CN106516109A - Slight-splashing high-performance two-hull amphibious aircraft - Google Patents
Slight-splashing high-performance two-hull amphibious aircraft Download PDFInfo
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- CN106516109A CN106516109A CN201611093860.XA CN201611093860A CN106516109A CN 106516109 A CN106516109 A CN 106516109A CN 201611093860 A CN201611093860 A CN 201611093860A CN 106516109 A CN106516109 A CN 106516109A
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- type main
- lift type
- aerodynamic lift
- machine body
- main machine
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- 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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- Aviation & Aerospace Engineering (AREA)
- Cleaning Or Clearing Of The Surface Of Open Water (AREA)
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Abstract
The invention provides a slight-splashing high-performance two-hull amphibious aircraft which comprises an aerodynamic lift type main fuselage, wings, empennages, turbofan engines and slight-splashing sliding hulls. The wings 2 are arranged in the middle of the aerodynamic lift type main fuselage. The turbofan engines are arranged on the upper position, near the aerodynamic lift type main fuselage, of the wings. The empennages are arranged at the tail end of the aerodynamic lift type main fuselage. The two slight-splashing sliding hulls are arranged on the two longitudinal sides of the lower portion of the aerodynamic lift type main fuselage. A longitudinal aerodynamic groove channel 5 is formed after the connection of the two slight-splashing sliding hulls and the aerodynamic lift type main fuselage. The aerodynamic lift type main fuselage is provided with reverse profile planing steps which divide the aerodynamic lift type main fuselage into a front fuselage body and a rear fuselage body. An upper transverse bent sliding face and a lower transverse bent sliding face are arranged in the position, at the bottom of each slight-splashing sliding hull, on the sliding face of the front fuselage body sequentially from inside to outside. The anti-wave ability of the amphibious aircraft is improved, and the amphibious aircraft has an excellent hydrostatic and wave splashing controlling ability to adapt to a more complex marine environment.
Description
Technical field
The present invention relates to amphibious aircraft design field, and in particular to a kind of micro- splash high performance catamaran land and water two
Dwell aircraft.
Background technology
Conventional seaplane, planing surface is obvious V-type or W type profiles, and in hydroplaning, fuselage stem is leaned on
Exist the stationary point that speed of incoming flow retardance is zero at nearly free surface, and a stationary point is formed in fuselage bottom width range
Line, due to pressure highest near the line of stationary point, defines stationary point line and the immense pressure outside hull bottom topside is poor, so as to produce to outward transport
Dynamic jet water course, height and the shipform close relation of splash current.As splash is to amphibious aircraft safety
Property tremendous influence, at present on the one hand by, in airplane design, being optimized to cross section, to design with good splash
The hull of performance, on the other hand by the way of Local Members (wave suppression trough, vertical spray deflector etc.) is increased obtaining certain effect
Really.
In high performance craft field, most representational is that speedboat " dirk ", double M are tested in stealth to USN's latest model at a high speed
Fluid resistance when ship type is constituted with fully reflection and absorbs high speed operation, is translated into lift, while forming ground cushion pad
The effect for rising, and board, without flare, during high speed operation, pressure is less, it is not easy to the splash to outside hull is formed, with routine
The type speedboat of sliding is compared, and which suppresses two side of a ship splashing effects obvious.
Temporarily do not have what M types high performance craft and the seaplane with excellent splash performance were merged by similar land-and-sea aircraft at present
New micro- splash seaplane occurs.
The content of the invention
The purpose of the present invention be design it is a kind of can under the conditions of standing level and complicated sea situation safe landing it is amphibious
Aircraft, improves the anti-unrestrained ability of amphibious aircraft so as to excellent hydrostatic and wave splash control ability, so as to suitable
Answer increasingly complex marine environment.
The technical scheme is that：
A kind of micro- splash high performance catamaran amphibious aircraft, it is characterised in that：Including aerodynamic lift type main machine body
1st, wing 2, empennage 3, fanjet 4 and micro- splash planing hull 6；Wing 2 is arranged in the middle part of aerodynamic lift type main machine body 1,
Fanjet 4 is disposed with aerodynamic lift type main machine body 1 above wing 2；In the tail end of aerodynamic lift type main machine body 1
It is disposed with empennage 3；
Two micro- splash planing hulls 6 are arranged on 1 bottom of aerodynamic lift type main machine body longitudinal direction both sides, and two micro- splashes are slided
Hull 6 forms longitudinal pneumatic channel 5 after being connected with aerodynamic lift type main machine body 1；Aerodynamic lift type main machine body 1 is provided with reversely
Section faulted-stage 7, by aerodynamic lift type main machine body, 1 point is precursor and rear body.
Further preferred version, a kind of micro- splash high performance catamaran amphibious aircraft, it is characterised in that：It is pneumatic
Length-width ratio L/B of lift-type main machine body 1 is 4.68, the width B1 ratios of half-breadth B2 of pneumatic channel 5 and micro- splash planing hull 6
For 1, the ratio of the forebody length L1 and afterbody length degree L2 of aerodynamic lift type main machine body 1 is 1.
Further preferred version, a kind of micro- splash high performance catamaran amphibious aircraft, it is characterised in that：Reversely
The ratio of the height h1 and 1 width B of aerodynamic lift type main machine body of faulted-stage 7 is 0.23%, and 7 inclination angle of antithetic fault terrace is 4 °.
Further preferred version, a kind of micro- splash high performance catamaran amphibious aircraft, it is characterised in that：Micro- spray
Splash 6 bottom of planing hull and be disposed with transverse curvature planing surface 8 and lower transverse curvature on precursor planing surface from inside to outside
Planing surface 9, upper transverse curvature planing surface 8 and lower transverse curvature planing surface 9 are lower concave curved surface.
Further preferred version, a kind of micro- splash high performance catamaran amphibious aircraft, it is characterised in that：Upper horizontal stroke
It is 6% to the radius of curvature R 1 and 1 width B ratios of aerodynamic lift type main machine body of bending planing surface 8, lower transverse curvature planing surface 9
Radius of curvature R 2 and 1 width B ratios of aerodynamic lift type main machine body be 10%.
Beneficial effect
The method have the advantages that：By the present invention in that being pressed down with the splash current that planing surface is produced by the unconventional planing surface of inverted " V "
System in inner side, so as to reduce expulsion problem during seaplane landing, at the same the invention also have concurrently anti-unrestrained ability it is high the characteristics of, it is double
Between body, conduit is conducive to the air that fuselage pours in underbelly is compressed in fuselage bottom during navigation, between machine bottom and the water surface
Cushioning effect is formed, and hull is raised by the wave be filled with during by traveling, is reduced the area that hull is contacted with water, is reduced friction
Resistance.Micro- splash high-performance amphibious aircraft of the present invention has anti-unrestrained ability strong, under complicated sea situation the characteristics of the high rate of attendance,
Can be used for water life-saving and fast reserve.
Fuselage is merged with micro- splash hull, ground effect conduit is formed, be make use of similar inverted " V " to slide micro- spray
Lamellar body and conduit ground effect effect load shedding, the advantage of drag reduction are splashed, micro- splash binary amphibious aircraft can be greatly promoted
Performance.Power is provided using fanjet, splash can be suppressed, in conduit, hardly outwards to produce by micro- splash planing hull
Raw splash, reduces splash spray into the probability of electromotor.Pneumatic channel can play the gas-bearing formation effect of hovering in takeoff phase
Reduce resistance, and aircraft can be buffered during drop in water surface, water load when reducing landing is improved amphibious
The takeoff and landing performance of aircraft.
The additional aspect and advantage of the present invention will be set forth in part in the description, and partly will become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become from the description with reference to accompanying drawings below to embodiment
It is substantially and easy to understand, wherein：
Fig. 1：The top view of the present invention；
Fig. 2：The axonometric chart of the present invention；
Fig. 3：The rearview of aerodynamic lift type main machine body of the present invention and micro- splash planing hull；
Fig. 4：The enlarged drawing of antithetic fault terrace in Fig. 3；
Fig. 5：The frontal view of the present invention；
Fig. 6：The rear direction view of the present invention；
Fig. 7：The lateral view of the present invention.
Specific embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from start to finish
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to for explaining the present invention, and be not considered as limiting the invention.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", " length ", " width ",
" thickness ", " on ", D score, "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise " is, based on orientation shown in the drawings or position relationship, to be for only for ease of
The description present invention and simplified description, rather than indicate or imply that the device or element of indication must have specific orientation, Yi Te
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
The purpose of the present invention be design it is a kind of can under the conditions of standing level and complicated sea situation safe landing it is amphibious
Aircraft, improves the anti-unrestrained ability of amphibious aircraft so as to excellent hydrostatic and wave splash control ability, so as to suitable
Answer increasingly complex marine environment.Micro- splash high-performance amphibious aircraft in the present embodiment is a kind of new amphibious
Aircraft, is a kind of product that amphibious aircraft is combined with M type high performance crafts, but this combination is not simple folded again
Plus, but it is amphibious winged that the micro- splash high-performance for obtaining is designed after theory analysis, a large amount of fluid calculations and model test
Machine.
As shown in Figure 1, Figure 2, shown in Fig. 5 and Fig. 6, micro- splash high performance catamaran amphibious aircraft that the present embodiment is proposed, bag
Include aerodynamic lift type main machine body 1, wing 2, empennage 3, fanjet 4 and micro- splash planing hull 6；Wing 2 is arranged on pneumatic
In the middle part of lift-type main machine body 1, fanjet 4 is disposed with aerodynamic lift type main machine body 1 above wing 2；Pneumatic
The tail end of lift-type main machine body 1 is disposed with empennage 3.Two micro- splash planing hulls 6 are arranged on 1 bottom of aerodynamic lift type main machine body
Longitudinal both sides, two micro- splash planing hulls 6 form longitudinal pneumatic channel 5 after being connected with aerodynamic lift type main machine body 1；It is pneumatic
Lift-type main machine body 1 is provided with reversed profile faulted-stage 7, and by aerodynamic lift type main machine body, 1 point is precursor and rear body.
Further, by fluid calculation and model test, length-width ratio L/B of preferred aerodynamic lift type main machine body 1 is
4.68, water resistance now is less；Half-breadth B2 of pneumatic channel 5 is 1 with the width B1 ratios of micro- splash planing hull 6, both sides
The wave-making interaction of hull is less, and the effect that hovers of conduit is also more obvious；The forebody length L1 of aerodynamic lift type main machine body 1 with it is rear
The ratio of body length L2 is 1, and hull is slided and can keep stable attitude, is conducive to landing of taking off.
As shown in Fig. 3, Fig. 4, Fig. 6 and Fig. 7, height h1 and the aerodynamic lift type master of the faulted-stage 7 reverse with precursor planing surface
The ratio of 1 width B of fuselage is 0.23%, and 7 inclination angle of antithetic fault terrace is 4 ° so as to can depart from the water surface when body is slided afterwards and play disconnected
The effect that rank is slided.
As shown in Figure 3, Figure 5 and Figure 6, micro- 6 bottom of splash planing hull is set gradually on precursor planing surface from inside to outside
There are upper transverse curvature planing surface 8 and lower transverse curvature planing surface 9, upper transverse curvature planing surface 8 and lower transverse curvature planing surface 9 are equal
For lower concave curved surface.Tested by the repairing type to transverse curvature planing surface 8 on micro- splash aircraft and lower transverse curvature planing surface 9, really
The ratio of R1 and R2 and the beam, radius of curvature R 1 and the 1 width B of aerodynamic lift type main machine body of upper transverse curvature planing surface 8 are determined
Ratio is 6%, and radius of curvature R 2 and the 1 width B ratios of aerodynamic lift type main machine body of lower transverse curvature planing surface 9 are 10%.Stream
Body is calculated and test shows, is conducive to increasing the lift of planing surface using above-mentioned parameter, is reduced hull and is slided wave making, suppresses to slide
The splash current that face produces, it is ensured that the situation that resistance does not substantially increase, splash are effectively reduced, and increased the anti-wave of aircraft
Ability.
Micro- splash high-performance amphibious aircraft proposed by the present invention similar to catamaran planing craft, but with catamaran planing craft phase
It is not conventional V-type or W type profiles than, planing surface, but inverted " V " type, splash current are suppressed in machine by this planing surface
In bottom, so as to have preferable splash control ability.The conduit that two planing surfaces are formed, the air that fuselage stem is entered and water
Stream is pressed under hull bottom, and seldom having, and air-water mixture is flowed out by conduit tail end mouth, while having
The conduit surface of aerodynamic lift section, when gas introduces machine bottom, defines cushioning effect, and the wave be filled with during by traveling will
Hull is raised, and reduces machine bottom and water surface contact area, so as to reduce resistance of taxing.
When vessel berth is on the water surface, it is quiet floating that the pontoon being made up of two planing surface of falling V hulls 2 provides that foot has
Power, enables the seaplane to swim on the water surface, meanwhile, the arrangement of seaplane binary, it is ensured that aircraft has enough
Lateral stability.When seaplane needs navigation, start electromotor offer thrust forward, aircraft is gradually opened by static
Dynamic navigation, in the case where hull slides hydrodynamism, hull lifting, as headway constantly increases, cushioning effect in conduit
Gradually strengthen and conduit in air-water mixture increase and cause that aircraft is when wave high speed navigate by water, imitate with preferably buffering
Really, with good storm resistance, meanwhile, machine bottom both sides are compressed on splash current in machine bottom, so as to splash is controlled.Deng
To accelerate to from water speed when, machine bottom almost departs from the water surface, smoothly can take off.
During aircraft water landing, channel type air flue can form mattress, play buffering effect so that during landing
The water load of fuselage is reduced, so as to increased the safety of aircraft landing.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is in the principle and objective without departing from the present invention
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (5)
1. a kind of micro- splash high performance catamaran amphibious aircraft, it is characterised in that：Including aerodynamic lift type main machine body 1, wing
2nd, empennage 3, fanjet 4 and micro- splash planing hull 6；Wing 2 is arranged in the middle part of aerodynamic lift type main machine body 1, in wing 2
Top is disposed with fanjet 4 at aerodynamic lift type main machine body 1；It is disposed with the tail end of aerodynamic lift type main machine body 1
Empennage 3；
Two micro- splash planing hulls 6 are arranged on 1 bottom of aerodynamic lift type main machine body longitudinal direction both sides, two micro- splash planing hulls
6 be connected with aerodynamic lift type main machine body 1 after form longitudinal pneumatic channel 5；Aerodynamic lift type main machine body 1 is provided with reversed profile
Faulted-stage 7, by aerodynamic lift type main machine body, 1 point is precursor and rear body.
2. a kind of micro- splash high performance catamaran amphibious aircraft according to claim 1, it is characterised in that：Aerodynamic lift type
Length-width ratio L/B of main machine body 1 is 4.68, and half-breadth B2 of pneumatic channel 5 is 1 with the width B1 ratios of micro- splash planing hull 6, gas
The ratio of the forebody length L1 and afterbody length degree L2 of dynamic lift type main machine body 1 is 1.
3. a kind of micro- splash high performance catamaran amphibious aircraft according to claim 1 or claim 2, it is characterised in that：It is reversely disconnected
The ratio of the height h1 and 1 width B of aerodynamic lift type main machine body of rank 7 is 0.23%, and 7 inclination angle of antithetic fault terrace is 4 °.
4. a kind of micro- splash high performance catamaran amphibious aircraft according to claim 1, it is characterised in that：Micro- splash is slided
6 bottom of hull is disposed with transverse curvature planing surface 8 and lower transverse curvature planing surface on precursor planing surface from inside to outside
9, upper transverse curvature planing surface 8 and lower transverse curvature planing surface 9 are lower concave curved surface.
5. a kind of micro- splash high performance catamaran amphibious aircraft according to claim 4, it is characterised in that：Upper transverse curvature
The radius of curvature R 1 of planing surface 8 is 6% with 1 width B ratios of aerodynamic lift type main machine body, the curvature of lower transverse curvature planing surface 9
Radius R2 is 10% with 1 width B ratios of aerodynamic lift type main machine body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611093860.XA CN106516109B (en) | 2016-12-02 | 2016-12-02 | A kind of micro- splash high performance catamaran amphibious aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611093860.XA CN106516109B (en) | 2016-12-02 | 2016-12-02 | A kind of micro- splash high performance catamaran amphibious aircraft |
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| CN106516109A true CN106516109A (en) | 2017-03-22 |
| CN106516109B CN106516109B (en) | 2018-10-12 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573025A (en) * | 2018-11-02 | 2019-04-05 | 中国特种飞行器研究所 | It is a kind of quickly to support the land-effect plane ensured for marine |
| 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 |
| CN109606676A (en) * | 2018-12-14 | 2019-04-12 | 中国特种飞行器研究所 | A kind of tandem wing formula amphibious aircraft |
| CN110920883A (en) * | 2019-12-05 | 2020-03-27 | 中国特种飞行器研究所 | Three-stage speed-reducing water-landing seaplane |
| 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 |
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|---|---|---|---|---|
| GB2120990A (en) * | 1982-05-28 | 1983-12-14 | Kjoelseth Paul | Ground effect vehicle or aerofoil boat |
| US4691881A (en) * | 1985-10-08 | 1987-09-08 | Gioia G Leonard | High performance amphibious airplane |
| US6290174B1 (en) * | 1998-08-27 | 2001-09-18 | G. Leonard Gioia | Amphibious aircraft with aerodynamic/hydrodynamic sponsons |
| CN203111444U (en) * | 2013-03-06 | 2013-08-07 | 中国船舶重工集团公司第七○二研究所 | Half-small waterplane area twin-hull ship |
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2016
- 2016-12-02 CN CN201611093860.XA patent/CN106516109B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2120990A (en) * | 1982-05-28 | 1983-12-14 | Kjoelseth Paul | Ground effect vehicle or aerofoil boat |
| US4691881A (en) * | 1985-10-08 | 1987-09-08 | Gioia G Leonard | High performance amphibious airplane |
| US6290174B1 (en) * | 1998-08-27 | 2001-09-18 | G. Leonard Gioia | Amphibious aircraft with aerodynamic/hydrodynamic sponsons |
| CN203111444U (en) * | 2013-03-06 | 2013-08-07 | 中国船舶重工集团公司第七○二研究所 | Half-small waterplane area twin-hull ship |
Cited By (6)
| 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 |
| CN109573025A (en) * | 2018-11-02 | 2019-04-05 | 中国特种飞行器研究所 | It is a kind of quickly to support the land-effect plane ensured for marine |
| CN109606676A (en) * | 2018-12-14 | 2019-04-12 | 中国特种飞行器研究所 | A kind of tandem wing formula amphibious aircraft |
| CN110920883A (en) * | 2019-12-05 | 2020-03-27 | 中国特种飞行器研究所 | Three-stage speed-reducing water-landing seaplane |
| 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 |
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| Publication number | Publication date |
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| CN106516109B (en) | 2018-10-12 |
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Inventor after: Wu Bin Inventor after: Liu Tao Inventor after: Tang Binbin Inventor after: Cao Kai Inventor after: Wang Lili Inventor before: Wu Bin Inventor before: Liu Tao Inventor before: Tang Binbin Inventor before: Cao Kai Inventor before: Wang Lili |
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