CN201520409U - Backward-forward dual-rotor one-man aerobat - Google Patents
Backward-forward dual-rotor one-man aerobat Download PDFInfo
- Publication number
- CN201520409U CN201520409U CN2009202201476U CN200920220147U CN201520409U CN 201520409 U CN201520409 U CN 201520409U CN 2009202201476 U CN2009202201476 U CN 2009202201476U CN 200920220147 U CN200920220147 U CN 200920220147U CN 201520409 U CN201520409 U CN 201520409U
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- rotor
- main body
- control lever
- body rack
- aerobat
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Abstract
The utility model relates to a backward-forward dual-rotor one-man aerobat which belongs to the technical field of small-sized aerobat and comprises a power portion, a main body frame portion and a manipulation portion, wherein the power portion and the manipulation portion are hinged with the main body frame portion. An operator can stand on a foot rest and hold a manipulation rod by two hands hold to start up rotors and control the rotation speed through a throttle, the rotors produce lift force, when the aerobat goes up a certain height, the operator presses down the manipulation rod to lead the wind-blowing direction of the rotors to become lower-rear direction, and then the aerobat becomes to fly forwards, when landing, the wind direction of the rotors are changed to be vertically downward, and the rotation speed is decreased, thus the lading can be finished, when landing on the ground, a landing gear with elastic design can be used for damping impact. The Backward-forward dual-rotor one-man aerobat can be used for aerial photograph, flying sport, short-range traffic, entertainment and the like and has the advantages of reasonable design, simple structure, convenient use and the like.
Description
Technical field
The utility model relates to a kind of forward and backward double-rotor type single-person aircraft, belongs to small aircraft manufacturing technology field.
Background technology
Only dynamic gliding parachute of present existing miniaturization individual lift device and power delta-winged aircraft, powered paraglider need could take off smoothly by steep cliff or hillside, has application limit, delta-winged aircraft belongs to wing class aircraft, needing enough ground taxi speed and ground run distance just can take off, and landing the time also needs long smooth place, more than the two all belongs to the motion class aircraft, need or handle skilled airhog and could use by the sportsman who passes through specialized training, and the manipulation technology complexity, do not have practicality widely, multi-functional purposes.
The utility model content
The utility model is at the deficiencies in the prior art, and a kind of simple in structure, easy to use, forward and backward double-rotor type single-person aircraft with utility function is provided, and can be used for aerophotography, sporting flying, short distance traffic and amusement etc.
The purpose of this utility model is achieved through the following technical solutions:
A kind of forward and backward double-rotor type single-person aircraft, by power pack section, the main body rack partial sum is controlled part and is formed, power pack section and to control part all hinged with the main body rack part;
Power pack section comprises rotor, horizontal gird is controlled the hinged cover of sliding sleeve and support, and rotor is individually fixed in the horizontal gird two ends, control that sliding sleeve is placed on the horizontal gird and be connected with the connecting rod of controlling part, the hinged cover of support be placed in horizontal gird and be fixed in main body rack partly on;
Main body rack partly comprises H type support, stretcher, and base, alighting gear and damping spring, H type support lower end is connected with base and stretcher, is connected with alighting gear on the base, and is hinged and be provided with damping spring between alighting gear and the base;
Control part and comprise control lever cover, control lever, connecting rod, eccentric wheel, gauge panel, throttle grip and vertical tail, control lever cover are fixed in main body rack part middle part, control lever is through at control lever and puts, eccentric wheel is located at the control lever two ends, and connecting rod one end is connected in eccentric wheel, the other end with control sliding sleeve and be connected, throttle grip is located on the control lever, and vertical tail is located on the main body rack part.When the operator pulls control lever up or down, the eccentric wheel that is fixed in the control lever both sides rotates thereupon, drive fixedly by connecting rod that rotor and horizontal gird are the center swing with the hinged cover of support, thus the blowing direction of change rotor, with the heading of controlling aircraft.
Described rotor is by oil engined fan power mechanism, horizontal gird two ends configurations gyroplane rotate speed identical, hand of rotation is opposite, about the V-shaped symmetric configuration in center of two rotor axle center and main body rack part, can be in the control down conversion of the control lever direction of blowing downwards and backward.
Described eccentric wheel is the parts that connecting rod changes horizontal gird and rotor wind direction that pass through that are connected in control lever, and the eccentric wheel structure that is connected in the control lever both sides is symmetrical fully, and eccentricity values is identical.
Described alighting gear is the buffer unit of being located on the base of main body rack bottom that rises and falls, and three are landed the strong point from the outside equidistant extension of aircraft center of gravity, and be connected with damping spring between base and alighting gear.
One of feature of the present utility model, this utility model is a kind of individual lift device of vertical takeoff and landing, its power pack section is the left and right sides that two opposite rotors of hand of rotation are symmetricly set in the aircraft top, to offset the deflecting torque of rotor, the V-shaped arrangement of the rotor shaft of both sides, downwards or the air-flow that rearward blows out through intersecting behind the certain distance for a bit, with the stability of increase aircraft.
Two of feature of the present utility model, this utility model are to realize taking off vertically or flying forward with the angle of controlling rotor and aircraft body bracket component.
When the utility model used, the chaufeur standing position stood on the stretcher, and both hands are held control lever, start rotor and by the Throttle Opening Control rotating speed, rotor produces lift, treat that aircraft rises to certain altitude after, press down control lever, make the rotor blowing direction become rear down, aircraft changes flight forward into, during landing, change the rotor wind direction for vertically downward, rev down can be finished landing, when landing, the alighting gear available buffer of Flexible Design.The utlity model has advantages such as reasonable in design, simple in structure, easy to use.
Description of drawings
Accompanying drawing is a structural representation of the present utility model.
Wherein: 1, power pack section, 1-1, rotor, 1-2, horizontal gird, are controlled sliding sleeve, 1-4, the hinged cover of support at 1-3; 2, main body rack part, 2-1, H type support, 2-2, stretcher, 2-3, base, 2-4, alighting gear, 2-5, damping spring; 3, control part, 3-1, control lever cover, 3-2, control lever, 3-3, connecting rod, 3-4, eccentric wheel, 3-5, gauge panel, 3-6, throttle grip, 3-7, vertical tail.
The specific embodiment
Embodiment: structure as shown in drawings, it comprises power pack section 1, main body rack part 2 and control part 3, power pack section 1 is with to control part 3 all hinged with main body rack part 2.
Main body rack part 2 comprises H type support 2-1, stretcher 2-2, base 2-3, alighting gear 2-4 and damping spring 2-5, H type support 2-1 lower end is connected with base 2-3 and stretcher 2-2, is connected with alighting gear 2-4 on the base 2-3, and is hinged and be provided with damping spring 2-5 between alighting gear 2-4 and the base 2-3;
Described rotor 1-1 is by oil engined fan power mechanism, horizontal gird 1-2 two ends configurations rotor 1-1 rotating speed identical, hand of rotation is opposite, about the axle center of two rotor 1-1 and the V-shaped symmetric configuration in center of main body rack part 2, can be in the control down conversion of the control lever 3-2 direction of blowing downwards and backward.
Described eccentric wheel 3-4 is the parts that connecting rod 3-3 changes horizontal gird 1-2 and rotor 1-1 wind direction that pass through that are connected in control lever 3-2, and the eccentric wheel 3-4 structure that is connected in control lever 3-2 both sides is symmetrical fully, and eccentricity values is identical.
Described alighting gear 2-4 is the buffer unit of being located on the main body rack part 2 bottom base 2-3 that rises and falls, and three are landed the strong point from the outside equidistant extension of aircraft center of gravity, and be connected with damping spring 2-5 between base 2-3 and alighting gear 2-4.
During use, the chaufeur standing position stands on the stretcher 2-2, and both hands are held control lever 3-2, start rotor 1-1 and by throttle grip 3-6 control rotating speed, rotor 1-1 produces lift, treat that aircraft rises to certain altitude after, press down control lever 3-2, make rotor 1-1 blowing direction become rear down, aircraft changes flight forward into, during landing, change rotor 1-1 wind direction for vertically downward, rev down can be finished landing, when landing, the alighting gear 2-4 available buffer of Flexible Design.The utlity model has advantages such as reasonable in design, simple in structure, easy to use.
Claims (4)
1. a forward and backward double-rotor type single-person aircraft is characterized in that, by power pack section, the main body rack partial sum is controlled part and formed, power pack section and to control part all hinged with the main body rack part;
Described power pack section comprises rotor, horizontal gird is controlled the hinged cover of sliding sleeve and support, and rotor is individually fixed in the horizontal gird two ends, control that sliding sleeve is placed on the horizontal gird and be connected with the connecting rod of controlling part, the hinged cover of support be placed in horizontal gird and be fixed in main body rack partly on;
Described main body rack partly comprises H type support, stretcher, and base, alighting gear and damping spring, H type support lower end is connected with base and stretcher, is connected with alighting gear on the base, and is hinged and be provided with damping spring between alighting gear and the base;
The described part of controlling comprises control lever cover, control lever, connecting rod, eccentric wheel, gauge panel, throttle grip and vertical tail, control lever cover are fixed in main body rack part middle part, control lever is through at control lever and puts, eccentric wheel is located at the control lever two ends, and connecting rod one end is connected in eccentric wheel, the other end with control sliding sleeve and be connected, throttle grip is located on the control lever, and vertical tail is located on the main body rack part.
2. a kind of forward and backward double-rotor type single-person aircraft according to claim 1, it is characterized in that, described rotor is by oil engined fan power mechanism, horizontal gird two ends configurations gyroplane rotate speed identical, hand of rotation is opposite, about the V-shaped symmetric configuration in center of two rotor axle center and main body rack part.
3. a kind of forward and backward double-rotor type single-person aircraft according to claim 1, it is characterized in that, described eccentric wheel is the parts that connecting rod changes horizontal gird and rotor wind direction that pass through that are connected in control lever, and the eccentric wheel structure that is connected in the control lever both sides is symmetrical fully, and eccentricity values is identical.
4. a kind of forward and backward double-rotor type single-person aircraft according to claim 1 is characterized in that, described alighting gear is the buffer unit of being located on the base of main body rack bottom that rises and falls, and three are landed the strong point from the outside equidistant extension of aircraft center of gravity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202201476U CN201520409U (en) | 2009-10-26 | 2009-10-26 | Backward-forward dual-rotor one-man aerobat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202201476U CN201520409U (en) | 2009-10-26 | 2009-10-26 | Backward-forward dual-rotor one-man aerobat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201520409U true CN201520409U (en) | 2010-07-07 |
Family
ID=42506588
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202201476U Expired - Fee Related CN201520409U (en) | 2009-10-26 | 2009-10-26 | Backward-forward dual-rotor one-man aerobat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201520409U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102806994A (en) * | 2011-05-31 | 2012-12-05 | 王略 | Ultra-light single-person deceleration tilting type coaxial helicopter |
| CN103224024A (en) * | 2013-05-17 | 2013-07-31 | 谷承露 | Double-main-duct ultra-light type vertical take-off and landing solo aircraft |
-
2009
- 2009-10-26 CN CN2009202201476U patent/CN201520409U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102806994A (en) * | 2011-05-31 | 2012-12-05 | 王略 | Ultra-light single-person deceleration tilting type coaxial helicopter |
| CN103224024A (en) * | 2013-05-17 | 2013-07-31 | 谷承露 | Double-main-duct ultra-light type vertical take-off and landing solo aircraft |
| CN103224024B (en) * | 2013-05-17 | 2015-12-02 | 谷承露 | Two main duct microlight-type vertical takeoff and landing individual lift device |
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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: 20100707 Termination date: 20101026 |