CN202054142U - Umbrella-shaped foldable aircraft with multiple rotors - Google Patents
Umbrella-shaped foldable aircraft with multiple rotors Download PDFInfo
- Publication number
- CN202054142U CN202054142U CN2011201208723U CN201120120872U CN202054142U CN 202054142 U CN202054142 U CN 202054142U CN 2011201208723 U CN2011201208723 U CN 2011201208723U CN 201120120872 U CN201120120872 U CN 201120120872U CN 202054142 U CN202054142 U CN 202054142U
- Authority
- CN
- China
- Prior art keywords
- arm
- cylindrical body
- fastener
- hold
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Abstract
An umbrella-shaped foldable aircraft with multiple rotors belongs to the technical field of the design of aircrafts, and is characterized by comprising a cylindrical aircraft body (5), N supporting systems and a fastener (8). The N supporting systems are uniformly distributed on the periphery of the cylindrical aircraft body (5), the fastener (8) is located at the lower end of the cylindrical aircraft body (5), each supporting system consists of a main arm (6) and a supporting arm (7), wherein one end of the main arm (6) is hinged at the upper end of the cylindrical aircraft body (5), a rotor device (11) is mounted at the other end of the main arm (6), the upper end of the supporting arm (7) is hinged in the middle of the main arm (6), and the lower end of the supporting arm (7) is hinged onto the fastener (8). The aircraft can guarantee that the total aircraft body has sufficiently high strength and rigidity during usage, furthermore, the total aircraft can be folded when in need, the volume of the aircraft is greatly reduced, and the aircraft can be stored and carried conveniently.
Description
Affiliated technical field
The utility model relates to a kind of folding multi-rotor aerocraft, belongs to the Flight Vehicle Design technical field.
Background technology
At present, known multi-rotor aerocraft depends on fuselage by lift system, power system and control system and constitutes.It provides power by battery or fuel oil to a plurality of rotor devices that are circle distribution, handles rotor by control system Remote or autonomous navigation and realizes vertical takeoff and landing and maneuvering flight.The multi-rotor aerocraft fuselage often is a rigid unitary, is truncated cone-shaped, and volume is bigger, deposits and carry inconvenience.
Summary of the invention
Big in order to overcome existing multi-rotor aerocraft volume, deposit and carry inconvenient deficiency, the utility model provides a kind of umbrella shape collapsible multi-rotor aerocraft, this aircraft can not only guarantee that fuselage integral body in use has sufficiently high intensity and rigidity, and can be when needed with the fuselage foldable integral, reduce volume greatly, be convenient to deposit and carry.
The utility model is characterised in that: comprise cylindrical body, be uniformly distributed in the fastener that cylindrical body N all around organizes support system, is positioned at cylindrical body lower end; Wherein every group of support system formed by a principal arm and a hold-down arm, wherein an end of principal arm is articulated in cylindrical body upper end, the other end of principal arm is equipped with the rotor device, and the upper end of hold-down arm is articulated in the centre of principal arm, and the lower end of hold-down arm is articulated on the fastener.The N value can be got the natural number more than or equal to 2, as 2,3,4,5,6,7,8 etc., generally gets 4.
The utility model has used the slider-crank mechanism principle.If the cylindrical body of hypothesis is vertically fixing, then N the principal arm that the rotor device is installed can rotate at perpendicular, and green phase pivotally attached hold-down arm drives fastener and slides up and down.During use, N principal arm opened simultaneously, and be vertical with cylindrical body, and fastener is buckled on the cylindrical body, and integral body is the umbrella shape layout.Use and finish, drop-down fastener makes it separate with cylindrical body, drives hold-down arm and principal arm and rotates, and draws in around body, and similar cylindrical, volume is small and exquisite, and is easy to carry.
On the above-mentioned cylindrical body inhibiting device that cooperates with fastener is installed also, this inhibiting device effect is that the restriction fastener moves up and down when principal arm is expanded to cylindrical body axis upright position fully, prevent that principal arm from rotating, thereby guarantee that fuselage integral body has sufficiently high rigidity.
The lower end of above-mentioned hold-down arm is equipped with strut bar, and after the collapsible multi-rotor aerocraft of this umbrella shape launched, N strut bar constituted its alighting gear, can play the effect of ground supports.
The collapsible rotor craft of above-mentioned umbrella shape is characterized in that: above-mentioned hold-down arm and bracing frame are integral type, guarantee that hold-down arm and bracing frame possess sufficiently high intensity and rigidity, and simplified structure.
The utility model has used the slider-crank mechanism principle.If the cylindrical body of hypothesis is vertically fixing, then N the principal arm that the rotor device is installed can rotate at perpendicular, and green phase pivotally attached hold-down arm drives fastener and slides up and down.During use, N principal arm opened simultaneously, and be vertical with cylindrical body, and fastener is buckled on the cylindrical body, and integral body is the umbrella shape layout.Use and finish, drop-down fastener makes it separate with cylindrical body, drives hold-down arm and principal arm and rotates, and draws in around the cylindrical body axis, and volume is small and exquisite, and is easy to carry.
Description of drawings
Fig. 1 is a fundamental diagram of the present utility model;
Fig. 2 is the collapsible multi-rotor aerocraft deployed condition of a umbrella shape plane diagram;
Fig. 3 is the expansion birds-eye view (is example with four rotors) of not drive device;
Fig. 4 is the collapsible multi-rotor aerocraft folded state of a umbrella shape plane diagram;
Number in the figure title: 1, guide rod, 2, crank, 3, connecting rod, 4, slide block; 5, cylindrical body, 6, be principal arm, 7, hold-down arm, 8, fastener, 9, inhibiting device, 10, bracing frame, 11, the rotor device, 12, equipment cover.
The specific embodiment
In Fig. 1, guide rod 1 is fixing, and crank 2 is hinged with guide rod 1 upper end, and connecting rod 3 is hinged with crank 2 middle parts, slide block 4 respectively, and slide block 4 can slide along guide rod 1.When crank 2 clockwise direction level attitudes rotated, slide block upwards slided; Otherwise then slide block then moves downward.
In example shown in Figure 2, cylindrical body 5 is vertically fixing, its upper end erecting equipment cover 12, rotor device 11 is installed on the principal arm 6, and principal arm 6 is in the position with cylindrical body 5 axis normal, principal arm 6 middle parts and hold-down arm 7 upper ends are hinged, hold-down arm 7 lower ends and fastener 8 are hinged, and fastener 8 is buckled in cylindrical body lower end, are moved up and down by the inhibiting device 9 restriction fasteners 8 that are installed on the cylindrical body 5, bracing frame 10 is an integral type with hold-down arm often, plays the ground supports effect.
Birds-eye view (is example with four rotors) after the whole expansion of fuselage as shown in Figure 3.
In example shown in Figure 4, open inhibiting device 9, drop-down fastener 8 makes it separate with cylindrical body 5, drives hold-down arm 7, bracing frame 10 and principal arm 6 and rotates, and draws in around cylindrical body 5.
Claims (4)
1. the collapsible rotor craft of umbrella shape is characterized in that: comprise cylindrical body (5), be uniformly distributed in the fastener (8) that cylindrical body (5) N all around organizes support system, is positioned at cylindrical body (5) lower end; Wherein every group of support system formed by a principal arm (6) and a hold-down arm (7), wherein an end of principal arm (6) is articulated in cylindrical body (5) upper end, the other end of principal arm (6) is equipped with rotor device (11), the upper end of hold-down arm (7) is articulated in the middle part of principal arm (6), and the lower end of hold-down arm (7) is articulated on the fastener (8); Above-mentioned N is the natural number more than or equal to 2.
2. the collapsible rotor craft of umbrella shape according to claim 1, it is characterized in that: the inhibiting device (9) that cooperates with fastener (8) also is installed on the above-mentioned cylindrical body, this inhibiting device (9) effect is that restriction fastener (8) moves up and down when principal arm (6) is expanded to cylindrical body (5) axis normal position fully, prevents that hold-down arm (7) and principal arm (6) from rotating.
3. the collapsible rotor craft of umbrella shape according to claim 1 is characterized in that: the lower end of above-mentioned hold-down arm (7) is equipped with bracing frame (10), and after the collapsible multi-rotor aerocraft of this umbrella shape launched, N bracing frame (10) constituted its alighting gear.
4. the collapsible rotor craft of umbrella shape according to claim 3 is characterized in that: above-mentioned hold-down arm (7) and bracing frame (10) are integral type.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201208723U CN202054142U (en) | 2011-04-22 | 2011-04-22 | Umbrella-shaped foldable aircraft with multiple rotors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201208723U CN202054142U (en) | 2011-04-22 | 2011-04-22 | Umbrella-shaped foldable aircraft with multiple rotors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202054142U true CN202054142U (en) | 2011-11-30 |
Family
ID=45014124
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201208723U Expired - Fee Related CN202054142U (en) | 2011-04-22 | 2011-04-22 | Umbrella-shaped foldable aircraft with multiple rotors |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202054142U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102180267A (en) * | 2011-04-22 | 2011-09-14 | 南京航空航天大学 | Umbrella-shaped foldable multi-rotor aircraft |
| CN105857571A (en) * | 2016-04-08 | 2016-08-17 | 北京博瑞爱飞科技发展有限公司 | Unmanned aerial vehicle with multi-vehicle-arm synchronous folding mechanism |
| CN109204800A (en) * | 2018-10-19 | 2019-01-15 | 中卫航空科技发展有限公司 | A kind of foldable quadrotor individual soldier unmanned plane |
| WO2020122433A1 (en) * | 2018-12-11 | 2020-06-18 | 전남도립대학교산학협력단 | Drone provided with foldable rotary wing |
-
2011
- 2011-04-22 CN CN2011201208723U patent/CN202054142U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102180267A (en) * | 2011-04-22 | 2011-09-14 | 南京航空航天大学 | Umbrella-shaped foldable multi-rotor aircraft |
| CN105857571A (en) * | 2016-04-08 | 2016-08-17 | 北京博瑞爱飞科技发展有限公司 | Unmanned aerial vehicle with multi-vehicle-arm synchronous folding mechanism |
| WO2017173732A1 (en) * | 2016-04-08 | 2017-10-12 | 高鹏 | Unmanned aerial vehicle (uav) with multi-arm synchronous folding mechanism |
| CN109204800A (en) * | 2018-10-19 | 2019-01-15 | 中卫航空科技发展有限公司 | A kind of foldable quadrotor individual soldier unmanned plane |
| CN109204800B (en) * | 2018-10-19 | 2021-08-10 | 杭州木书科技有限公司 | Foldable four-rotor individual-soldier unmanned aerial vehicle |
| WO2020122433A1 (en) * | 2018-12-11 | 2020-06-18 | 전남도립대학교산학협력단 | Drone provided with foldable rotary wing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102180267A (en) | Umbrella-shaped foldable multi-rotor aircraft | |
| US10414483B2 (en) | Tiltrotor articulated wing extension | |
| CN110049919A (en) | The air-launched of unmanned vehicle and/or recycling and relevant system and method | |
| CN202054142U (en) | Umbrella-shaped foldable aircraft with multiple rotors | |
| RU2648303C2 (en) | Rotable inclined wing end | |
| CN205131625U (en) | Small -size portable all -wing aircraft overall arrangement unmanned aerial vehicle | |
| CN108820229B (en) | Hybrid unmanned aerial vehicle based on computer state control | |
| CN104290906A (en) | Vertical take-off and landing aircraft | |
| CN106347626A (en) | Foldable multi-rotor plant protection unmanned aerial vehicle | |
| CN108860579A (en) | A kind of contractile shock-absorbing type unmanned plane undercarriage | |
| CN205131674U (en) | Small -size all -wing aircraft overall arrangement unmanned aerial vehicle | |
| CN101850852A (en) | SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite | |
| CN107364577B (en) | Solar vertical take-off and landing reconnaissance patrol aircraft | |
| US10329006B2 (en) | Aircraft external viewing system, apparatus, and method | |
| CN208085991U (en) | Folded unmanned plane | |
| CN102424111A (en) | Flexible saucer-shaped aircraft | |
| WO2017215462A1 (en) | Reusable air-launched carrier rocket having no landing leg | |
| WO2020201644A2 (en) | Apparatus for aerial navigation and devices thereof | |
| CN210310861U (en) | Automatic expansion undercarriage | |
| RU69837U1 (en) | BOUNTING FOLDING FAT | |
| RU53649U1 (en) | UNMANNED AERIAL VEHICLE | |
| CN107380425A (en) | A kind of go straight up to puts down winged energy-saving safe aircraft | |
| CN208630869U (en) | The fixed-wing unmanned plane of power plant module | |
| CN113184164A (en) | Folding wing type airplane | |
| CN208963311U (en) | A kind of tail pushes away rotor mixed layout unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111130 Termination date: 20140422 |