CN109850112A - A kind of floating integrated aircraft of upper inverse taper liter - Google Patents
A kind of floating integrated aircraft of upper inverse taper liter Download PDFInfo
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- 238000005183 dynamical system Methods 0.000 claims abstract description 5
- 241000755266 Kathetostoma giganteum Species 0.000 claims abstract description 3
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Abstract
A kind of upper inverse taper of the present invention rises floating integrated aircraft, including body, dynamical system, body includes the head in the preceding storehouse of carrying device and the tail portion of tail engine bin box, under overlooking state, head is flat-head shape, tail portion outer end forms body aerofoil profile using lateral lacing wire structure using inverse taper shape in the class of sweepforward, internal body space, and the centre of body is provided with upper inverse taper sky nest up and down.Tack and upper inverse taper body shape increase the ratio of air dynamic lift and quiet buoyancy, improve flying speed and wind loading rating, reduce resistance；The setting in aerofoil profile and the preceding storehouse of equipment and rear engine storehouse box further corrects non-rigid body because of aerofoil profile distortion caused by inflating body deformation and motion deformation；The elevator for the both ends lordosis installed at trailing edge/aileron mixing control rudder face, effectively improve rudder effectiveness, body uses double layer material, it is ensured that improves the flatness and anti-puncture intensity of body.
Description
Technical field
The invention belongs to vehicle technology fields, and in particular to a kind of upper floating integrated aircraft of inverse taper liter.
Background technique
In recent years, the unmanned vehicle constantly risen because cost that it has it is low, it is easy to operate, have high flexibility and
It can be increasingly widely used by all trades and professions with the features such as hedgehopping, existing most of unmanned vehicles are mainly answered
For fields such as scientific research, geographical detection, agricultural plant protection, security protection monitoring and video captures.
Have airborne period long by traditional aerostatics of representative of dirigible, have a safety feature, the features such as specific fuel consumption is low,
The military domains such as civil fields and seashore monitoring, air-borne early warning such as transport in the sky, communication relaying suffer from extensive purposes.But
Traditional aerostatics rely primarily on it is internal full of lighter-than-air gas generate buoyancy lift-off, lift and aircraft volume size at
Direct ratio must just increase the size of aircraft to increase load, especially true in the lesser stratosphere of atmospheric density；And mistake
Big size often will increase flight resistance, reduce movement velocity, the even more than limit of envelop materials tension.The present inventor it
The patent of invention of the Patent No. 2015105557995 of preceding application is found in actual fabrication with during taking a flight test, the liter of the structure
Floating one aircraft has that wind loading rating difference and Project Realization are difficult, it is necessary to redesign to former scheme.It sends out thus
A kind of floating integrated aircraft of upper inverse taper liter is illustrated.
Summary of the invention
Aiming at the problems existing in the prior art, the purpose of the present invention is to provide a kind of upper inverse tapers to rise floating one flight
Device, pneumatic efficiency, flight stability, structural strength and wind loading rating of the aircraft etc. are greatly improved.Suitable for
A variety of airspaces such as low latitude, stratosphere execute multiple-task, can select to fill helium to body according to user task and convenience needs
Or fill air.
The present invention is realized by the following technical programs:
A kind of upper inverse taper rises floating integrated aircraft, it is characterised in that aircraft includes body, is arranged on body
Dynamical system, the body have head and tail portion, and the head is provided with the preceding storehouse of equipment, and tail portion is provided with rear engine storehouse
Box, under overlooking state, head is flat-head shape, tail portion outer end using inverse taper shape in the class of sweepforward, the body by eight or
Multi-disc gummed cloth heat seal is welded, the lateral lacing wire structure formation body aerofoil profile of internal body space use, in the body
Between be provided with space of the upper inverse taper sky nest as load-accommodating up and down.
A kind of described upper inverse taper rises floating integrated aircraft, it is characterised in that the body made of double layer material and
At cladding material is using the elastic smaller and preferable light material of intensity with extensibility；Internal layer is using the biggish airtight material of elasticity
Material, cladding material are fixed by the open pore that inner layer material sticking patch bar passes through outer layer again.The setting can effectively improve body
Depression problem at integral smoothness and anti-puncture intensity and solution body sky nest.
A kind of upper inverse taper rises floating integrated aircraft, it is characterised in that the dynamical system includes being mounted on body
The engine of tail portion and front, installing is forward concave arc shape among the body tail portion of odd number engine, installs even number engine
Body tail portion among be straight rear.
A kind of upper inverse taper rises floating integrated aircraft, it is characterised in that the body longitudinal cross-section is using relatively thick
Spend larger while more efficient aerofoil profile MT722.The aerofoil profile can effectively increase aircraft interior volume, further increase quiet buoyancy.
A kind of upper inverse taper rises floating integrated aircraft, it is characterised in that the preceding storehouse shape of equipment is aerofoil profile leading edge
Shape, rear engine storehouse box shaped are close conformal with airfoil trailing edge.Using the preceding storehouse of equipment and rear engine storehouse box, further
Non-rigid body is corrected because of aerofoil profile distortion caused by deforming when body is inflated and is moved.
A kind of upper inverse taper rises floating integrated aircraft, it is characterised in that rear of the body tail portion or so is external
Elevator/aileron mixing control rudder face of both ends lordosis is installed.The setting can reduce thick wing body and go up and down to aircraft tail portion
The influence of rudder/aileron pneumatic efficiency, and then improve rudder effectiveness.
A kind of upper inverse taper rises floating integrated aircraft, it is characterised in that the upper inverse taper sky nest is vertical by what is holded up
The foldable rigid truss structure of body is formed, which includes upper support frame and lower bracing frame, the upper support frame and lower branch
Longitudinal bracing frame is detachably provided between support, the upper support frame and lower bracing frame are detachably arranged with body.It is upper anti-
The setting of trapezoidal sky nest, which can lower the resistance of carrying task load and its interior shelf, can effectively reinforce body resistance to deformation energy
Power.
A kind of upper inverse taper rises floating integrated aircraft, it is characterised in that the upper inverse taper sky nest top is equipped with upper
Cover board, lower part are equipped with lower magazine.The setting of upper cover plate and lower magazine convenient for handling goods and mission payload and keeps body shape
Integrality.
A kind of upper inverse taper rises floating integrated aircraft, it is characterised in that the type of installation even number engine is equipped with
Single vertical fin and rudder are equipped with a piece of or two-piece type elevator among tail portion；The type tail portion installation of odd number engine is installed
There is twin vertical fin, tailplane and elevator are between twin vertical fin.
Structure of the invention is novel, design is reasonable, and each structure member is equipped with, and can be improved and rises floating resistance ratio, wind loading rating；
The setting of lateral lacing wire can also simplify Project Realization technique while mitigating body weight, increasing housing construction intensity.
Detailed description of the invention
Fig. 1 is the overall structure diagram of twin vertical fin body of the present invention；
Fig. 2 is the structural schematic diagram of Fig. 1 not ipsilateral；
Fig. 3 is the structural schematic diagram of the single vertical fin body of the present invention；
Fig. 4 is the structural schematic diagram of Fig. 3 not ipsilateral；
Fig. 5-Fig. 6 is partial internal structure schematic diagram；
Fig. 7 is body outer layer unfolding assumption diagram；
Fig. 8 is body internal layer unfolding assumption diagram；
Fig. 9-Figure 10 is that the structural schematic diagram on body is arranged in lateral lacing wire；
Figure 11-Figure 12 is truss structure schematic diagram；
Figure 13-Figure 14 extends the structural schematic diagram on type different directions
Figure 15 is that air-flow is attached to the schematic diagram on conventional dalta wing；
Figure 16 is that air-flow is attached to the schematic diagram on dalta wing after cutting off；
State of flight figure of the Figure 17 for the aircraft compared with thick wing type under big-elevation state；
Figure 18-Figure 19 is state of flight figure of the aircraft in 40 ° of angles of attack；
Figure 20 is body layer materials attachment structure schematic diagram.
Specific embodiment
Below in conjunction with Figure of description, the invention will be described in further detail, and provides specific embodiment.
A kind of upper inverse taper of the present invention rises floating integrated aircraft, and overall mechanism is shown in that Fig. 1-Fig. 4, including body, setting exist
Dynamical system on body, body have head and tail portion, and the head is provided with the preceding storehouse of equipment, and tail portion is provided with tail portion and starts
Cabin box, 1 plan view shape of body uses tack, and the upper inverse taper body shape of tail portion outer end sweepforward, body 1 are faced shape and adopted
With mimetic design on two sides, Fig. 2 and Fig. 4 are seen；Install odd number engine body tail portion among have forward concave arc shape, see Fig. 1 and
Fig. 2, installing among the body tail portion of even number engine is straight rear, sees Fig. 3 and Fig. 4；Body longitudinal cross-section is using relatively thick
Larger while more efficient aerofoil profile MT722 is spent, sees Fig. 2 and Fig. 4, the ratio of air dynamic lift and quiet buoyancy is increased, improves
Flying speed, flight stability and wind loading rating, and reduce resistance；The preceding storehouse shape of equipment and aerofoil profile leading edge are conformal, tail portion
Engine bin box shaped and airfoil trailing edge are conformal, using the preceding storehouse 2 of equipment and rear engine storehouse box 3, correct non-rigid body because
Aerofoil profile caused by deformation is distorted when body inflation and movement, and the preceding storehouse shape of equipment task is aerofoil profile leading edge shape and is installed on body
Front end, rear engine storehouse shape are close to airfoil trailing edge shape and to be installed on body tail portion；Because thick wing type body is to aircraft
Tail portion elevator/aileron pneumatic efficiency is affected, to improve the external liter for being equipped with both ends lordosis of rudder effectiveness trailing edge or so
Rudder/aileron mixing control rudder face 7 is dropped, sees Fig. 2 and Fig. 4.The type of installation even number engine is equipped with single vertical fin and rudder, tail
A piece of or two-piece type elevator is installed among portion.The type tail portion of installation odd number engine is equipped with twin vertical fin, tailplane
And elevator is between twin vertical fin.
As seen in figs. 5-6, in order to lower the resistance and reinforcement body non-deformability that carry mission payload, have among body
Space of the trapezoidal empty nest 5 in inside up and down as load-accommodating, sees Fig. 5 and Fig. 6, and using the solid of new intermediate riser
Foldable rigid truss structure enhancing complete machine rigidity, is shown in Figure 10-12, for the flatness and anti-puncture intensity and solution of raising body
Certainly the depression problem at body sky nest 5, body are made of the double-deck different materials, and body outer layer is smaller simultaneously using elasticity and extensibility
And the preferable light material of intensity, internal layer select the biggish gastight material of elasticity, see Fig. 6 to Figure 10.
In order to simplify body moulding process, body it is wing be formed by lateral 4 frame mode of lacing wire, body shape uses
Eight or multi-disc gummed cloth heat seal are welded, and see Fig. 8 to Figure 10, and the centre of body is provided with the sky of upper inverse taper up and down
Space of the nest as load-accommodating, upper inverse taper sky nest 5 are formed by the stereo foldable rigid truss structure holded up, the truss knot
Structure includes upper support frame 8 and lower bracing frame 9, and longitudinal bracing frame 10 is detachably provided between upper support frame 8 and lower bracing frame 9,
Upper support frame 8 and lower bracing frame 9 are detachably arranged with body.For the ease of handling goods and mission payload and keep outside body
Shape integrality, empty 5 top of nest are equipped with upper cover plate 11, and lower part is equipped with lower magazine 12.
In order to adapt to different levels user and different application scene, upper inverse taper is risen floating integrated aircraft and is set using modularization
Meter theory, the seriation for forming the generally applicable exchange of most of module extend type, see Figure 13 to Figure 14, are included in inflation body dress
Upper ship type chassis 16 forms amphibious type, further increases pneumatic liter rising floating integrated aircraft trailing edge installation cross flow fan 17
Power can especially significantly improve the flow separation phenomenon etc. of the top airfoil in High Angle of Attack.
A kind of mixing that floating integrated aircraft is a kind of aerodynamic lift by when moving and the quiet buoyancy of air combines is risen to fly
Row device.In order to make internal body of aircraft while with stronger dynamic lift effect with the quiet buoyancy of generation as big as possible
Volume, and then obtain the more excellent entirety for the performance that more preferably flies at low speed compared to traditional dirigible smaller size smaller and compared to fixed-wing
Lift effect, while should take into account preferable aeroperformance on body and whole Design of Aerodynamic Configuration, body has again
Biggish body surface plot ratio.It by CFD analogue simulation and calculates and actually takes a flight test, and comprehensively consider raising structural strength
Weight ratio and simplified actual processing technique etc. require, and carry out Optimized System Design on this basis, propose vertical view shape
Shape uses tack, and the body shape design scheme of tail portion outer end sweepforward.Global shape such as Fig. 1 and Fig. 3.
Body type selecting
In order to improve the plot ratio of aircraft, aircraft is using lifting body (fuselage and wing are integrated) scheme and uses thick wing type
MT722.In order to guarantee the dynamic lift performance of body, need to improve as far as possible aerofoil profile extend to integrality, and also to
Material the piece number as few as possible is combined into body shape, and body plan view shape is made into tack thus (see Fig. 1 and Fig. 3).Due to
Entire MT722 profile lift body After-Body is relatively thin, causes vertical cross-section direction rigidly poor, is easy to produce on wing both ends
Lower swing, body rear is designed using sweepforward thus, installs stabilization zone to form a triangle rigid support in After-Body
Domain.(see Fig. 1, Fig. 2, Fig. 3, Fig. 4 and Figure 11).Body and rigid support are fixed using sticking patch.Entire body forms one above instead
Trapezoidal shape.So simultaneously also bring improve body surface plot ratio benefit, can reduce while improving buoyancy used in
The area of material, and then mitigate body weight.
Upper anti-tack rises floating all-in-one machine shape to the principle in terms of raising aeroperformance:
Upper anti-tack rises floating all-in-one machine shape and is actually similar to cutting head (root) dalta wing, cut that root dalta wing has compared with
Principle of the lift resistance ratio compared with dalta wing preferably, is also suitble to herein under low-speed situations.
After why dalta wing cuts root (head), the lift resistance ratio of subsonic speed state also increases, this will be from dalta wing
Feature is talked about.Air-flow below dalta wing upward surface rollers under pressure, form many weak whirlpool beams.In the little angle of attack
Under, just produce the separation of leading edge air-flow.If air-flow is attached to leading edge, that can generate leading edge suction, and being equivalent to reduces resistance.
But due to being easy to the separation of leading edge air-flow occurs for dalta wing, this effectively lowers leading edge suctions, increase resistance.And it is preceding
Edge air-flow separation vortex also generates very big induced drag, this is also the unfavorable one side of dalta wing, such as Figure 15.
It is big to solve dalta wing subsonic speed induced drag, the lower problem of lift resistance ratio.One means is permanent twist, is improved
Its pressure is opened up to distribution (such as J10).Second is that configuration droope snoot and trailing edge flap, allowing wing to become bent curvature wing.This two
A method is larger for the machine-shaping difficulty of flexible body, cannot use.
Third method is exactly to cut root (cutting head).By reducing root (head) angle of sweep, separation delay occurs, and protects
Leading edge suction is held, resistance is reduced.And then its lift resistance ratio that cruises, such as Figure 16 just can be improved.It can be seen that intermediate region is extended to maintaining
Complete air foil shape, air-flow can produce preferable lift effect by this region.Furthermore using external upper mimetic design obtain compared with
The thickness that both ends wing is reduced while good roll stability, to further decreasing induced drag advantageously.Simultaneously also
The benefit for improving body surface plot ratio is brought, the area of material therefor can be reduced while improving buoyancy, and then mitigate
Body weight.
Body forming:
Guarantee that flexible machine body forms good aerodynamic configuration, is a relatively difficult job.Inverse taper shape in selection, greatly
Forming difficulty is simplified greatly.Body gas impermeable surfaces are welded by 8 gastight materials, see Fig. 8, B3 and B1 weld, A2 with
A1 welding, A1 and the front B1 or tail portion are welded, and after having welded corresponding lacing wire 4 up and down, C1 is welded with A2 and B3 respectively, are finally welded
Connect tail portion or front sealing.
Good aerodynamic configuration is formed, other than body shape, also wants to be produced with flexible material few as far as possible
It is more crucial that body section meets selected air foil shape.Here the wing of body section is realized using the method for internal lacing wire 4
Type shape is shown in Figure 10.But spherical form can be tended to after flexible body inflation, lacing wire is few, and the spherical surface of body protrusion will become larger,
Distorting transformation if lacing wire is overstocked and will increase weight with regard to big, and furthermore the arrangement density of lacing wire and direction can all influence body
Section forming.
The implementation method of " non-dominated ranking algorithm (NSGA_II) " Lai Youhua aerofoil profile machine-shaping is employed herein.
The initial configuration of inflatable wing models
Firstly, the region between two neighboring lacing wire is defined as a unit, 4 unit number of lacing wire is set as N,
The initial level coordinate value at each garden center is provided in two-dimensional surface referential, wherein coordinate origin is arranged in aerofoil profile wheel
Then wide most leading edge according to the tangent position relationship between circular arc and aerofoil profile baseline, can calculate ordinate and radius
Value,
However, the coordinate value in the initial center of circle by limit in a limitation range so that two have the adjacent gardens of tangential relationship
Can clearly it intersect, and these gardens cover the area of inflatable airfoil section as much as possible.
The elevator of both ends lordosis/aileron mixing control rudder face
Since in order to improve plot ratio, body is used compared with thick wing type.Compared with thick wing type can to tail portion generate block, especially compared with
When high-angle-of-attack flight, big chord length lifting body (wing) can generate flow separation phenomenon, these factors can all greatly reduce lifting
Rudder/aileron mixing control rudder face 2 control efficiency, is shown in Figure 17.
Using elevator/aileron mixing control rudder face of both ends lordosis, its both ends is extended to body left and right ends,
Make rudder face directly facing air-flow, significantly improves control efficiency referring to Figure 16 and Fig. 7.The rudder face of lordosis also plays trim simultaneously
The effect of rudder face control moment.
The design of load storehouse and realization in the middle part of body
In order to lower the resistance and reinforcement body non-deformability that carry mission payload, distractive load, will to the active force of body
Only organism bottom carrying becomes up and down bearing load active force simultaneously.There is the trapezoidal empty nest in inside up and down to make among body
For the space of load-accommodating, Fig. 5, Fig. 6 and Figure 10 are seen, and increased using the quick disassembled rigid truss structure of solid of new intermediate riser
Strong complete machine rigidity, is shown in Figure 11 and Figure 12, for the ease of handling goods and mission payload and body shape integrality is kept, on empty nest
Portion is equipped with upper cover plate 11, and lower part is equipped with lower magazine 12.
An advantage for rising floating integrated aircraft is exactly that can realize biggish load with the power of equal-wattage, if larger
Load all using plug-in or be loaded into the plug-in case specially designed, the aerodynamic configuration of entire body will certainly be destroyed, caused
Resistance increases considerably, and lift is greatly lowered, and also will increase construction weight and processing cost.Therefore design cabinet load
Empty nest storehouse is very important, although empty nest can occupy charging volume among body, compared to using plug-in mode bring gas
The loss of dynamic performance is much smaller to overall performance impact, and when application scenarios need flying height higher, empty nest storehouse can
Position as reserved installation balloonet.
Empty nest is designed to up-small and down-big trapezium structure, sees Fig. 5, Fig. 6, Fig. 8 and Figure 10, is because upper small can subtract as far as possible
Small upper opening is big and influences the upper surface shape of body, lower to increase the size that can carry mission payload as far as possible greatly, simultaneously
Trapezium structure is also beneficial to more consolidate when installation internal stent, and bracket can play the role of following referring to Figure 12 and Figure 13:
1) load-carrying construction that can be used as load becomes body by the power that load can be acted on merely organism bottom by bracket
Upper and lower surface while stress.
2) the rigid support skeleton of entire body can be become three-dimensional from two dimension, increase entire body resistance to deformation by bracket
Ability.
Empty nest is welded to each other by four pieces of gummed cloths and is welded again with body, and bracket is connect with body by sticking patch, sees
Fig. 8.Cladding material is made using the elastic smaller and preferable light material of intensity with extensibility by double layer material in body；Internal layer is adopted
With the biggish gastight material of elasticity, cladding material is fixed by the open pore that inner layer material sticking patch bar passes through outer layer again, is such as schemed
Shown in 20.
Body flatness is solved by the way of the double-deck organism material in the invention, improve anti-puncture intensity with
And the problems such as being recessed at body sky nest, body is made of the double-deck different materials, and body outer layer is using the lesser material of elasticity, internal layer
The biggish gastight material of elasticity is selected, sees Fig. 6 to Figure 10.
Body flatness problem
From the foregoing it will be appreciated that form the air foil shape of body, needs to constrain body using modes such as lacing wires and generated because of inflation
Deformation, and then form ideal body (wing) aerofoil profile, be welded on fuselage by making lacing wire according to aforementioned algorism
It is interior, in the case where using material less as far as possible, the body section shape close to ideal airfoil profile can be formed, but body surface is difficult at all
Wavy fluctuating is eliminated, sees Figure 10, such case will lead to the increase of body drag.Using elasticity, extensibility is lesser light
Matter exterior material can play the function served as bridge across recess, so that body is smoothened.
Improve anti-puncture ability
Floating integrated aircraft is risen to need to keep the gas of certain pressure to keep certain buoyancy and body shape in internal body,
If body just touches sharp objects when shock occurs, scratches, it is likely that cause body to perforate or tear, lead
The leakage of internal body gas is caused, buoyancy is caused to decline, shape changes, it is difficult to continue flight even air crash.Using elasticity, extensibility
The preferable lightweight exterior material safeguard measure of smaller and intensity, will be very useful.
Depression problem at body sky nest
It has been observed that body of the present invention is using intermediate empty nest design, inflation space-time nest edge will form recess, see Figure 10, in this way meeting
The air foil shape for seriously affecting body in turn results in aeroperformance variation.Thus using elasticity, outside the lesser lightweight of extensibility
Material can also play the function served as bridge across recess.Debugging in order to facilitate internal stent installation and to mission payload, it is external
Organism material is driveed there are two hole.Since rigid hatchcover is arranged at lower part, external engine body material is provided with and empty nest bottom in empty nest lower part
The identical hole of size.
External engine body material and inner body are without being directly connected to, only at the patch location both ends of bracket connection inner body
It is all provided with a pair of holes, so that bracket passes through, while ectonexine organism material being clamped.
External engine body material cut out size according to certain gas pressure lower outer portion and inner body material elasticity and stretch
Malleability performance difference determines the size magnification ratio of external engine body material.
Serial expanded type is formed by installation disparate modules
In order to adapt to different levels user and different application scene, the upper inverse taper, which rises floating integrated aircraft, can both fill helium
Air can also be filled, and uses modular design concept, the seriation type of the generally applicable exchange of most of module is formed, sees figure
13 to Figure 14.It is included in the inflation body type chassis 16 that takes on board and forms amphibious type, floating integrated aircraft trailing edge installation is horizontal rising
Flow fan 17 further increases aerodynamic lift, can especially significantly improve the airflow diversion phenomenon of the top airfoil in High Angle of Attack
Deng.
Figure 18-Figure 19 illustrates the aircraft in 40 ° of angles of attack, and embedded horizontal flow fan is closed and opened in the case of two kinds
Flow Field Distribution situation, obviously there is air-flow and separates to form stall in Figure 18, and Figure 19 does not occur stall then.
Cross flow fan has been applied to multiple fields, such as air-conditioning, and there have been the aircraft using cross flow fan in foreign countries, but
There are no being applied to rise by cross flow fan to float integrated aircraft, Figure 13 is seen.
Cross flow fan can also be the same with other component module in the connection for rising floating integrated aircraft, first connects right with bracket
After-poppet is connect by sticking patch with body.
For the demand in response to the scenes fishery and tourist industry such as ocean and North America Great Lakes, ship type machine can be installed in underpart
Capsule, Figure 13 and Figure 14, the same other component of connection type, are connected to body by bracket and sticking patch.Since body sheet is as filling
Mechanism of qi body, therefore buoyancy waterborne is very big, has enough safetybuoyance deposits.
Claims (9)
1. a kind of upper inverse taper rises floating integrated aircraft, it is characterised in that including body (1), the power being arranged on body (1)
System, the body (1) have head and tail portion, and the head is provided with the preceding storehouse of equipment (2), and tail portion is provided with rear engine
Storehouse box (3), under overlooking state, head is flat-head shape, and using inverse taper shape in the class of sweepforward, the body (1) is logical for tail portion outer end
It crosses eight or multi-disc gummed cloth heat seal is welded, body (1) inner space forms the body wing using lateral lacing wire (4) structure
Type, the centre of the body (1) are provided with space of the upper inverse taper sky nest (5) as load-accommodating up and down.
2. a kind of upper inverse taper as described in claim 1 rises floating integrated aircraft, it is characterised in that the body (1) is using double
Layer material is made, and cladding material is using the elastic smaller and preferable light material of intensity with extensibility；Internal layer is using elasticity
Biggish gastight material, cladding material are fixed by the open pore that inner layer material sticking patch bar passes through outer layer again.
3. a kind of upper inverse taper as described in claim 1 rises floating integrated aircraft, it is characterised in that the dynamical system includes
It is mounted on the engine of body tail portion and front, installing is forward concave arc shape (6), peace among the body tail portion of odd number engine
Filling is straight trailing edge among the body tail portion of even number engine.
4. a kind of upper inverse taper as described in claim 1 rises floating integrated aircraft, it is characterised in that the body (1) is longitudinally cut
Face uses area larger while the aerofoil profile MT722 of more efficient.
5. a kind of upper inverse taper as described in claim 1 rises floating integrated aircraft, it is characterised in that the preceding storehouse of equipment (2) is
Conformal with aerofoil profile, shape is aerofoil profile leading edge, and rear engine storehouse box (3) is equally conformal with aerofoil profile, and shape is close to airfoil trailing edge.
6. a kind of upper inverse taper as described in claim 1 rises floating integrated aircraft, it is characterised in that body (1) tail portion
Elevator/aileron mixing control rudder face (7) of both ends lordosis is installed outside rear or so.
7. a kind of upper inverse taper as described in claim 1 rises floating integrated aircraft, it is characterised in that the upper inverse taper sky nest
(5) it is formed by the stereo foldable rigid truss structure holded up, which includes upper support frame (8) and lower bracing frame (9),
Detachably be provided with longitudinal bracing frame (10) between the upper support frame (8) and lower bracing frame (9), the upper support frame (8) and
Lower bracing frame (9) is detachably arranged with body (1).
8. a kind of upper inverse taper as described in claim 1 rises floating integrated aircraft, it is characterised in that the upper inverse taper sky nest
(5) top is equipped with upper cover plate (11), and lower part is equipped with lower magazine (12).
9. a kind of upper inverse taper as claimed in claim 3 rises floating integrated aircraft, it is characterised in that installation even number engine
Type is equipped with single vertical fin (13) and rudder, and a piece of or two-piece type elevator (14) is equipped among tail portion；Odd number hair is installed
The type tail portion of motivation is equipped with twin vertical fin (15), and tailplane and elevator are between twin vertical fin.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910193977.2A CN109850112A (en) | 2019-03-14 | 2019-03-14 | A kind of floating integrated aircraft of upper inverse taper liter |
| PCT/CN2019/124804 WO2020181855A1 (en) | 2019-03-14 | 2019-12-12 | Dihedral trapezoidal lifting and floating integrated aircraft |
| CA3132892A CA3132892C (en) | 2019-03-14 | 2019-12-12 | Dihedral trapezoidal lifting and floating integrated aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910193977.2A CN109850112A (en) | 2019-03-14 | 2019-03-14 | A kind of floating integrated aircraft of upper inverse taper liter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109850112A true CN109850112A (en) | 2019-06-07 |
Family
ID=66900937
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910193977.2A Withdrawn CN109850112A (en) | 2019-03-14 | 2019-03-14 | A kind of floating integrated aircraft of upper inverse taper liter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109850112A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020181855A1 (en) * | 2019-03-14 | 2020-09-17 | 杭州佳翼科技有限公司 | Dihedral trapezoidal lifting and floating integrated aircraft |
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Application publication date: 20190607 |