阅读说明：本技术 一种分离式可折叠的油动涵道飞行器起动平台 (Disconnect-type folding oil moves duct aircraft and starts platform ) 是由 吴江浩 张建飞 林海英 李泽宇 于 2021-11-09 设计创作，主要内容包括：本发明公开了一种分离式可折叠的油动涵道飞行器起动平台,包括用于承载涵道飞行器的折叠平台、设置在所述平台板下方的起动机构和设置在所述平台板下方的起落架固定机构；所述起动机构包括起动机构支架、起动杆、起动电机和伞齿轮；所述起落架固定机构包括起落钩、摇杆轴、摇杆、摇杆轴座、第一连杆、第二连杆、曲柄、曲柄座、电推杆和电推杆座。本发明的提供了与涵道飞行器分离的起动机构,起动机构可以在升降旋转架上升降来方便地与飞行器传动轴接合和分离,可以减轻飞行器重量和方便总体布置；提供了起落架固定机构和稳定的起飞平台,保证了起动过程中起动机构和飞行器传动轴可以接合准确运行平稳,还使飞行器起飞不受地面条件限制。(The invention discloses a separated foldable oil-driven ducted aircraft starting platform, which comprises a folding platform for bearing a ducted aircraft, a starting mechanism arranged below a platform plate and an undercarriage fixing mechanism arranged below the platform plate, wherein the undercarriage fixing mechanism comprises a supporting plate and a supporting plate; the starting mechanism comprises a starting mechanism bracket, a starting rod, a starting motor and a bevel gear; the undercarriage fixing mechanism comprises a landing 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 jointed with and separated from a transmission shaft of the aircraft, thereby reducing the weight of the aircraft and facilitating the overall arrangement; the landing gear fixing mechanism and the stable takeoff platform are provided, the starting mechanism and the transmission shaft of the aircraft can be jointed in the starting process to accurately and stably operate, and the takeoff of the aircraft is not limited by ground conditions.)

1. The utility model provides a folding oily duct aircraft of disconnect-type starts platform which characterized in that: comprises that

A folding platform (2) for carrying a ducted aircraft (6); the folding platform (2) comprises a platform plate (201), a support (3) is arranged below the platform plate (201), and the platform plate (201) is provided with a plurality of hook holes (206) and a starting hole (207);

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 a 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 activation rod (102) is capable of passing through an activation aperture (207);

and a landing gear fixing mechanism (5) arranged below the platform plate (201); 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 one group and are arranged oppositely, and a crank rocker mechanism is arranged below each hook hole (206), so that the landing 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 an electric push rod (508), the push rod end of the electric push rod (508) is further 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 a crank seat (507), the mounting end of the electric push rod (508) is hinged with an electric push rod seat (509), and two groups of crank rocker mechanisms driven by one electric push rod (508) at the same time are formed.

2. The breakaway collapsible oiled ducted aircraft starting platform of claim 1, wherein: a one-way clutch is arranged between the starting rod (102) and the bevel gear (104).

3. The breakaway collapsible oiled ducted aircraft starting platform of claim 1, wherein: the folding platform (2) further comprises a side plate (202), an angle 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 angle plate (203), the folding electric push rod (204) is arranged between the two hinged plates, two ends of each folding electric push rod (204) are hinged to the corresponding folding electric push rod seat (205) respectively, and the folding electric push rod seats (205) are fixed on the inner sides of the plates.

4. The breakaway collapsible oiled ducted aircraft starting platform of claim 1, wherein: a plurality of guide rails (406) are arranged between the folding platform (2) and the bracket (3), each guide rail (406) is provided with a sliding block (407), and a plurality of lifting rotating frames (4) are connected between the sliding blocks (407).

5. The breakaway collapsible oiled ducted aircraft starting platform of claim 4, wherein: a lifting block (410) is fixed on the lifting rotating frame (4), a lifting screw (408) is in threaded connection with the lifting block (410), 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 support (3); folding platform (2) below is provided with elevator motor (411), through a pair of synchronous pulley (413) and hold-in range (414) transmission between elevator motor (411) and lifting screw (408).

6. The breakaway collapsible oiled 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 swinging 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 breakaway collapsible oiled ducted aircraft starting platform of claim 6, wherein: the starting hole (207) is long.

8. The breakaway collapsible oiled ducted aircraft starting platform of claim 1, wherein: the number of the hook holes (206) is four.

Technical Field

The invention relates to the field of starting platforms of oil-driven ducted aircrafts, in particular to a separating type foldable starting platform of an oil-driven ducted aircraft.

Background

In the case of ducted aircraft using piston engines, the resistance of the compressed gas in the cylinder and the frictional resistance of the relative movement in the engine itself and in the accessories must be overcome at the start of the engine. Overcoming the starting drag torque and generating sufficient starting rotation speed are the necessary conditions for smooth starting of the engine. The starting mode of the piston engine can be divided into three types of hand starting, compressed air starting and electric starting according to the external energy source for starting. The hand-cranking starting scheme not only has higher requirements on professional knowledge and use experience of operators, but also has certain dangers. The compressed air starting device has a complex structure and heavier weight, and is generally only used for large engines such as marine main engines. Because the starting of the electric starter has the advantages of simple structure, convenient operation, quick starting, low cost and good reliability, the aviation piston type engine mostly adopts the mode at present.

Some piston engines are produced with electric starters and often with transmission components, which not only increase the weight of the aircraft, but also make the overall arrangement more cumbersome to design and use because of the bulk problems. The engine without the starting mechanism needs to be additionally installed when in use, and besides the problems, the starting mechanism of each set of system 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 flat and stable takeoff plane during takeoff so as to reduce disturbance during takeoff and ensure safer and more stable takeoff process.

Therefore, there is a need for a starting platform that is separate from the aircraft, not only that is convenient to engage and disengage from the drive shaft of the aircraft, but also that secures the aircraft during starting to ensure proper engagement and smooth operation and to provide a platform for smooth takeoff of the aircraft.

Disclosure of Invention

The invention aims to provide a starting take-off platform of a split piston engine ducted aircraft, 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 duct aircraft starting platform, which comprises

A folding platform for carrying the ducted aircraft; the folding platform comprises a platform plate, a support 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 disposed below the deck; the starting mechanism comprises a starting mechanism support, a starting rod, a starting motor and a bevel gear, the starting mechanism support is arranged below the platform plate, the starting motor, the starting rod and the bevel gear are all arranged on the starting mechanism support, and the starting motor is connected with the starting rod through the bevel gear; the actuating rod can pass through the actuating hole;

and a landing gear fixing mechanism arranged below the platform plate; the undercarriage fixing mechanism comprises a landing 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 end of the lifting hook and one end of 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 arranged oppositely, and a crank rocker mechanism is arranged below each hook hole, so that the landing hook can pass 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 an electric push rod, the push rod end of the electric push rod is further 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 arranged between the starting rod and the bevel gear.

Still further, folding platform still includes curb plate, scute, folding electric push rod and folding electric push rod seat, the landing slab with the curb plate is articulated, the curb plate with the scute is articulated, all has between looks articulated two boards folding electric push rod, every folding electric push rod both ends with corresponding folding electric push rod seat is articulated respectively, folding electric push rod seat is fixed at 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, it is a plurality of be connected with the lift swivel mount between the slider.

Furthermore, a lifting block is fixed on the lifting rotating frame, the lifting block is in threaded connection with a lifting screw rod, the lifting screw rod is connected with a screw rod seat through a bearing, and the screw rod seat is fixed at the lower end of the support; a lifting motor is arranged below the folding platform, and the lifting motor and the lifting screw are driven by a pair of synchronous belt wheels and a synchronous belt.

Furthermore, a swing groove and a track groove are formed in the lifting rotating frame, and the starting mechanism is fixedly connected with the swing 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 swinging groove, and the starting mechanism can rotate around the axis of the rotating shaft under the driving of the starting electric push rod.

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 jointed and separated with the transmission shaft of the aircraft, the weight of the aircraft can be lightened, the overall arrangement is convenient, the trouble of designing starting mechanisms of different engine systems can be saved, and the model selection and the updating of the engine are facilitated; the landing gear fixing mechanism and the stable takeoff platform are provided, so that the starting mechanism and the transmission shaft of the aircraft can be jointed accurately and stably operated in the starting process, and a platform is provided for the stable takeoff of the aircraft, so that the takeoff of the aircraft is not limited by ground conditions; the folding platform and the starting mechanism can be folded, and the system can be folded into a cuboid box body after being completely folded, so that the structure is compact and the use is convenient.

Drawings

The invention is further illustrated in the following description with reference to the drawings.

FIG. 1 is a schematic structural view of the present invention in an unfolded state;

FIG. 2 is a bottom view of the expanded state of the present invention;

FIG. 3 is a schematic view of the construction of the starting mechanism and the elevating rotary frame in the unfolded state of the present invention;

FIG. 4 is a schematic view showing the construction of the actuating mechanism and the elevating rotary frame in a folded state according to the present invention;

FIG. 5 is a schematic structural view of the landing gear attachment mechanism of the present invention in a deployed state;

FIG. 6 is a schematic view of the landing gear attachment mechanism of the present invention in a collapsed configuration;

FIG. 7 is a schematic structural view of the present invention in a folded state;

figure 8 is a state diagram of the present invention in use with a ducted aircraft.

Description of reference numerals: 1. a starting mechanism; 101. a starter mechanism support; 102. a start lever; 103. starting the motor; 104. a bevel gear;

2. folding the platform; 201. a platform plate; 202. a side plate; 203. a gusset; 204. folding the electric push rod; 205. folding the electric push rod seat; 206. a hook hole; 207. a starter hole;

3. a support;

4. a lifting rotating frame; 401. lifting and rotating the bracket; 402. a rotating shaft; 403. a swinging groove; 404. a track groove; 405. starting the electric push rod; 406. a guide rail; 407. a slider; 408. a lifting screw; 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. lifting and falling hooks; 502. a rocker shaft; 503. a rocker; 504. a rocker shaft seat; 505. a first link; 506. a crank; 507. a crank carrier; 508. an electric push rod; 509. an electric push rod seat; 510. a second link;

6. a ducted aircraft; 601. a landing gear.

Detailed Description

The invention is further described with reference to the following figures and detailed description.

As shown in fig. 1-4, one specific embodiment of a starting platform of a split foldable oil-driven ducted aircraft includes a starting mechanism 1, a foldable platform 2, a bracket 3, a lifting rotating frame 4, and a landing gear fixing mechanism 5. The starting mechanism 1 is connected with a lifting rotating frame 4 through a rotating shaft 402 and a bearing, the lifting rotating frame 4 is connected with a support 3 through a sliding block 407 and a guide rail 406, the folding platform 2 is fixed above the support 3, and the landing gear fixing mechanism 5 is fixed below the folding platform 2.

More specifically, as shown in fig. 2, the foldable platform 2 includes a platform plate 201, a side plate 202, an angle plate 203, a foldable electric push rod 204 and a foldable electric push rod seat 205, the platform plate 201 is hinged to the side plate 202, the side plate 202 is hinged to the angle plate 203, the foldable electric push rod 204 is disposed between the two hinged plates, two ends of each foldable electric push rod 204 are hinged to the corresponding foldable electric push rod seat 205, and the foldable electric push rod seats 205 are fixed on the inner sides of the plates to control the folding of the side plate and the angle plate.

As shown in fig. 3 and 4, a support 3 is welded and fixed below the platform board 201, and the support plays a role of supporting the folding platform. The platform plate 201 is provided with a starting hole 207, and a starting mechanism 1 is 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 installed below a platform plate 201, the starting motor 103, the starting rod 102 and the bevel gear 104 are all installed on the starting mechanism support 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, the starting motor drives the starting rod to rotate, and the starting rod 102 can penetrate through a starting hole 207 and extend upwards to the oil-driven bypass aircraft 6 to start the oil-driven bypass aircraft 6. Four guide rails 406 are arranged between the folding platform 2 and the bracket 3, each guide rail 406 is provided with a sliding block 407, and a lifting rotating frame 4 is connected between the four sliding blocks 407, so that the lifting rotating frame 4 can move up and down along the guide rails. The lifting rotary frame 4 is fixed 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 installed at the lower end of the support 3. A lifting motor 411 is fixedly installed below the folding platform 2, and the lifting motor 411 and the lifting screw 408 are driven by a pair of synchronous belt wheels 413 and a synchronous belt 414. When the lifting motor drives the lifting screw rod to rotate, the lifting block moves up and down along the lifting screw rod due to the transmission effect of the threads, so that the lifting rotating frame is driven to move up and down. The lifting rotating frame 4 is provided with a swinging groove 403 and a track groove 404, the lifting rotating frame 4 is further provided with a lifting rotating support 401, and the starting mechanism 1 is installed on the lifting rotating support and is fixedly connected with the swinging 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, so that the rotation of the starting mechanism is realized. The starting hole 207 is long, and after the lifting rotating frame 4 drives the starting mechanism 1 to lift and rotate, the starting rod can penetrate through the starting hole to start the oil-driven ducted aircraft 6; after the oil-driven ducted aircraft 6 is started, the lifting rotating frame 4 withdraws the starting rod below the folding platform through rotating and lifting actions.

Four hook holes 206 are formed in the platform plate 201, each two hook holes are in a group, and two hook holes in each group are arranged oppositely. An undercarriage fixing mechanism 5 is installed below the platform plate 201, and the undercarriage fixing mechanism 5 comprises a lifting 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 arranged oppositely, and a crank rocker mechanism is arranged below each hook hole 206, so that the landing hook 501 can penetrate through the hook hole 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 to one end of a first connecting rod 505, the other end of the first connecting rod 505 is hinged to one end of the crank 506, the other end of the crank 506 is hinged to the push rod end of an electric push rod 508, the push rod end of the electric push rod 508 is further hinged to one end of a second connecting rod 510, and the other end of the second connecting rod 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 a crank seat 507, the mounting end of the electric push rod 508 is hinged with an electric push rod seat 509 to form two groups of crank rocker mechanisms driven by one electric push rod 508 at the same time, and when the electric push rod extends and shortens, lifting hooks are simultaneously actuated in two opposite hook holes to lock and release the landing gear 601 of the oil-driven ducted aircraft 6.

The action process of the embodiment of the starting platform of the separated foldable oil-driven duct aircraft is as follows:

as shown in fig. 1 and 3, in the unfolded state, the electric actuating rod 405 is retracted, the rod end slides in the track groove 404 and the swing groove 403, the whole actuating mechanism 1 is driven to rotate around the rotating shaft 402, and the actuating rod 102 is in the upright state. The lifting motor 413 works to drive the lifting screw 408 to rotate through the synchronous belt wheel 413 and the synchronous belt 414, and the lifting block 410 rises under the action of the threads to drive the whole lifting rotating frame 5 and the starting mechanism 1 to rise.

As shown in fig. 1 and fig. 5, in the unfolded state, the electric push rod 508 is retracted, and the second link 510, the crank 506 and the first link 505 are driven to rotate the crank-rocker mechanisms at both sides, so that the lifting hook 501 fixedly connected to the rocker 503 rotates along with the rocker 503 to extend out of the platform plate 201.

As shown in fig. 1, 3, 5, and 8, in the deployed state, the landing hook 501 rotates to extend out of the platform plate 201, and fixes the landing gear 601 of the ducted aircraft 6. When the starting rod 102 is in the vertical state, the whole lifting rotating frame 5 and the starting mechanism 1 are lifted 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 is extended, and the push rod end slides in the track groove 404 and the swing groove 403, thereby rotating the entire actuating mechanism 1 around the rotating shaft 402, and the actuating lever 102 becomes the lowered state. The lifting motor 413 works to drive the lifting screw 408 to rotate through the synchronous belt pulley 413 and the synchronous belt 414, the lifting block 410 descends under the action of the threads 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 out 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 to rotate back to the platform plate 201, 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 platform plate 201 at this time.

As shown in fig. 2 and 7, the folding electric push rod 204 is retracted, the corner plate 203 is retracted, and then the side plate 203 is retracted, and the whole system is retracted into a rectangular box body shown in fig. 7.

The above-described embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements of the technical solutions of the present invention can be made by those skilled in the art without departing from the spirit of the present invention, and the technical solutions of the present invention are within the scope of the present invention defined by the claims.