CN112550737A - Novel multipurpose autorotation rotorcraft - Google Patents
Novel multipurpose autorotation rotorcraft Download PDFInfo
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- CN112550737A CN112550737A CN202011593768.6A CN202011593768A CN112550737A CN 112550737 A CN112550737 A CN 112550737A CN 202011593768 A CN202011593768 A CN 202011593768A CN 112550737 A CN112550737 A CN 112550737A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 24
- 230000007246 mechanism Effects 0.000 claims description 40
- 238000005096 rolling process Methods 0.000 claims description 11
- 238000003825 pressing Methods 0.000 claims description 7
- 230000009471 action Effects 0.000 claims description 4
- 238000005516 engineering process Methods 0.000 abstract description 4
- 238000003466 welding Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 238000009966 trimming Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/22—Other structures integral with fuselages to facilitate loading, e.g. cargo bays, cranes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings or cowlings
- B64D29/04—Power-plant nacelles, fairings or cowlings associated with fuselages
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Transmission Devices (AREA)
Abstract
本发明提供了一种新型多用途自转旋翼机，包括机身、机架、尾翼、动力装置、旋翼、起落架、螺旋桨，机架上设置有机身，机架后方设置有动力装置和尾翼，机架底部设置有起落架，所述的机架顶部通过分体式旋翼毂装置连接有单主旋翼，分体式旋翼毂装置内设置有预旋离合器装置；所述动力装置后置在机架上，动力装置连接有推进式螺旋桨，动力装置通过旋翼预旋操纵装置与预旋离合器装置相连。本发明采用旋翼预旋技术，即起飞前通过传动装置将旋翼预先驱转，然后通过离合器切断传动链路后起飞，可使得旋翼机可以鹞式跳跃或超短距起飞。
The invention provides a novel multi-purpose autorotor, comprising a fuselage, a frame, a tail, a power device, a rotor, a landing gear, and a propeller. The frame is provided with a fuselage, and the rear of the frame is provided with a power device and a tail. The bottom of the frame is provided with a landing gear, the top of the frame is connected with a single main rotor through a split rotor hub device, and a pre-rotation clutch device is arranged in the split rotor hub device; the power device is rear-mounted on the frame, The power device is connected with a propulsion propeller, and the power device is connected with the pre-rotation clutch device through the rotor pre-rotation control device. The invention adopts the rotor pre-rotation technology, that is, the rotor is pre-rotated by the transmission device before takeoff, and then takes off after the transmission link is cut off by the clutch, so that the rotorcraft can jump or take off at an ultra-short distance.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a novel multipurpose autorotation rotorcraft.
Background
The autorotation gyroplane (called gyroplane for short) is a gyroplane taking an autorotation rotor as a lifting surface, propeller pushing/pulling force or other energy supply modes as advancing power, and has the characteristics of simple mechanism, high safety, low cost and the like, and the rotor of the gyroplane realizes autorotation by depending on the forward incoming flow driving during flight to provide lift force.
The existing autorotation gyroplanes have the following defects:
1, the overall structure height size is great, and the whole transportation is inconvenient, can't pack into the container transportation.
2, adopt the gas circuit to realize balancing, rotor brake and prewhirl, the structure is complicated, and the reliability is low, and weight is big, overhauls complicacy.
And 3, the rotor head cannot be replaced, the precision is difficult to control during welding and machining, and the machining is complex.
4, the welding deformation of the frame causes the assembly of the frame and the shell to be complicated.
5, the seesaw adopts a structure with the same thickness and the same section, and due to the action of centrifugal force, the stress applied to the seesaw is larger when the seesaw is closer to the outer side, so that bolts with different sizes are required to be used for fixing.
And 6, the transmission hard connection has poor reliability.
And 7, the size of the payload which can be carried is small.
8, the front wheel bracket adopts a bent pipe and welding process, so that the processing difficulty is high.
9, the flight performance on plateau is poor.
Disclosure of Invention
The invention provides a novel multipurpose autorotation gyroplane, which aims to solve the problems in the prior art and adopts a gyroplane prerotation technology, namely, the gyroplane is driven to rotate in advance through a transmission device before taking off, and then takes off after a transmission link is cut off through a clutch, so that the gyroplane can take off in a ray type jumping mode or an ultrashort distance mode.
The invention comprises a machine body, a rack, an empennage, a power device, a rotor wing, an undercarriage and a propeller, wherein the machine body is arranged on the rack, the power device and the empennage are arranged behind the rack, the undercarriage is arranged at the bottom of the rack, the top of the rack is connected with a single main rotor wing through a split rotor wing hub device, and a pre-rotation clutch device is arranged in the split rotor wing hub device; the power device is arranged on the frame in the rear position and is connected with a propelling propeller, and the power device is connected with the pre-rotation clutch device through a rotor wing pre-rotation control device.
The split rotor hub device comprises a seesaw hub mechanism and a detachable rotor head mechanism, wherein the seesaw hub mechanism comprises an upper equal-thickness clamp plate and a lower equal-thickness clamp plate which are connected through a stand column, a rotor wing is clamped between the upper equal-thickness clamp plate and the lower equal-thickness clamp plate, and a tower block is arranged on the upper equal-thickness clamp plate; the detachable rotor head mechanism mainly comprises a tower column upright post, a tower column bottom, a big fluted disc, a pre-rotation clutch device, an operating cantilever, a pitching rolling shaft and a support, wherein the tower column upright post is connected with the upright post of the seesaw paddle hub mechanism and is fixed with a tower block; the control cantilever is connected with a pitching and rolling shaft, and the pitching and rolling shaft is connected with the rack through a support.
The upper and lower equal-thickness clamping plates adopt the clamping plate structure with the equal-thickness and non-equal-section, the section with the same thickness is gradually reduced, and the size complexity of the rotor blade mounting bolt is reduced, so that the cost and the assembly complexity are reduced.
The pre-rotation clutch device comprises an inner shaft connected with the operating cantilever through a bearing structure, the inner shaft is connected with the transmission mechanism, an inner gear ring is arranged on the inner shaft, the inner gear ring is meshed with an outer gear ring through helical teeth, an outer gear moves up and down along the helical teeth of the inner shaft under the action of centrifugal force, and when the outer gear moves to the highest position, the outer gear is meshed with a large gear of the split rotor hub device.
The rotor wing pre-rotation control device comprises a pre-rotation mechanism and a control mechanism, wherein the pre-rotation mechanism comprises a belt transmission structure and a tensioning structure, the belt transmission structure consists of a large belt wheel and a small belt wheel through a belt, the large belt wheel is positioned on an output shaft of the power device, and the small belt wheel is connected with the pre-rotation clutch device through a transmission mechanism; the tensioning structure comprises a belt tensioning rocker arm, a belt tensioning wheel and a belt pressing block, wherein the belt tensioning wheel and the belt pressing block are fixed on the belt tensioning rocker arm; the operating mechanism is positioned in front of the machine body and is connected with the belt tensioning rocker arm through the pre-rotation pull wire, when the operating mechanism tensions the pre-rotation pull wire, the belt tensioning wheel compresses the belt to enable the belt to be in a tensioning state between the large belt wheel and the small belt wheel, and the power of the output shaft of the engine is transmitted to the rotor clutch gear through the belt transmission structure and the transmission mechanism.
The split rotor hub device is characterized in that an operation cantilever of the split rotor hub device is connected with a balancing device, the balancing device comprises two linear motors arranged on two sides of the operation cantilever, pitching balancing is carried out when the two linear motors extend in the same direction, and rolling balancing is carried out when the two linear motors extend in a differential mode.
In further improvement, both sides of the fuselage are provided with detachable wings.
The improved rotor wing structure is characterized in that the rack is mechanically connected with the tail beam through detachable bolts and clamping plates, and the rack is mechanically connected with the split rotor wing hub device through detachable bolts and clamping plates.
The improved airplane comprises a front airplane body, a left airplane body, a right airplane body, an engine cover, a mast fairing and seats, wherein the seats are detachable seats, a front row of single seats and a rear row of double seats are arranged in parallel.
Further improved, the landing gear adopts a front three-point landing gear, and the tail wing adopts a mountain-shaped tail wing.
The split rotor hub device is further improved, a brake pad is arranged in the split rotor hub device, and the brake pad is connected to the front end of the machine body through a brake cable.
The invention has the beneficial effects that:
1. the rotor prerotation technology is adopted, namely the rotor is driven to rotate in advance through the transmission device before takeoff, then the rotor takes off after the transmission link is cut off through the clutch, and the rotorcraft can jump or take off in a short distance in a ray mode.
2. The backseat can carry one to two people or goods, has expanded the usage of rotation gyroplane, can install the wing additional according to the task demand and realize the plateau flight.
3. The trim arrangement enables trimming of the rotorcraft at various speeds, thereby reducing the load on the operating rod and improving the comfort of the pilot.
4. The mast and the tail beam are connected with the frame by bolts, so that the transportation and the disassembly are convenient.
5. The equipment such as the cylinder of traditional gyroplane has been cancelled, the kind and the quantity of welding spare have been reduced to processing technology nature has been improved, reduction in production cost.
Drawings
Figure 1 is a perspective view of a rotorcraft;
figure 2 is a front view of the rotorcraft;
FIG. 3 is a side view of the rotorcraft;
figure 4 is a top view of the rotorcraft;
FIG. 5 is a perspective view of a rotorcraft with additional wings;
FIG. 6 is an elevation view of a rotorcraft with wings added;
FIG. 7 is a side view of the rotorcraft with the wing attached;
FIG. 8 is a top view of a wing-mounted rotorcraft;
FIG. 9 is a view of the tail boom attached to the frame;
FIG. 10 is a perspective view of the tail boom connected to the frame;
FIG. 11 is an exploded view of the tail boom attached to the frame;
FIG. 12 is a perspective view of the mast and frame connection;
FIG. 13 is a view of the mast connected to the frame;
FIG. 14 is an exploded view of the mast and frame connection;
FIG. 15 is a perspective view of the mast in a folded state;
FIG. 16 is a view of the mast folded condition;
FIG. 17 is a rear view of the trim apparatus;
FIG. 18 is a side view of the trim apparatus;
FIG. 19 is a perspective view of the trimming device;
FIG. 20 is a perspective view of the pre-rotation drive;
FIG. 21 is a pre-rotation map;
FIG. 22 is a front joystick prerotation control diagram;
FIG. 23 is a normal state view of the front joystick;
FIG. 24 is a normal state perspective view of the front joystick;
FIG. 25 is a component view of a rotorcraft fuselage;
FIG. 26 is a block diagram of the frame, engine, and pre-rotation system;
FIG. 27 is a rotor braking diagram;
figure 28 is a rotor braking schematic.
In the figure, a rotor blade 1, a body 2, an undercarriage 3, a tail boom 4, an empennage 5, a propeller 6, an engine 7, a tail boom clamp plate 8, a frame 9, a mast clamp plate 10, an upper mast 11, a rocker arm 12, a tension spring 13, a linear motor 14, a belt releasing spring 15, a belt pressing block 16, a small belt pulley 17, a belt tensioning pulley 18, a belt 19, a large belt pulley 20, a flexible shaft 21, a pre-rotation stay 22, a pre-rotation hook 23, a front control lever 24, a right body 25, a front windshield 26, a front body 27, a front seat 28, a left body 29, a rear seat 30, an engine fairing 31, a mast fairing 32, a rotor brake shoe 33, a rotor brake stay 34 and a wing 35.
Detailed Description
The invention is further described with reference to the following figures and detailed description.
The specific structure of the invention is shown in figures 1 to 28, and the novel multipurpose autorotation rotorcraft adopts the layout form of a single main rotor, a power rear-mounted propeller, a propulsion propeller, a front three-point landing gear, a single rotor and a mountain-shaped empennage. The autorotation rotorcraft comprises a body shell 2, a frame, a mountain-shaped empennage 5, an engine 7, a propulsion propeller 6, a rotor wing 1, a front three-point type undercarriage 3 and the like.
The top of the frame is connected with a single main rotor through a split rotor hub device, and a pre-rotation clutch device is arranged in the split rotor hub device; the power device is arranged on the frame in the rear position and is connected with a propelling propeller, and the power device is connected with the pre-rotation clutch device through a rotor wing pre-rotation control device.
The autorotation rotorcraft adopts an open type cabin, a front row single seat is the position of a driver, a back row is provided with two seats in parallel and used for carrying passengers or goods, and a front row and a back row are respectively provided with a set of flight control lever and an accelerator brake control mechanism. The back row can be used for seating a single person or two persons, and can also be used for loading single person and goods or only loads goods.
The two sides of the back seat of the autorotation rotorcraft body are provided with short wings which can be used for butting the additionally arranged wings 35. When long-distance flight or plateau flight is needed, the wings are butted with the short wings, and the wings are additionally arranged on the gyroplane, so that the lift-drag ratio and the flight efficiency are improved. During normal flight tasks, the wings can be detached.
The autorotation gyroplane frame 9 and the tail boom 4 adopt a detachable mechanical connection mode and are connected with the frame and the tail boom through bolts and tail boom clamping plates 8.
The autogyro frame 9 and the upper mast 11 are mechanically connected by means of detachable bolts and clamping plates (fig. 12 to 14).
After partial bolts of the frame 9 and the mast clamp plate 10 are removed, the upper mast can rotate around a bolt shaft to tilt forward for a certain angle, after the upper mast rotates for a certain angle, the bolt holes in the mast clamp plate 10 can be overlapped with the bolt holes in the frame 9, and the forward-tilting upper mast 11 can be fixed after the bolts or the bolts are inserted. Therefore, the overall height of the gyroplane is reduced, and transportation is facilitated (fig. 15-16).
Two linear motors 14 are used to pull the rotor control rocker 12 through a tension spring 13 to achieve rotorcraft pitch and roll trim. The two linear motors 14 are used for pitching balancing when extending in the same direction, and for rolling balancing when extending in the differential direction (fig. 17-19).
The split rotor hub device comprises a seesaw hub mechanism and a detachable rotor head mechanism, wherein the seesaw hub mechanism comprises an upper equal-thickness clamp plate and a lower equal-thickness clamp plate which are connected through a stand column, a rotor wing is clamped between the upper equal-thickness clamp plate and the lower equal-thickness clamp plate, and a tower block is arranged on the upper equal-thickness clamp plate; the detachable rotor head mechanism mainly comprises a tower column upright post, a tower column bottom, a big fluted disc, a pre-rotation clutch device, an operating cantilever, a pitching rolling shaft and a support, wherein the tower column upright post is connected with the upright post of the seesaw paddle hub mechanism and is fixed with a tower block; the control cantilever is connected with a pitching and rolling shaft, and the pitching and rolling shaft is connected with the rack through a support.
The prerotation clutch device comprises an inner shaft connected with the control cantilever through a bearing structure, the inner shaft is connected with a transmission mechanism, an inner gear ring is arranged on the inner shaft, the inner gear ring is meshed with an outer gear ring through helical teeth, an outer gear moves up and down along the helical teeth of the inner shaft under the action of centrifugal force, and when the outer gear moves to the highest position, the outer gear is meshed with a large gear of the split rotor hub device.
The rotor wing pre-rotation control device comprises a pre-rotation mechanism and a control mechanism, wherein the pre-rotation mechanism comprises a belt transmission structure and a tensioning structure, the belt transmission structure consists of a large belt wheel 20 and a small belt wheel 17 through a belt 19, the large belt wheel is positioned on an output shaft of the power device, and the small belt wheel is connected with a pre-rotation clutch device through a transmission mechanism; the tensioning structure comprises a belt tensioning rocker arm, a belt tensioning wheel 18 and a belt pressing block 16, wherein the belt tensioning wheel 18 and the belt pressing block 16 are fixed on the belt tensioning rocker arm; the control mechanism is located in front of the machine body and connected with the belt tensioning rocker arm through the pre-rotation pull wire, when the pre-rotation pull wire is tensioned by the control mechanism, the belt tensioning wheel compresses the belt to enable the belt to be in a tensioning state between the large belt wheel and the small belt wheel, and the power of the output shaft of the engine is transmitted to the rotor clutch gear through the belt transmission structure and the flexible shaft 21. The upper and lower equal-thickness clamping plates adopt the clamping plate structure with the equal-thickness and non-equal-section, the section with the same thickness is gradually reduced, and the size complexity of the rotor blade mounting bolt is reduced, so that the cost and the assembly complexity are reduced.
The autorotation rotorcraft adopts a prerotation pull wire 22 to tighten a belt tension pulley 18, and transmits the power of a large belt pulley 20 to a small belt pulley 17 to realize prerotation of the rotor.
When the rotor wing prerotates, the front part of the prerotation pull wire 22 is connected 24 with the front control lever through the prerotation hook 23, when the control lever 24 is pushed forwards, the belt tension pulley 18 is tensioned by the prerotation pull wire 22, and when the control lever 24 is pulled backwards, the prerotation hook 23 is automatically disconnected with the front control lever 24.
The autogyro casing is composed of a front windshield 26, a front body 27, a left body 29, a right body 25, a hood 31, a mast fairing 32, a front seat 28, a rear seat 30, and the like.
The soft shaft 21 is adopted to transmit the power of the small belt wheel 17 to the rotor wing, so that the prerotation of the rotor wing is realized. Rotor braking is achieved by means of brake cables 34 and rotor brake shoes 33.
While the invention has been described in terms of its preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention.
Claims (10)
1. The utility model provides a novel multipurpose rotation gyroplane, includes fuselage, frame, fin, power device, rotor, undercarriage, screw, is provided with the fuselage in the frame, and the frame rear is provided with power device and fin, and the frame bottom is provided with undercarriage, its characterized in that: the top of the machine frame is connected with a single main rotor wing through a split rotor wing hub device, and a pre-rotation clutch device is arranged in the split rotor wing hub device; the power device is arranged on the frame in the rear position and is connected with a propelling propeller, and the power device is connected with the pre-rotation clutch device through a rotor wing pre-rotation control device.
2. The novel multipurpose autorotation rotorcraft according to claim 1, characterized in that: the split rotor hub device comprises a seesaw hub mechanism and a detachable rotor head mechanism, wherein the seesaw hub mechanism comprises an upper equal-thickness clamp plate and a lower equal-thickness clamp plate which are connected through a stand column, a rotor wing is clamped between the upper equal-thickness clamp plate and the lower equal-thickness clamp plate, and a tower block is arranged on the upper equal-thickness clamp plate; the detachable rotor head mechanism mainly comprises a tower column upright post, a tower column bottom, a big fluted disc, a pre-rotation clutch device, an operating cantilever, a pitching rolling shaft and a support, wherein the tower column upright post is connected with the upright post of the seesaw paddle hub mechanism and is fixed with a tower block; the control cantilever is connected with a pitching and rolling shaft which is connected with the rack through a support; the upper and lower equal-thickness splints adopt splints with equal thickness and unequal cross-section, and the cross section with the same thickness is gradually reduced.
3. The novel multipurpose autorotation rotorcraft according to claim 2 wherein: the prerotation clutch device comprises an inner shaft connected with the control cantilever through a bearing structure, the inner shaft is connected with a transmission mechanism, an inner gear ring is arranged on the inner shaft, the inner gear ring is meshed with an outer gear ring through helical teeth, an outer gear moves up and down along the helical teeth of the inner shaft under the action of centrifugal force, and when the outer gear moves to the highest position, the outer gear is meshed with a large gear of the split rotor hub device.
4. The novel multipurpose autorotation rotorcraft according to claim 1, characterized in that: the rotor wing pre-rotation control device comprises a pre-rotation mechanism and a control mechanism, wherein the pre-rotation mechanism comprises a belt transmission structure and a tensioning structure, the belt transmission structure consists of a large belt wheel and a small belt wheel through a belt, the large belt wheel is positioned on an output shaft of the power device, and the small belt wheel is connected with the pre-rotation clutch device through a transmission mechanism; the tensioning structure comprises a belt tensioning rocker arm, a belt tensioning wheel and a belt pressing block, wherein the belt tensioning wheel and the belt pressing block are fixed on the belt tensioning rocker arm; the operating mechanism is positioned in front of the machine body and is connected with the belt tensioning rocker arm through the pre-rotation pull wire, when the operating mechanism tensions the pre-rotation pull wire, the belt tensioning wheel compresses the belt to enable the belt to be in a tensioning state between the large belt wheel and the small belt wheel, and the power of the output shaft of the engine is transmitted to the rotor clutch gear through the belt transmission structure and the transmission mechanism.
5. The novel multipurpose autorotation rotorcraft according to claim 2 wherein: the control cantilever of the split rotor hub device is connected with a balancing device, the balancing device comprises two linear motors arranged on two sides of the control cantilever, pitching balancing is carried out when the two linear motors stretch in the same direction, and rolling balancing is carried out when the two linear motors stretch in a differential mode.
6. The novel multipurpose autorotation rotorcraft according to claim 1, characterized in that: the two sides of the fuselage are provided with detachable wings.
7. The novel multipurpose autorotation rotorcraft according to claim 1, characterized in that: the frame and the tail beam are mechanically connected through detachable bolts and clamping plates, and the frame and the split rotor hub device are mechanically connected through detachable bolts and clamping plates.
8. The novel multipurpose autorotation rotorcraft according to claim 1, characterized in that: the machine body comprises a front machine body, a left machine body, a right machine body, an engine cover, a mast fairing and a seat, wherein the seat is a detachable seat, a front row of single seats and a rear row of double seats are arranged in parallel.
9. The novel multipurpose autorotation rotorcraft according to claim 1, characterized in that: the landing gear adopts a front three-point landing gear, and the empennage adopts a mountain-shaped empennage.
10. The novel multipurpose autorotation rotorcraft according to claim 1, characterized in that: and a brake pad is arranged in the split rotor hub device and is connected to the front end of the machine body through a brake cable.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011593768.6A CN112550737A (en) | 2020-12-29 | 2020-12-29 | Novel multipurpose autorotation rotorcraft |
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| CN202011593768.6A CN112550737A (en) | 2020-12-29 | 2020-12-29 | Novel multipurpose autorotation rotorcraft |
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| CN110539881A (en) * | 2019-09-04 | 2019-12-06 | 北京航空航天大学 | Unmanned autorotation gyroplane control system |
| CN211592925U (en) * | 2020-02-25 | 2020-09-29 | 河北天启通宇航空器材科技发展有限公司 | Pedal type pre-rotation mechanism of autorotation rotorcraft |
| CN214112889U (en) * | 2020-12-29 | 2021-09-03 | 南京华航翼飞行器技术有限公司 | Novel multipurpose autorotation rotorcraft |
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2020
- 2020-12-29 CN CN202011593768.6A patent/CN112550737A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN207523926U (en) * | 2017-09-08 | 2018-06-22 | 陕西宝鸡专用汽车有限公司 | Novel gyroplane |
| CN109131851A (en) * | 2018-09-21 | 2019-01-04 | 湖南湘晨飞机工业有限公司 | A kind of gyroplane is prewhirled clutch |
| CN110539881A (en) * | 2019-09-04 | 2019-12-06 | 北京航空航天大学 | Unmanned autorotation gyroplane control system |
| CN211592925U (en) * | 2020-02-25 | 2020-09-29 | 河北天启通宇航空器材科技发展有限公司 | Pedal type pre-rotation mechanism of autorotation rotorcraft |
| CN214112889U (en) * | 2020-12-29 | 2021-09-03 | 南京华航翼飞行器技术有限公司 | Novel multipurpose autorotation rotorcraft |
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