CN110015400A - A kind of distributed power formula aircraft - Google Patents
A kind of distributed power formula aircraft Download PDFInfo
- Publication number
- CN110015400A CN110015400A CN201910233061.5A CN201910233061A CN110015400A CN 110015400 A CN110015400 A CN 110015400A CN 201910233061 A CN201910233061 A CN 201910233061A CN 110015400 A CN110015400 A CN 110015400A
- Authority
- CN
- China
- Prior art keywords
- cabin
- sustainer
- wing
- tail boom
- cockpit
- 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.)
- Pending
Links
- 230000008450 motivation Effects 0.000 claims description 6
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 description 15
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 230000006870 function Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/008—Amphibious sea planes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C2003/143—Aerofoil profile comprising interior channels
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of distributed power formula aircraft, cockpit including being sequentially connected setting, sustainer cabin and tail portion deflector, cockpit is equipped with openable and closable hatch door, the bottom in cockpit and sustainer cabin is evenly equipped with multiple wheels, the two sides in sustainer cabin are equipped with wing, wing is equipped with airflow channel, one end of airflow channel is airfoil air scoop, the other end is wing exhaust outlet, multiple interplane power devices are evenly distributed in airflow channel, wing is equipped with end plate far from the one end in sustainer cabin, the rear end in sustainer cabin is equipped with propeller and tail boom, tail portion deflector is equipped with the duct for surrounding the annular of propeller, tail boom is equipped with two pieces of vertical vertical fins far from the one end in sustainer cabin, vertical rudder is equipped on two pieces of vertical fins, the upper end of rudder is equipped with tailplane.The present invention can effectively improve and improve flight characteristic, flying quality, security reliability, economy and the most important place adaptability of hovercar.
Description
Technical field
The present invention relates to technical field of transportation means, and in particular to a kind of distributed power formula aircraft.
Background technique
Middle-size and small-size manned vehicle especially light aerocraft is parked and landing because its is light and small without big airport, is existed in recent years
Civil field is widely applied and is developed rapidly, and aircraft also has the tendency that studying great development greatly, these represent not
Carry out an important development direction of the vehicles.In various small-sized people-transport's works such as light aerocraft, ultra light aircraft, aircraft
In tool scheme, aircraft class has biggish development potentiality because being not necessarily to airport.But existing aircraft or ground effect vehicle exist
There is also many not as good as in place of people's will for the use of with high-altitude flight on land.
Summary of the invention
Problem to be solved by this invention is: providing a kind of distributed power formula aircraft, can effectively improve and improve
Flight characteristic, flying quality, security reliability, economy and the most important place adaptability of aircraft.
The present invention in order to solve the above problem provided by technical solution are as follows: a kind of distributed power formula aircraft, including successively
Cockpit, sustainer cabin and the tail portion deflector of setting are connected, the cockpit is equipped with openable and closable hatch door, the driving
The bottom in cabin and sustainer cabin is evenly equipped with multiple wheels, and the two sides in the sustainer cabin are equipped with wing, on the wing
Equipped with airflow channel, one end of the airflow channel is airfoil air scoop, and the other end is wing exhaust outlet, in the airflow channel
Multiple interplane power devices are evenly distributed with, the wing is equipped with end plate, the main hair far from the one end in the sustainer cabin
The rear end in motivation cabin is equipped with propeller and tail boom, and the tail portion deflector is equipped with the duct for surrounding the annular of the propeller,
The tail boom is equipped with two pieces of vertical vertical fins far from the one end in the sustainer cabin, and it is vertical to be equipped on two pieces of vertical fins
The upper end of rudder, the rudder is equipped with tailplane.
Preferably, the tail boom includes left tail boom and right tail boom, and the left tail boom and right tail boom are symmetrically horizontally set on institute
State the rear end in sustainer cabin.
Preferably, the wheel includes wheel after a preceding wheel and two, and the preceding wheel is arranged in the cockpit
Lower end, it is described two after wheels the lower end in the sustainer cabin is set.
Preferably, the tailplane is equipped with elevator.
Preferably, the power device is motor either internal combustion engine.
Preferably, the interplane power device is minitype motivation fan.
Compared with prior art, the invention has the advantages that 1, have in two wings of aircraft an air-flow logical respectively
Road formula structure is extended in channel to multiple minitype motivation fans are disposed with, and manipulation and control drives interior carry out by driver's cabin.When
When these power fans work, there is a large amount of air-flow in wing channel, effect similar with stitching wing flap more, and aircraft has very big liter
Power effect, can be with high-altitude flight；When power is smaller, end plate forms the ground effect machine wing of ground effect vehicle on the outside of aircraft wing, can
With extreme low-altitude or water surface flying.When aircraft high-altitude flight, its cruising ability can be improved；When ground park or road surface,
When water surface flying, wing is shorter, reduces the span, saves space, it is not easy to brush up against peripheral obstacle.2, body tail active force
Propeller is in duct, and there are two effects: 1 keeps the air-flow for flowing through propeller more straight, improves the pneumatic efficiency of propeller
With whole thrust；2 are not easy to injure ground staff when driving or get to ground object on ground or low latitude.3, behind sustainer cabin
There is tail portion deflector in portion, under the airflow function of propeller, forms a lift member, generates additional lift.4, aircraft
Rear-wheel has electronic power drive, travels aircraft equally in ground image surface automobile.5, aircraft has wheel, both can be on ground
It parks and landing, and can be parked in road and landing, can not be influenced by airport.6, it does not work or flies in sustainer
When device declines because of other accidents, the case where the power fan in wing can be manipulated, improve wing channel interior air-flow, there is it
Bigger lift slows down the speed of whereabouts, when it being made to be slipped to ground, is unlikely to seriously to damage, can more preferably protect occupant.
Detailed description of the invention
The drawings described herein are used to provide a further understanding of the present invention, constitutes a part of the invention, this hair
Bright illustrative embodiments and their description are used to explain the present invention, and are not constituted improper limitations of the present invention.
Fig. 1 is overall structure diagram of the invention；
Fig. 2 is the cross-sectional view of wing of the invention；
Attached drawing mark: 1, cockpit, 2, wing, 3, tail portion deflector, 4, end plate, 5, left tail boom, 6, propeller, 7, hang down
Tail, 8, elevator, 9, tailplane, 10, rudder, 11, duct, 12, right tail boom, 13, rear wheel, 14, hatch door, 15, preceding machine
Wheel, 16, interplane power device, 17, airfoil air scoop, 18, wing exhaust outlet, 19, sustainer cabin.
Specific embodiment
Carry out the embodiment that the present invention will be described in detail below in conjunction with accompanying drawings and embodiments, how the present invention is applied whereby
Technological means solves technical problem and reaches the realization process of technical effect to fully understand and implement.
Specific embodiments of the present invention are as shown in Figure 1 to Figure 2, a kind of distributed power formula aircraft, it is characterised in that: including
It is sequentially connected cockpit 1, sustainer cabin 19 and the tail portion deflector 20 of setting, the cockpit 1 is equipped with openable and closable cabin
Door 14, is equipped with power device in the sustainer cabin 19, and the bottom in the cockpit 1 and sustainer cabin 19 is evenly equipped with more
A wheel, the two sides in the sustainer cabin 19 are equipped with wing 2, and the wing 2 is equipped with airflow channel, the airflow channel
One end be airfoil air scoop 17, the other end is wing exhaust outlet 18, and it is dynamic that multiple interplanes are evenly distributed in the airflow channel
Power device 16, the rear end in the sustainer cabin 19 are equipped with propeller 6 and tail boom, and the tail portion deflector 20, which is equipped with, surrounds institute
The duct 11 of the annular of propeller 6 is stated, the tail boom is equipped with two pieces of vertical vertical fins far from the one end in the sustainer cabin 19
7, vertical rudder 10 is equipped on two pieces of vertical fins 7, the upper end of the rudder 10 is equipped with tailplane 9, the machine
Wheel and propeller 6 are driven by the power device.
The tail boom includes left tail boom 5 and right tail boom 12, and the left tail boom 5 and right tail boom 12 are symmetrically horizontally set on described
The rear end in sustainer cabin 19.
The wheel includes wheel 13 after a preceding wheel 15 and two, and the preceding wheel 15 is arranged in the cockpit 1
Lower end, it is described two after wheels 13 lower end in the sustainer cabin 19 is set.
The tailplane 9 is equipped with elevator 8.
The power device is motor either internal combustion engine.
The interplane power device 16 is minitype motivation fan.
Specific work process of the invention is sketched now in conjunction with flight course of the invention；Its mode is as follows:
(1) ground nap of the earth flight: aircraft is slided on ground with wheel, and fan power unit is in low function between wing at this time
Rate working condition, active force are in mid power state, reach ladder wing and the whole all formation lift of fuselage after certain speed,
In addition the ground effect that end plate is formed on the outside of ladder wing, at this moment aircraft can paste ground flying or hedgehopping.
(2) airflight: aircraft is slided with wheel on ground and is taken off, and wing fan power unit is in high-power at this time
When working condition, two wings in left and right form huge circulation effect, the lift effect of more seam wing flaps are generated, after active force accelerates
Aircraft takeoff rises, and at this moment aircraft can draw relatively high altitude, and resistance is relatively small at this time.
(3) land travels: when aircraft is at smooth-riding surface, rear-wheel can be driven by motor, front-wheel is deflecting roller, as
Face vehicle equally travels, and at this moment wing can go up folding, to reduce occupancy ground space.
(4) control of aircraft rises or falls it by elevator deflection as conventional airplane；Pass through deflection
Left and right both direction rudder makes it change course；Change table on the wing of two sides by the size of fan power between control left and right wing
Rolling control may be implemented to realize that two sides lift is poor in the speed of face air-flow velocity in this way.
The beneficial effects of the present invention are: 1, have an airflow channel formula structure respectively in two wings of aircraft,
It is extended in channel to multiple minitype motivation fans are disposed with, manipulation and control drives interior carry out by driver's cabin.When these power wind
When fanning work, there is a large amount of air-flow in wing channel, effect similar with stitching wing flap more, and aircraft has very big lift effect, can
With high-altitude flight；When power is smaller, end plate forms the ground effect machine wing of ground effect vehicle on the outside of aircraft wing, can it is extreme low-altitude or
Water surface flying.When aircraft high-altitude flight, its cruising ability can be improved；When being parked on ground or when road surface, water surface flying,
Wing is shorter, reduces the span, saves space, it is not easy to brush up against peripheral obstacle.2, body tail active force propeller is being contained
In road, there are two effects: 1 keeps the air-flow for flowing through propeller more straight, improves the pneumatic efficiency and entirety thrust of propeller；
2 are not easy to injure ground staff when driving or get to ground object on ground or low latitude.3, sustainer cabin rear portion has tail portion to lead
Flowing plate forms a lift member under the airflow function of propeller, generates additional lift.4, the rear-wheel of aircraft has electronic
Power drive travels aircraft equally in ground image surface automobile.5, aircraft has wheel, both can park and rise on ground
Drop, and can be parked in road and landing, it can not be influenced by airport.6, it does not work in sustainer or aircraft is because of other
When surprisingly declining, the case where the power fan in wing can be manipulated, improve wing channel interior air-flow, it is made to have bigger liter
Power slows down the speed of whereabouts, when it being made to be slipped to ground, is unlikely to seriously to damage, can more preferably protect occupant.
Only highly preferred embodiment of the present invention is described above, but is not to be construed as limiting the scope of the invention.This
Invention is not only limited to above embodiments, and specific structure is allowed to vary.All protection models in independent claims of the present invention
Interior made various change is enclosed to all fall in the scope of protection of the present invention.
Claims (6)
1. a kind of distributed power formula aircraft, it is characterised in that: cockpit (1), sustainer cabin including being sequentially connected setting
(19) and tail portion deflector (20), the cockpit (1) are equipped with openable and closable hatch door (14), in the sustainer cabin (19)
Equipped with power device, the bottom of the cockpit (1) and sustainer cabin (19) is evenly equipped with multiple wheels, the sustainer cabin
(19) two sides are equipped with wing (2), and the wing (2) is equipped with airflow channel, one end of the airflow channel be wing into
Port (17), the other end are wing exhaust outlet (18), are evenly distributed with multiple interplane power devices (16) in the airflow channel,
The wing (2) is equipped with end plate (4) far from one end of the sustainer cabin (19), and the rear end of the sustainer cabin (19) is set
There are propeller (6) and tail boom, the tail portion deflector (20) is equipped with the duct (11) for surrounding the annular of the propeller (6),
The tail boom is equipped with two pieces of vertical vertical fins (7) far from one end of the sustainer cabin (19), on two pieces of vertical fins (7)
Equipped with vertical rudder (10), the upper end of the rudder (10) is equipped with tailplane (9), the wheel and propeller (6)
It is driven by the power device.
2. a kind of distributed power formula aircraft according to claim 1, it is characterised in that: the tail boom includes left tail boom
(5) and right tail boom (12) after, the left tail boom (5) and right tail boom (12) are symmetrically horizontally set on the sustainer cabin (19)
End.
3. a kind of distributed power formula aircraft according to claim 1, it is characterised in that: the wheel includes a preceding machine
Wheel (13) after (15) and two is taken turns, preceding wheel (15) setting is in the lower end of the cockpit (1), described two wheels afterwards
(13) it is arranged in the lower end of the sustainer cabin (19).
4. a kind of distributed power formula aircraft according to claim 1, it is characterised in that: set on the tailplane (9)
There are elevator (8).
5. a kind of distributed power formula aircraft according to claim 1, it is characterised in that: the power device be motor or
Person is internal combustion engine.
6. a kind of distributed power formula aircraft according to claim 1, it is characterised in that: the interplane power device (16)
For minitype motivation fan.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910233061.5A CN110015400A (en) | 2019-03-26 | 2019-03-26 | A kind of distributed power formula aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910233061.5A CN110015400A (en) | 2019-03-26 | 2019-03-26 | A kind of distributed power formula aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110015400A true CN110015400A (en) | 2019-07-16 |
Family
ID=67189985
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910233061.5A Pending CN110015400A (en) | 2019-03-26 | 2019-03-26 | A kind of distributed power formula aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110015400A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3614028A (en) * | 1970-01-12 | 1971-10-19 | Mc Donnell Douglas Corp | Turbofan-powered stol aircraft |
| GB2088521A (en) * | 1980-11-26 | 1982-06-09 | Walmsley Sidney | Inducing lift on a stationary wing |
| US5687934A (en) * | 1995-08-04 | 1997-11-18 | Owens; Phillip R. | V/STOL aircraft and method |
| US20060284010A1 (en) * | 2005-06-06 | 2006-12-21 | Meekins John A | Hydrofoil for an amphibious aircraft |
| CN101348170A (en) * | 2008-09-01 | 2009-01-21 | 北京航空航天大学 | Wing structure having lamellar flow flowing control and separation control |
| CN102762451A (en) * | 2009-12-08 | 2012-10-31 | 空中客车运作有限责任公司 | Aircraft with an arrangement of flow-influencing devices |
| CN102774493A (en) * | 2012-08-08 | 2012-11-14 | 南昌航空大学 | Variable wing type land, sea and air triphibian aircraft |
| WO2018059244A1 (en) * | 2016-09-28 | 2018-04-05 | 韩建刚 | Aircraft |
-
2019
- 2019-03-26 CN CN201910233061.5A patent/CN110015400A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3614028A (en) * | 1970-01-12 | 1971-10-19 | Mc Donnell Douglas Corp | Turbofan-powered stol aircraft |
| GB2088521A (en) * | 1980-11-26 | 1982-06-09 | Walmsley Sidney | Inducing lift on a stationary wing |
| US5687934A (en) * | 1995-08-04 | 1997-11-18 | Owens; Phillip R. | V/STOL aircraft and method |
| US20060284010A1 (en) * | 2005-06-06 | 2006-12-21 | Meekins John A | Hydrofoil for an amphibious aircraft |
| CN101348170A (en) * | 2008-09-01 | 2009-01-21 | 北京航空航天大学 | Wing structure having lamellar flow flowing control and separation control |
| CN102762451A (en) * | 2009-12-08 | 2012-10-31 | 空中客车运作有限责任公司 | Aircraft with an arrangement of flow-influencing devices |
| CN102774493A (en) * | 2012-08-08 | 2012-11-14 | 南昌航空大学 | Variable wing type land, sea and air triphibian aircraft |
| WO2018059244A1 (en) * | 2016-09-28 | 2018-04-05 | 韩建刚 | 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 | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190716 |