CN107585294A - A kind of interior rotor craft structure - Google Patents
A kind of interior rotor craft structure Download PDFInfo
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- CN107585294A CN107585294A CN201610532393.XA CN201610532393A CN107585294A CN 107585294 A CN107585294 A CN 107585294A CN 201610532393 A CN201610532393 A CN 201610532393A CN 107585294 A CN107585294 A CN 107585294A
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- air stream
- stream outlet
- flow deflector
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 20
- 239000000725 suspension Substances 0.000 abstract description 6
- 239000013598 vector Substances 0.000 description 18
- 230000009187 flying Effects 0.000 description 6
- 238000006243 chemical reaction Methods 0.000 description 5
- 239000012530 fluid Substances 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000002153 concerted effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Abstract
The present invention relates to aircraft, there is provided a kind of interior rotor craft structure.Including body, rotor cavity, air flow inlet, air stream outlet, flow deflector, rotor, wherein described rotor cavity is embedded in the internal body, the body is provided with the air flow inlet and the air stream outlet, the air flow inlet, the air stream outlet and the rotor cavity are interconnected, the flow deflector is arranged at or near the air flow inlet, at or near the air stream outlet, three in the rotor cavity in position it is any one or more, the rotor is arranged in the rotor cavity.The present invention is compact-sized, and flight and suspension control are stablized flexible, possess the ability for adapting to narrow and small complex three-dimensional space.
Description
Technical field
The present invention relates to aircraft field, in particular to a kind of interior rotor craft structure.
Background technology
Conventional aircraft is generally divided into fixed-wing and the major class of rotor two, Fixed Wing AirVehicle flying speed it is fast but mostly without
Method realizes VTOL and air suspension, although rotor craft can realize VTOL and air suspension flying speed not
It is high.The rotor of most of rotor crafts is exposed outside, and flight stability is easily influenceed by flow perturbation, and exposed rotor is to surrounding
Environment structure threatens, and needs to increase paddle size so as to meet small form factor requirements to increase lift.Some rotor flyings
Device adds duct on rotor, although can weaken to a certain extent flow perturbation influence, prevent rotor endanger surrounding environment,
Paddle size is reduced on the premise of lift is ensured, but its rotor part still separates with body, and structure is not compact enough, and volume does not have
Have and further reduced.The defects of summarizing the conventional aircraft is：Mobility can not meet simultaneously with speed, to environment
Adaptability deficiency, can not in complex environment, such as in narrow and small city low latitude, forest, the complex three-dimensional space such as in building,
Free and stable shuttle flight and suspension.
Recently the spherical aircraft occurred, its rotor is wrapped up by whole spherical or hemispherical body, although can overcome
The segmental defect of the conventional aircraft, but its flight stability, flying speed, structural compactness still have larger room for improvement.
For above mentioned problem present in correlation technique, other effective solutions are not yet found at present.
The content of the invention
It is compact-sized in correlation technique at least to solve the embodiments of the invention provide a kind of interior rotor craft structure
Property, it is insufficient in terms of adaptive capacity to environment, flying quality and stability the problem of.
Technical solution of the present invention is as follows：
A kind of interior rotor craft structure, including body (1), rotor cavity (2), air flow inlet (8), air stream outlet (7), lead
Flow (5), rotor (3), wherein the embedded body (1) of the rotor cavity (2) is internal, the body (1) is provided with the air-flow
Entrance (8) and the air stream outlet (7), the air flow inlet (8), the air stream outlet (7) and the rotor cavity (2) mutually interconnect
It is logical, the flow deflector (5) is arranged at or near the air flow inlet (8), at or near the air stream outlet (7), the rotation
At three in wing chamber (2) in position it is any one or more, the rotor (3) is arranged in the rotor cavity (2).
Alternatively, the flow deflector (5) is strip flake, and the flow deflector (5) is provided with water conservancy diversion disk rotating shaft (6),
The flow deflector (5) can rotate around the water conservancy diversion disk rotating shaft (6).
Alternatively, flow deflector described in multi-disc (5) forms a flow deflector group (4), the institute in the same flow deflector group (4)
Flow deflector (5) plane is stated to be parallel to each other.
Alternatively, in the rotor cavity (2), at least provided with a pair of rotors (3).
Alternatively, rotor pair, the left-handed wing (13) are at least formed by a left-handed wing (13) and a dextrorotation wing (11)
It is symmetrically dispersed in the dextrorotation wing (11) in the rotor cavity (2) at left and right sides of body axis (15).
Alternatively, the surfaces of revolution of the left-handed wing (13) and the dextrorotation wing (11) is parallel with body plane (12) or around institute
It is angled to state body axis (15).
Alternatively, rotor pair, the upper rotor (24) are at least formed by a upper rotor (24) and a lower rotor (25)
It is arranged on the lower rotor (25) with cascade form in the rotor cavity (2).
Alternatively, upper rotor (24) rotary shaft, lower rotor (25) rotary shaft, body center indulge vertical line (23) three
Person is coaxial, and upper rotor (24) Plane of rotation is parallel to each other with lower rotor (25) Plane of rotation.
Alternatively, the air flow inlet (8) is located at the body (1) top (16).
Alternatively, the air stream outlet (7) is located at the body (1) bottom (17), and the air stream outlet (7) is relative to institute
State body axis (15) and be symmetrically divided into left air stream outlet (18) and right air stream outlet (19), left air stream outlet (18)
Connected respectively with the rotor cavity (2) with right air stream outlet (19).
Alternatively, it is respectively equipped with independently of each other at or near the left air stream outlet (18) and the right air stream outlet (19)
The flow deflector group (4).
Alternatively, one or more separate flow deflector groups are provided with or near the left air stream outlet (18)
(4) one or more separate flow deflector groups (4), are provided with or near the right air stream outlet (19).
Alternatively, the body (1) bottom (17) is provided with the left flap for being symmetrical with the body axis (15)
(21) and right flap (22), the left flap (21) and the right flap (22) correspond to the left air stream outlet respectively
And the right air stream outlet (19) (18).
Alternatively, the left flap (21) and the right flap (22) are flake, are respectively equipped with independent water conservancy diversion
Wing rotary shaft (20), the left flap (21) and the right flap (22) can each rotate independently about the flap
Axle (20) rotates.
Alternatively, body (1) afterbody is provided with left flap (21) and the right side for being symmetrical with the body axis (15)
Flap (22).
Alternatively, the left flap (21) and the right flap (22) are flake, are respectively equipped with independent water conservancy diversion
Wing rotary shaft (20), the left flap (21) and the right flap (22) can each rotate independently about the flap
Axle (20) rotates.
The present invention has the beneficial effect that：
Flight Vehicle Structure provided by the invention is compact, possesses the ability for adapting to narrow and small complex three-dimensional space；The present invention provides
Interior rotor structure rotor is isolated with external environment condition, it is therefore prevented that the rotation of rotor damages to surrounding environment；The present invention carries
The airflow channel structure of confession can obstruct the disturbance of outer gas stream, concentrate and strengthen lift and thrust；Water conservancy diversion knot provided by the invention
Structure can be converted to kinetic energy caused by rotor vectored thrust, vectored thrust make aircraft can VTOL and suspension and can it is quick
Flight and steering, and the more common gyroplane of flying speed is fast, while the direction of vectored thrust can be with aircraft itself with distribution
The regulation of flow-guiding structure and be dynamically varied and be assigned to position needed for pose adjustment, without to environment and itself state of flight
There is particular/special requirement and without additionally increasing thrust source, it is ensured that aircraft balance and stability, therefore flight provided by the invention
Device its adaptive capacity to environment, flight flexibility, mobility are strong.
Brief description of the drawings
Accompanying drawing described herein is used for providing a further understanding of the present invention, forms the part of the application, this hair
Bright illustrative examples, accompanying drawing and its illustrate to be used to explain the present invention, do not form inappropriate limitation of the present invention.In accompanying drawing
In：
Fig. 1 is sectional structure chart on the left of interior rotor craft body；
Fig. 2 is rotor craft body upper top view cross section structure chart in left and right；
Fig. 3 is rotor craft body upper top view in left and right；
Fig. 4 is rotor craft body left side view in left and right；
Fig. 5 is rotor craft underpart upward view in left and right；
Fig. 6 is rotor craft housing construction exploded view in left and right；
Fig. 7 is rotor craft body left side sectional structure chart in upper and lower；
Fig. 8 is flow deflector side sectional view force analysis figure；
Fig. 9 is the side sectional view force analysis figure that flow deflector simplifies topology with flap
Figure 10 is cross-section structure force analysis figure on the left of body；
Wherein：1 is body, and 2 be rotor cavity, and 3 be rotor, and 4 be flow deflector group, and 5 be flow deflector, and 6 be water conservancy diversion disk rotating shaft,
7 be air stream outlet, and 8 be air flow inlet, and 9 be air-flow, and 11 be the dextrorotation wing, and 12 be body plane, and 13 be the left-handed wing, and 15 be in body
Axis, 16 be body upper, and 17 be underpart, and 18 be left air stream outlet, and 19 be right air stream outlet, and 20 be that flap rotates
Axle, 21 be left flap, and 22 be right flap, and 23 be that body center indulges vertical line, and 24 be upper rotor, and 25 be lower rotor, and 27 be gas
Infinitesimal is flowed to reaction force vector caused by flow deflector, and 28 be that flow deflector is gas to force vector caused by air-flow infinitesimal, 29
Flow infinitesimal contact the flow deflector moment initial velocity vector, 30 be air-flow infinitesimal contact flow deflector after instantaneous velocity vector, 31
It is air-flow infinitesimal, 32 be that thrust vectoring is closed caused by a flow deflector group, and 33 be lift vector caused by rotor, and 34 be left water conservancy diversion
Thrust vectoring caused by the wing.
Embodiment
Describe the present invention in detail below with reference to accompanying drawing and in conjunction with the embodiments.It should be noted that in the feelings not conflicted
Under condition, the feature in embodiment and embodiment in the application can be mutually combined.
Embodiment 1
Present embodiments providing one kind has rotor craft structure in left and right, as follows：
As shown in figures 1 to 6, including body (1), rotor cavity (2), air flow inlet (8), air stream outlet (7), flow deflector (5),
Rotor (3), wherein the embedded body (1) of the rotor cavity (2) is internal, the body (1) be provided with the air flow inlet (8) and
The air stream outlet (7), the air flow inlet (8), the air stream outlet (7) and the rotor cavity (2) are interconnected, described to lead
Flow (5) is arranged on the air stream outlet (7) place, and the rotor (3) is arranged in the rotor cavity (2).
Alternatively, the flow deflector (5) is strip flake, and the flow deflector (5) is provided with water conservancy diversion disk rotating shaft (6),
The flow deflector (5) can rotate around the water conservancy diversion disk rotating shaft (6).
Alternatively, flow deflector described in multi-disc (5) forms a flow deflector group (4), the institute in the same flow deflector group (4)
Flow deflector (5) plane is stated to be parallel to each other.
Alternatively, in the rotor cavity (2), provided with a pair of rotors (3), respectively a left-handed wing (13) and one
The individual dextrorotation wing (11), the left-handed wing (13) and the dextrorotation wing (11) are symmetrically dispersed in body in the rotor cavity (2)
At left and right sides of axis (15).
Alternatively, the surfaces of revolution of the left-handed wing (13) and the dextrorotation wing (11) is parallel with body plane (12) or around institute
It is angled to state body axis (15).
Alternatively, the air flow inlet (8) is located at the body (1) top (16).
Alternatively, the air stream outlet (7) is located at the body (1) bottom (17), and the air stream outlet (7) is for described
Body axis (15) is symmetrically divided into left air stream outlet (18) and right air stream outlet (19), respectively with the rotor cavity
(2) connect.
Alternatively, the left air stream outlet (18) and the right air stream outlet (19) place are respectively equipped with separate described
Flow deflector group (4).
Alternatively, left air stream outlet (18) place is provided with two separate flow deflector groups (4), described in two
Flow deflector group (4) one close to the body (1) front end and another close to the body (1) rear end, the right air stream outlet
(19) place is provided with two separate flow deflector groups (4), and two flow deflector groups (4) one are close to the body
(1) front end and another close to the body (1) rear end.
Alternatively, the body (1) bottom (17) rear end tails are provided with and are symmetrical with the body axis (15)
Left flap (21) and right flap (22), the left flap (21) and the right flap (22) correspond to the left gas respectively
The flow deflector group (4) of close body (1) rear end of flow export (18) place installation and the installation of the right air stream outlet (19) place
Close body (1) rear end flow deflector group (4).
Alternatively, the left flap (21) and the right flap (22) are flake, are respectively equipped with independent water conservancy diversion
Wing rotary shaft (20), the left flap (21) and the right flap (22) can each rotate independently about the flap
Axle (20) rotates.
Have in one kind that the present embodiment provides and this aircraft is expanded on further in left and right on rotor craft architecture basics
Control principle, it is as follows：
As shown in figure 1, air-flow (9) enters rotor cavity (2) from air flow inlet (8), produced after rotor (3) acceleration to flight
The lift of device, while obtain kinetic energy and be excluded from air stream outlet (7) through flow deflector (5) or flow deflector group (4).According to fluid
Wall attachment effect, for air-flow by that can be split and be moved along water conservancy diversion plate plane slipstream during flow deflector, water conservancy diversion plate plane is tangential just
It is air current flow direction, changes flow deflector in-plane with regard to air flow direction can be changed around water conservancy diversion disk rotating shaft.According to air force
Momentum formula on power, it is as follows：
Wherein F be fluid infinitesimal to reaction force vector caused by object, V is the velocity of fluid infinitesimal, and m is fluid
The quality of infinitesimal, d/dt are differential signs.
Momentum formula shows：Because V is velocity, the change of velocity attitude or size can produce vectorial force.According to this
One principle, aircraft change air current flow direction to obtain direction and the adjustable arrow of size by adjusting flow deflector in-plane
Thrust is measured, itself posture and motion state can be adjusted using the thrust.Simultaneously in order to keep the compactedness of Flight Vehicle Structure, often
Piece flow deflector area is unsuitable excessive, therefore monolithic flow deflector lifting surface area is inadequate, in order to increase lifting surface area, by multi-disc compared with small area
Strip flake flow deflector parallel interval form a flow deflector group to increase lifting surface area, so as to strengthen in same direction
Vectored thrust.As shown in figure 1, the flow direction of the air-flow (9) after rotor (3) acceleration is distinguished by two independent flow deflector groups
Regulation, realize the distribution of force decoupling adjustment at body (1) former and later two positions.
As shown in figure 8, air-flow infinitesimal (31) fallen on after rotor accelerates on flow deflector (5) after because of fluid wall attachment effect edge
Water conservancy diversion plate plane tangential motion, now air-flow infinitesimal (31) velocity by the contact flow deflector moment initial velocity vector
(29) it is changed into touching the instantaneous velocity vector (30) after flow deflector, instantaneous velocity vector (30) direction is put down with flow deflector (5) plane
OK, force vector (28), air-flow are acted to air-flow infinitesimal according to active force and reaction force principle and momentum formula, flow deflector
Infinitesimal produces reaction force vector (27) to flow deflector, and both size equidirectionals are opposite.Flow deflector (5) is adjusted around flow deflector to turn
Moving axis (6) rotates direction and the size that can then change reaction force vector (27), adjustable so as to be generated by flow deflector
Vectored thrust.Because the water conservancy diversion plate plane in same flow deflector group is parallel to each other, every flow deflector therein is produced
Raw vectored thrust direction is identical, so that a flow deflector group can produce larger conjunction thrust in the direction indicated.
As shown in Figure 10, in terms of aircraft body left side view plane, there are two separate flow deflector groups (4), one
Individual close body (1) front end and another produces the conjunction thrust arrow in both direction close to body (1) rear end in front and back end respectively
Measure (32).Visible left flap (21) in other figure, it is located at rear end flow deflector group close beneath, and is produced using flow deflector group
Windstream form thrust vectoring (34) again, as shown in figure 9, air-flow (9) is directed to left flap through flow deflector (5)
(21) in table plane, adjustment flap direction can adjustment effect in thrust vectoring (34) size and Orientation thereon.Return to figure
10, suffered by whole body (1) make a concerted effort and torque lift vector (33) as caused by rotor (3) divides with two flow deflector groups (4)
It is not caused conjunction thrust vectoring (32) and flap caused by thrust vectoring (34) jointly synthesize, by adjust flow deflector group and
The direction of flap can independently adjust the size and Orientation of body front and rear part stress, so as to adjust flight attitude, keep
Dynamic equilibrium, and change of flight state.
As shown in figure 5, in order to strengthen the dynamics of pose adjustment, at left air stream outlet (18) place of body (1) bottom (17)
Flow deflector group (4) close to body (1) rear end is attached close to the flow deflector group (4) of body rear end with right air stream outlet (19) place nearby
Left flap (21) and right flap (22) are closely separately installed with, air-flow (9) touches after the exclusion of flow deflector group (4) directive property
Water conservancy diversion wing surface, and produce vectored thrust and act on body or so rear portion, the size and Orientation of the thrust is adjusted by flap, its
Principle is with the narration above with respect to flow deflector, and here is omitted.
As shown in fig. 6, air-flow (9) enters after rotor cavity (2) by the left-handed wing (13) and the dextrorotation wing (11) from air flow inlet (8)
Shunting accelerates, and is finally excluded respectively from left air stream outlet (18) and right air stream outlet (19), lift on the left of aircraft body (1)
Vector is produced by the left-handed wing (13), and right side lift vector is produced by the dextrorotation wing (11), therefore adjusts the rotating speed of left and right rotor respectively
The size of body or so portion lift can be adjusted, so as to adjust flight attitude, keeps dynamic equilibrium, and change of flight state.
In summary, a kind of aircraft with rotor structure in left and right, its flight control mode are by adjusting left and right
Rotor rotating speed adjusts the lift vector size in body or so portion, passes through four for adjusting left and right air flow outlet and nearby installing
Flow deflector group and two respective directions of flap come adjust body it is left front, it is right before, the thrust vectoring size at left back, right rear portion and
Direction, aircraft is suffered to be synthesized with torque by these lift vectors and thrust vectoring with joint efforts.I.e. can by adjusting aircraft itself
Structure changes come change air flow direction so as to controllably adjust each component of institute's stress distribution, direction and size, finally to determine it
Flight suspension posture and state.
Embodiment 2
Present embodiments providing one kind has rotor craft structure in up and down, and it is one kind provided in embodiment 1
Another modification with rotor craft structure in left and right, to illustrate a kind of interior rotor craft provided by the invention
The changeability of structure.
As shown in fig. 7, rotor is changed to rotor in up and down in left and right in the rotor cavity that embodiment 1 is described, i.e., in institute
State and a upper rotor (24) and a lower rotor (25) are provided with rotor cavity (2), the upper rotor (24) and the lower rotor
(25) installed in the rotor cavity (2) with cascade form, upper rotor (24) rotary shaft, lower rotor (25) rotary shaft
It is coaxial that vertical line (23) is indulged with body center, and upper rotor (24) Plane of rotation is mutually flat with lower rotor (25) Plane of rotation
OK.The upper rotor (24) and lower rotor (25) direction of rotation are jointly machine on the contrary, the coaxial lift vector in the same direction of generation
Body (1), which provides, closes lift.
In the present embodiment, except the change of rotor structure is outside the pale of civilization, other parts are same as Example 1, therefore repeat no more.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (9)
- A kind of 1. interior rotor craft structure, it is characterised in that：Including body (1), rotor cavity (2), air flow inlet (8), air stream outlet (7), flow deflector (5), rotor (3), wherein described The embedded body (1) of rotor cavity (2) is internal, and the body (1) is provided with the air flow inlet (8) and the air stream outlet (7), The air flow inlet (8), the air stream outlet (7) and the rotor cavity (2) are interconnected, and the flow deflector (5) is arranged on institute State at or near air flow inlet (8), at or near the air stream outlet (7), three in the rotor cavity (2) at it is any one in position Place or many places, the rotor (3) are arranged in the rotor cavity (2).
- 2. interior rotor craft structure according to claim 1, it is characterised in that：The flow deflector (5) is strip flake, and the flow deflector (5) is provided with water conservancy diversion disk rotating shaft (6), the flow deflector (5) can be rotated around the water conservancy diversion disk rotating shaft (6)；Flow deflector described in multi-disc (5) forms a flow deflector group (4), the flow deflector (5) in the same flow deflector group (4) Plane is parallel to each other.
- 3. interior rotor craft structure according to claim 1 or claim 2, it is characterised in that：In the rotor cavity (2), at least provided with a pair of rotors (3).
- 4. interior rotor craft structure according to claim 3, it is characterised in that：Rotor pair, the left-handed wing (13) and the dextrorotation wing are at least formed by a left-handed wing (13) and a dextrorotation wing (11) (11) it is symmetrically dispersed in the rotor cavity (2) at left and right sides of body axis (15)；The surfaces of revolution of the left-handed wing (13) and the dextrorotation wing (11) is parallel with body plane (12) or around the body axis Line (15) is angled.
- 5. interior rotor craft structure according to claim 3, it is characterised in that：Rotor pair, the upper rotor (24) and the lower rotor are at least formed by a upper rotor (24) and a lower rotor (25) (25) it is arranged on cascade form in the rotor cavity (2)；Upper rotor (24) rotary shaft, lower rotor (25) rotary shaft, vertical vertical line (23) three of body center are coaxial, described Upper rotor (24) Plane of rotation is parallel to each other with lower rotor (25) Plane of rotation.
- 6. according to the interior rotor craft structure of claim 4 or 5, it is characterised in that：The air flow inlet (8) is located at the body (1) top (16)；The air stream outlet (7) is located at the body (1) bottom (17), and the air stream outlet (7) is relative to the body axis Line (15) is symmetrically divided into left air stream outlet (18) and right air stream outlet (19), and left air stream outlet (18) and right air-flow go out Mouth (19) connects with the rotor cavity (2) respectively；The separate water conservancy diversion is respectively equipped with or near the left air stream outlet (18) and the right air stream outlet (19) Piece group (4).
- 7. interior rotor craft structure according to claim 6, it is characterised in that：One or more separate flow deflector groups (4), the right side are provided with or near the left air stream outlet (18) One or more separate flow deflector groups (4) are provided with or near air stream outlet (19).
- 8. interior rotor craft structure according to claim 7, it is characterised in that：The body (1) bottom (17) is provided with and is symmetrical with the left flap (21) of the body axis (15) and right water conservancy diversion The wing (22), the left flap (21) and the right flap (22) correspond to the left air stream outlet (18) and the right gas respectively Flow export (19)；The left flap (21) and the right flap (22) are flake, are respectively equipped with independent flap rotary shaft (20), the left flap (21) and the right flap (22) can each turn independently about the flap rotary shaft (20) It is dynamic.
- 9. interior rotor craft structure according to claim 7, it is characterised in that：Body (1) afterbody is provided with the left flap (21) and right flap (22) for being symmetrical with the body axis (15)；The left flap (21) and the right flap (22) are flake, are respectively equipped with independent flap rotary shaft (20), the left flap (21) and the right flap (22) can each turn independently about the flap rotary shaft (20) It is dynamic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610532393.XA CN107585294A (en) | 2016-07-08 | 2016-07-08 | A kind of interior rotor craft structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610532393.XA CN107585294A (en) | 2016-07-08 | 2016-07-08 | A kind of interior rotor craft structure |
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| CN107585294A true CN107585294A (en) | 2018-01-16 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891337A (en) * | 2020-07-15 | 2020-11-06 | 浙江安浮航空科技有限公司 | High-speed shaftless duct type rotor wing |
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| CN102897317A (en) * | 2011-07-29 | 2013-01-30 | 奥格斯塔韦斯兰股份公司 | Convertiplane |
| CN104918853A (en) * | 2012-12-10 | 2015-09-16 | 贝尔蒙·热罗姆 | Convertible aircraft provided with two ducted rotors at the wing tips and with a horizontal fan in the fuselage |
| CN103332293A (en) * | 2013-06-13 | 2013-10-02 | 上海大学 | Tilting double-duct subminiature unmanned plane |
| CN105292444A (en) * | 2014-07-08 | 2016-02-03 | 吴建伟 | Vertical take-off and landing aircraft |
| CN105620740A (en) * | 2016-03-09 | 2016-06-01 | 西北工业大学 | Coaxial opposite-rotating dual-rotating-wing duct type vertical take-off and landing aircraft |
| CN206087295U (en) * | 2016-07-08 | 2017-04-12 | 袁洪跃 | Interior rotor craft structure |
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| CN111891337A (en) * | 2020-07-15 | 2020-11-06 | 浙江安浮航空科技有限公司 | High-speed shaftless duct type rotor wing |
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