CN115060122A - Carrier rocket cabin section structure for modularized rapid assembly - Google Patents
Carrier rocket cabin section structure for modularized rapid assembly Download PDFInfo
- Publication number
- CN115060122A CN115060122A CN202210590597.4A CN202210590597A CN115060122A CN 115060122 A CN115060122 A CN 115060122A CN 202210590597 A CN202210590597 A CN 202210590597A CN 115060122 A CN115060122 A CN 115060122A
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- cabin section
- groove
- column
- sides
- threaded column
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- 238000013016 damping Methods 0.000 claims abstract description 22
- 230000035939 shock Effects 0.000 claims abstract description 12
- 230000000694 effects Effects 0.000 claims description 10
- 238000010521 absorption reaction Methods 0.000 claims description 6
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 230000013011 mating Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 17
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000002146 bilateral effect Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 210000002421 cell wall Anatomy 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Images
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
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/06—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs
- F16F15/067—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs using only wound springs
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Mechanical Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a modular and fast-assembled carrier rocket cabin section structure which comprises a lower cabin section, an upper cabin section and a damping support base. The invention has the beneficial effects that: lower cabin section and last cabin section between through screw thread post one, cooperation between go-between and the screw thread post two is connected, the radome fairing is connected with the last cabin section through the screw thread groove two with screw thread post two's cooperation, the boost motor passes through the mounting panel, cooperation and the lower lateral wall of lower cabin section between fastening bolt and the screw are connected, the downside at lower cabin section is installed through the screw thread groove one and the cooperation of screw thread head to the shock attenuation support base, high assembly efficiency, through setting up the shock attenuation support base, when this carrier rocket cabin section structure receives vibrations, the movable block can reciprocate in the installation through groove, thereby utilize the damping rod, cooperation between spring one and the spring two is to the shock attenuation carrier rocket cabin section, avoid its connection structure to relax because of frequent vibrations.
Description
Technical Field
The invention relates to a rocket cabin section structure, in particular to a carrier rocket cabin section structure for modularized rapid assembly, and belongs to the technical field of rocket assembly.
Background
The carrier rocket refers to various carriers which are manufactured by people and push spacecrafts to space, the aerospace technology of our country is more mature along with the continuous development of science and technology, the development of the aerospace technology is convenient for us to well develop advanced technologies such as satellite positioning, satellite navigation and the like, in the process of researching and manufacturing the rocket, the engine of the rocket needs to be tested to run, the engine is usually installed in the lower cabin section of the test-flight carrier rocket, then all cabin sections of the carrier rocket are assembled, and finally the flying condition of the rocket is observed through an ignition test.
When the existing carrier rocket cabin section structures are assembled and used, the following defects are often existed:
1) the connection mode among all cabin sections in the existing some carrier rocket cabin section structures is complex, and the existing carrier rocket cabin section structures consume time and labor during assembly and are inconvenient to disassemble;
2) when some current carrier rocket combination cabin section structures are placed on the guiding gutter that ground set up, because the inside damper that lacks of support base that it set up, can't play certain cushioning effect to the carrier rocket, lead to placing the in-process, rocket cabin section structure is direct and ground contact, and the impact force of receiving is great, causes the damage to the carrier rocket easily.
Disclosure of Invention
The present invention is directed to solving at least one of the above problems by providing a modular, quick-assembly launch vehicle hull section structure.
The invention achieves the above purpose through the following technical scheme: a carrier rocket cabin section structure for modularized rapid assembly comprises
The lower cabin section is arranged on the lower side of the rocket cabin section, a nozzle is fixedly arranged at the center of the lower end of the lower cabin section, connecting columns are symmetrically arranged on two sides of the nozzle, a first threaded groove is formed in the lower end of each connecting column, and a booster is arranged on the periphery of the lower side wall of the lower cabin section;
the upper cabin section is arranged at the upper end of the lower cabin section, and the upper end of the upper cabin section is provided with a fairing;
the shock absorption supporting base is installed on the two sides of the lower end of the lower cabin section through a connecting column and comprises a base which is directly contacted with the ground and a movable block which is arranged inside the base in a sliding mode.
As a still further scheme of the invention: the upper end of the lower cabin section is fixedly provided with a first threaded column, the upper end and the lower end of the upper cabin section are fixedly connected with a second threaded column, a connecting ring matched with the first threaded column and the second threaded column is arranged between the lower cabin section and the upper cabin section, internal threads matched with the first threaded column and the second threaded column are arranged inside the connecting ring, and the lower cabin section and the upper cabin section are connected through the matching effect among the first threaded column, the connecting ring and the second threaded column.
As a still further scheme of the invention: and a second thread groove is formed in the bottom wall of the lower end of the fairing, an internal thread matched with the second thread column arranged at the upper end of the upper cabin section is arranged in the second thread groove, and the fairing is connected with the upper cabin section through the matching effect of the second thread groove and the second thread column.
As a still further scheme of the invention: the booster is characterized in that a fixed rod is fixedly mounted on one side wall of the booster, one end, far away from the booster, of the fixed rod is connected with a mounting plate, fastening bolts are arranged on two sides of the mounting plate in a penetrating mode, screw holes matched with the fastening bolts are formed in the surface of the shell of the lower cabin section, and the booster is connected with the lower side wall of the lower cabin section through the matching effect among the mounting plate, the fastening bolts and the screw holes.
As a still further scheme of the invention: the installation is seted up to the inside of base and is led to the groove, the bilateral symmetry that the groove was led to in the installation installs damping rod, both sides the equal rigid coupling in upper end of damping rod has the connecting block, and sliding connection between connecting block and the installation lead to the groove cell wall, spring one has been cup jointed in the pole body outside of damping rod, two liang of sides the rigid coupling has the movable block between the connecting block, the interior diapire upside rigid coupling that the groove was led to in the installation has the slide bar, and the pole body both sides slip of slide bar have cup jointed the sliding sleeve, two the both sides that the sliding sleeve was kept away from all are provided with the spring two of cup jointing on the slide bar, and the upside of two sliding sleeves all articulates there is the connecting rod, two the one end that the sliding sleeve was kept away from to the connecting rod all is put through the diapire central point of articulated shaft and movable block and is articulated.
As a still further scheme of the invention: the upper surface central point of movable block puts fixedly connected with erection column, and the upper end of erection column is connected with the screw thread head with thread groove one matched with, the shock attenuation supports the base and installs through the mating reaction of thread groove one and screw thread head the downside of lower cabin section.
The invention has the beneficial effects that:
1) according to the invention, the lower cabin section is connected with the upper cabin section through the matching action of the threaded column I, the connecting ring and the threaded column II, the fairing is connected with the upper cabin section through the matching action of the threaded groove II and the threaded column II, the booster is connected with the lower side wall of the lower cabin section through the matching action of the mounting plate, the fastening bolt and the screw hole, and the damping support base is mounted on the lower side of the lower cabin section through the matching action of the threaded groove I and the threaded head;
2) according to the invention, by arranging the damping support base, when the carrier rocket cabin section structure is vibrated in the placing process, the movable block can move up and down in the installation through groove, so that the carrier rocket cabin section is damped by utilizing the cooperation effect among the damping rod, the first spring and the second spring, the connecting structure of the carrier rocket cabin section is prevented from being loosened due to frequent vibration, and a certain protection effect is achieved on the carrier rocket.
Drawings
FIG. 1 is a schematic view of a structural connection of the launch vehicle capsule sections of the present invention;
FIG. 2 is a schematic illustration of a disassembled structure of a launch vehicle bay section of the present invention;
FIG. 3 is a cross-sectional view of the shock absorbing support base of the present invention.
In the figure: 1. the auxiliary device comprises a lower cabin section, 2, an upper cabin section, 3, a fairing, 4, a connecting ring, 5, a booster, 6, a connecting column, 7, a damping supporting base, 701, a base, 702, an installation through groove, 703, a damping rod, 704, a spring I, 705, a connecting block, 706, a movable block, 707, an installation column, 708, a sliding rod, 709, a sliding sleeve, 7010, a spring II, 7011, a connecting rod, 8, a thread groove II, 9, a thread column II, 10, a thread groove I, 11, a thread column I, 12, a fixing rod, 13, an installation plate, 14 and a fastening bolt.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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.
Example one
As shown in fig. 1 to 3, a structure of a launch vehicle cabin segment for modular rapid assembly comprises
The lower cabin section 1 is arranged on the lower side of the rocket cabin section, a nozzle is fixedly arranged at the center of the lower end of the lower cabin section, connecting columns 6 are symmetrically arranged on two sides of the nozzle, a first thread groove 10 is formed in the lower end of each connecting column 6, and a booster 5 is arranged on the periphery of the lower side wall of the lower cabin section 1;
the upper cabin section 2 is arranged at the upper end of the lower cabin section 1, and the upper end of the upper cabin section is provided with a fairing 3;
and the shock absorption supporting bases 7 are arranged on two sides of the lower end of the lower cabin section 1 through connecting columns 6 and comprise bases 701 directly contacted with the ground and movable blocks 706 arranged inside the bases 701 in a sliding mode.
In the embodiment of the invention, the upper end of the lower cabin section 1 is fixedly provided with the threaded column I11, the upper end and the lower end of the upper cabin section 2 are fixedly connected with the threaded column II 9, the connecting ring 4 matched with the threaded column I11 and the threaded column II 9 is arranged between the lower cabin section 1 and the upper cabin section 2, the inner thread matched with the threaded column I11 and the threaded column II 9 is arranged inside the connecting ring 4, and the lower cabin section 1 and the upper cabin section 2 are connected through the matching action among the threaded column I11, the connecting ring 4 and the threaded column II 9, so that the lower cabin section 1 and the upper cabin section 2 can be conveniently assembled and disassembled.
In the embodiment of the invention, the inner part of the bottom wall of the lower end of the fairing 3 is provided with the second thread groove 8, the inner part of the second thread groove 8 is provided with the internal thread matched with the second thread column 9 arranged at the upper end of the upper cabin section 2, and the fairing 3 is connected with the upper cabin section 2 through the matching action of the second thread groove 8 and the second thread column 9, so that the assembly and disassembly of the fairing 3 and the upper cabin section 2 are convenient.
In the embodiment of the invention, a fixing rod 12 is fixedly installed on one side wall of the booster 5, one end of the fixing rod 12, which is far away from the booster 5, is connected with an installation plate 13, fastening bolts 14 are arranged on two sides of the installation plate 13 in a penetrating manner, screw holes matched with the fastening bolts 14 are formed in the surface of the shell of the lower cabin section 1, and the booster 5 is connected with the lower side wall of the lower cabin section 1 through the matching action among the installation plate 13, the fastening bolts 14 and the screw holes, so that the booster 5 is conveniently connected with the lower cabin section 1.
Example two
As shown in fig. 1 to 3, a structure of a launch vehicle cabin segment for modular rapid assembly comprises
The lower cabin section 1 is arranged on the lower side of the rocket cabin section, a nozzle is fixedly arranged at the center of the lower end of the lower cabin section, connecting columns 6 are symmetrically arranged on two sides of the nozzle, a first thread groove 10 is formed in the lower end of each connecting column 6, and a booster 5 is arranged on the periphery of the lower side wall of the lower cabin section 1;
an upper cabin section 2 which is installed at the upper end of the lower cabin section 1, and the upper end of which is installed with a fairing 3;
and the shock absorption supporting bases 7 are installed on two sides of the lower end of the lower cabin section 1 through connecting columns 6 and comprise bases 701 directly contacting with the ground and movable blocks 706 arranged inside the bases 701 in a sliding mode.
In the embodiment of the invention, an installation through groove 702 is formed inside a base 701, damping rods 703 are symmetrically installed on two sides of the installation through groove 702, connecting blocks 705 are fixedly connected to the upper ends of the damping rods 703 on two sides, the connecting blocks 705 are slidably connected with the groove walls of the installation through groove 702, a first spring 704 is sleeved on the outer side of the rod body of the damping rods 703, a movable block 706 is fixedly connected between the connecting blocks 705 on two sides, a sliding rod 708 is fixedly connected to the upper side of the inner bottom wall of the installation through groove 702, sliding sleeves 709 are slidably sleeved on two sides of the rod body of the sliding rod 708, a second spring 7010 sleeved on the sliding rod 708 is arranged on two sides where the two sliding sleeves 709 are separated, connecting rods 7011 are hinged on the upper sides of the two sliding sleeves 709, one ends of the two connecting rods 7011 far away from the sliding sleeves 709 are hinged to the center position of the bottom wall of the movable block 706 through hinge shafts, and when the cabin structure of the carrier rocket is vibrated in use, the movable block 706 can move up and down in the installation through groove 702, therefore, the damping rod 703, the first spring 704 and the second spring 7010 are used for damping the cabin section of the carrier rocket, the connection structure of the carrier rocket is prevented from being loosened due to frequent vibration, and the modular assembled rocket is protected to a certain extent.
In the embodiment of the invention, the central position of the upper surface of the movable block 706 is fixedly connected with the mounting column 707, the upper end of the mounting column 707 is connected with the screw head matched with the first threaded groove 10, and the shock absorption support base 7 is installed on the lower side of the lower cabin section 1 through the matching action of the first threaded groove 10 and the screw head, so that the shock absorption support base 7 and the lower cabin section 1 can be conveniently assembled and disassembled.
The working principle is as follows: when the carrier rocket cabin section structure for modularized rapid assembly is used, all module structures are assembled, the lower cabin section 1 and the upper cabin section 2 are connected through the matching action among the threaded post I11, the connecting ring 4 and the threaded post II 9, then the fairing 3 is connected with the upper cabin section 2 through the matching action of the threaded groove II 8 and the threaded post II 9, then the booster 5 is connected with the lower side wall of the lower cabin section 1 through the matching action among the mounting plate 13, the fastening bolt 14 and the screw hole, finally the damping support base 7 is mounted on the lower side of the lower cabin section 1 through the matching action of the threaded groove I10 and the threaded head, the assembly efficiency is high, convenience is provided for later-stage disassembly and maintenance, and by arranging the damping support base 7, when the carrier rocket cabin section structure is vibrated in the use process, the movable block 706 can move up and down in the mounting through groove 702, therefore, the damping effect is realized on the cabin section of the carrier rocket by the aid of the cooperation effect of the damping rods 703, the first springs 704 and the second springs 7010, and the connecting structure of the carrier rocket is prevented from being loosened due to frequent vibration.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present specification describes embodiments, not every embodiment includes only a single embodiment, and such description is for clarity purposes only, and it is to be understood that all embodiments may be combined as appropriate by one of ordinary skill in the art to form other embodiments as will be apparent to those of skill in the art from the description herein.
Claims (6)
1. A carrier rocket cabin section structure for modularized rapid assembly is characterized by comprising
The lower cabin section (1) is arranged on the lower side of the rocket cabin section, a nozzle is fixedly arranged in the center of the lower end of the lower cabin section, connecting columns (6) are symmetrically arranged on two sides of the nozzle, a first threaded groove (10) is formed in the lower end of each connecting column (6), and boosters (5) are arranged on the periphery of the lower side wall of the lower cabin section (1);
an upper cabin section (2) which is arranged at the upper end of the lower cabin section (1), and the upper end of which is provided with a fairing (3);
and the shock absorption supporting base (7) is arranged on two sides of the lower end of the lower cabin section (1) through a connecting column (6), and comprises a base (701) directly contacted with the ground and a movable block (706) arranged inside the base (701) in a sliding manner.
2. A launch vehicle bay structure for modular rapid assembly according to claim 1, wherein: the upper end of the lower cabin section (1) is fixedly provided with a first threaded column (11), the upper end and the lower end of the upper cabin section (2) are fixedly connected with a second threaded column (9), a connecting ring (4) matched with the first threaded column (11) and the second threaded column (9) is arranged between the lower cabin section (1) and the upper cabin section (2), internal threads matched with the first threaded column (11) and the second threaded column (9) are arranged inside the connecting ring (4), and the lower cabin section (1) and the upper cabin section (2) are connected through the matching effect among the first threaded column (11), the connecting ring (4) and the second threaded column (9).
3. A launch vehicle bay structure for modular rapid assembly according to claim 1, wherein: a second thread groove (8) is formed in the bottom wall of the lower end of the fairing (3), an internal thread matched with a second thread column (9) arranged at the upper end of the upper cabin section (2) is arranged in the second thread groove (8), and the fairing (3) is connected with the upper cabin section (2) through the matching effect of the second thread groove (8) and the second thread column (9).
4. A launch vehicle bay structure for modular rapid assembly according to claim 1, wherein: fixed mounting has dead lever (12) on one side lateral wall of boost motor (5), the one end that boost motor (5) were kept away from in dead lever (12) is connected with mounting panel (13), the both sides through-thread of mounting panel (13) is provided with fastening bolt (14), the shell surface of cabin section (1) down seted up with fastening bolt (14) matched with screw, boost motor (5) are connected with the lower lateral wall of cabin section (1) down through the mating reaction between mounting panel (13), fastening bolt (14) and the screw.
5. A launch vehicle bay structure for modular rapid assembly according to claim 1, wherein: a mounting through groove (702) is formed in the base (701), damping rods (703) are symmetrically mounted on two sides of the mounting through groove (702), connecting blocks (705) are fixedly connected to the upper ends of the damping rods (703) on the two sides, and the connecting blocks (705) are connected with the groove wall of the mounting through groove (702) in a sliding way, the outer side of the rod body of the damping rod (703) is sleeved with a first spring (704), a movable block (706) is fixedly connected between the connecting blocks (705) at two sides, a sliding rod (708) is fixedly connected to the upper side of the inner bottom wall of the mounting through groove (702), sliding sleeves (709) are sleeved on two sides of the rod body of the sliding rod (708) in a sliding mode, two sides, away from each other, of the two sliding sleeves (709) are provided with second springs (7010) sleeved on the sliding rod (708), and the upside of two sliding sleeves (709) all articulates there is connecting rod (7011), two the one end that sliding sleeve (709) were kept away from in connecting rod (7011) all hinges through the articulated shaft with the diapire central point of movable block (706) puts.
6. A launch vehicle nacelle segment structure for modular rapid assembly according to claim 5, wherein: the upper surface central point of movable block (706) puts fixedly connected with erection column (707), and the upper end of erection column (707) is connected with the screw head with screw groove (10) matched with, shock attenuation support base (7) are installed through screw groove (10) and screw head's mating reaction the downside of cabin section (1) down.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210590597.4A CN115060122A (en) | 2022-05-27 | 2022-05-27 | Carrier rocket cabin section structure for modularized rapid assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210590597.4A CN115060122A (en) | 2022-05-27 | 2022-05-27 | Carrier rocket cabin section structure for modularized rapid assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115060122A true CN115060122A (en) | 2022-09-16 |
Family
ID=83198153
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210590597.4A Pending CN115060122A (en) | 2022-05-27 | 2022-05-27 | Carrier rocket cabin section structure for modularized rapid assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115060122A (en) |
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|---|---|---|---|---|
| US3351307A (en) * | 1964-05-06 | 1967-11-07 | Dassault Electronique | Damped suspension system |
| CN106247871A (en) * | 2016-07-27 | 2016-12-21 | 江西洪都航空工业集团有限责任公司 | A kind of cabin, aircraft circular section segment connecting method |
| CN207961404U (en) * | 2018-03-01 | 2018-10-12 | 北京爱尔达电子设备有限公司 | Damping device and sounding rocket emit transport vehicle |
| CN111332492A (en) * | 2020-03-06 | 2020-06-26 | 北京机电工程研究所 | Aircraft cabin section cable-free butt joint device and butt joint method thereof |
| CN213481148U (en) * | 2021-05-13 | 2021-06-18 | 中国科学院力学研究所 | Three-boosting carrier based on modular fixed power system |
| CN213810920U (en) * | 2020-11-29 | 2021-07-27 | 无锡玛德安防爆电器有限公司 | Explosion-proof dehumidifier with shock-absorbing structure |
| CN214053729U (en) * | 2020-11-26 | 2021-08-27 | 无锡腾跃特种钢管有限公司 | Steel pipe perforation stabilizing device |
| CN214582822U (en) * | 2020-12-31 | 2021-11-02 | 北京中科宇航技术有限公司 | Rod system connection carrier based on modular solid power system |
| CN215798322U (en) * | 2021-09-16 | 2022-02-11 | 无锡世鼎建筑机械有限公司 | Intelligent remote control electric hanging basket |
-
2022
- 2022-05-27 CN CN202210590597.4A patent/CN115060122A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3351307A (en) * | 1964-05-06 | 1967-11-07 | Dassault Electronique | Damped suspension system |
| CN106247871A (en) * | 2016-07-27 | 2016-12-21 | 江西洪都航空工业集团有限责任公司 | A kind of cabin, aircraft circular section segment connecting method |
| CN207961404U (en) * | 2018-03-01 | 2018-10-12 | 北京爱尔达电子设备有限公司 | Damping device and sounding rocket emit transport vehicle |
| CN111332492A (en) * | 2020-03-06 | 2020-06-26 | 北京机电工程研究所 | Aircraft cabin section cable-free butt joint device and butt joint method thereof |
| CN214053729U (en) * | 2020-11-26 | 2021-08-27 | 无锡腾跃特种钢管有限公司 | Steel pipe perforation stabilizing device |
| CN213810920U (en) * | 2020-11-29 | 2021-07-27 | 无锡玛德安防爆电器有限公司 | Explosion-proof dehumidifier with shock-absorbing structure |
| CN214582822U (en) * | 2020-12-31 | 2021-11-02 | 北京中科宇航技术有限公司 | Rod system connection carrier based on modular solid power system |
| CN213481148U (en) * | 2021-05-13 | 2021-06-18 | 中国科学院力学研究所 | Three-boosting carrier based on modular fixed power system |
| CN215798322U (en) * | 2021-09-16 | 2022-02-11 | 无锡世鼎建筑机械有限公司 | Intelligent remote control electric hanging basket |
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