CN113998135A - Axial locking and releasing assembly of non-falling type broken unmanned aerial vehicle - Google Patents
Axial locking and releasing assembly of non-falling type broken unmanned aerial vehicle Download PDFInfo
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- CN113998135A CN113998135A CN202111209932.3A CN202111209932A CN113998135A CN 113998135 A CN113998135 A CN 113998135A CN 202111209932 A CN202111209932 A CN 202111209932A CN 113998135 A CN113998135 A CN 113998135A
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- 230000009471 action Effects 0.000 claims abstract description 6
- 238000000034 method Methods 0.000 claims description 7
- 230000008569 process Effects 0.000 claims description 7
- 238000013016 damping Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 2
- 230000007246 mechanism Effects 0.000 description 6
- 230000006378 damage Effects 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000004308 accommodation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D25/00—Details of other kinds or types of rigid or semi-rigid containers
- B65D25/02—Internal fittings
- B65D25/10—Devices to locate articles in containers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D25/00—Details of other kinds or types of rigid or semi-rigid containers
- B65D25/20—External fittings
- B65D25/24—External fittings for spacing bases of containers from supporting surfaces, e.g. legs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D85/00—Containers, packaging elements or packages, specially adapted for particular articles or materials
- B65D85/68—Containers, packaging elements or packages, specially adapted for particular articles or materials for machines, engines or vehicles in assembled or dismantled form
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention provides an axial locking and releasing assembly of a fracture non-falling type unmanned aerial vehicle, which comprises a bearing pin, an installation frame and a translation rod, wherein two ends of the translation rod are respectively rotatably installed on a swing rod seat through a first swing rod and a second swing rod, one end of the translation rod close to the second swing rod is provided with a connecting plate; when the unmanned aerial vehicle is launched, the bearing pin can be broken under the action of launching thrust of the unmanned aerial vehicle and enters an unlocking state, and at the moment, two ends of the bearing pin respectively stop on the mounting frame and the connecting plate.
Description
Technical Field
The invention relates to the technical field of axial locking and releasing of unmanned aerial vehicles of weaponry systems, in particular to an axial locking and releasing assembly of a fracture non-falling type unmanned aerial vehicle.
Background
At present, the unmanned aerial vehicle is mostly fixed and unlocked by adopting a locking and releasing assembly during storage, transportation and launching, and a shear pin, a breaking pin and the like are widely applied to the technical field of locking and releasing of the unmanned aerial vehicle due to simple structural forms. However, in the prior art, after the launch of the unmanned aerial vehicle is completed, free state redundancy which moves at a high speed is generated due to the breakage of the shear pin and the breaking pin, certain damage is caused to surrounding products and personnel, the products are damaged if the damage is slight, casualties are caused if the damage is serious, and the launch safety of the unmanned aerial vehicle cannot be guaranteed.
Therefore, the industry needs an axial locking and releasing assembly of a fracture non-falling type unmanned aerial vehicle, which can meet the requirements of storage, transportation and launching working conditions of the unmanned aerial vehicle, ensure that the unmanned aerial vehicle is reliable in locking and convenient to release, and the assembly cannot fall off after being released and fractured, so that no redundant material is generated, and the launching safety is improved.
For example, patent document CN204279987U discloses a booster separating mechanism for an aircraft, which includes a zipper mechanism, a pull rod, a shear pin and a flag plate, wherein the flag plate is arranged at an outlet of a jet pipe of the booster and is connected with one end of the pull rod through the shear pin, and the other end of the pull rod is connected with the zipper mechanism arranged at the abdomen of an unmanned aerial vehicle to form interlocking, so as to reliably connect the unmanned aerial vehicle and the booster; the zipper mechanism comprises a fixed lock, a brake block and a brake pull rod, wherein the brake block is arranged in the fixed lock, the brake pull rod is installed on the brake block, and the design still has the generation of redundant materials after the shear pin is broken, so that unsafe factors exist.
Disclosure of Invention
In view of the defects in the prior art, the invention aims to provide an axial locking and releasing assembly of a fracture non-falling type unmanned aerial vehicle.
The invention provides an axial locking and releasing assembly of a fracture non-falling type unmanned aerial vehicle, which comprises:
the two ends of the translation rod are respectively rotatably arranged on the swing rod seat through a first swing rod and a second swing rod, and one end of the translation rod close to the second swing rod is provided with a connecting plate;
the mounting rack is fixedly arranged on the second swing rod or the swing rod seat;
the bearing pin fixes the connecting plate on the mounting frame, has two states of locking and unlocking, and does not allow the translation rod to move relative to the swing rod seat in the locking state; when the unmanned aerial vehicle launches, the bearing pin can be broken under the action of launching thrust of the unmanned aerial vehicle and enters an unlocking state, and at the moment, two ends of the bearing pin respectively stop on the mounting frame and the connecting plate.
Preferably, the bearing pin comprises an end part threaded section, a middle part threaded section, a polished rod section and a support section which are sequentially connected, and a weak section is arranged between the end part threaded section and the middle part threaded section; wherein, in the process of the bearing pin from the locking state to the unlocking state, the weak section is broken.
Preferably, the mounting bracket is provided with a first threaded hole, the connecting plate is provided with a second threaded hole and an accommodating space, the outer diameter of the middle threaded section is larger than that of the end threaded section and smaller than that of the support section, and the inner diameter of the accommodating space is larger than that of the middle threaded section;
the end part thread section is matched with the first threaded hole, the middle part thread section is matched with the second threaded hole, when the bearing pin is in a locking state, the end part thread section is installed in the first threaded hole in a matching mode, the middle part thread section is located in the containing space, and the inner side face of the supporting section is in contact and abutted with the outer side face of the connecting plate.
Preferably, the contact surfaces of the connecting plates and the mounting frame are both flat surfaces.
Preferably, the translational motion rod is provided with a translational motion rod main body, and the translational motion rod main body is detachably connected or integrally connected with the connecting plate.
Preferably, when the unmanned aerial vehicle launches, the self-contained slider slides on the matched slide rail so as to keep the height before being separated from the launching device.
Preferably, the leveling rod is provided with a positioning structure, and in an unlocking state, the unmanned aerial vehicle pushes the positioning structure to drive the leveling rod main body to move so as to enable the positioning structure to move below the unmanned aerial vehicle, so that the height of the bottom end face of the unmanned aerial vehicle is higher than that of the top end face of the positioning structure.
Preferably, the support section has a head recess thereon.
Preferably, the lower ends of the first swing rod and the second swing rod are in running fit with the swing rod seat through a first rotating shaft, and the upper ends of the first swing rod and the second swing rod are in running fit with the two ends of the translation rod through a second rotating shaft.
Preferably, the parts of the first swing rod, the second swing rod and the swing rod seat, and the parts of the first swing rod, the second swing rod and the translation rod which are connected are provided with rotary damping, so that the translation rod can be kept on the swing rod seat in a static manner through the first swing rod and the second swing rod in a natural state and can enter a rotatable state when being driven by external force.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention effectively solves the problem that the high-speed flying-out falling object is formed in the launching process of the unmanned aerial vehicle, overcomes the harm of the falling object to surrounding products and personnel in the launching process on the premise of effectively meeting the requirements of the storage, transportation and launching working conditions of the unmanned aerial vehicle, and greatly improves the launching safety.
2. The invention has simple structure, convenient operation and good universality.
3. The invention is examined by utilizing multiple ground transfer tests and launching tests, so that the invention can meet the actual requirements and can be widely used in the technical field of axial locking and releasing of the unmanned aerial vehicle.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural view of a load bearing pin of the present invention in a locked condition;
FIG. 2 is an enlarged view of a portion of the load bearing pin of the present invention in a locked condition;
FIG. 3 is a schematic structural view of a load pin in a complete state;
FIG. 4 is a schematic structural view of the load pin of the present invention in an unlocked condition wherein the lock release assembly is broken and does not fall;
fig. 5 is an enlarged view of a portion of the load pin of the present invention in an unlocked condition.
The figures show that:
Threaded section 13 at end of mounting bracket 2
The translation bar 3 is a polished rod section 14
First threaded hole 21 of slide rail 9
Second rotating shaft 10 second screw hole 31
The accommodation space 32 of the mid-thread segment 11
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The invention provides an axial locking and releasing assembly of a fracture non-falling type unmanned aerial vehicle, which comprises a bearing pin 1, a mounting frame 2 and a translation rod 3, and is shown in figures 1, 2, 3, 4 and 5.
Specifically, two ends of the tie rod 3 are rotatably mounted on the swing rod seat 6 through the first swing rod 4 and the second swing rod 17 respectively, and a connecting plate 18 is arranged at one end close to the second swing rod 17, and the tie rod 3 is provided with a positioning structure 19, wherein the positioning structure 19 is used for positioning the unmanned aerial vehicle 7.
And a mounting block 2 mounted on the second swing link 17 or on the swing link base 6, the position corresponding to the mounting block 2 being fixed when the mounting block 2 is mounted on the swing link base 6.
The bearing pin 1 fixes the connecting plate 18 on the mounting frame 2, and has two states of locking and unlocking, wherein the translation rod 3 is not allowed to move relative to the swing rod seat 6 in the locking state; when the unmanned aerial vehicle 7 launches, the bearing pin 1 can be broken and enters an unlocking state under the action of the launching thrust of the unmanned aerial vehicle 7, and at the moment, two ends of the bearing pin 1 respectively stop on the mounting frame 2 and the connecting plate 18.
Specifically, in the unlocked state, the unmanned aerial vehicle 7 pushes the positioning structure 19 to drive the translational rod main body to move, so that the positioning structure 19 can move below the unmanned aerial vehicle 7, the height of the bottom end face of the unmanned aerial vehicle 7 can be higher than that of the top end face of the positioning structure 19, and at this time, the positioning structure 19 can no longer prevent the unmanned aerial vehicle 7 from launching.
Specifically, the bearing pin 1 comprises an end threaded section 13, a middle threaded section 11, a polished rod section 14 and a support section 16 which are sequentially connected, wherein a weak section 12 is arranged between the end threaded section 13 and the middle threaded section 11; in the process that the bearing pin 1 is in the locking state to the unlocking state, the weak section 12 is broken, the weak section 12 is lower than other partition strengths, when the bearing pin 1 is subjected to external tension, the weak section 12 is the part which is firstly broken, the weak section 12 is preferably the part with the smallest outer diameter on the bearing pin 1, and the bearing pin 1 is preferably made of aluminum alloy.
The mounting bracket 2 is provided with a first threaded hole 21, the connecting plate 18 is provided with a second threaded hole 31 and a containing space 32, the outer diameter of the middle threaded section 11 is larger than that of the end threaded section 13 and smaller than that of the supporting section 16, and the inner diameter of the containing space 32 is larger than that of the middle threaded section 11. The end part threaded section 13 is matched with the first threaded hole 21, the middle part threaded section 11 is matched with the second threaded hole 31, when the bearing pin 1 is in a locking state, the end part threaded section 13 is installed in the first threaded hole 21 in a matching mode, the middle part threaded section 11 is located in the accommodating space 32, and the inner side face of the support section 16 is in contact and abutted with the outer side face of the connecting plate 18.
When the bearing pin 1 is installed, firstly, the end threaded section 13 penetrates through the second threaded hole 31, when the middle threaded section 11 contacts the second threaded hole 31, the middle threaded section 11 enters the accommodating space 32 through the second threaded hole 31 and then the middle threaded section 11 in a threaded rotating mode, when the end threaded section 13 contacts the first threaded hole 21, the end threaded section 13 is screwed into the first threaded hole 21 through the head groove 15 arranged on the tool operation supporting section 16 until the supporting section 16 contacts and abuts against the connecting plate 18, at the moment, the connecting plate 18 and the mounting frame 2 are fixedly connected together through the bearing pin 1, and the contact surface of the connecting plate 18 and the mounting frame 2 is preferably a plane.
When the unmanned aerial vehicle 7 launches, the sliding block 8 of the unmanned aerial vehicle slides on the matched sliding rail 9 to keep the height before being separated from the launching device, the sliding block 8 leaves the sliding rail 9 after being separated from the launching device, the sliding rail 9 is installed on the launching device, and the bearing pin 1, the installation frame 2, the horizontal moving rod 3 and the swing rod seat 6 are all part of the launching device.
Specifically, the tie rod 3 is provided with a tie rod main body, the tie rod main body is detachably connected or integrally connected with the connecting plate 18, the lower ends of the first swing rod 4 and the second swing rod 17 are in running fit with the swing rod seat 6 through the first rotating shaft 5, and the upper ends of the first swing rod 4 and the second swing rod 17 are in running fit with the two ends of the tie rod 3 through the second rotating shaft 10.
In practical application, the positions where the first swing rod 4, the second swing rod 17 and the swing rod seat 6 are connected, and the positions where the first swing rod 4, the second swing rod 17 and the tie rod 3 are connected have rotational damping, so that the tie rod 3 can be statically kept on the swing rod seat 6 through the first swing rod 4 and the second swing rod 17 in a natural state and can enter a rotatable state when being driven by external force.
It should be noted that the mounting bracket 2 is mounted on the second swing link 17 or on the swing link seat 6, and the effect of the present invention can be achieved when the leveling rod 3 is pushed.
The working principle of the invention is as follows:
as shown in fig. 1, 2 and 3, arrows in the drawings indicate courses, wherein the translational rod 3, the first swing rod 4, the second swing rod 17, the first rotating shaft 5, the second rotating shaft 10 and the swing rod seat 6 form a parallelogram mechanism, when the unmanned aerial vehicle 7 is loaded in place along the guide rail 9 by using a self sliding block 8 of the unmanned aerial vehicle 7 along the opposite course, the positioning structure 19 on the translational rod 3 is attached to the tail end face of the unmanned aerial vehicle 7, the bearing pin 1 is installed in place by using a tool and pre-tightening force is applied, and reliable axial locking of the unmanned aerial vehicle 7 in the processes of storage and transportation is realized.
As shown in fig. 4 and 5, arrows in the figures indicate headings, when the unmanned aerial vehicle 7 launches, under the action of launching thrust of the unmanned aerial vehicle 7, the unmanned aerial vehicle 7 starts to move along the headings to push the parallelogram mechanism to overturn rightwards and downwards, and during overturning, the translation rod 3 applies the thrust to the support section 16 on the bearing pin 1, so that the weak section 12 on the bearing pin 1 is finally broken, and the axial constraint of the unmanned aerial vehicle 7 is released. After the bearing pin 1 is broken, the end part threaded section 13 on the bearing pin 1 remains in the first threaded hole 21 on the support frame 2, the rest components (including the middle part threaded section 11, the support section 16, the polish rod section 14 and the head groove 15) on the bearing pin 1 remain on the connecting plate 18 on the flat moving rod 3, and the bearing pin 1 is prevented from falling off after being broken under the combined action of the middle part threaded section 11 on the bearing pin 1 and the second threaded hole 31 on the flat moving rod 3.
By carrying out a transfer test on the ground, the bearing pin 1 is reliably locked in the test process; launch test is carried out on ground, and among the 7 launch separation processes of unmanned vehicles, the reliable fracture in weak section 12 position on the carrier pin 1, and all remain on this subassembly after carrier pin 1 breaks, and the no high-speed departure thing that flies out produces, does not form harm to product and personnel on every side, has promoted the launch security, satisfies design requirement and user demand.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. An axial locking and releasing assembly of a fracture non-falling type unmanned aerial vehicle is characterized by comprising:
the translation rod (3) is used for positioning the unmanned aerial vehicle (7), two ends of the translation rod are respectively rotatably arranged on the swing rod seat (6) through the first swing rod (4) and the second swing rod (17), and one end of the translation rod close to the second swing rod (17) is provided with a connecting plate (18);
the mounting rack (2) is mounted on the second swing rod (17) or the swing rod seat (6);
the bearing pin (1) is used for fixing the connecting plate (18) on the mounting frame (2) and has two states of locking and unlocking, and in the locking state, the translation rod (3) is not allowed to move relative to the swing rod seat (6); when the unmanned aerial vehicle (7) launches, the bearing pin (1) can be broken under the action of the launching thrust of the unmanned aerial vehicle (7) and enters an unlocking state, and the two ends of the bearing pin (1) stop on the mounting frame (2) and the connecting plate (18) respectively.
2. The axial locking and releasing assembly of the unmanned aerial vehicle with no break-off phenomenon according to claim 1, wherein the bearing pin (1) comprises an end threaded section (13), a middle threaded section (11), a polish rod section (14) and a support section (16) which are connected in sequence, and a weak section (12) is arranged between the end threaded section (13) and the middle threaded section (11); wherein, in the process that the bearing pin (1) is in a locking state and in an unlocking state, the weak section (12) is broken.
3. The axial lock release assembly of the unmanned aerial vehicle with no break-off in fracture as claimed in claim 2, wherein the mounting bracket (2) is provided with a first threaded hole (21), the connecting plate (18) is provided with a second threaded hole (31) and a receiving space (32), the middle threaded section (11) has an outer diameter larger than the outer diameter of the end threaded section (13) and smaller than the outer diameter of the supporting section (16), and the receiving space (32) has an inner diameter larger than the outer diameter of the middle threaded section (11);
the end part thread section (13) is matched with the first threaded hole (21), the middle part thread section (11) is matched with the second threaded hole (31), when the bearing pin (1) is in a locking state, the end part thread section (13) is installed in the first threaded hole (21) in a matching mode, the middle part thread section (11) is located in the containing space (32), and the inner side face of the support section (16) is in contact and abutted with the outer side face of the connecting plate (18).
4. The axial lock release assembly of a break-free unmanned aerial vehicle according to claim 1, wherein the contact surfaces of the connecting plate (18) and the mounting frame (2) are both flat surfaces.
5. The axial locking and releasing assembly of the non-dropping type unmanned aerial vehicle in fracture as claimed in claim 1, wherein the translational rod (3) has a translational rod main body, and the translational rod main body is detachably or integrally connected with the connecting plate (18).
6. The axial lock release assembly of a break-free unmanned aerial vehicle according to claim 1, wherein when the unmanned aerial vehicle (7) is launched, the self-contained slider (8) slides on the matched slide rail (9) to maintain the height before disengaging from the launching device.
7. The axial locking and releasing assembly of the fracture non-falling type unmanned aerial vehicle according to claim 1, wherein the translational rod (3) is provided with a positioning structure (19), and in an unlocked state, the unmanned aerial vehicle (7) pushes the positioning structure (19) to drive the translational rod main body to move so as to enable the positioning structure (19) to move below the unmanned aerial vehicle (7) and enable the height of the bottom end face of the unmanned aerial vehicle (7) to be higher than the height of the top end face of the positioning structure (19).
8. The axial lock release assembly of a break-free unmanned aerial vehicle according to claim 2, wherein the support section (16) has a head groove (15) thereon.
9. The axial locking and releasing assembly of the fracture non-dropping type unmanned aerial vehicle according to claim 1, wherein the lower ends of the first swing link (4) and the second swing link (17) are in running fit with the swing link seat (6) through a first rotating shaft (5), and the upper ends of the first swing link (4) and the second swing link (17) are in running fit with the two ends of the translation rod (3) through a second rotating shaft (10).
10. The axial locking and releasing assembly of the unmanned aerial vehicle capable of preventing the aircraft from falling off after fracture as claimed in claim 9, wherein the positions of the first swing link (4), the second swing link (17), the swing link seat (6), the first swing link (4), the second swing link (17) and the tie rod (3) which are connected are provided with rotational damping, so that the tie rod (3) can be statically kept on the swing link seat (6) through the first swing link (4) and the second swing link (17) in a natural state and can enter a rotatable state when being driven by external force.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111209932.3A CN113998135B (en) | 2021-10-18 | 2021-10-18 | Axial locking and releasing assembly for fracture-resistant unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111209932.3A CN113998135B (en) | 2021-10-18 | 2021-10-18 | Axial locking and releasing assembly for fracture-resistant unmanned aerial vehicle |
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| CN113998135B CN113998135B (en) | 2023-11-28 |
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| WO2019216975A1 (en) * | 2018-05-07 | 2019-11-14 | Strong Force Iot Portfolio 2016, Llc | Methods and systems for data collection, learning, and streaming of machine signals for analytics and maintenance using the industrial internet of things |
| CN109883275A (en) * | 2019-02-27 | 2019-06-14 | 上海机电工程研究所 | Easy to disassemble and anti-dropout guided missile tail-hood |
| CN210479065U (en) * | 2019-09-30 | 2020-05-08 | 哈工大机器人（岳阳）军民融合研究院 | Zero-length launching stand |
| CN110758762A (en) * | 2019-11-12 | 2020-02-07 | 航天时代飞鸿技术有限公司 | Unmanned aerial vehicle ejection locking releasing device and method |
| CN111426242A (en) * | 2020-04-14 | 2020-07-17 | 上海机电工程研究所 | Guided missile fixing mechanism |
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