CN201737157U - Mini-type aircraft with two parallel rotary wings - Google Patents
Mini-type aircraft with two parallel rotary wings Download PDFInfo
- Publication number
- CN201737157U CN201737157U CN2010202687951U CN201020268795U CN201737157U CN 201737157 U CN201737157 U CN 201737157U CN 2010202687951 U CN2010202687951 U CN 2010202687951U CN 201020268795 U CN201020268795 U CN 201020268795U CN 201737157 U CN201737157 U CN 201737157U
- Authority
- CN
- China
- Prior art keywords
- rocker arm
- half shafts
- semiaxis
- aircraft
- hinged
- 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
Landscapes
- Toys (AREA)
Abstract
A mini-type aircraft with two parallel rotary wings comprises a center bearing fixed on an aircraft body, wherein two torsion half shafts are respectively mounted on both sides of the center bearing, power racks are connected to the tail ends of the torsion half shafts, and screw propellers and power units are mounted on the power racks. Rocker arm devices are respectively mounted on the two torsion half shafts, the two rocker arm devices are mounted in an axial symmetrical manner or a centrosymmetric manner, each rocker arm device comprises a rudder spindle arm, a tie rod and an executive steering engine, wherein one ends of the rudder spindle arms are fixedly mounted on the torsion half shafts, and the other ends of the rudder spindle arms are hinged with the tie rods, the tie rods are hinged on the rocker arm discs driven by the executive steering engines, the rocker arm discs play the role of the rocker arms, and the torsion half shafts are driven by the rocker arm discs to rotate axially, so as to realize that the flying attitude and actions of the two rotary wings in the air can be adjusted. The aircraft with two parallel rotary wings that lift vertically and fly horizontally has simple mechanical structure and low failure rate, and has the characteristics of both a helicopter and an airplane with fixed wings.
Description
Technical field
The utility model relates to and a kind ofly can be applicable to aerial reconnaissance and take, and speedily carries out rescue work and aircraft that the safety inspection of skyscraper is used, also can be used as model plane, toy uses.
Background technology
Have only series type (front and back) cyclogyro at present on the market, its keystone configuration is all identical with helicopter structure, its long-pending tool complex structure.
The utility model content
Based on the problems referred to above, I have designed a kind of bispin wing small aircraft arranged side by side.
The purpose of this utility model is achieved through the following technical solutions:
A kind of bispin wing small aircraft arranged side by side comprises the center bearing pilot bearing that is fixed on the aircraft body, and the both sides of center bearing pilot bearing are installed one respectively and reversed semiaxis, and the described end that reverses semiaxis connects power rack, and screw propeller and engine installation are installed on the power rack; Described two are reversed a rocker arrangement are installed respectively on the semiaxis, two rocker arrangements axisymmetricly or the center symmetry install, described rocker arrangement comprises rudderpost arm, ball-head tension rod, execution steering wheel, one end of rudderpost arm is fixedly mounted on and reverses on the semiaxis, the other end and ball-head tension rod are hinged, ball-head tension rod is hinged on the rocking arm dish of carrying out the steering wheel driving, described rocking arm is folded the effect of rocking arm, reverse semiaxis by the driving drive of rocking arm dish and do axial rotation, realize that the bispin wing carries out aerial flight attitude and action.
This patent be the bispin wing arranged side by side (about) the peaceful aircraft that flies of vertical takeoff and landing, its physical construction is simple, and fault rate is low, and the characteristics with helicopter also have the flight characteristic of fixed wing aircraft, finish automatic navigation in conjunction with the GPS position fixing system, can pass video data back ground in real time.State of flight is by computer controlled.
Description of drawings
With embodiment the utility model is described in further detail with reference to the accompanying drawings below.
Fig. 1 is the stravismus constructional drawing of bispin wing small aircraft arranged side by side;
Fig. 2 is the constructional drawing of facing of bispin wing small aircraft arranged side by side.
Because half side screw propeller has been omitted in pagewidth restriction among Fig. 1, clearer in order to make structure representation, all omitted the agent structure of bispin wing small aircraft arranged side by side among two figure.
The specific embodiment
Shown in Fig. 1-2, bispin wing small aircraft comprises the center bearing pilot bearing 1 that is fixed on the aircraft body side by side, and the both sides of center bearing pilot bearing 1 are installed one respectively and reversed semiaxis 2, the described end that reverses semiaxis 2 is used to connect power rack 3, and screw propeller 4 and engine installation 5 are installed on the power rack 3; Described two are reversed a rocker arrangement are installed respectively on the semiaxis 2, two rocker arrangements axisymmetricly or the center symmetry install, described rocker arrangement comprises rudderpost arm 6, ball-head tension rod 7, carries out steering wheel 8, one end of rudderpost arm 6 is fixedly mounted on and reverses on the semiaxis 2, the other end and ball-head tension rod 7 are hinged, ball-head tension rod 7 is hinged on the rocking arm dish 9 of carrying out steering wheel 8 drivings, described rocking arm dish 9 plays the effect of rocking arm, reverse semiaxis 2 by the driving drive of rocking arm dish 9 and do axial rotation, realize aerial flight attitude and the action of bispin rotor aircraft adjustment.
This patent be the bispin wing arranged side by side (about) the peaceful aircraft that flies of vertical takeoff and landing, its physical construction is simple, and fault rate is low, and the characteristics with helicopter also have the flight characteristic of fixed wing aircraft, finish automatic navigation in conjunction with the GPS position fixing system, video data can be gone here and there go back to ground in real time.State of flight is by computer controlled.
Person skilled in the art should be familiar with, the above embodiment is used for illustrating the purpose of this utility model, and be not with opposing qualification of the present utility model, as long as in essential scope of the present utility model, variation, modification (for example the type of drive with each several part changes gear transmission, belt-driving, odontoid belt transmission etc. into) that the foregoing description is done all will drop in the claim scope of the present utility model.
Claims (3)
1. bispin wing small aircraft arranged side by side, comprise the center bearing pilot bearing that is fixed on the aircraft body, it is characterized in that the both sides of center bearing pilot bearing are installed one respectively and reversed semiaxis, the described end that reverses semiaxis connects power rack, and screw propeller and engine installation are installed on the power rack; Described two are reversed a rocker arrangement are installed respectively on the semiaxis.
2. a kind of bispin wing small aircraft arranged side by side according to claim 1, it is characterized in that, described rocker arrangement comprises rudderpost arm, ball-head tension rod, execution steering wheel, one end of rudderpost arm is fixedly mounted on and reverses on the semiaxis, the other end and ball-head tension rod are hinged, and ball-head tension rod is hinged on the rocking arm dish of carrying out the steering wheel driving.
3. a kind of bispin wing small aircraft arranged side by side according to claim 2 is characterized in that, two rocker arrangements axisymmetricly or the center symmetry install.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202687951U CN201737157U (en) | 2010-07-23 | 2010-07-23 | Mini-type aircraft with two parallel rotary wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202687951U CN201737157U (en) | 2010-07-23 | 2010-07-23 | Mini-type aircraft with two parallel rotary wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201737157U true CN201737157U (en) | 2011-02-09 |
Family
ID=43552440
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010202687951U Expired - Fee Related CN201737157U (en) | 2010-07-23 | 2010-07-23 | Mini-type aircraft with two parallel rotary wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201737157U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314761A (en) * | 2016-08-31 | 2017-01-11 | 北京航空航天大学 | All-moving wing mechanism applied to small compound helicopter |
| USRE48205E1 (en) | 2013-07-17 | 2020-09-15 | Lg Electronics Inc. | Laundry treating apparatus |
-
2010
- 2010-07-23 CN CN2010202687951U patent/CN201737157U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| USRE48205E1 (en) | 2013-07-17 | 2020-09-15 | Lg Electronics Inc. | Laundry treating apparatus |
| CN106314761A (en) * | 2016-08-31 | 2017-01-11 | 北京航空航天大学 | All-moving wing mechanism applied to small compound helicopter |
| CN106314761B (en) * | 2016-08-31 | 2018-11-23 | 北京航空航天大学 | A kind of all-moving wing mechanism applied to small compound helicopter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103612755B (en) | A kind of binodal main wing Bionic ornithopter | |
| CN200995782Y (en) | Airplane | |
| CN110341951B (en) | Unmanned aerial vehicle with foldable wings and tilting rotor wings | |
| CN205707297U (en) | Fixed-wing unmanned plane | |
| CN102582832B (en) | Flapping-wing aircraft | |
| CN202071985U (en) | Novel plane symmetrical layout type multi-rotor unmanned air vehicle | |
| CN202754143U (en) | Rotating engine vertical take-off and landing aircraft | |
| CN100391790C (en) | Multi-rotor aerocraft | |
| CN200951831Y (en) | Multi-rotor wing craft | |
| CN103359283A (en) | High-reliability unmanned aerial vehicle with tilt rotors | |
| CN101575004A (en) | Flight-mode-variable unmanned aircraft with multiple sets of coaxial rotors | |
| CN104816824A (en) | Fixed structure type vertical takeoff and landing aircraft based on dual-flight control system and control method for fixed structure type vertical takeoff and landing aircraft | |
| CN105691606B (en) | A kind of the unmanned plane device and control method in high cruise duration | |
| CN103144769A (en) | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct | |
| CN109398751B (en) | Method for detecting whether unmanned aerial vehicle wing with tilting mechanism loosens or not | |
| CN105329443B (en) | One kind flutter twisted coupling motion flapping wing aircraft | |
| CN102963526A (en) | Cycloidal propeller aerial vehicle | |
| CN203558206U (en) | Bionic flapping-wing aircraft with double sections of main wings | |
| CN110857145A (en) | Apparatus and method for improved stall/over-stall condition fixed wing aircraft pitch control | |
| CN205060006U (en) | Four -rotor unmanned aerial vehicle | |
| CN105173076B (en) | A kind of vertical take-off and landing drone | |
| CN103721421A (en) | Aircraft with a plurality of rotors | |
| CN205554578U (en) | High time of endurance's unmanned aerial vehicle device | |
| CN108423173A (en) | One kind plunderring dynamic formula flapping wing aircraft device | |
| CN201737157U (en) | Mini-type aircraft with two parallel rotary wings |
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: 20110209 Termination date: 20120723 |