CN113844670B - Separated foldable oil-driven ducted aircraft starting platform - Google Patents
Separated foldable oil-driven ducted aircraft starting platform Download PDFInfo
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- CN113844670B CN113844670B CN202111318641.8A CN202111318641A CN113844670B CN 113844670 B CN113844670 B CN 113844670B CN 202111318641 A CN202111318641 A CN 202111318641A CN 113844670 B CN113844670 B CN 113844670B
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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
- B64F1/007—Helicopter portable landing pads
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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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a split type foldable starting platform of an oil-driven ducted aircraft, which comprises a folding platform for bearing the ducted aircraft, a starting mechanism arranged below the platform plate and a landing gear fixing mechanism arranged below the platform plate, wherein the landing gear fixing mechanism is arranged below the landing gear fixing mechanism; the starting mechanism comprises a starting mechanism bracket, a starting rod, a starting motor and a bevel gear; the landing gear fixing mechanism comprises a landing gear hook, a rocker shaft, a rocker shaft seat, a first connecting rod, a second connecting rod, a crank seat, an electric push rod and an electric push rod seat. The invention provides a starting mechanism separated from a ducted aircraft, which can be lifted on a lifting rotating frame to be conveniently connected with and separated from a transmission shaft of the aircraft, so that the weight of the aircraft can be reduced, and the overall arrangement is convenient; the landing gear fixing mechanism and the stable take-off platform are provided, so that the starting mechanism and the transmission shaft of the aircraft can be accurately connected and stably run in the starting process, and the take-off of the aircraft is not limited by ground conditions.
Description
Technical Field
The invention relates to the field of oil-driven ducted aircraft starting platforms, in particular to a separated foldable oil-driven ducted aircraft starting platform.
Background
For ducted aircraft using piston engines, the resistance of the compressed gas in the cylinder and the frictional resistance of the relative motion in the engine itself and in the accessories must be overcome when the engine is started. Overcoming the starting resistance moment and generating enough starting rotational speed are the necessary conditions for the smooth starting of the engine. The starting mode of the piston engine can be classified into three types of hand starting, compressed air starting and electric starting according to the external energy source of the starting. The hand starting scheme has high requirements on the expertise and the use experience of operators and has certain dangers. The compressed air starting device has a complex structure and heavy weight, and is generally only used for large engines such as ship main engines. Because the electric starter has the advantages of simple structure, convenient operation, quick starting, low cost and good reliability, most aviation piston engines currently adopt the mode.
Some piston engines are equipped with an electric starter during production and often also with transmission components, which not only increases the weight of the aircraft, but also affects the overall layout due to the bulk problems, which can be troublesome for design and use. The engine without the starting mechanism needs additional installation when in use, besides the problems, the starting mechanism of each set of system also needs to be designed respectively, which is not beneficial to the model selection and the updating of the engine.
In addition, the ducted aircraft needs a smooth and stable take-off plane during take-off, so that disturbance during take-off is reduced, and the take-off process is safer and more stable.
Therefore, there is a need to design a set of start platforms that are separate from the aircraft, not only to facilitate engagement and disengagement with the aircraft drive shafts, but also to secure the aircraft during start-up to ensure accurate engagement and smooth operation, and to provide a platform for smooth take-off of the aircraft.
Disclosure of Invention
The invention aims to provide a split piston engine ducted aircraft starting take-off platform which is convenient to use and stable in operation.
In order to solve the technical problems, the invention adopts the following technical scheme:
the invention relates to a separated foldable oil-driven ducted aircraft starting platform, which comprises
A folding platform for carrying a ducted aircraft; the folding platform comprises a platform plate, a bracket is arranged below the platform plate, and a plurality of hook holes and a starting hole are formed in the platform plate;
a starting mechanism arranged below the platform plate; the starting mechanism comprises a starting mechanism support, a starting rod, a starting motor and a bevel gear, wherein the starting mechanism support is arranged below the platform plate, the starting motor, the starting rod and the bevel gear are arranged on the starting mechanism support, and the starting motor is connected with the starting rod through the bevel gear; the starting rod can pass through the starting hole;
and a landing gear securing mechanism disposed below the platform plate; the landing gear fixing mechanism comprises a landing gear hook, a rocker shaft, a rocker shaft seat, a first connecting rod, a second connecting rod, a crank seat, an electric push rod and an electric push rod seat; the lifting hook, the rocker shaft, the rocker and the rocker shaft seat form a crank rocker mechanism, the rocker shaft seat is fixed on the lower surface of the platform plate, the rocker shaft is hinged with the rocker shaft seat, and one ends of the lifting hook and the rocker are fixed on the rocker shaft; the number of the hook holes is even, every two hook holes are in a group and are oppositely arranged, and a crank rocker mechanism is arranged below each hook hole, so that a lifting hook can penetrate through the hook holes to lock the landing gear; the crank seat and the electric push rod seat are fixed on the lower surface of the platform plate, the other end of the rocker of one crank rocker mechanism is hinged with one end of a first connecting rod, the other end of the first connecting rod is hinged with one end of a crank, the other end of the crank is hinged with the push rod end of the electric push rod, the push rod end of the electric push rod is also hinged with one end of a second connecting rod, and the other end of the second connecting rod is hinged with the other end of the rocker of the other crank rocker mechanism; the middle part of the crank is hinged with the crank seat, and the mounting end of the electric push rod is hinged with the electric push rod seat to form two groups of crank rocker mechanisms driven by one electric push rod at the same time.
Further, a one-way clutch is provided between the actuating lever and the bevel gear.
Still further, folding platform still includes curb plate, scute, folding electric putter and folding electric putter seat, the platform board with the curb plate is articulated, the curb plate with the scute is articulated, has between two articulated boards folding electric putter, every folding electric putter both ends with corresponding folding electric putter seat articulates respectively, folding electric putter seat is fixed in the inboard of each board.
Still further, be provided with a plurality of guide rails between folding platform and the support, every all be provided with the slider on the guide rail, a plurality of be connected with the lift swivel mount between the slider.
Still further, a lifting block is fixed on the lifting rotating frame, a lifting screw is connected with the lifting block in a threaded manner, the lifting screw is connected with a screw seat through a bearing, and the screw seat is fixed at the lower end of the bracket; and a lifting motor is arranged below the folding platform, and a pair of synchronous pulleys and a synchronous belt are used for transmission between the lifting motor and the lifting screw.
Still further, the lifting rotating frame is provided with a swinging groove and a track groove, and the starting mechanism is fixedly connected with the swinging groove through a rotating shaft; the lifting rotating frame is hinged with a starting electric push rod, the push rod end of the starting electric push rod is arranged in the track groove and the swing groove, and the starting mechanism can be driven by the starting electric push rod to rotate around the axis of the rotating shaft.
Still further, the starting hole is long.
Still further, the number of the hook holes is four.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides the starting mechanism separated from the ducted aircraft, the starting mechanism can be lifted on the lifting rotating frame to be conveniently connected with and separated from the transmission shaft of the aircraft, the weight of the aircraft can be reduced, the overall arrangement is convenient, the trouble of designing starting mechanisms of different engine systems can be saved, and the engine is beneficial to the selection and updating of the engine; the landing gear fixing mechanism and the stable take-off platform are provided, so that the starting mechanism and the transmission shaft of the aircraft can be accurately connected and stably run in the starting process, and the platform is provided for stable take-off of the aircraft, so that the take-off of the aircraft is not limited by ground conditions; the folding platform and the starting mechanism can be folded and retracted, and the system can be retracted into a cuboid box body after being completely folded, so that the folding platform is compact in structure and convenient to use.
Drawings
The invention is further described with reference to the following description of the drawings.
FIG. 1 is a schematic view of the structure of the present invention in its deployed state;
FIG. 2 is a bottom view of the invention in its expanded state;
FIG. 3 is a schematic view of the starting mechanism and lifting and rotating frame in the deployed state of the present invention;
FIG. 4 is a schematic view of the starting mechanism and lifting and rotating frame in a folded state of the present invention;
FIG. 5 is a schematic view of the landing gear securement mechanism of the present invention in the deployed state;
FIG. 6 is a schematic view of the landing gear securement mechanism of the present invention in a folded condition;
FIG. 7 is a schematic view of the folded state of the present invention;
FIG. 8 is a state diagram of the present invention in use with a ducted aircraft.
Reference numerals illustrate: 1. a starting mechanism; 101. a starting mechanism bracket; 102. a starting lever; 103. starting a motor; 104. a bevel gear;
2. a folding platform; 201. a platform plate; 202. a side plate; 203. a corner plate; 204. folding the electric push rod; 205. folding the electric push rod seat; 206. a hook hole; 207. a starting hole;
3. a bracket;
4. lifting the rotating frame; 401. lifting and rotating the bracket; 402. a rotating shaft; 403. a swinging groove; 404. a track groove; 405. starting an electric push rod; 406. a guide rail; 407. a slide block; 408. lifting screw rods; 409. a screw seat; 410. a lifting block; 411. a lifting motor; 412. a motor bracket; 413. a synchronous pulley; 414. a synchronous belt;
5. a landing gear fixing mechanism; 501. a landing hook; 502. a rocker shaft; 503. a rocker; 504. a rocker shaft seat; 505. a first link; 506. a crank; 507. a crank mount; 508. an electric push rod; 509. an electric push rod seat; 510. a second link;
6. a ducted aircraft; 601. and (5) landing gear.
Detailed Description
The invention is further described below with reference to the drawings and detailed description.
As shown in fig. 1-4, one specific embodiment of a split foldable oil-powered ducted aircraft starting platform comprises a starting mechanism 1, a folding platform 2, a bracket 3, a lifting rotating frame 4 and a landing gear fixing mechanism 5. The starting mechanism 1 is connected with the lifting rotating frame 4 through a rotating shaft 402 and a bearing, the lifting rotating frame 4 is connected with the support 3 through a sliding block 407 and a guide rail 406, the folding platform 2 is fixed above the support 3, and the undercarriage fixing mechanism 5 is fixed below the folding platform 2.
More specifically, as shown in fig. 2, the folding platform 2 includes a platform plate 201, a side plate 202, a corner plate 203, a folding electric push rod 204 and a folding electric push rod seat 205, the platform plate 201 is hinged to the side plate 202, the side plate 202 is hinged to the corner plate 203, the folding electric push rod 204 is arranged between two hinged plates, two ends of each folding electric push rod 204 are respectively hinged to the corresponding folding electric push rod seat 205, and the folding electric push rod seat 205 is fixed on the inner side of each plate and controls the folding of the side plate and the corner plate.
As shown in fig. 3 and 4, a bracket 3 is welded and fixed below the platform plate 201, and the bracket plays a role of supporting the folding platform. The platform plate 201 is provided with a starting hole 207, and the starting mechanism 1 is arranged below the platform plate 201. The starting mechanism 1 comprises a starting mechanism bracket 101, a starting rod 102, a starting motor 103 and a bevel gear 104, the starting mechanism bracket 101 is arranged below a platform plate 201, the starting motor 103, the starting rod 102 and the bevel gear 104 are arranged on the starting mechanism bracket 101, the starting motor 103 is connected with the starting rod 102 through the bevel gear 104, a one-way clutch is arranged between the starting rod 102 and the bevel gear 104, so that the starting motor drives the starting rod to rotate, and the starting rod 102 can pass through a starting hole 207 and extend upwards to the oil-operated bypass aircraft 6 for starting the oil-operated bypass aircraft 6. Four guide rails 406 are arranged between the folding platform 2 and the support 3, sliding blocks 407 are arranged on each guide rail 406, and lifting rotating frames 4 are connected between the four sliding blocks 407, so that the lifting rotating frames 4 can move up and down along the guide rails. The lifting rotary frame 4 is fixedly provided with a lifting block 410, the lifting block 410 is in threaded connection with a lifting screw 408, the lifting screw 408 is connected with a screw seat 409 through a bearing, and the screw seat 409 is fixedly arranged at the lower end of the bracket 3. A lifting motor 411 is fixedly installed below the folding platform 2, and a pair of synchronous pulleys 413 and a synchronous belt 414 are used for driving between the lifting motor 411 and the lifting screw 408. When the lifting motor drives the lifting screw to rotate, the lifting block moves up and down along the lifting screw due to the transmission effect of the threads, so that the lifting rotating frame is driven to move up and down. The lifting rotary frame 4 is provided with a swing groove 403 and a track groove 404, the lifting rotary frame 4 is also provided with a lifting rotary frame 401, and the starting mechanism 1 is arranged on the lifting rotary frame and is fixedly connected with the swing groove 403 through a rotating shaft 402. The lifting rotating frame 4 is hinged with a starting electric push rod 405, the push rod end of the starting electric push rod 405 is arranged in the track groove 404 and the swing groove 403, and the starting mechanism 1 can be driven to rotate around the axis of the rotating shaft 402 by the starting electric push rod 405, so that the starting mechanism can rotate. The starting hole 207 is long, and when the lifting rotating frame 4 drives the starting mechanism 1 to lift and rotate, the starting rod can pass through the starting hole to start the oil-driven ducted aircraft 6; when the oil-powered ducted aircraft 6 is started, the lifting and lowering rotating frame 4 withdraws the starting rod below the folding platform through rotation and lifting actions.
Four hook holes 206 are formed in the platform plate 201, two hook holes in each group are arranged oppositely. A landing gear fixing mechanism 5 is installed below the platform plate 201, and the landing gear fixing mechanism 5 comprises a landing hook 501, a rocker shaft 502, a rocker 503, a rocker shaft seat 504, a first connecting rod 505, a second connecting rod 510, a crank 506, a crank seat 507, an electric push rod 508 and an electric push rod seat 509. The lifting hook 501, the rocker shaft 502, the rocker 503 and the rocker shaft seat 504 form a crank rocker mechanism, the rocker shaft seat 504 is fixed on the lower surface of the platform plate 201, the rocker shaft 502 is hinged with the rocker shaft seat 504, and one ends of the lifting hook 501 and the rocker 503 are fixed on the rocker shaft 502. The number of the hook holes 206 is even, every two hook holes 206 are in a group and are oppositely arranged, and a crank rocker mechanism is arranged below each hook hole 206, so that the landing gear 601 can be locked by the landing gear 501 through the hook holes 206. The crank seat 507 and the electric push rod seat 509 are fixed on the lower surface of the platform plate 201, the other end of the rocker 503 of one crank rocker mechanism is hinged to one end of a first link 505, the other end of the first link 505 is hinged to one end of a crank 506, the other end of the crank 506 is hinged to the push rod end of the electric push rod 508, the push rod end of the electric push rod 508 is also hinged to one end of a second link 510, and the other end of the second link 510 is hinged to the other end of the rocker 503 of the other crank rocker mechanism. The middle part of the crank 506 is hinged with the crank seat 507, the installation end of the electric push rod 508 is hinged with the electric push rod seat 509 to form two groups of crank rocker mechanisms driven by one electric push rod 508 at the same time, when the electric push rod stretches and shortens, the lifting hooks are simultaneously operated in two opposite hook holes to lock and release the landing gear 601 of the oil-driven ducted aircraft 6.
The operation process of the embodiment of the split type foldable oil-driven ducted aircraft starting platform is as follows:
in the unfolded state, as shown in fig. 1 and 3, the starting electric push rod 405 is retracted, the push rod end slides in the track groove 404 and the swing groove 403, the whole starting mechanism 1 is driven to rotate around the rotating shaft 402, and the starting rod 102 is in an upright state. The lifting motor 413 drives the lifting screw 408 to rotate through the synchronous pulley 413 and the synchronous belt 414, and the lifting block 410 ascends under the action of the screw thread to drive the whole lifting rotating frame 5 and the starting mechanism 1 to ascend.
In the unfolded state, as shown in fig. 1 and 5, the electric push rod 508 is retracted, and the second link 510 and the crank 506 are driven, and the first link 505 drives the crank-rocker mechanisms on both sides to rotate, so that the lifting hook 501 fixedly connected with the rocker 503 rotates along with the rocker 503, and extends out of the platform plate 201.
As shown in fig. 1, 3, 5 and 8, in the unfolded state, the landing hook 501 rotates to extend out of the platform plate 201, and the landing gear 601 of the ducted aircraft 6 is fixed. The starting rod 102 is in an upright state, the whole lifting rotary frame 5 and the starting mechanism 1 ascend and extend into the driving shaft of the ducted aircraft 6, and at the moment, the starting motor 103 works to drive the driving shaft of the ducted aircraft 6 to rotate through the bevel gear 104 and the starting rod 102 so as to start the ducted aircraft 6.
In the folded state, as shown in fig. 4, the actuating electric push rod 405 extends, and the push rod end slides in the track groove 404 and the swing groove 403, so that the whole actuating mechanism 1 is driven to rotate around the rotating shaft 402, and the actuating rod 102 is changed to the lowered state. The lifting motor 413 works to drive the lifting screw 408 to rotate through the synchronous pulley 413 and the synchronous belt 414, and under the action of the threads, the lifting block 410 descends to drive the whole lifting rotating frame 5 and the starting mechanism 1 to descend, and at the moment, the starting mechanism 1 is separated from the ducted aircraft 6.
As shown in fig. 6, in the folded state, the electric push rod 508 extends to drive the crank-rocker mechanism formed by the crank 506, the connecting rod 505 and the rocker 503 to rotate, the landing hook 501 fixedly connected with the rocker 503 rotates along with the rocker 503, and the landing plate 201 is rotated, at this time, the landing hook 501 is separated from the landing gear 601 of the ducted aircraft 6, and the ducted aircraft 6 can take off from the landing plate 201 at this time.
As shown in fig. 2 and 7, the folding electric push rod 204 is retracted, the angle plate 203 is retracted first, then the side plate 203 is retracted, and the whole system is retracted into a cuboid box body shown in fig. 7.
The above embodiments are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art to the technical solutions of the present invention should fall within the protection scope defined by the claims of the present invention without departing from the design spirit of the present invention.
Claims (8)
1. A split foldable oil-powered ducted aircraft starting platform, characterized in that: comprising
A folding platform (2) for carrying a ducted aircraft (6); the folding platform (2) comprises a platform plate (201), a bracket (3) is arranged below the platform plate (201), and a plurality of hook holes (206) and a starting hole (207) are formed in the platform plate (201);
a starting mechanism (1) arranged below the platform plate (201); the starting mechanism (1) comprises a starting mechanism support (101), a starting rod (102), a starting motor (103) and a bevel gear (104), wherein the starting mechanism support (101) is arranged below the platform plate (201), the starting motor (103), the starting rod (102) and the bevel gear (104) are arranged on the starting mechanism support (101), and the starting motor (103) is connected with the starting rod (102) through the bevel gear (104); the starting rod (102) can pass through a starting hole (207);
and a landing gear fixing mechanism (5) provided below the platform plate (201); the landing gear fixing mechanism (5) comprises a landing gear hook (501), a rocker shaft (502), a rocker (503), a rocker shaft seat (504), a first connecting rod (505), a second connecting rod (510), a crank (506), a crank seat (507), an electric push rod (508) and an electric push rod seat (509); the lifting hook (501), the rocker shaft (502), the rocker (503) and the rocker shaft seat (504) form a crank rocker mechanism, the rocker shaft seat (504) is fixed on the lower surface of the platform plate (201), the rocker shaft (502) is hinged with the rocker shaft seat (504), and one ends of the lifting hook (501) and the rocker (503) are fixed on the rocker shaft (502); the number of the hook holes (206) is even, every two hook holes (206) are in a group and are oppositely arranged, and a crank rocker mechanism is arranged below each hook hole (206), so that a lifting hook (501) can penetrate through the hook holes (206) to lock the landing gear (601); the crank seat (507) and the electric push rod seat (509) are fixed on the lower surface of the platform plate (201), the other end of the rocker (503) of one crank rocker mechanism is hinged with one end of a first connecting rod (505), the other end of the first connecting rod (505) is hinged with one end of a crank (506), the other end of the crank (506) is hinged with the push rod end of the electric push rod (508), the push rod end of the electric push rod (508) is also hinged with one end of a second connecting rod (510), and the other end of the second connecting rod (510) is hinged with the other end of the rocker (503) of the other crank rocker mechanism; the middle part of the crank (506) is hinged with the crank seat (507), and the mounting end of the electric push rod (508) is hinged with the electric push rod seat (509) to form two groups of crank rocker mechanisms driven by one electric push rod (508) at the same time.
2. The split foldable oil-powered ducted aircraft starting platform of claim 1, characterized by: a one-way clutch is provided between the starting lever (102) and the bevel gear (104).
3. The split foldable oil-powered ducted aircraft starting platform of claim 1, characterized by: folding platform (2) still include curb plate (202), scute (203), folding electricity push rod (204) and folding electricity push rod seat (205), platform board (201) with curb plate (202) are articulated, curb plate (202) with scute (203) are articulated, all have between two articulated boards folding electricity push rod (204) mutually, every folding electricity push rod (204) both ends with corresponding folding electricity push rod seat (205) are articulated respectively, folding electricity push rod seat (205) are fixed in the inboard of each board.
4. The split foldable oil-powered ducted aircraft starting platform of claim 1, characterized by: a plurality of guide rails (406) are arranged between the folding platform (2) and the support (3), sliding blocks (407) are arranged on each guide rail (406), and lifting rotating frames (4) are connected between the sliding blocks (407).
5. The split and collapsible oil-powered ducted aircraft starting platform of claim 4, wherein: a lifting block (410) is fixed on the lifting rotating frame (4), the lifting block (410) is in threaded connection with a lifting screw (408), the lifting screw (408) is connected with a screw seat (409) through a bearing, and the screw seat (409) is fixed at the lower end of the bracket (3); a lifting motor (411) is arranged below the folding platform (2), and a pair of synchronous pulleys (413) and a synchronous belt (414) are used for transmission between the lifting motor (411) and the lifting screw (408).
6. The split and collapsible oil-powered ducted aircraft starting platform of claim 5, wherein: a swing groove (403) and a track groove (404) are formed in the lifting rotating frame (4), and the starting mechanism (1) is fixedly connected with the swing groove (403) through a rotating shaft (402); the lifting rotating frame (4) is hinged with a starting electric push rod (405), the push rod end of the starting electric push rod (405) is arranged in the track groove (404) and the swing groove (403), and the starting mechanism (1) can be driven by the starting electric push rod (405) to rotate around the axis of the rotating shaft (402).
7. The split foldable oil-powered ducted aircraft starting platform of claim 6, characterized by: the starting hole (207) is elongated.
8. The split foldable oil-powered ducted aircraft starting platform of claim 1, characterized by: the number of the hook holes (206) is four.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111318641.8A CN113844670B (en) | 2021-11-09 | 2021-11-09 | Separated foldable oil-driven ducted aircraft starting platform |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111318641.8A CN113844670B (en) | 2021-11-09 | 2021-11-09 | Separated foldable oil-driven ducted aircraft starting platform |
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| CN113844670A CN113844670A (en) | 2021-12-28 |
| CN113844670B true CN113844670B (en) | 2023-07-14 |
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| CN116317333B (en) * | 2023-05-24 | 2023-07-28 | 北京蓝天航空科技股份有限公司 | Moving platform disengaging gear |
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|---|---|---|---|---|
| FR1348089A (en) * | 1963-02-08 | 1964-01-04 | Anthony Co | Folding type lifting platform |
| CN106379550A (en) * | 2016-06-15 | 2017-02-08 | 珠海市磐石电子科技有限公司 | Take-off and landing platform for aircraft |
| CN206511136U (en) * | 2016-12-19 | 2017-09-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of assisted unmanned plane launcher |
| WO2018077298A1 (en) * | 2016-10-31 | 2018-05-03 | 比亚迪股份有限公司 | Unmanned aerial vehicle landing platform |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180370652A1 (en) * | 2017-06-26 | 2018-12-27 | Martin Pierre George Vendrame | Portable drone landing platform |
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2021
- 2021-11-09 CN CN202111318641.8A patent/CN113844670B/en active Active
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|---|---|---|---|---|
| FR1348089A (en) * | 1963-02-08 | 1964-01-04 | Anthony Co | Folding type lifting platform |
| CN106379550A (en) * | 2016-06-15 | 2017-02-08 | 珠海市磐石电子科技有限公司 | Take-off and landing platform for aircraft |
| WO2018077298A1 (en) * | 2016-10-31 | 2018-05-03 | 比亚迪股份有限公司 | Unmanned aerial vehicle landing platform |
| CN206511136U (en) * | 2016-12-19 | 2017-09-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of assisted unmanned plane launcher |
Non-Patent Citations (1)
| Title |
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| 无人机自力起飞方式研究;叶帅辰;姚晓先;;火力与指挥控制(第04期);全文 * |
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