-1);
the transmission assembly penetrates through the rocket cabin section wall (5-1) and is fixedly connected with the camera mounting assembly;
the driving component is arranged in the rocket cabin section wall (5-1) and is used for driving the transmission component to rotate along a first axis; the first axis is arranged perpendicular to the rocket tank section wall (5-1);
the positive light emitting direction of the lens of the camera (10) is perpendicular to the first axis.
2. Shooting system on a launch vehicle cabin segment according to claim 1, characterised in that the transmission assembly comprises a swivel shaft (2), the end face of the swivel shaft (2) near the camera mounting assembly is provided with a positioning hole, the camera mounting assembly is provided with a positioning pin inserted into the positioning hole, and the camera mounting assembly is fixed on the end face of the swivel shaft (2) by bolts.
3. The camera system of claim 1, wherein the rocket pod wall (5-1) is perforated with through holes, and wherein the transmission assembly further comprises:
the mounting plate (4) is positioned in the rocket cabin section wall (5-1), covers the through hole and is fixed on the rocket cabin section wall (5-1), and the transfer shaft (2) is matched and connected with the mounting plate (4) through a first bearing (3);
the bearing gland (6) is positioned outside the rocket cabin section wall (5-1), and the transfer shaft (2) extends out of the bearing gland (6) and is connected with the camera mounting plate (4);
the adapter shaft (2) is connected with the bearing gland (6) in a matching mode through a second bearing (8).
4. The camera system on a launch vehicle bay according to claim 2 or 3, wherein the drive assembly comprises:
a drive element (1) having an output shaft arranged parallel to the rocket cabin segment wall (5-1);
the output shaft is in transmission connection with one end, far away from the camera mounting assembly, of the transfer shaft (2) through a bevel gear set.
5. Photographic system on a launch vehicle bay section according to claim 4, characterised in that the drive element (1) is fixedly connected to the mounting plate (4) when the transmission assembly has the structure of claim 3.
6. The shooting system on a launch vehicle bay section of claim 1, wherein the rocket bay section wall (5-1) is perforated with mounting holes (11), the camera mounting assembly comprises a hollow annular mounting block (12), and an annular side wall of the mounting block (12) is perforated with an annular mounting groove (13); the edge of the mounting hole (11) is embedded into the mounting groove (13) and is matched and connected with the mounting groove (13) through a third bearing (14).
7. Photographic system on a launch vehicle bay section according to claim 6, characterised in that the end of the mounting block (12) inside the wall (5-1) of the rocket bay section is provided with a ring of annular tooth flanks (15); a gear (16) meshed with the annular tooth surface (15) is rotatably arranged in the rocket cabin section wall (5-1); the gear (16) is driven to rotate by the driving component; the diameter of the annular tooth surface (15) is larger than that of the gear (16).
8. Shooting system on a launch vehicle bay according to claim 7, characterised in that the transmission assembly comprises a driving element (1) mounted on the wall (5-1) of the rocket bay, the output shaft of the driving element (1) being arranged parallel to the wall (5-1) of the rocket bay, the output shaft being drivingly connected to the gear wheel (16) by means of a bevel gear set two.
9. Shooting system on a launcher capsule section according to claim 8, characterized in that the mounting block (12) has an L-shaped support plate (18) fixed in the middle of its end face outside the rocket capsule, and the camera (10) is fixed on the L-shaped support plate (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210701872.5A CN114993119A (en) | 2022-06-21 | 2022-06-21 | Shooting system on carrier rocket cabin section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210701872.5A CN114993119A (en) | 2022-06-21 | 2022-06-21 | Shooting system on carrier rocket cabin section |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114993119A true CN114993119A (en) | 2022-09-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210701872.5A Pending CN114993119A (en) | 2022-06-21 | 2022-06-21 | Shooting system on carrier rocket cabin section |
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| Country | Link |
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| CN (1) | CN114993119A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010006218A1 (en) * | 1999-12-27 | 2001-07-05 | Matsushita Electric Industrial Co., Ltd. | Structure of motor-driven swing unit |
| CN2451866Y (en) * | 2000-11-24 | 2001-10-03 | 深圳市艾立克电子有限公司 | Side-mounting ball-shape telecamera stand |
| JP2010107772A (en) * | 2008-10-30 | 2010-05-13 | Victor Co Of Japan Ltd | Tilt mechanism of monitoring camera apparatus |
| CN113022899A (en) * | 2020-12-09 | 2021-06-25 | 北京星际荣耀空间科技股份有限公司 | External camera mounting structure of carrier rocket |
| CN113022870A (en) * | 2021-03-10 | 2021-06-25 | 上海海事大学 | Measuring device for coast remote sensing |
| CN114295014A (en) * | 2021-12-30 | 2022-04-08 | 宁波天擎航天科技有限公司 | Rocket of external rudder system |
-
2022
- 2022-06-21 CN CN202210701872.5A patent/CN114993119A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010006218A1 (en) * | 1999-12-27 | 2001-07-05 | Matsushita Electric Industrial Co., Ltd. | Structure of motor-driven swing unit |
| CN2451866Y (en) * | 2000-11-24 | 2001-10-03 | 深圳市艾立克电子有限公司 | Side-mounting ball-shape telecamera stand |
| JP2010107772A (en) * | 2008-10-30 | 2010-05-13 | Victor Co Of Japan Ltd | Tilt mechanism of monitoring camera apparatus |
| CN113022899A (en) * | 2020-12-09 | 2021-06-25 | 北京星际荣耀空间科技股份有限公司 | External camera mounting structure of carrier rocket |
| CN113022870A (en) * | 2021-03-10 | 2021-06-25 | 上海海事大学 | Measuring device for coast remote sensing |
| CN114295014A (en) * | 2021-12-30 | 2022-04-08 | 宁波天擎航天科技有限公司 | Rocket of external rudder system |
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