CN106672228A - Multi-blade rotor tandem type aircraft - Google Patents
Multi-blade rotor tandem type aircraft Download PDFInfo
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- CN106672228A CN106672228A CN201510757487.2A CN201510757487A CN106672228A CN 106672228 A CN106672228 A CN 106672228A CN 201510757487 A CN201510757487 A CN 201510757487A CN 106672228 A CN106672228 A CN 106672228A
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- pitman
- bascule
- skeleton
- frame
- break
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Abstract
The invention discloses a multi-blade rotor tandem type aircraft. The multi-blade rotor tandem type aircraft comprises a framework, a front shell connected with the framework, wings fixedly connected to the rear part of the framework, a lower support for supporting the framework, an energy device arranged in the framework, an azimuth controller arranged on the framework, and a central control unit which can receive external signals and control the energy device and the azimuth controller. The multi-blade rotor tandem type aircraft disclosed by the invention is very simple in structure, light in weight, easy to control and carry when a user goes out, more stable in flight and more free in operation for a board main body plate, low in flight site requirements, namely only requiring a dozen square meters of barrier-free space, and capable of generally adapting to various flight environments.
Description
Technical field
The present invention relates to a kind of electronic toy, more particularly to one kind of multiple bladed rotors tandem aircraft.
Background technology
General various bladed rotors tandem aircraft aircraft systems are complicated, and volume is larger, it is desirable to which there is broader space flying field.Therefore Many times, people are to carry out various bladed rotors tandem aircraft flights in open field place.With life change increasingly, many people wish at home, the relatively narrower space such as private office can also play various bladed rotors tandem aircraft.Various bladed rotors tandem aircraft fly in narrow space, on the one hand small volume is required, on the other hand require that position controller is sensitive, there is certain limit in the volume for reducing various bladed rotors tandem aircraft after all, so, just not only the volume of various bladed rotors tandem aircraft required, also the central control unit of various bladed rotors tandem aircraft is put forward higher requirement simultaneously.
The content of the invention
Based on the deficiencies in the prior art, problem to be solved by this invention is to provide a kind of flexible various bladed rotors tandem aircraft of steering.
To solve the above problems，Various bladed rotors tandem aircraft that the present invention is provided include skeleton、The front shell being connected with skeleton、It is fixedly connected on the wing at skeleton rear、Support the lower carriage of the skeleton、The energy source device being arranged on the skeleton、The position controller being arranged on the skeleton、And external signal can be received and the central control unit of the energy source device and position controller can be controlled，The energy source device includes front power source、Power source afterwards、The pitman being connected with front power source、The little pitman being connected through in the pitman and with rear power source、The bow oar being arranged on pitman and the rear oar being arranged on little pitman，The position controller includes the bascule being fixed on the pitman、Two steering wheels、Connect the drive link of the steering wheel and bascule，Connect the connecting rod of the bow oar and bascule，The bascule includes the steering ball being fixed on the pitman、The break-in disk being socketed on the steering ball、Bascule frame、And connect the bearing of the bascule frame and break-in disk，The connecting rod is connected between the bow oar and break-in disk，The drive link is connected on the bascule frame.
Used as one embodiment, the bascule frame is provided with spherical keeper, and one end of the drive link connection bascule frame is fastening structure, and the fastening structure is enclosed within the spherical keeper.One end of the drive link connection steering wheel is provided with screw thread, and the end is connected by a gear drive with steering wheel.The bow oar includes two panels front vane, the front vane fixing device of fixed front vane, fixes L-type frame of the front vane fixing device on the pitman, the union joint being conformed with the front vane fixing device, connecting hole is provided with the L-type frame, described connecting rod one end is connected with break-in disk, and the other end is connected through the connecting hole with union joint.The union joint is spherical, and the break-in disk is provided with spherical connector, and the connecting rod is double end ball cover connecting rod, is respectively fitted on the union joint and spherical connector.
As another embodiment, it also includes steadily of centre of gravity device, the rear oar includes two panels rear blade, the rear blade fixing device of fixed rear blade and fixes blade clamping connection mouth of the rear blade fixing device on the little pitman, the blade clamping connection mouth is provided with V-type interface, and the steadily of centre of gravity device is installed on the V-type interface.The central control unit is electrically connected respectively with the front power source, rear power source and two steering wheels.
Compared with prior art, the structure very simple of the model plane, lightweight, easily controllable and outgoing carrying, roomy main board makes its flight more steadily, and manipulate more freely, and, flying field is less demanding, it is only necessary to more than ten square metres of clear space；Because fuselage leg bottom surface is stained with frosted paster, thus place it in water or on lawn can free flight, can generally be adapted to various flight environment of vehicle.
To make the present invention easier to understand, various bladed rotors tandem aircraft of the present invention are expanded on further below in conjunction with accompanying drawing.
Description of the drawings
Fig. 1 is various bladed rotors tandem aircraft schematic perspective views of a preferred embodiment of the present invention.
Fig. 2 is the enlarged drawing in Fig. 1 at B.
Fig. 3 is the explosive view of various bladed rotors tandem aircraft shown in Fig. 1.
Fig. 4 is the three-dimensional exploded view of the bascule of various bladed rotors tandem aircraft shown in Fig. 1.
Fig. 5 is the dimensional structure diagram of connecting rod shown in Fig. 2.
Fig. 6 is the dimensional structure diagram of drive link shown in Fig. 2.
Specific embodiment
With reference now to Description of Drawings the preferred embodiments of the present invention,.
With reference to Fig. 1-3, various bladed rotors tandem aircraft of the present invention include skeleton 20 and the front shell 10 for connecting of skeleton 20, the wing 40 for being fixedly connected on the rear of skeleton 20, the lower carriage 30 for supporting the skeleton 20, the energy source device 50 for being arranged at the top of the skeleton 20, are arranged at the top of skeleton 20 and drive the position controller 60 and can receive external signal and can control the central control unit 70 of the energy source device 50 and position controller 60 that the energy source device 50 turns to.The central control unit 70 is fixed on skeleton 20.The front shell 10 is fixed on the front end of skeleton 20, and the front shell 10 is effectively protected central control unit 70.The wing 40 is fixed on the rearmost end of skeleton 20, and its function is to allow an operator to clearly take one's bearings.The lower carriage 30 is fixed on the lower end of skeleton 20, and during various bladed rotors tandem aircraft contact ground, the lower carriage 30 plays a part of to support and protect various bladed rotors tandem aircraft bodies.
With reference to Fig. 1,3, various bladed rotors tandem aircraft of the present embodiment also include for various bladed rotors tandem aircraft for electric energy power supply 80.The energy source device 50 is used to produce aerostatic buoyancy during various bladed rotors tandem aircraft flights, come so that various bladed rotors tandem aircraft can fly up, it includes front power source 55, rear power source 56 pitman 54 being connected with front power source 55, the little pitman 53 being connected through in the pitman 54 and with rear power source 56, the bow oar 51 being arranged on pitman 54 and the rear oar 52 being arranged on little pitman 53.The power supply 80 to the front power source 55, rear power source 56 and central control unit 70 provide electric energy.The pitman 54 is connected by a main gear transmission mechanism 58 with front power source 55, and the little pitman 53 passes through the pitman 54, and is connected with rear power source 56 using a pinion drive mechanism 59.The bow oar 51 includes two panels front vane 511 and the front vane fixing device 512 that these front vanes 511 are fixed on the pitman 54.The pitman 54 is provided with T-shaped frame 57, and on the L-type frame 57 connecting hole 571 is offered.The rear oar 52 includes two panels rear blade 521, the rear blade fixing device 522 for fixing these rear blades 521 and the blade clamping connection mouth 523 that the rear blade fixing device 522 is fixed on the little pitman 53.The blade clamping connection mouth 523 is provided with V-type interface 91.Steadily of centre of gravity device 90 is additionally provided with the little pitman 53, the steadily of centre of gravity device 90 is positioned on little pitman 53 by V-type interface 91.During various bladed rotors tandem aircraft flights, the steadily of centre of gravity device 90 plays a part of to balance flight attitude.
With reference to Fig. 2, the position controller 60 includes 61, two steering wheels 62 of bascule being fixed on the pitman 54, the drive link 63 for connecting the steering wheel 62 and bascule 61, is connected the bow oar 51（With reference to Fig. 1）With the connecting rod 64 of bascule 61.Described two steering wheels 62 are respectively arranged in the both sides of the skeleton 20.With reference to Fig. 1,2 and Fig. 4, the bascule 61 includes the steering ball 612 being fixed on the pitman 54, the break-in disk 614 being socketed on the steering ball 612, bascule frame 611 and connects the bearing 613 of the bascule frame 611 and break-in disk 614.The steering ball 612 increases the flexible performance of the motion of break-in disk 614, expands the range of activity of the break-in disk 614.The connection that the bascule frame 611 passes through bearing 613 and break-in disk 614.The break-in disk 614 is provided with the spherical connector 6141 of projection, and the spherical union joint 5121 of projection also is provided with the front vane fixing device 512（As shown in Figure 2 and Figure 3）.It is ball cover shape that the connecting rod 64 is double end ball cover connecting rod, the i.e. two ends of connecting rod 64（Such as Fig. 5）.One end of the connecting rod 64 is enclosed within the union joint 5121 in front vane fixing device 512, on the spherical connector 6141 that the other end is enclosed within the break-in disk 614 through the connecting hole 571 of the T-shaped frame 57, so as to play a part of to connect bow oar 51 and break-in disk 614.The connecting hole 571 of the T-shaped frame 57 plays a part of positioning link bar 64.With continued reference to Fig. 2,4, the bascule frame 611 is provided with two spherical keepers 6111.Each steering wheel 62 is connected respectively by a drive link 63 spherical keeper 6111 corresponding with.One end of the drive link 63 is fastening structure 631, and threaded threaded ends 632 are set on the other end（Such as Fig. 6）, the fastening structure 631 is enclosed within the spherical keeper 6111, and threaded ends 632 are connected by a gear drive with steering wheel 62（It is not shown）.The central control unit 70 is electrically connected with front power source 55, rear power source 56 and two steering wheels 62（It is not shown）, the central control unit 70 can control front power source 55, rear power source 56 and two steering wheels 62 with wireless receiving external signal, enable various bladed rotors tandem aircraft to complete flare maneuver according to external signal.
The drive link 63 pulls the bascule 61, bascule 61 to control bow oar 51 by connecting rod 64 and turned under the driving of steering wheel 62.Wherein, the steering ball 612 in the bascule 61 increased the flexible performance of the motion of break-in disk 614, substantially improve the sensitivity of bascule 61.It is relatively reliable, effectively make bascule frame 611 to the transition of the power of break-in disk 614 in addition, the connection that the bascule frame 611 passes through bearing 613 and break-in disk 614, turn to sensitive effect so as to reach various bladed rotors tandem aircraft.
Above disclosed is only presently preferred embodiments of the present invention, can not limit the interest field of the present invention, therefore the equivalent variations made according to scope of the present invention patent with this certainly, still belongs to the scope that the present invention is covered.
Claims (4)
1. one kind of multiple bladed rotors tandem aircraft, it is characterised in that：It includes skeleton、The front shell being connected with skeleton、It is fixedly connected on the wing at skeleton rear、Support the lower carriage of the skeleton、The energy source device being arranged on the skeleton、The position controller being arranged on the skeleton、And external signal can be received and the central control unit of the energy source device and position controller can be controlled，The energy source device includes front power source、Power source afterwards、The pitman being connected with front power source、The little pitman being connected through in the pitman and with rear power source、The bow oar being arranged on pitman and the rear oar being arranged on little pitman，The position controller includes the bascule being fixed on the pitman、Two steering wheels、Connect the drive link of the steering wheel and bascule，Connect the connecting rod of the bow oar and bascule，The bascule includes the steering ball being fixed on the pitman、The break-in disk being socketed on the steering ball、Bascule frame、And connect the bearing of the bascule frame and break-in disk，The connecting rod is connected between the bow oar and break-in disk，The drive link is connected on the bascule frame，Spherical keeper is additionally provided with the bascule frame，One end of the drive link connection bascule frame is fastening structure，The fastening structure is enclosed within the spherical keeper.
2. various bladed rotors tandem aircraft as claimed in claim 1, it is characterised in that：One end of the drive link connection steering wheel is provided with screw thread, and the end is connected by a gear drive with steering wheel.
3. various bladed rotors tandem aircraft as claimed in claim 1, it is characterised in that：The bow oar includes two panels front vane, the front vane fixing device of fixed front vane, fixes L-type frame of the front vane fixing device on the pitman, the union joint being conformed with the front vane fixing device, connecting hole is provided with the L-type frame, described connecting rod one end is connected with break-in disk, the other end is connected through the connecting hole with union joint, the union joint is spherical, the break-in disk is provided with spherical connector, and the connecting rod is double end ball cover connecting rod and is respectively fitted on the union joint and spherical connector.
4. various bladed rotors tandem aircraft as claimed in claim 1, it is characterised in that：It also includes steadily of centre of gravity device, the rear oar includes two panels rear blade, the rear blade fixing device of fixed rear blade and fixes blade clamping connection mouth of the rear blade fixing device on the little pitman, the blade clamping connection mouth is provided with V-type interface, and the steadily of centre of gravity device is installed on the V-type interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510757487.2A CN106672228A (en) | 2015-11-07 | 2015-11-07 | Multi-blade rotor tandem type aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510757487.2A CN106672228A (en) | 2015-11-07 | 2015-11-07 | Multi-blade rotor tandem type aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106672228A true CN106672228A (en) | 2017-05-17 |
Family
ID=58863347
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510757487.2A Withdrawn CN106672228A (en) | 2015-11-07 | 2015-11-07 | Multi-blade rotor tandem type aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106672228A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107284656A (en) * | 2017-07-12 | 2017-10-24 | 重庆国飞通用航空设备制造有限公司 | Coaxial double-oar rotor mechanism in the same direction and its aircraft |
| CN107352024A (en) * | 2017-07-12 | 2017-11-17 | 重庆国飞通用航空设备制造有限公司 | The reverse rotor mechanism of coaxial double-oar and its aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1724192A1 (en) * | 2005-05-04 | 2006-11-22 | Mauro Achille Nostrini | Structure and control system of an aircraft equipped with rotors for lift and vertical flight, and with a pusher-propeller for horizontal thrust |
| CN204219777U (en) * | 2014-10-25 | 2015-03-25 | 马铿钧 | aerial toy |
| CN204233763U (en) * | 2014-10-25 | 2015-04-01 | 马铿钧 | Ultralight energy-conservation flight instruments |
| CN204337750U (en) * | 2014-10-25 | 2015-05-20 | 马铿钧 | High sensitivity aircraft |
-
2015
- 2015-11-07 CN CN201510757487.2A patent/CN106672228A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1724192A1 (en) * | 2005-05-04 | 2006-11-22 | Mauro Achille Nostrini | Structure and control system of an aircraft equipped with rotors for lift and vertical flight, and with a pusher-propeller for horizontal thrust |
| CN204219777U (en) * | 2014-10-25 | 2015-03-25 | 马铿钧 | aerial toy |
| CN204233763U (en) * | 2014-10-25 | 2015-04-01 | 马铿钧 | Ultralight energy-conservation flight instruments |
| CN204337750U (en) * | 2014-10-25 | 2015-05-20 | 马铿钧 | High sensitivity aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107284656A (en) * | 2017-07-12 | 2017-10-24 | 重庆国飞通用航空设备制造有限公司 | Coaxial double-oar rotor mechanism in the same direction and its aircraft |
| CN107352024A (en) * | 2017-07-12 | 2017-11-17 | 重庆国飞通用航空设备制造有限公司 | The reverse rotor mechanism of coaxial double-oar and its aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170517 |
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| DD01 | Delivery of document by public notice | ||
| DD01 | Delivery of document by public notice |
Addressee: Ma Kengjie Document name: Notification of Approving Refund |