CN105775128A - Flight vehicle - Google Patents
Flight vehicle Download PDFInfo
- Publication number
- CN105775128A CN105775128A CN201610094300.XA CN201610094300A CN105775128A CN 105775128 A CN105775128 A CN 105775128A CN 201610094300 A CN201610094300 A CN 201610094300A CN 105775128 A CN105775128 A CN 105775128A
- Authority
- CN
- China
- Prior art keywords
- wing
- rotor
- fuselage
- flight vehicle
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 15
- 238000010276 construction Methods 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 5
- 230000006872 improvement Effects 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000013011 mating Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000004899 motility Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a flight vehicle. The flight vehicle comprises a flight vehicle body; two wings rotating automatically are symmetrically installed on the two sides of the flight vehicle body, and four rotor wing rods are arranged on the periphery of the flight vehicle body; each rotor wing rod is provided with a rotor wing, and each wing is connected with the flight vehicle body through a rotating shaft; the back portion of each wing is provided with a tangential flow wing body, and the front portion of each wing is provided with a sharp leading edge; and each rotor wing rod is connected with the flight vehicle body through a rotating mechanism and capable of driving the corresponding rotor wing to bend forwards relative to the flight vehicle body. The flight vehicle adopts a mechanical mechanism with the four rotor wings, all the rotor wings are controlled to move in a coordinated mode by a controller, and the flight attitude of the four rotor wings is adjusted; the adopted rotor wings can take off and land perpendicularly and are not limited by a taking off and landing field, through the cooperation effect of the rotor wings and the rotating mechanisms, the rotor wing rods can rotate relative to the flight vehicle body, and the rotor wings can bend forwards relative to the flight vehicle body, so that flight is more flexible; the wings are adjusted to be horizontal, the sharp leading edges of front wing sheets are made to face the wind direction, the air resistance is reduced, the stability of the flight vehicle is improved, and the flight vehicle is worth applying and popularizing.
Description
Technical field
The present invention relates to the technical field of flight equipment, particularly relate to a kind of aircraft.
Background technology
Aircraft be manufactured by the mankind, ground can be flown away from, at space flight the apparatus flying object flown in endoatmosphere or space, exoatmosphere (space) that controlled by people.At present, development along with technology, aircraft starts to play a significant role in every field, aircraft is broadly divided into helicopter and the big class of fixed wing airplane two, and helicopter has superior low speed low-altitude performance, but inefficient, fixed wing airplane flying radius is big, efficiency is high, but low-altitude low-speed poor-performing, airport condition is required higher.Existing aircraft adopts rotor also to have VTOL ability, when horizontal flight, fuselage meeting run-off the straight, and existing rotor will not adjust automatically, it is difficult to reach the purpose of stabilized flight, the rotor structure relative complex verted of appearance, structure link is many, and rotor is simultaneously to an azimuthal tilt, adds and stablizes parallel difficulty, and motility is not high.
Summary of the invention
For the deficiencies in the prior art, the technical problem to be solved is in that to provide that a kind of motility is good, the aircraft of operation stability, adjustable flight attitude.
In order to solve above-mentioned technical problem, the present invention is achieved through the following technical solutions: a kind of aircraft, including fuselage, and at the monosymmetric wing being provided with two automatic rotations of fuselage, at four the rotor bars that are formed around of fuselage, each rotor bar is provided with a rotor, and described wing is connected with fuselage by rotating shaft, the rear portion of each wing has the slipstream wing, and the front portion of each wing has tip leading edge；Described each rotor bar is connected with fuselage respectively through rotating mechanism and rotor can be driven to lean forward relative to fuselage.The aircraft of the present invention adopt rotor can VTOL, not by the restriction of landing site, with the mating reaction of rotating mechanism so that rotor bar can rotate relative to fuselage so that rotor can lean forward relative to fuselage, fly more flexible, convenient.
As the improvement of technique scheme, described rotating mechanism includes the driven gear of driving gear that drive motor is connected and described driving gear engaged transmission with the output shaft of described drive motor, and described driven gear is affixed with the end of described rotor bar.
As the improvement of such scheme, the controller that the drive motor also including answering with each rotor pole pair is electrically connected, control to make each rotor coordination exercise by controller, it is achieved the adjustment of the flight attitude of four rotors.
Further, described four rotor bars are divided into two pairs of both sides being symmetricly set on fuselage, this tandem side being arranged on described wing of two pairs of rotor bars.
As the improvement of such scheme, described wing includes front fin, rear fin and dihedral wing sheet, and described rotating shaft is arranged horizontally between front fin and rear fin, and one end of rotating shaft is connected with fuselage, and the other end is connected with dihedral wing sheet；Front fin has tip leading edge, rear fin has the slipstream wing.
As the improvement of such scheme, described fuselage is provided with the motor that verts driving described axis of rotation, by verting motor and rotating shaft makes wing become vertical or near normal ground, does not increase the VTOL resistance that aircraft is extra；When aircraft is raised to certain high-altitude, it is necessary to flat when flying, again through verting motor and rotating shaft makes wing become being parallel to ground or being approximately parallel to ground, and the tip leading edge of fin direction facing the wind before ensureing, reduce resistance, and provided a part of lift by wing.
Further, described fuselage is additionally provided with two be arranged in parallel turn to steering wheel, when aircraft is unstable in the process of flight, turns to operation by turning to what steering wheel improved aircraft, realize the stability contorting of aircraft.Described afterbody is provided with empennage, and underbelly is provided with undercarriage, and described undercarriage adopts wheeled construction.
Relative to prior art, the invention have the benefit that the aircraft of the present invention adopts the mechanical mechanism of four rotors, control to make each rotor coordination exercise by controller, realize the adjustment of the flight attitude of four rotors, the aircraft of the present invention adopt rotor can VTOL, not by the restriction of landing site, mating reaction with rotating mechanism so that rotor bar can rotate relative to fuselage, so that rotor can lean forward relative to fuselage, more flexible, convenience of flying.When the aircraft vertical of the present invention takes off, control rotor bar to rotate, ensure that rotor is perpendicular to the ground upward, to produce lift upwards, rotor is made to turn forward when aircraft is raised to certain high-altitude by controlling four drive motors, and by verting motor and wing is adjusted to level by rotating shaft, and by the tip leading edge of front fin direction facing the wind, reduce air drag, improve the stability of aircraft；When aircraft is unstable in the process of flight, turns to operation by turning to what steering wheel improved aircraft, realize the stability contorting of aircraft；When high-altitude flight, wing still keeps level, and during aircraft forward flight, wing also can provide a part of lift.By above structure, can be leaned forward four rotors simultaneously, achieving VTOL and the quick flat chikung energy of aircraft, when VTOL, wing becomes vertical or near normal ground, do not increase the VTOL resistance that aircraft is extra, when running into complicated weather condition, four rotors angle relative to fuselage can be adjusted respectively, the suitable angle of pitch and lifting force are provided for aircraft, adjust flexibly, strong adaptability.
Accompanying drawing explanation
In order to be illustrated more clearly that the technical scheme of the embodiment of the present invention, the accompanying drawing of embodiment will be briefly described below.
Fig. 1 is the structural representation of the aircraft of the preferred embodiment of the present invention.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is only a part of embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of protection of the invention.
As shown in Figure 1, it it is the structural representation of the aircraft of the preferred embodiment of the present invention, the aircraft of the present invention includes fuselage 10, wing 20, wing 30, rotor bar 40, rotor bar 50, rotor bar 60 and rotor bar 70, wing 20 and wing 30 are symmetrically installed on fuselage 10 both sides, and wing 20 and wing 30 rotate automatically relative to fuselage 10, rotor bar 40, rotor bar 50, rotor bar 60 and rotor bar 70 are separately positioned on the surrounding of fuselage 10, and rotor bar 40, rotor bar 50, rotor bar 60 and rotor bar 70 are divided into two pairs of both sides being symmetricly set on fuselage 10, this tandem side being arranged on wing 20 and wing 30 of two pairs of rotor bars.Each rotor bar is provided with a rotor 80, aircraft takeoff is driven by rotor 80, the afterbody of fuselage 10 is provided with empennage 11, fuselage 10 bottom is provided with undercarriage, described undercarriage adopts wheeled construction, empennage 11 includes tailplane and vertical tail, and tailplane plays the effect of horizontal stabilizer and elevator, and vertical tail plays the effect of vertical stabilization and rudder.
nullDescribed wing 20 and wing 30 are connected with fuselage 10 by rotating shaft 90，The rear portion of wing 20 and wing 30 has the slipstream wing，The front portion of wing 20 and wing 30 has tip leading edge，Wing 20 is identical with the structure of wing 30，Specifically，Each wing all includes front fin 21、Rear fin 22 and dihedral wing sheet 23，Described rotating shaft 90 is arranged horizontally between front fin 21 and rear fin 22，One end of rotating shaft 90 is connected with fuselage 10，The other end is connected with dihedral wing sheet 23，Front fin 21 has tip leading edge，Rear fin 22 has the slipstream wing，Fuselage 10 is provided with the motor 91 that verts driving described rotating shaft 90 to rotate，Rotating shaft 90 is driven to rotate by the motor 91 that verts，And then the front fin of adjustable 21 and rear fin 22 and angle，By the zone of action motivation body 10 of four rotors 80、When wing 20 and wing 30 VTOL，By verting motor 91 and rotating shaft 90 makes wing 20 and wing 30 entirety become vertical or near normal ground，Do not increase the VTOL resistance that aircraft is extra；When aircraft is raised to certain high-altitude, when needing flat flying, again through verting motor 91 and rotating shaft 90 makes wing 20 and wing 30 become being parallel to ground or being approximately parallel to ground, and the tip leading edge of fin 21 direction facing the wind before ensureing, reduce resistance, and provided a part of lift by wing 20 and wing 30.Rear fin 22 is the slipstream wing, in order to when aircraft flight, it is provided that variable thrust guides, and is suitable to control the gradient of aircraft.
In an embodiment of the present invention, rotor bar 40, rotor bar 50, rotor bar 60 and rotor bar 70 are connected with fuselage 10 respectively through rotating mechanism and rotor 80 can be driven to lean forward relative to fuselage 10, specifically, described rotating mechanism includes the driven gear 43 of driving gear 42 that drive motor 41 is connected and described driving gear 42 engaged transmission with the output shaft of described drive motor 41, described driven gear 43 is affixed with the end of described rotor bar, therefore, can pass through drive motor 41 drives each rotor bar to rotate, and makes rotor lean forward relative to fuselage 20.The aircraft of the present invention also includes the controller (not indicating in figure) that the drive motor answered with each rotor pole pair is electrically connected, and is controlled the rotation of drive motor 41 by controller, and then controls each rotor and tilt relative to fuselage 10.When aircraft vertical takes off, control drive motor 41 by controller and rotate, control rotor bar then through gear drive, it is ensured that rotor 80 is perpendicular to the ground upward, to produce lift upwards；When aircraft changes to horizontal fly-cutting from taking off vertically, control rotor bar by rotating mechanism and rotate, it is achieved leaning forward of rotor 80, it is ensured that the horizontal flight of aircraft, simplify structure of the prior art, simple in construction, be beneficial to maintenance.When running into complicated weather condition, the angle relative to fuselage 10 of the rotor on rotor bar 40, rotor bar 50, rotor bar 60 and rotor bar 70 can be adjusted respectively, the suitable angle of pitch and lifting force are provided for aircraft, adjust flexibly, strong adaptability.
In another embodiment of the present invention, described fuselage 10 is additionally provided with two be arranged in parallel turn to steering wheel 12, when aircraft is unstable in the process of flight, turns to operation by turning to what steering wheel improved aircraft, realize the stability contorting of aircraft.
The aircraft of the present invention adopts the mechanical mechanism of four rotors, control to make each rotor coordination exercise by controller, realize the adjustment of the flight attitude of four rotors, the aircraft of the present invention adopt rotor can VTOL, not by the restriction of landing site, mating reaction with rotating mechanism, rotor 80 rotor bar can be rotated, so that can lean forward relative to fuselage 10, more flexible, convenience of flying relative to fuselage 10.When the aircraft vertical of the present invention takes off, control rotor bar 40, rotor bar 50, rotor bar 60 and rotor bar 70 to rotate, ensure that rotor 80 is perpendicular to the ground upward, to produce lift upwards, rotor is made to turn forward when aircraft is raised to certain high-altitude by controlling four drive motors 41, and by verting motor 91 and wing 20 and wing 30 are adjusted to level by rotating shaft 90, and by the tip leading edge of front fin 21 direction facing the wind, reduce air drag, improve the stability of aircraft；When aircraft is unstable in the process of flight, turns to operation by turning to what steering wheel 12 improved aircraft, realize the stability contorting of aircraft；When high-altitude flight, wing still keeps level, and during aircraft forward flight, wing also can provide a part of lift.By above structure, can be leaned forward four rotors simultaneously, achieving VTOL and the quick flat chikung energy of aircraft, when VTOL, wing becomes vertical or near normal ground, do not increase the VTOL resistance that aircraft is extra, when running into complicated weather condition, the angle relative to fuselage 10 of the rotor on rotor bar 40, rotor bar 50, rotor bar 60 and rotor bar 70 can be adjusted respectively, the suitable angle of pitch and lifting force are provided for aircraft, adjust flexibly, strong adaptability.
Above disclosed it is only presently preferred embodiments of the present invention, certainly can not limit the interest field of the present invention, the equivalent variations therefore made according to the claims in the present invention with this, still belong to the scope that the present invention contains.
Claims (8)
1. an aircraft, including fuselage, it is characterized in that: at the monosymmetric wing being provided with two automatic rotations of fuselage, it is formed around four rotor bars at fuselage, each rotor bar is provided with a rotor, described wing is connected with fuselage by rotating shaft, and the rear portion of each wing has the slipstream wing, and the front portion of each wing has tip leading edge；Described each rotor bar is connected with fuselage respectively through rotating mechanism and rotor can be driven to lean forward relative to fuselage.
2. aircraft according to claim 1, it is characterized in that, described rotating mechanism includes the driven gear of driving gear that drive motor is connected and described driving gear engaged transmission with the output shaft of described drive motor, and described driven gear is affixed with the end of described rotor bar.
3. aircraft according to claim 2, it is characterised in that the controller that the drive motor also including answering with each rotor pole pair is electrically connected.
4. aircraft according to claim 1, it is characterised in that described four rotor bars are divided into two pairs of both sides being symmetricly set on fuselage, this tandem side being arranged on described wing of two pairs of rotor bars.
5. the aircraft according to any one of Claims 1-4, it is characterized in that, described wing includes front fin, rear fin and dihedral wing sheet, and described rotating shaft is arranged horizontally between front fin and rear fin, one end of rotating shaft is connected with fuselage, and the other end is connected with dihedral wing sheet；Front fin has tip leading edge, rear fin has the slipstream wing.
6. aircraft according to claim 5, it is characterised in that described fuselage is provided with the motor that verts driving described axis of rotation.
7. aircraft according to claim 1, it is characterised in that described fuselage is additionally provided with two be arranged in parallel turn to and use steering wheel.
8. aircraft according to claim 1, it is characterised in that described afterbody is provided with empennage, underbelly is provided with undercarriage, and described undercarriage adopts wheeled construction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610094300.XA CN105775128A (en) | 2016-02-22 | 2016-02-22 | Flight vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610094300.XA CN105775128A (en) | 2016-02-22 | 2016-02-22 | Flight vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105775128A true CN105775128A (en) | 2016-07-20 |
Family
ID=56403506
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610094300.XA Pending CN105775128A (en) | 2016-02-22 | 2016-02-22 | Flight vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105775128A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081098A (en) * | 2016-08-24 | 2016-11-09 | 广州朱雀航空科技有限公司 | A kind of unmanned plane |
| CN107416178A (en) * | 2017-07-24 | 2017-12-01 | 金良 | Aircraft |
| CN107933904A (en) * | 2017-12-06 | 2018-04-20 | 佛山市神风航空科技有限公司 | A kind of flexible aircraft |
| CN108408025A (en) * | 2018-05-08 | 2018-08-17 | 成都军融项目管理有限公司 | A kind of aircraft system with stretching, extension function |
| CN108482668A (en) * | 2018-05-24 | 2018-09-04 | 深圳智航无人机有限公司 | Tilting type vertically taking off and landing flyer |
| CN108583910A (en) * | 2018-06-25 | 2018-09-28 | 山东飞奥航空发动机有限公司 | A kind of central power type multi-rotor aerocraft and control method |
| CN109661345A (en) * | 2016-09-08 | 2019-04-19 | 通用电气公司 | For the tilting rotor propulsion system of aircraft and with the aircraft of this system |
| CN115157946A (en) * | 2021-07-22 | 2022-10-11 | 田丰年 | Aerocar wing and rotor hybrid retraction system and aerocar |
| CN119058948A (en) * | 2024-11-04 | 2024-12-03 | 张宇阳 | A comprehensive non-spinning rotorcraft and its use method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060016930A1 (en) * | 2004-07-09 | 2006-01-26 | Steve Pak | Sky hopper |
| CN104443371A (en) * | 2013-09-16 | 2015-03-25 | 惠铁军 | Airplane capable of vertically taking off and landing |
| US20150151831A1 (en) * | 2013-12-04 | 2015-06-04 | Tamarack Aerospace Group, Inc. | Airflow Interrupting Devices |
| CN105129081A (en) * | 2015-08-12 | 2015-12-09 | 江阴市翔诺电子科技有限公司 | Novel multiaxial rotor aircraft and steering control method of the same under hovering state |
| CN105270622A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Composite wing aircraft with dihedral angle |
| CN105292460A (en) * | 2015-10-14 | 2016-02-03 | 南昌航空大学 | Tilt-rotor based on combination of four rotor wings and fixed wing |
-
2016
- 2016-02-22 CN CN201610094300.XA patent/CN105775128A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060016930A1 (en) * | 2004-07-09 | 2006-01-26 | Steve Pak | Sky hopper |
| CN104443371A (en) * | 2013-09-16 | 2015-03-25 | 惠铁军 | Airplane capable of vertically taking off and landing |
| US20150151831A1 (en) * | 2013-12-04 | 2015-06-04 | Tamarack Aerospace Group, Inc. | Airflow Interrupting Devices |
| CN105129081A (en) * | 2015-08-12 | 2015-12-09 | 江阴市翔诺电子科技有限公司 | Novel multiaxial rotor aircraft and steering control method of the same under hovering state |
| CN105292460A (en) * | 2015-10-14 | 2016-02-03 | 南昌航空大学 | Tilt-rotor based on combination of four rotor wings and fixed wing |
| CN105270622A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Composite wing aircraft with dihedral angle |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081098A (en) * | 2016-08-24 | 2016-11-09 | 广州朱雀航空科技有限公司 | A kind of unmanned plane |
| CN109661345A (en) * | 2016-09-08 | 2019-04-19 | 通用电气公司 | For the tilting rotor propulsion system of aircraft and with the aircraft of this system |
| CN109661345B (en) * | 2016-09-08 | 2022-04-12 | 通用电气公司 | Tilt-rotor propulsion system for aircraft and aircraft with such system |
| CN107416178A (en) * | 2017-07-24 | 2017-12-01 | 金良 | Aircraft |
| CN107933904A (en) * | 2017-12-06 | 2018-04-20 | 佛山市神风航空科技有限公司 | A kind of flexible aircraft |
| CN108408025A (en) * | 2018-05-08 | 2018-08-17 | 成都军融项目管理有限公司 | A kind of aircraft system with stretching, extension function |
| CN108482668A (en) * | 2018-05-24 | 2018-09-04 | 深圳智航无人机有限公司 | Tilting type vertically taking off and landing flyer |
| CN108583910A (en) * | 2018-06-25 | 2018-09-28 | 山东飞奥航空发动机有限公司 | A kind of central power type multi-rotor aerocraft and control method |
| CN115157946A (en) * | 2021-07-22 | 2022-10-11 | 田丰年 | Aerocar wing and rotor hybrid retraction system and aerocar |
| CN119636309A (en) * | 2021-07-22 | 2025-03-18 | 武汉玄天飞车航空科技有限公司 | A hybrid retractable system for flying car wings and rotors and flying car |
| CN119058948A (en) * | 2024-11-04 | 2024-12-03 | 张宇阳 | A comprehensive non-spinning rotorcraft and its use method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105775128A (en) | Flight vehicle | |
| CN204250360U (en) | Culvert type verts aircraft | |
| CN105620743B (en) | One kind is verted three rotor craft inclining rotary mechanisms | |
| CN202754143U (en) | Rotating engine vertical take-off and landing aircraft | |
| CN104401480A (en) | Ducted tilt aircraft | |
| CN107933909A (en) | A kind of high-speed and high-efficiency tilting wing unmanned vehicle | |
| CN204674831U (en) | Many fan arms aircraft | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN106938701A (en) | It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula four | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN106927040A (en) | It is a kind of can VTOL the rotor tailless configuration aircraft of tailstock formula four | |
| CN105346719A (en) | Perpendicular take-off and landing aircraft | |
| CN108394556A (en) | A kind of efficient tilting rotor wing unmanned aerial vehicle | |
| CN111232196A (en) | Three-tilting aircraft | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN106828919A (en) | It is a kind of can VTOL the coaxial Fan Jiang tailless configurations aircraft of tailstock formula | |
| CN204507265U (en) | Be with the multi-rotor aerocraft of the fixed-wing that verts | |
| CN205381400U (en) | Aircraft | |
| CN206187340U (en) | Aircraft | |
| CN205998126U (en) | A kind of unmanned plane during flying system | |
| CN208198824U (en) | A kind of vertically taking off and landing flyer | |
| CN212243812U (en) | Tilting duck type layout aircraft | |
| CN105173076A (en) | VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160720 |