CN108674652A - A kind of amphibious aircraft of double rectifications - Google Patents
A kind of amphibious aircraft of double rectifications Download PDFInfo
- Publication number
- CN108674652A CN108674652A CN201810539526.5A CN201810539526A CN108674652A CN 108674652 A CN108674652 A CN 108674652A CN 201810539526 A CN201810539526 A CN 201810539526A CN 108674652 A CN108674652 A CN 108674652A
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- China
- Prior art keywords
- fuselage
- trim panel
- disconnecting
- aircraft
- faulted
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/001—Flying-boats; Seaplanes with means for increasing stability on the water
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/008—Amphibious sea planes
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a kind of amphibious aircrafts of double rectifications, including：Fuselage, wing and floating drum；Wing is fixed on the hump of fuselage back, and floating drum is arranged in waist both sides；Body bottom surface is provided with disconnecting trim panel, and disconnecting trim panel is hinged by rotary shaft and fuselage；Body bottom surface is divided into front fuselage bottom surface and rear end body bottom surface by disconnecting trim panel, and the forward edge of disconnecting trim panel contacts and concordant with the posterior edges of front fuselage bottom surface, at seamlessly transitting between the posterior edges and rear fuselage bottom surface of disconnecting trim panel；Disconnecting trim panel is rotated along rotary shaft, forms the first rectification faulted-stage on front side of disconnecting trim panel with front fuselage bottom surface, and rear side forms the second rectification faulted-stage with rear fuselage bottom surface.The present invention not only effectively reduces resistance and aerodynamic noise of the aircraft in normal flight, improves the flight efficiency of aircraft, and is effectively prevented flow and is adsorbed on the rear fuselage bottom surface of fuselage, ensure that amphibious aircraft controls the effect of its pitch attitude.
Description
Technical field
The present invention relates to a kind of aircraft, more particularly to a kind of amphibious aircraft of double rectifications belongs to manned
Aircraft technology field.
Background technology
Amphibious aircraft can on the road of land takeoff and landing, while also can takeoff and landing on the water.Tradition
The bottom of fuselage of amphibious aircraft be formed with a rectification faulted-stage, amphibious aircraft is disconnected by rectification in water surface landing
Rank separated flow so that amphibious aircraft controls its pitch attitude during water surface high speed slide.Rectification faulted-stage is usually set
It sets at the center of gravity of amphibious aircraft position to the front, flow is easy to be adsorbed to fuselage again after detaching at rectification faulted-stage
On the bottom surface of back segment, the effect that amphibious aircraft controls its pitch attitude can be influenced in this way.In addition, working as amphibious aircraft just
When normal flight, high-speed flow can detach at the rectification faulted-stage on the fuselage bottom of amphibious aircraft, and rectification faulted-stage makes water
The resistance of land amphibian increases, and the aerodynamic noise generated also will increase.
Therefore, how providing a kind of pitch attitude can preferably control and can reduce flight resistance and the water of aerodynamic noise
Land amphibian becomes the problem of those skilled in the art's urgent need to resolve.
Invention content
In view of this, the present invention provides a kind of amphibious aircraft of double rectifications, not only significantly reduces aircraft and exist
Resistance when normal flight and aerodynamic noise, while the flight efficiency of aircraft is improved, and be effectively prevented flow and be adsorbed to machine
On the rear fuselage bottom surface of body, it ensure that amphibious aircraft controls the effect of its pitch attitude.
To achieve the goals above, the present invention adopts the following technical scheme that：
A kind of amphibious aircraft of double rectifications, including：Fuselage, wing and floating drum；Wherein, the wing is fixed on the fuselage
On the hump at back, the floating drum is arranged in the waist both sides, and positioned at the lower section of the wing；The body bottom surface
It is provided with disconnecting trim panel, the disconnecting trim panel is hinged by rotary shaft and the fuselage；The disconnecting trim panel will be described
Body bottom surface is divided into front fuselage bottom surface and rear end body bottom surface, and the forward edge of the disconnecting trim panel and the leading portion
The posterior edges of body bottom surface contact and concordant, between the posterior edges of the disconnecting trim panel and the rear fuselage bottom surface at
It seamlessly transits；The disconnecting trim panel is rotated along the rotary shaft, on front side of the disconnecting trim panel and front fuselage bottom surface
The first rectification faulted-stage is formed, rear side forms the second rectification faulted-stage with the rear fuselage bottom surface.
The present invention is hidden the first rectification faulted-stage by faulted-stage trim panel when in land traveling or state of flight
Come, significantly reduces resistance and aerodynamic noise of the aircraft in normal flight in this way, while improving the flight efficiency of aircraft.When
During water surface high speed slide, flow carries out again after the separation of the first rectification faulted-stage using the second rectification faulted-stage aircraft
Secondary separation is effectively prevented flow and is adsorbed on the rear fuselage bottom surface of fuselage, ensure that amphibious aircraft controls its pitching
The effect of posture；Floating drum is set to waist both sides, floating drum is set compared to wing outer end or floating drum is arranged in fuselage bottom end
Layout, fuselage weight reduces, and the weight at wing both ends is greatly reduced, to improve the followability of aircraft and operate motor-driven
Property, and the balance that aircraft flies and slided in water in the air can be increased.
Further, the rotary shaft is located at position to the rear among the faulted-stage trim panel, when turning an angle, disconnecting
Lifting height is more than the height that rear side declines on front side of trim panel.
Further, the height of the second rectification faulted-stage is less than the height of the first rectification faulted-stage, convenient for being flowed into water
The secondary rectification separation of row.
Further, further include empennage, the empennage includes horizontal tail, vertical fin and dorsal fin, and the vertical fin splices with the dorsal fin
It is connected with the horizontal tail at the top of the tail portion of the fuselage back, the vertical fin.
Further, it leaves a blank among the vertical fin, in one propeller of the longitudinal vertical arrangement installation in position of leaving a blank, in this way
Wide-angle turns to when facilitating hang or low speed.
Further, it leaves a blank among the horizontal tail, in position transverse horizontal arrangement one propeller of installation of leaving a blank, in this way
Facilitate aircraft steadily hovering or wide-angle pitching.
Further, the floating drum is streamlined flat cylinder, reduces the influence of its pneumatic power to aircraft flight when, this
Outside, in aircraft flight, fairshaped design can also provide certain climbing power for aircraft, and can play certain balance
Effect.
Further, further include engine nacelle, the engine nacelle is equipped with two groups, is installed in the wing head end,
And be symmetrical arranged about the fuselage, provide power and lift for aircraft.
Further, the upright position of the floating drum is higher than the belly, and less than the blade of the engine nacelle
The minimum point of circular-rotation, when blade rotation for avoiding engine nacelle, touch the water surface, and can make aircraft on the water surface
Fast and stable slides.
Further, further include undercarriage, the undercarriage includes undercarriage after a nose-gear and two, is risen before described
The bottom end that frame is mounted on the fuselage stem is fallen, two rear undercarriages are mounted on the bottom end two in the fuselage centre position
Side.Nose-gear and rear undercarriage can be unfolded with folding and unfolding, when aircraft landing by land in nose-gear and rear undercarriage,
Nose-gear and rear undercarriage are then packed up when sliding in water so that aircraft can planking and land rise
Drop.
Description of the drawings
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Structural schematic diagram when Fig. 1 attached drawings are flight in the air of the invention；
Fig. 2 attached drawings are structural schematic diagram of the present invention in hydroplaning；
Fig. 3 attached drawings are the vertical view of the present invention；
Fig. 4 attached drawings are the left view of the present invention；
The structural schematic diagram of disconnecting trim panel when Fig. 5 attached drawings are flight in the air of the invention；
Fig. 6 attached drawings are the structural schematic diagram of present invention disconnecting trim panel in hydroplaning.
Wherein, in figure,
1- fuselages；101- front fuselages bottom surface；102- rear fuselages bottom surface；103- the first rectification faulted-stages；The second rectifications of 104- are disconnected
Rank；2- wings；3- floating drums；4- disconnecting trim panels；5- rotary shafts；6- empennages；61- horizontal tails；62- vertical fins；63- dorsal fins；7- starts
Machine nacelle；8- undercarriages；81- nose-gears；Undercarriage after 82-.
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The embodiment of the invention discloses a kind of amphibious aircrafts of double rectifications, not only significantly reduce aircraft normal
Resistance when flight and aerodynamic noise, while the flight efficiency of aircraft is improved, and be effectively prevented flow and be adsorbed to fuselage
On rear fuselage bottom surface, it ensure that amphibious aircraft controls the effect of its pitch attitude.
Attached drawing 1-6 is please referred to, the present invention provides a kind of amphibious aircrafts of double rectifications, including：Fuselage 1,2 and of wing
Floating drum 3；Wherein, wing 2 is fixed on the hump at 1 back of fuselage, and floating drum 3 is arranged in 1 on both sides of the middle of fuselage, and is located at wing 2
Lower section；1 bottom surface of fuselage is provided with disconnecting trim panel 4, and disconnecting trim panel 4 is hinged by rotary shaft 5 and fuselage 1；Disconnecting shaping
1 bottom surface of fuselage is divided into front fuselage bottom surface 101 and rear end body bottom surface 102, and the forward edge of disconnecting trim panel 4 by plate 4
It is contacted with the posterior edges of front fuselage bottom surface 101 and concordant, posterior edges and the rear fuselage bottom surface 102 of disconnecting trim panel 4
Between at seamlessly transitting；Disconnecting trim panel 4 is rotated along rotary shaft 5, and 4 front side of disconnecting trim panel is formed with front fuselage bottom surface 101
First rectification faulted-stage 103, rear side form the second rectification faulted-stage 104 with rear fuselage bottom surface 102.
The present invention is hidden the first rectification faulted-stage 103 by faulted-stage trim panel 4 when in land traveling or state of flight
Get up, significantly reduces resistance and aerodynamic noise of the aircraft in normal flight in this way, while improving the flight efficiency of aircraft.
When aircraft is during water surface high speed slide, flow is after the separation of the first rectification faulted-stage 103, using the second rectification faulted-stage
104 are detached again, are effectively prevented flow and are adsorbed on rear fuselage bottom surface 102, ensure that amphibious aircraft control
The effect of its pitch attitude；Floating drum 3 is set to 1 on both sides of the middle of fuselage, floating drum 3 or 1 bottom of fuselage are set compared to 2 outer end of wing
The layout of end setting floating drum 3,1 weight of fuselage reduce, and the weight at 2 both ends of wing is greatly reduced, to improve aircraft with
Casual and operation mobility, and the balance that aircraft flies and slided in water in the air can be increased.
Rotary shaft 5 is located at position to the rear among faulted-stage trim panel 4, with rotary shaft 5 apart from 4 forward edge of disconnecting trim panel
Length be the three times of length of its posterior edges 220 apart from faulted-stage trim panel 200 be best, when turning an angle, break
It connects lifting height on front side of trim panel and is more than the height that rear side declines.The height of second rectification faulted-stage 104 is the first rectification faulted-stage 103
Height one third.Aircraft during water surface high speed slide, after the separation of the first rectification faulted-stage 103 adsorbed by flow
It to the lower face of faulted-stage trim panel 4, is detached again using the second rectification faulted-stage 104, is effectively prevented flow absorption
To the rear fuselage bottom surface 102 of fuselage 1, it ensure that amphibious aircraft controls the effect of its pitch attitude.
The invention also includes empennage 6, empennage 6 includes horizontal tail 61, vertical fin 62 and dorsal fin 63, vertical fin 62 and dorsal fin 63 splice in
The tail portion at 1 back of fuselage, 62 top of vertical fin are connected with horizontal tail 61.When flight, horizontal tail 61 mainly controls the longitudinal stability of aircraft
And operability, it leaves a blank among horizontal tail 61, in position transverse horizontal arrangement one propeller of installation of leaving a blank so that it is convenient to which aircraft is stablized
Hovering or wide-angle pitching；Vertical fin 62 mainly controls the lateral stability and operability of aircraft, leaves a blank, is leaving a blank among vertical fin 62
Longitudinal vertical arrangement one propeller of installation in position is so that it is convenient to which wide-angle turns to when hang or low speed；Dorsal fin 63 is used for
Improve the lateral navigation stability of aircraft.
Floating drum 3 is streamlined flat cylinder, the influence of its pneumatic power to aircraft flight when is reduced, in addition, in aircraft
In flight course, fairshaped design can also provide certain climbing power for aircraft, and can play certain balanced action, when winged
Machine slide in water appearance it is laterally unstable when, tilting the displacement of the floating drum 3 of side will increase, lateral floating to provide
Power makes aircraft be restored to equilibrium state.
The invention also includes engine nacelle 7, engine nacelle 7 is equipped with two groups, is installed in 2 head end of wing, and about
Fuselage 1 is symmetrical arranged, and every group includes two propellers, and when taking off, wing 2 has certain angle of lift, on engine nacelle 7
Four propellers start running, generate airflow act on wing 2, provide power and lift for aircraft so that aircraft
It can take off and stabilized flight.
The upright position of floating drum 3 is higher than the abdomen of fuselage 1, and minimum less than the blade circular-rotation of engine nacelle 7
Point, when blade rotation for avoiding engine nacelle 7, touch the water surface, and aircraft fast and stable on the water surface can be made to slide,
Guarantee simultaneously in high 2 meters of the water surface landing of wave.
The invention also includes undercarriage 8, undercarriage 8 includes undercarriage 82 after a nose-gear 81 and two, preceding to rise and fall
The undercarriage 82 behind the bottom end of 1 stem of fuselage, two of frame 81 is mounted on the bottom end both sides in 1 centre position of fuselage.Before rise and fall
Nose-gear 81 and rear undercarriage 82 can be unfolded with folding and unfolding, when aircraft landing by land in frame 81 and rear undercarriage 82,
Nose-gear 81 and rear undercarriage 82 are then packed up when being slided in water so that aircraft can planking and in land
Landing.
The present invention realize the water surface, land landing ability, can quickly fly to accident sea area, search for distress personnel, and
Targetedly rescue work is carried out according to sea situation, rescue efficiency is high, to solve existing rescue at sea equipment and technology transport
Problem difficult, efficiency is low.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest range caused.
Claims (10)
1. a kind of amphibious aircraft of double rectifications, which is characterized in that including：Fuselage, wing and floating drum；Wherein, the wing
It is fixed on the hump of the fuselage back, the floating drum is arranged in the waist both sides, and under the wing
Side；The body bottom surface is provided with disconnecting trim panel, and the disconnecting trim panel is hinged by rotary shaft and the fuselage；It is described disconnected
It connects trim panel and the body bottom surface is divided into front fuselage bottom surface and rear end body bottom surface, and the front side of the disconnecting trim panel
Edge is contacted with the posterior edges of the front fuselage bottom surface and concordant, posterior edges and the back segment of the disconnecting trim panel
At seamlessly transitting between body bottom surface；The disconnecting trim panel is rotated along the rotary shaft, the disconnecting trim panel front side and institute
It states front fuselage bottom surface and forms the first rectification faulted-stage, rear side forms the second rectification faulted-stage with the rear fuselage bottom surface.
2. a kind of amphibious aircraft of double rectifications according to claim 1, which is characterized in that the rotary shaft is located at institute
State position to the rear among faulted-stage trim panel.
3. a kind of amphibious aircraft of double rectifications according to claim 1 or 2, which is characterized in that second rectification
The height of faulted-stage is less than the height of the first rectification faulted-stage.
4. a kind of amphibious aircraft of double rectifications according to claim 1, which is characterized in that further include empennage, it is described
Empennage includes horizontal tail, vertical fin and dorsal fin, and the vertical fin splices with the dorsal fin in the tail portion of the fuselage back, the vertical fin top
Portion is connected with the horizontal tail.
5. a kind of amphibious aircraft of double rectifications according to claim 4, which is characterized in that stayed among the vertical fin
Sky, in one propeller of the longitudinal vertical arrangement installation in position of leaving a blank.
6. a kind of amphibious aircraft of double rectifications according to claim 4 or 5, which is characterized in that among the horizontal tail
It leaves a blank, in position transverse horizontal arrangement one propeller of installation of leaving a blank.
7. a kind of amphibious aircraft of double rectifications according to claim 1, which is characterized in that the floating drum is streamlined
Flat cylinder.
8. a kind of amphibious aircraft of double rectifications according to claim 1 or claim 7, which is characterized in that further include engine
Nacelle, the engine nacelle are equipped with two groups, are installed in the wing head end, and be symmetrical arranged about the fuselage.
9. a kind of amphibious aircraft of double rectifications according to claim 8, which is characterized in that the vertical position of the floating drum
It sets and is higher than the belly, and the minimum point of the blade circular-rotation less than the engine nacelle.
10. a kind of amphibious aircraft of double rectifications according to claim 1, which is characterized in that further include undercarriage, institute
It includes undercarriage after a nose-gear and two to state undercarriage, and the nose-gear is mounted on the bottom end of the fuselage stem,
Two rear undercarriages are mounted on the bottom end both sides in the fuselage centre position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810539526.5A CN108674652A (en) | 2018-05-30 | 2018-05-30 | A kind of amphibious aircraft of double rectifications |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810539526.5A CN108674652A (en) | 2018-05-30 | 2018-05-30 | A kind of amphibious aircraft of double rectifications |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108674652A true CN108674652A (en) | 2018-10-19 |
Family
ID=63809255
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810539526.5A Withdrawn CN108674652A (en) | 2018-05-30 | 2018-05-30 | A kind of amphibious aircraft of double rectifications |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108674652A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592072A (en) * | 2018-10-26 | 2019-04-09 | 中国飞行试验研究院 | A kind of large size amphibious aircraft Flight Test Method waterborne |
| CN110979667A (en) * | 2019-12-10 | 2020-04-10 | 中国特种飞行器研究所 | Splash suppression ship type of amphibious aircraft |
| CN113232832A (en) * | 2021-03-29 | 2021-08-10 | 南京航空航天大学 | Amphibious aircraft |
-
2018
- 2018-05-30 CN CN201810539526.5A patent/CN108674652A/en not_active Withdrawn
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592072A (en) * | 2018-10-26 | 2019-04-09 | 中国飞行试验研究院 | A kind of large size amphibious aircraft Flight Test Method waterborne |
| CN109592072B (en) * | 2018-10-26 | 2022-02-11 | 中国飞行试验研究院 | Water test flight method for large-scale amphibious aircraft |
| CN110979667A (en) * | 2019-12-10 | 2020-04-10 | 中国特种飞行器研究所 | Splash suppression ship type of amphibious aircraft |
| CN113232832A (en) * | 2021-03-29 | 2021-08-10 | 南京航空航天大学 | Amphibious aircraft |
| CN113232832B (en) * | 2021-03-29 | 2023-08-22 | 南京航空航天大学 | Amphibious aircraft |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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Application publication date: 20181019 |