CN207045727U - A kind of aircraft - Google Patents
A kind of aircraft Download PDFInfo
- Publication number
- CN207045727U CN207045727U CN201720856289.6U CN201720856289U CN207045727U CN 207045727 U CN207045727 U CN 207045727U CN 201720856289 U CN201720856289 U CN 201720856289U CN 207045727 U CN207045727 U CN 207045727U
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- Prior art keywords
- wing
- fixed
- spiral shell
- aircraft
- rotation spiral
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Abstract
The utility model discloses a kind of aircraft, including set, structure identical upper strata fixed-wing, lower floor's fixed-wing relatively；The main machine body being connected and installed between upper strata fixed-wing and lower floor's fixed-wing；The empennage being installed in main machine body；And be installed on upper strata fixed-wing and lower floor's fixed-wing, the rotation spiral shell wing of flying power is provided for aircraft.Wherein, the front and rear edges in the left wing face of upper strata fixed-wing is symmetrically provided with rotation spiral shell wing, and on upper strata, the front and rear edges in the right flank face of fixed-wing is symmetrically provided with rotation spiral shell wing；Front and rear edges in fixed-wing left wing of lower floor face is symmetrically provided with rotation spiral shell wing, and the front and rear edges in the right flank face of lower floor's fixed-wing is symmetrically provided with rotation spiral shell wing.Aircraft of the present utility model using " double-deck fixed-wing+eight revolve spiral shell wing " mixing wing distribution form so that aircraft can realize VTOL, fly after lift-off the fuselage that steadily can little by little vert is flat, be changed into fixed-wing flight.
Description
Technical field
Aircraft field is the utility model is related to, more particularly to a kind of eight rotations spiral shell wing combines double-deck fixed-wing VTOL
Aircraft.
Background technology
Although the growth momentum of current civilian unmanned plane is violent, the market demand is vast, also runs into huge neck bottle.Nobody
Application " pain spot " of the machine in professional domain：Landing spatial domain is smaller and the project of the long endurance of demand, fixed-wing unmanned plane can not landing,
Helicopter or more rotation spiral shell wings are simple, and landing is convenient, but speed is slow, endurance is too short, can not meet endurance demand, wind loading rating
Low, unmanned plane " has more than is needed "；Helicopter, although landing is convenient, price, and also it is complicated, cost is of a relatively high, and
Then partially expensive when the rotation same quality of spiral shell wing unmanned plane is somewhat better more, unmanned plane " can not afford "；Unmanned plane is bought back home, finds nothing
It is man-machine complicated, it is cumbersome, how to use all " with bad ", it is desirable to it is also difficult to cultivate a high-quality winged hand；
Fixed-wing unmanned plane, endurance is long, speed is fast, but landing is inconvenient, causes user same " with bad ".Have only and create endurance
Length, VTOL, simple in construction, simple to operate, cheap unmanned plane, have concurrently fixed-wing unmanned plane endurance is long, speed is high,
Apart from it is remote the characteristics of and rotation spiral shell wing unmanned plane VTOL fly flexible function, meet the needs of user, could really solve
" pain spot " of industry-level unmanned plane.
But it is so simple to realize that VTOL is easy to be not intended to as in, and countless talentes open brain hole greatly in history, design
Many schemes.Wherein the most famous as shown in Fig. 1 U.S. V-22 " osprey " opportunity of combat, its landing solution are the rotation spiral shells that verts
The wing, revolve spiral shell wing vertically upward when taking off, spiral shell wing is revolved after lift-off and is slowly reversed forwards, is deformed into fixed-wing.Undoubtedly this is a kind of
Very first and then cleverly VTOL fixed-wing pattern, exactly because but it is also too first and then ingenious, so expensive and complicated,
The problem of in use, is quite a few." osprey " is just incomparable bumpy on the road of development, even if still accident is continuous after volume production, is especially hanging down
It is straight to turn easily to fall in flat winged transition, allow U.S. army pilot often " how sad that he had to die before he gained victory ".
And another famous solution is exactly " 1+1 types ", as shown in Fig. 2 simple superposition on fixed wing aircraft
A set of vertical lift system is simple and crude effective.Such as " No. four tasks " of shown Chinese nineteen sixty-eight, the scheme finally determined
It is exactly this：It will destroy and four lift fans are filled in -6 opportunities of combat.It is four rotation spiral shell wings when such landing, it is fighter plane to put down when flying.
There are many unmanned plane enterprises to use similar system in research and development both at home and abroad now.This is a kind of relatively safe scheme, a side
Face does not need complicated vector spray or verts rotation spiral shell wing technology；On the one hand it is vertical to turn easily to keep in flat winged handoff procedure
Vertical lift.But shortcoming is also apparent from：It is heavy！Also weight is wasted with heavy vertical lift component when flat winged, increased again
Big resistance.Can have a significant impact to flying quality.
A kind of hence it is highly desirable to type aircraft for overcoming all types of scheme defects of the above in a simple and reliable way.
Utility model content
In view of the shortcomings of the prior art, the purpose of this utility model aims to provide a kind of simple in construction, and vertical rise can be achieved
The aircraft of drop.
To achieve the above object, the utility model adopts the following technical scheme that：
A kind of aircraft, including upper strata fixed-wing, lower floor's fixed-wing relative and set；Be connected and installed in upper strata fixed-wing and
Main machine body between lower floor's fixed-wing；The empennage being installed in main machine body；And it is installed on upper strata fixed-wing and lower floor's fixed-wing
On, the rotation spiral shell wing of flying power is provided for aircraft；Wherein, the front and rear edges in the left wing face of upper strata fixed-wing is symmetrically provided with
Spiral shell wing is revolved, the front and rear edges in the right flank face of fixed-wing is symmetrically provided with rotation spiral shell wing on upper strata；In fixed-wing left wing of lower floor face
Front and rear edges is symmetrically provided with rotation spiral shell wing, and the front and rear edges in the right flank face of lower floor's fixed-wing is symmetrically provided with rotation spiral shell wing.
Front and rear edges in the middle part of the lower surface in the left wing face of the upper strata fixed-wing is symmetrically provided with a pair of rotation spiral shell wings,
Front and rear edges in the middle part of the lower surface in the right flank face of upper strata fixed-wing is symmetrically provided with a pair of rotation spiral shell wings；In lower floor's fixed-wing
The front and rear edges of the upper surface middle part in left wing face is symmetrically provided with a pair of rotation spiral shell wings, the upper table in the right flank face of lower floor's fixed-wing
The front and rear edges of Middle face is symmetrically provided with a pair of rotation spiral shell wings.
The axial direction of the rotation spiral shell wing is parallel with the direction of main machine body.
The upper strata fixed-wing, lower floor's fixed-wing and empennage are removably installed in main machine body by screw.
The empennage causes aircraft is holded up to be placed on level land as base.
The empennage is using X-type is either cross or double vertical-types.
It is also equipped with flying control plate in the main body, flies to be provided with signal transmitting and receiving unit, sensor unit, control on control plate
Device processed；Wherein, the sensor unit obtains flight attitude and location parameter, and obtained parameter is sent in controller,
Controller obtains parameter to control the rotary speed of the blade of rotation spiral shell wing according to it.
The beneficial effects of the utility model are：
Aircraft of the present utility model using " double-deck fixed-wing+eight revolve spiral shell wing " mixing wing distribution form so that
Aircraft can realize VTOL, flat winged in the fuselage that steadily can little by little vert after lift-off, be changed into fixed-wing flight；It is double
Layer fixed-wing combines the mixing wing distribution form of eight rotation spiral shell wings, and simple in construction, pneumatic efficiency is high, solves in a simple and reliable way
The problem of fixed-wing unmanned plane VTOL, have concurrently fixed-wing unmanned plane endurance is long, speed is high, apart from it is remote the characteristics of and rotation spiral shell
The function of wing unmanned plane VTOL.The VTOL rotary wings fixed-wing integrated flight device does not need runway and landing spatial domain
The characteristics of, the mission phases such as VTOL, state of flight conversion, cruise are easily accomplished, ensure that it can be in mountain area, hills, jungle
The region smooth operation intensive etc. complicated landform and building, have greatly expanded unmanned plane application, be industry-level unmanned plane
Ideal chose.The use of double-deck fixed-wing, adds gross wing area, improves lift, allow aircraft in the situation compared with low speed still
Can put down it is winged, without switch to power consumption rotation spiral shell wing fly.Aircraft of the present utility model revolves spiral shell wing by eight power and provides fixed point
Propulsive force when suspending power during suspension and cruise；The control of flight attitude is also to revolve spiral shell wing by eight power to complete.
Brief description of the drawings
Fig. 1 is the rotation spiral shell wing type aircaft configuration schematic diagram that verts；
Fig. 2 " 1+1 types " aircaft configuration schematic diagram；
Fig. 3 is the vertical view diagram of the aircraft provided according to the utility model embodiment；
The aircraft that Fig. 4 provides according to the utility model embodiment looks up diagram；
The aircraft forward sight diagram that Fig. 5 provides according to the utility model embodiment；
The aircraft backsight diagram that Fig. 6 provides according to the utility model embodiment；
The aircraft side view diagram that Fig. 7 provides according to the utility model embodiment；
The fixed-wing dismounting schematic diagram for the aircraft that Fig. 8 provides according to the utility model embodiment；
The empennage scheme of installation for the aircraft that Fig. 9 provides according to the utility model embodiment；
In figure：1st, spiral shell wing is revolved；2nd, upper strata fixed-wing；3rd, lower floor's fixed-wing；4th, main machine body；5th, empennage；6th, screw；11、
Blade.
Embodiment
The utility model preferred embodiment is provided below in conjunction with the accompanying drawings, to describe the technical solution of the utility model in detail.
Given is only the better embodiment according to thought of the present utility model, it may occur to persons skilled in the art that can be real
Existing other modes of the present utility model.Herein presented directional terminology, such as "front", "rear", "left", "right", " on ", " under "
Be relative to cruise when airframe for.
Fig. 3 is the aircraft schematic top plan view provided according to a kind of better embodiment of the present utility model, and Fig. 4 is Fig. 3
The elevational schematic view of shown aircraft.As shown in Figure 3 and Figure 4, according to the flying instrument of better embodiment of the present utility model
There is the profile of high degree of symmetry, back is similar with belly, and left and right is also symmetrical.Its eight rotation spiral shell wings 1 are arranged in double in a symmetrical manner
Between layer fixed-wing, wherein, on upper strata, the lower surface of fixed-wing 2 is provided with four rotation spiral shell wings 1, the left wing of fixed-wing 2 on upper strata
The front and rear edges at the middle part in face and right flank face is mounted on a pair of rotation spiral shell wings 1；Four are installed in the upper surface of lower floor's fixed-wing 3
Spiral shell wing 1 is revolved, the front and rear edges in the left wing face of lower floor's fixed-wing 3 and the middle part in right flank face is mounted on a pair of rotation spiral shell wings 1；
That is axially coincident, that is, the arrowhead promoted of the rotation spiral shell wing 1 before and after upper strata fixed-wing 2, lower floor's fixed-wing 3 in a pair
Overlap.Rotation spiral shell wing 1 disposes in pairs, and can also cancel each other anti-twisted power.Main machine body 4 is connected and installed on upper strata in strip cigar shape
Center between fixed-wing 2 and lower floor's fixed-wing 3.
It follows that aircraft of the present utility model is laid out using the mixing wing of " double-deck fixed-wing+eight revolves spiral shell wing "
Form so that aircraft can realize VTOL, flat winged in the fuselage that steadily can little by little vert after lift-off, be changed into fixation
The wing flies；Double-deck fixed-wing combines the mixing wing distribution form of eight rotation spiral shell wings, and simple in construction, pneumatic efficiency is high, with simple and reliable
Mode solve the problem of fixed-wing unmanned plane VTOL, have that fixed-wing unmanned plane endurance is long, speed is high, distance is remote concurrently
Feature and the function of rotation spiral shell wing unmanned plane VTOL.The VTOL rotary wings fixed-wing integrated flight device does not need runway
The characteristics of with landing spatial domain, be easily accomplished VTOL, state of flight conversion, cruise etc. mission phase, ensure it can mountain area,
The complicated landforms such as hills, jungle and the intensive smooth operation in region of building, have greatly expanded unmanned plane application, are industries
The ideal chose of level unmanned plane.The use of double-deck fixed-wing, gross wing area is added, improve lift, allow aircraft compared with low speed
Situation can still put down it is winged, without switch to power consumption rotation spiral shell wing fly.Aircraft of the present utility model revolves spiral shell wing by eight power
Propulsive force when suspending power and the cruise when fixed point suspends is provided；The control of flight attitude is also complete by eight power rotation spiral shell wings
Into.
Fig. 5 is the front-view schematic diagram of aircraft shown in Fig. 3 and Fig. 4, and Fig. 6 is the backsight of aircraft shown in Fig. 3, Fig. 4 and Fig. 5
Schematic diagram.As shown in Figure 5 and Figure 6, the rotation spiral shell wing 1 used according to the aircraft of better embodiment of the present utility model uses three
The structure of blade, its length of blade 11 is also long, roughly equal to 1/5th of fixed-wing length.Eight three blades revolve spiral shell wing 1,
Along with longer blade 11, the maximum lift of aircraft can be greatly improved, the efficiency for revolving spiral shell wing can also be improved.Aircraft
Maximum take-off weight is determined by the factor such as " rotor disk area " and the rotary speed of blade 11." rotor disk area " refers to revolve spiral shell wing 1 half
The disk area that footpath is formed in the rotation formation level of spiral shell wing 1.The rotary speed of blade 11 reaches to a certain degree, under the meeting of its efficiency is quick
Drop, therefore " rotor disk area " is significantly increased using eight rotation spiral shell wings 1, maximum take-off weight can be effectively increased.Wherein, spiral shell wing 1 is revolved
Axial direction (rotation spiral shell wing applies the direction of power) be not mutually perpendicular to fixed airfoil, but it is parallel with the direction of main machine body 4 (i.e.
It is parallel with the direction flown during cruise).
As shown in Fig. 5 Fig. 6, the cross section of aircraft main machine body 4 is circle, such as to increase main machine body space, can also be changed to
Four side rhombuses.
Fig. 7 is the schematic side view of aircraft shown in Fig. 3, Fig. 4, Fig. 5 and Fig. 6.As shown in Fig. 5, Fig. 6 and Fig. 7, according to this
The empennage 5 of the aircraft of the better embodiment of utility model is cross big empennage.Cross big empennage 5 has pneumatic from steady
It is set for using, plays counterbalance moment and lifting moment effect, can also be base arranged orthogonal using it on level land.Art technology
Personnel can select other class type tails according to other situations, such as：X-type empennage, double vertical wings, etc..
According in a kind of better embodiment of the present utility model, this aircraft is without aileron, wing flap, rudder, liter
The steerable active faces such as rudder are dropped, and the control of flight attitude is completed by eight power rotation spiral shell wings 1 completely.Those skilled in the art can
To increase the steerable active face such as these ailerons, wing flap, rudder, elevator and add-on systems according to special circumstances, to grasp
Vertical flight attitude.
Fig. 8 is that the fixed-wing of aircraft of the present utility model dismantles schematic diagram.Fig. 9 is the scheme of installation of empennage 5.Such as Fig. 8
Shown in Fig. 9, according in a kind of better embodiment of the present utility model, by upper strata fixed-wing by the way of screw 6
2nd, lower floor's fixed-wing 3 and empennage 5 and main machine body 4 are closed admittedly, easy and effective, also extremely convenient dismounting.Because according to the utility model
Aircraft structure it is simple, so very convenient installing/dismounting, reduce space, be convenient for carrying transport.
In a kind of better embodiment, above-mentioned upper strata fixed-wing 2, lower floor's fixed-wing 3, the blade 11 for revolving spiral shell wing, master
Fuselage 4, empennage 5 are glass fiber compound material using main composition material, are partly some carbon fibre composites.Glass fibre
Composite and carbon fibre composite all have the characteristics of light weight intensity is high, are advantageous to improve aeroplane performance.Permitted in budget
Can under, titanium alloy etc materials can also be used, further lift aeroplane performance.
In a kind of better embodiment, take off using the mode that takes off vertically.It is disposed vertically with empennage 5 for base
Level land, after startup, eight rotation spiral shell wings 1 produce lift and gone up to the air by aircraft.It is also equipped with flying control plate in main machine body 4, flies to set on control plate
There are signal transmitting and receiving unit, sensor unit, controller；Wherein, the sensor unit obtains flight attitude and location parameter, and
Obtained parameter is sent in controller, controller obtains parameter to control the rotation speed of the blade 11 of rotation spiral shell wing according to it
Degree.After lift-off, in the case where flying control plate control, aircraft main machine body of gradually verting tiltedly flies, when upper strata fixed-wing 2 and lower floor's fixed-wing
When lift caused by 3 is gradually increased to support the weight of whole aircraft, it is flat that winged control plate control aircraft switchs to cruise completely
Fly.
In a kind of better embodiment, above-mentioned upper strata fixed-wing 2 and lower floor's fixed-wing 3 use planoconvex aerofoil profile.
It will be apparent to those skilled in the art that technical scheme that can be as described above and design, make other various
Corresponding change and deformation, and all these changes and deformation should all belong to the protection of the utility model claims
Within the scope of.
Claims (8)
- A kind of 1. aircraft, it is characterised in that upper strata fixed-wing, the lower floor's fixed-wing set including relative；It is connected and installed in Main machine body between layer fixed-wing and lower floor's fixed-wing；The empennage being installed in main machine body；And be installed on upper strata fixed-wing and On lower floor's fixed-wing, the rotation spiral shell wing of flying power is provided for aircraft；Wherein, in the front and rear edges pair in the left wing face of upper strata fixed-wing Rotation spiral shell wing is installed with claiming, the front and rear edges in the right flank face of fixed-wing is symmetrically provided with rotation spiral shell wing on upper strata；Fixed in lower floor The front and rear edges in the left wing face of the wing is symmetrically provided with rotation spiral shell wing, and the front and rear edges in the right flank face of lower floor's fixed-wing is symmetrically pacified Equipped with rotation spiral shell wing.
- 2. aircraft as claimed in claim 1, it is characterised in that in the middle part of the lower surface in the left wing face of the upper strata fixed-wing Front and rear edges a pair of rotation spiral shell wings are symmetrically installed, the front and rear edges pair in the middle part of the lower surface in the right flank face of upper strata fixed-wing A pair of rotation spiral shell wings are installed with claiming；Symmetrically it is provided with a pair in the front and rear edges of the upper surface middle part in fixed-wing left wing of lower floor face Spiral shell wing is revolved, a pair of rotation spiral shell wings are symmetrically installed in the front and rear edges of the upper surface middle part in the right flank face of lower floor's fixed-wing.
- 3. aircraft as claimed in claim 1 or 2, it is characterised in that the axial direction of the rotation spiral shell wing and the direction phase of main machine body It is parallel.
- 4. aircraft as claimed in claim 1 or 2, it is characterised in that the rotation spiral shell spiral shell wing uses the structure of three blades.
- 5. aircraft as claimed in claim 1, it is characterised in that the upper strata fixed-wing, lower floor's fixed-wing and empennage are equal It is removably installed in by screw in main machine body.
- 6. the aircraft as described in claim 1 or 5, it is characterised in that the empennage causes aircraft to hold up peace as base It is placed on level land.
- 7. aircraft as claimed in claim 6, it is characterised in that the empennage is either cross or double vertical using X-type Type.
- 8. aircraft as claimed in claim 1 or 2, it is characterised in that be also equipped with flying control plate in the main body, fly control Signal transmitting and receiving unit, sensor unit, controller are provided with plate；Wherein, the sensor unit obtains flight attitude and position Parameter is put, and obtained parameter is sent in controller, controller obtains parameter to control the blade of rotation spiral shell wing according to it Rotary speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720856289.6U CN207045727U (en) | 2017-07-14 | 2017-07-14 | A kind of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720856289.6U CN207045727U (en) | 2017-07-14 | 2017-07-14 | A kind of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207045727U true CN207045727U (en) | 2018-02-27 |
Family
ID=61494788
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720856289.6U Expired - Fee Related CN207045727U (en) | 2017-07-14 | 2017-07-14 | A kind of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207045727U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2757693C1 (en) * | 2021-05-24 | 2021-10-20 | Закрытое акционерное общество "Инновационный центр "Бирюч" (ЗАО "ИЦ "Бирюч") | Vertical take-off and landing aircraft with propellers on rotary wing flaps |
-
2017
- 2017-07-14 CN CN201720856289.6U patent/CN207045727U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2757693C1 (en) * | 2021-05-24 | 2021-10-20 | Закрытое акционерное общество "Инновационный центр "Бирюч" (ЗАО "ИЦ "Бирюч") | Vertical take-off and landing aircraft with propellers on rotary wing flaps |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180227 Termination date: 20200714 |