CN2736257Y - Composite coaxial double-oar culvert channel fan sole flight - Google Patents
Composite coaxial double-oar culvert channel fan sole flight Download PDFInfo
- Publication number
- CN2736257Y CN2736257Y CN 200420063676 CN200420063676U CN2736257Y CN 2736257 Y CN2736257 Y CN 2736257Y CN 200420063676 CN200420063676 CN 200420063676 CN 200420063676 U CN200420063676 U CN 200420063676U CN 2736257 Y CN2736257 Y CN 2736257Y
- Authority
- CN
- China
- Prior art keywords
- aircraft
- oar
- culvert channel
- wing
- shrouded propeller
- 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
The utility model discloses a composite coaxial sole aircraft with double oars, a culvert channel and a fan. Both sides of a machine body is provided with a front wing and a back wing which are distributed forward and backward in parallel, and the front end position of the machine body is provided with an electronic instrument cover. The position of the machine body above the front wing is provided with a driving room which is provided with a joy stick which is connected with an operating mechanism, the back portion of the driving room is assembled with the flying transmission connection device of the culvert channel of the aircraft, and the propeller shaft of the culvert channel is arranged on the flying transmission connection device. An upper propeller blade and a lower propeller blade are respectively and fixedly arranged on the propeller shaft of the culvert channel, and the back wing which is connected with the machine body is provided with a guide vane. The tail portion of the machine body is provided with the oar shaft of the tail oar of the thrust force culvert channel which is matched with the propeller blade of the thrust force culvert channel. The composite coaxial sole aircraft with double oars, a culvert channel and a fan has main purposes of photography in the sky, advertisement propaganda, communication relay, pursuing and capturing escaped criminals, traffic guidance, antiterrorism battle, scouting enemy situations, etc.
Description
Affiliated technical field
The utility model relates to a kind of single airflight vehicle, especially can vertical takeoff and landing, and the vehicle that can aloft fly.
Background technology
At present, known early stage individual lift device subject matter is under power, and Power train is undesirable, and sensor and automatic control technology are immature at that time.Modern ordinary fixed wing individual lift device takes off to land and needs special-purpose airfield runway, needs higher speed and could produce enough lift, causes the generation when taking off landing of about 50% left and right sides aircraft accident, and park occupied ground on ground very big.Modern common rotor individual lift device great majority adopt single rotor magnetic tape trailer paddle structure of helicopter.The rotor of high speed revolution is fatal threats to the personnel of disembarking.The blade of high speed revolution also is easy to run into object and produces aircraft accident; Air resistance and induced drag cause flying speed lower more greatly.
Summary of the invention
The technical problems to be solved in the utility model is: overcoming weak point in the above-mentioned technology provides a kind of compound coaxial pair of oar duct fan individual lift device that all can be used as the vehicle in land, sea and air.
The technical scheme that its technical matters that solves the utility model adopts is: the front wing and the rear wing of parallel distribution before and after body both sides are equipped with, front end position at body is equipped with the electronic machine cover, front wing top body area is provided with cockpit, joystick is installed in it and is connected with steering unit, the rear portion of cockpit is equipped with aircraft duct flight transmission joint, shrouded propeller axle and following shrouded propeller axle are installed on it, be fixed with screw blade and following screw blade on last shrouded propeller axle and the following shrouded propeller axle respectively, on the body bonded assembly rear wing breather vane that aircraft turns to usefulness is installed, at the afterbody of body thrust ducted tail rotor oar axle is installed and matches with thrust shrouded propeller blade.
The beneficial effects of the utility model are:
1, anywhere vertical takeoff and landing, hover, spiral, noise in flight is very low, disguised very good;
2, it has fast, the mobility strong of speed, can do various aerobatics;
3, flight efficiency height, and fuel saving, so easy maintenance is economical and practical;
4, comformability is strong; Adapt to the city, country, factory, seashore, naval vessels, grassland, high mountain, the vertical takeoff and landing flight that express highway etc. are local;
5, safe and reliable, the design of duct umbrella, safety to aircraft flight and aviator benefits, if it is high aerial just in case break down, the rotation of duct umbrella with aircraft and occupant safety send ground back to, during low-latitude flying, break down and can adopt zero catapult technique that aircraft is served certain altitude, by the duct umbrella with aircraft and occupant safety send ground back to;
6, be the vehicle that save time most and increase work efficiency, and take advantage of a commercial air flights to compare not to be subjected to the flight time limitation, do not have the time of waiting, transferring to the vehicle.
7, various vertical takeoff and landing duct umbrella oar close coupled types series aircraft will become the most attractive a kind of sports item, a kind of convenience that everybody likes and cheap aircraft;
8, wide application: can take photo in the sky on civilian, advertising, communication repeating, the oil pipeline supervision, the monitoring of fire flood situation pursues and captures an escaped prisoner guiding of traffic etc.; The advantage that has other vehicle to hardly match equally militarily, fight-terrorism warfare, military situation is scouted, antisubmarine clearance, the strike of all types of target, attacks armed helicopter and low-to-medium altitude cruise missile etc.The present invention is a kind of rational in infrastructure, design ingenious, function admirable, convenient and practical individual lift device.
Description of drawings:
Fig. 1 is the utility model structural representation;
Fig. 2 is that the A of Fig. 1 is to scheme drawing;
Fig. 3 is the cutaway view of Figure 1A-A;
Fig. 4 is the back view of Fig. 1.
The specific embodiment
Be described in further details this use is novel below in conjunction with accompanying drawing and example.
By Fig. 1-Fig. 4 as can be known the utility model be: the front wing 2 and the rear wing 3 of parallel distribution before and after body 1 both sides are equipped with, front end position at body 1 is equipped with electronic machine cover 4, front wing 2 top bodies 1 position is provided with cockpit 6, joystick 14 is installed in it and is connected with steering unit, the rear portion of cockpit 6 is equipped with aircraft duct flight transmission joint 10, shrouded propeller axle 8 and following shrouded propeller axle 15 are installed on it, be fixed with screw blade 9 and following screw blade 11 on last shrouded propeller axle 8 and the following shrouded propeller axle 15 respectively, on the body 1 bonded assembly rear wing 3 breather vane 7 that aircraft turns to usefulness is installed, at the afterbody of body 1 thrust ducted tail rotor oar axle 12 is installed and matches with thrust shrouded propeller blade 13.
Position, body 1 front-end electronics cover, 4 both sides is separately installed with illuminating lamp 5.
As shown in Figure 1; the parallel front wing 2 and rear wing 3 that aircraft is installed in the both sides of body 1; the flight breather vane 7 that keeps the aircraft flight balance and be used for turning to is installed on the rear wing 3; breather vane 7 is awing by replacing swinging up and down of property or synchronism; be that flight waited action about aircraft carried out can aloft fly the time; on body 1 top electronic machine cover 4 is installed; electronic control package is installed in it; he is effective protection barrier of the crucial electronic machine of aircraft; the front portion of body 1 is a cockpit 6 above front wing 2; body 1 is by being equipped with shrouded propeller oar axle 8 and last shrouded propeller blade 9 on the position, back; drive by last shrouded propeller oar axle 8 and to go up shrouded propeller blade 9 and carry out clickwise, for the flight of aircraft provides lift.
As shown in Figure 2, illuminating lamp 5 symmetries are installed in the both sides of body 1, provide illumination when flying in the time of night or poor visibility for aircraft, and front wing 2 is installed in body 1 both sides with rear wing 3 parallel symmetries.
As shown in Figure 3, by power connecting device 10 last shrouded propeller oar axle 8, following shrouded propeller oar axle 15 and afterbody thrust shrouded propeller oar axle 12 link together, for all shrouded propellers rotation provide power to connect, under driving, the rotation of last shrouded propeller oar axle 8 is right-hand revolution with shrouded propeller blade 9 on last shrouded propeller oar axle 8 bonded assemblys, and shrouded propeller oar axle 15 is connected with following shrouded propeller blade 11 down, and shrouded propeller blade 11 is the anticlockwise direction rotation under driving, afterbody thrust shrouded propeller blade 13 is connected with afterbody thrust shrouded propeller oar axle 12, body 1 front portion is a cockpit 6, and chaufeur is controlled by the flight that is installed in 14 pairs of aircraft of cockpit in-to-in joystick.
As shown in Figure 4, the thrust shrouded propeller oar axle 13 that is installed in body 1 afterbody carries out the high speed right-hand revolution by the conduction of engine installation, and drive afterbody thrust shrouded propeller blade 13 is rotated simultaneously, for the flight of aircraft provides enough thrust, aircraft can be advanced fast.
Claims (2)
1, a kind of compound coaxial pair of oar duct fan individual lift device, comprise body, the flight transmission joint, steering unit, it is characterized in that a body (1) both sides are equipped with the front wing (2) and the rear wing (3) of the parallel distribution in front and back, at the front end position of body (1) electronic machine cover (4) is installed, body (1) position, front wing (2) top is provided with cockpit (6), joystick (14) is installed in it and is connected with steering unit, the rear portion of cockpit (6) is equipped with aircraft duct flight transmission joint (10), shrouded propeller axle (8) and following shrouded propeller axle (15) are installed on it, be fixed with screw blade (9) and following screw blade (11) respectively on last shrouded propeller axle (8) and the following shrouded propeller axle (15), the breather vane (7) that aircraft turns to usefulness is installed on body (1) the bonded assembly rear wing (3), at the afterbody of body (1) thrust ducted tail rotor oar axle (12) is installed and matches with thrust shrouded propeller blade (13).
2, compound coaxial pair of oar duct fan individual lift device according to claim 1 is characterized in that: body (1) front-end electronics cover (4) both sides are equipped with the illuminating lamp (5) of parallel symmetry.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420063676 CN2736257Y (en) | 2004-10-29 | 2004-10-29 | Composite coaxial double-oar culvert channel fan sole flight |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420063676 CN2736257Y (en) | 2004-10-29 | 2004-10-29 | Composite coaxial double-oar culvert channel fan sole flight |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2736257Y true CN2736257Y (en) | 2005-10-26 |
Family
ID=35306992
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200420063676 Expired - Fee Related CN2736257Y (en) | 2004-10-29 | 2004-10-29 | Composite coaxial double-oar culvert channel fan sole flight |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2736257Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102295073A (en) * | 2011-06-07 | 2011-12-28 | 张斗三 | Ducted helicopter |
| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
-
2004
- 2004-10-29 CN CN 200420063676 patent/CN2736257Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102295073A (en) * | 2011-06-07 | 2011-12-28 | 张斗三 | Ducted helicopter |
| CN102295073B (en) * | 2011-06-07 | 2013-08-21 | 张斗三 | Ducted helicopter |
| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN200995782Y (en) | Airplane | |
| CN203681869U (en) | Power system structure suitable for vertical take-off and landing air vehicle | |
| CN201211928Y (en) | Culvert single rotor saucer-shaped unmanned aircraft | |
| CN103552435B (en) | Many sprays self-balancing carplane | |
| CN101704415A (en) | Ducted single-propeller saucer-shaped unmanned aerial vehicle | |
| CN103738496A (en) | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof | |
| WO2010024593A2 (en) | Vtol aircraft using variable rotor | |
| CN101367436B (en) | Miniature hybrid power flying platform and implementing method thereof | |
| CN204527630U (en) | A kind of oil electric mixed dynamic fixed-wing VUAV system | |
| CN2736257Y (en) | Composite coaxial double-oar culvert channel fan sole flight | |
| CN2753673Y (en) | Tandem dual culvert pipe four-ejector single aircraft | |
| CN2776844Y (en) | Heavy load unmanned vertical flight | |
| CN1118385C (en) | Flapping-wing flying water automobile | |
| EP3838753A1 (en) | Convertiplano | |
| CN2748384Y (en) | One-man flight vehicle with coaxial culvert and umbrella paddle | |
| CA2507280A1 (en) | Auxiliary, rotatable, independent jet engines on plane fuselage | |
| CN101857086A (en) | Dual-culvert vertical take-off and landing unmanned aerial vehicle | |
| CN101746505B (en) | Disc-shaped unmanned aircraft of single-thrust paddle | |
| CN201753104U (en) | Single-oar disc-shaped unmanned aircraft | |
| CN2767323Y (en) | Float bowl type loop umbrella one-seater aerobat | |
| CN2753672Y (en) | Vector thrust culvert pipe fan type single aircraft | |
| CN201317462Y (en) | Small hybrid power flying platform | |
| US20080173769A1 (en) | Stabilized tilt rotor aircraft | |
| CN2767322Y (en) | Circular wing aerobat | |
| CN1206130C (en) | Multifunctional airplane and application thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |