CN206502045U - Mobile launch formula autogyro - Google Patents
Mobile launch formula autogyro Download PDFInfo
- Publication number
- CN206502045U CN206502045U CN201621309666.6U CN201621309666U CN206502045U CN 206502045 U CN206502045 U CN 206502045U CN 201621309666 U CN201621309666 U CN 201621309666U CN 206502045 U CN206502045 U CN 206502045U
- Authority
- CN
- China
- Prior art keywords
- propeller hub
- propeller
- fuselage
- support
- rotor
- 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.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a kind of Mobile launch formula autogyro, fuselage, radome fairing, constraint bag, the first to the second V-type horizontal tail, vertical fin, folding rotor, rotating shaft, stand spring, motor, propeller, propeller installation axle, the mechanical, electrical tune of first to fourth rudder, receiver and power module are included.The utility model can by Canon launching, submarine it is latent penetrate, opportunity of combat is carried the modes such as air-drop and launched and arrives at purpose spatial domain, then it flies not against self power during this, while flying speed is faster, launches more hidden, penetration ability is stronger；And compact conformation, with transmitting offline mode and cruise mode both of which, structure is different in both modes, and aerodynamic configuration is different；In addition, in engine cut-off, drought resisting crash ability can be improved by the advantage that self gravitation potential energy is rotor maneuver energy.
Description
Technical field
The utility model is related to unmanned plane field, more particularly to a kind of Mobile launch formula autogyro.
Background technology
Conventional unmanned plane, mainly rolling start, hand-thrown or catapult-assisted take-off, aircraft need to arrive at mesh by itself flight
Region is marked, while there are certain requirements to time place.
In general, conventional unmanned plane reaches the destination by self power flight, and speed is slow, and penetration ability is weak, takes off
Requirement to place is higher, and after engine cut-off, easily crashes.
Utility model content
Technical problem to be solved in the utility model is that there is provided a kind of machine for defect involved in background technology
Dynamic emission-type autogyro.
The utility model uses following technical scheme to solve above-mentioned technical problem：
Mobile launch formula autogyro, includes fuselage, radome fairing, constraint bag, the first to the second V-type horizontal tail, vertical fin, folding
Folded rotor, rotating shaft, stand spring, motor, propeller, propeller installation axle, the mechanical, electrical tune of first to fourth rudder, receiver and electricity
Source module；
The motor is arranged on the head end of fuselage；The first to the second V-type horizontal tail and vertical fin are correspondingly arranged at the machine
The afterbody of body；The mechanical, electrical tune of electricity, receiver, power module are arranged in fuselage；
Described propeller installation axle one end and the output shaft of the motor are fixedly linked, and the other end is used to install the spiral
Oar；The blade of the propeller can install the axially fuselage around the propeller on its sub warhead and fold；
The folding rotor includes folding propeller hub, the first to the 3rd rotary blade, universal joint and propeller hub support；
The folding propeller hub includes propeller hub body, propeller hub axis, bearing and the first to the 3rd development mechanism；
One end of the propeller hub axis is connected by bearing with the propeller hub body so that the propeller hub body can be around oar
Hub axis is freely rotated；
Described first to the 3rd development mechanism includes oar folder, gantry, rotor spring and latch-up structure, wherein, the oar
Folder is hinged by screw shaft and the propeller hub body, can be rotated upwardly and downwardly around the propeller hub body；Described gantry and the propeller hub
Body is fixedly linked；The rotor spring one end and described gantry are fixedly linked, and the other end and oar folder are fixedly linked, described
Plane when rotor spring and oar folder are rotated is in same plane, and in extended state；The latch-up structure is used for
The oar folder, which is turned to, determines the oar clamp lock when being in same plane with the propeller hub body, it is not rotated further by；
Described first to the 3rd rotary blade is corresponding with the oar folder of the described first to the 3rd development mechanism respectively to be fixedly linked；
The fuselage is provided with the support-folding groove for being used for accommodating propeller hub support and correspondence accommodates the first to the 3rd rotor
The rotor folded slot of piece；
One end of the propeller hub support is connected by universal joint with the other end of the propeller hub axis, and the other end is away from end
It is side walls hinged by two of the rotating shaft and the support-folding groove at default distance so that the propeller hub support can be around
The axis of rotation is folded in the support-folding groove, and when propeller hub support-folding is into the support-folding groove, it is described
First to the 3rd rotary blade can be separately folded into the described first to the 3rd rotor folded slot；
Described stand spring one end is connected with the one end of propeller hub support away from propeller hub, and the other end is connected with fuselage, in stretching
State, for by the propeller hub support from the support-folding groove pull-up, cause folding rotor be in deployed condition；
3rd steering wheel, the 4th steering wheel are arranged on the propeller hub support, pass through pull bar and the Universal connector respectively
Head is connected, and is respectively used to control the universal joint progress pitch and left and right to vert, and then control the pitching of propeller hub plane
With verting；
The constraint bag includes a circular constraint circle and two restrainings；The blade of the propeller is in rugosity
State, the radome fairing is covered on the propeller；The constraint circle is fixed on the fuselage, for by the propeller hub support beam
It is tied in the support-folding groove, the first to the 3rd rotary blade is strapped in the described first to the 3rd rotor folded slot respectively；Institute
State two equal one end of restraining with the radome fairing to be connected, the other end is connected with the radome fairing, and the radome fairing is fixed on
On the head end of the fuselage；
First steering wheel is arranged in fuselage, and its output end is connected with blade by rocking arm, for receiving control
The constraint circle is cut off after electric current, the fuselage is provided with the through hole that the constraint circle is cut off for blade；
Second steering wheel is arranged on fuselage, the driftage for controlling vertical fin and then control gyroplane；
The universal joint is adjusted and is electrically connected by steering wheel and the electricity, and the electricity is adjusted also mechanical, electrical with motor, reception respectively
Source module is electrically connected, wherein, the receiver, which is used to receive, to be instructed, and passes to the electricity by instruction morphing for control signal
Adjust；The electricity is adjusted according to the control signal distribution electric current for being used to receive to the motor and first to fourth steering wheel；The electricity
Machine is used to then control speed winged before gyroplane according to the rotating speed of the current control propeller received.
As the further prioritization scheme of the utility model Mobile launch formula autogyro, the latch-up structure includes card
Hook and spring leaf, wherein, the end of the snap fit and propeller hub body is hinged, hook part can be rotated around the propeller hub body；Spring
Piece one end and the propeller hub body offset, and the end of the other end and the snap fit offsets, for being turned to and institute in oar folder
Stating spring leaf when propeller hub body is in same plane promotes the hook part of the snap fit that the oar clamp lock is dead.
As the further prioritization scheme of the utility model Mobile launch formula autogyro, the fuselage is streamlined.
As the further prioritization scheme of the utility model Mobile launch formula autogyro, the power module uses lithium
Battery.
The utility model uses above technical scheme compared with prior art, with following technique effect：
1. by Canon launching, submarine it is latent penetrate, opportunity of combat is carried the modes such as air-drop and launched and arrives at purpose spatial domain, then during this
It flies not against self power, while flying speed is faster, launches more hidden, penetration ability is stronger；
2. the utility model compact conformation, with offline mode and cruise mode both of which is launched, in both modes
Structure is different, and aerodynamic configuration is different；
Can be the excellent of rotor maneuver energy by self gravitation potential energy 3. the utility model is in engine cut-off
Gesture, improves drought resisting crash ability.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model；
Fig. 2 is the structural representation of propeller hub support-folding in the utility model；
The structural representation that motor is connected with propeller in Fig. 3 the utility model；
Fig. 4 is the structural representation of folding rotor in the utility model；
Fig. 5 is structural representation when propeller hub expansion is folded in the utility model；
Fig. 6 is that structural representation when propeller hub is folded is folded in the utility model；
Fig. 7 is the structural representation that bag is fettered in the utility model；
Fig. 8 is the structural representation of the utility model in the transmission mode；
Fig. 9 is structural representation of the utility model under expansion pattern；
Figure 10 is structural representation of the utility model under cruise mode.
In figure, 1- radome fairings, 2- propellers, 3- rotor folded slots, 4- support-folding grooves, 5- vertical fins, 6-V type horizontal tails, 7-
Spring connecting hole on propeller hub support, 8- rotating shafts, 9- propeller hub supports, 10- power modules, 11- motors, the steering wheels of 12- first, 13-
Spring connecting hole in fuselage, 14- electricity is adjusted, the steering wheels of 15- second, 16- receivers, 17- propellers, 18- propeller installation axles,
19- sub warheads, 20- rotary blades, 21- folds propeller hub, 22- universal joints, the steering wheels of 23- the 3rd, the steering wheels of 24- the 4th, 25- propeller hub branch
Spring mounting hole on spring mounting hole on frame, 26- oars folder, 27- gantry, 28- gantry, 29- bearings, 30- propeller hub axis,
31- screw shafts, 32- grabs, 33- spring leafs, 34-- oars folder, 35- restrainings, 36- constraint circles.
Embodiment
The technical solution of the utility model is described in further detail below in conjunction with the accompanying drawings：
The utility model discloses a kind of Mobile launch formula autogyro, fuselage, radome fairing, constraint bag, first are included
To the second V-type horizontal tail, vertical fin, folding rotor, rotating shaft, stand spring, motor, propeller, propeller installation axle, first to fourth
The mechanical, electrical tune of rudder, receiver and power module.
As shown in figure 1, the motor is arranged on the head end of fuselage；The first to the second V-type horizontal tail is corresponding with vertical fin to be set
Put the afterbody in the fuselage.
As shown in Fig. 2 the mechanical, electrical tune of electricity, receiver, power module are arranged in fuselage.
As shown in figure 3, described propeller installation axle one end and the output shaft of the motor are fixedly linked, the other end is used to pacify
Fill the propeller；
The blade of the propeller can install the axially fuselage around the propeller on its sub warhead and fold.
As shown in figure 4, the folding rotor includes folding propeller hub, the first to the 3rd rotary blade, universal joint and propeller hub branch
Frame.
As shown in figure 5, the folding propeller hub includes propeller hub body, propeller hub axis, bearing and the first to the 3rd development mechanism；
One end of the propeller hub axis is connected by bearing with the propeller hub body so that the propeller hub body can be around oar
Hub axis is freely rotated.
Described first to the 3rd development mechanism includes oar folder, gantry, rotor spring and latch-up structure, wherein, the oar
Folder is hinged by screw shaft and the propeller hub body, can be rotated upwardly and downwardly around the propeller hub body；Described gantry and the propeller hub
Body is fixedly linked；The rotor spring one end and described gantry are fixedly linked, and the other end and oar folder are fixedly linked, described
Plane when rotor spring and oar folder are rotated is in same plane, and in extended state；The latch-up structure is used for
The oar folder, which is turned to, determines the oar clamp lock when being in same plane with the propeller hub body, it is not rotated further by；
Described first to the 3rd rotary blade is corresponding with the oar folder of the described first to the 3rd development mechanism respectively to be fixedly linked.
The latch-up structure includes snap fit and spring leaf, wherein, the end of snap fit and the propeller hub body are hinged, hook part energy
It is enough to be rotated around the propeller hub body；Spring leaf one end and the propeller hub body offset, and the end of the other end and the snap fit offsets,
For the oar press from both sides turn to be in same plane with the propeller hub body when spring leaf promote the hook part of the snap fit by institute
State oar clamp lock dead.
The fuselage is provided with the support-folding groove for being used for accommodating propeller hub support and correspondence accommodates the first to the 3rd rotor
The rotor folded slot of piece.
As shown in figure 4, one end of the propeller hub support is connected by universal joint with the other end of the propeller hub axis, separately
One end is far from side walls hinged by two of the rotating shaft and the support-folding groove at the default distance in end so that the propeller hub
Support can be folded in the support-folding groove around the axis of rotation, and in propeller hub support-folding to the support-folding groove
When middle, the described first to the 3rd rotary blade can be separately folded into the described first to the 3rd rotor folded slot.
Described stand spring one end is connected with the one end of propeller hub support away from propeller hub, and the other end is connected with fuselage, in stretching
State, for by the propeller hub support from the support-folding groove pull-up, cause folding rotor be in deployed condition.
3rd steering wheel, the 4th steering wheel are arranged on the propeller hub support, pass through pull bar and the Universal connector respectively
Head is connected, and is respectively used to control the universal joint progress pitch and left and right to vert, and then control the pitching of propeller hub plane
With verting.
As shown in fig. 7, the constraint bag includes a circular constraint circle and two restrainings.
As shown in figure 8, the blade of the propeller is in folded state, the radome fairing is covered on the propeller；
The constraint circle is fixed on the fuselage, for the propeller hub support to be strapped in the support-folding groove,
First to the 3rd rotary blade is strapped in the described first to the 3rd rotor folded slot respectively；
Described equal one end of two restrainings is connected with the radome fairing, and the other end is connected with the radome fairing, will be described whole
Stream cover is fixed on the head end of the fuselage.
As shown in Fig. 2 first steering wheel is arranged in fuselage, its output end is connected with blade by rocking arm, for
Receive and the constraint circle is cut off after control electric current, the fuselage is provided with the through hole that the constraint circle is cut off for blade.
Second steering wheel is arranged on fuselage, the driftage for controlling vertical fin and then control gyroplane.
The universal joint is adjusted and is electrically connected by steering wheel and the electricity, and the electricity is adjusted also mechanical, electrical with motor, reception respectively
Source module is electrically connected, wherein, the receiver, which is used to receive, to be instructed, and passes to the electricity by instruction morphing for control signal
Adjust；The electricity is adjusted according to the control signal distribution electric current for being used to receive to the motor and first to fourth steering wheel；The electricity
Machine is used to then control speed winged before gyroplane according to the rotating speed of the current control propeller received.
As shown in fig. 6, when folding rotor is folded, the grab in the first to the 3rd development mechanism is gently turned round
Dynamic, grab can not catch on oar folder end, and now the unblock of oar folder, can be rotated around propeller hub body, first by propeller hub support-folding in fuselage
Neck, then fuselage is close in rotary blade folding.
The fuselage decision design is streamlined.
The power module preferentially uses lithium battery.
This law also discloses a kind of control method based on the Mobile launch formula autogyro, comprises the steps of：
Step 1）, launch the Mobile launch formula autogyro；
Step 2）, expansion instruction is sent to the Mobile launch formula autogyro；
Step 3）, the receiver, which is received, to deploy after instruction, and distribution electric current gives first steering wheel；
Step 4）, first steering wheel, which is received, controls the blade on its output end rocking arm to cut off the beam after control electric current
Tie up circle；
Step 5）, radome fairing with constraint bag come off；
Step 6）, the rotor spring in the first to the 3rd development mechanism pull respectively the first to the 3rd rotary blade from first to
Upspring in 3rd rotor folded slot so that the oar folder in the first to the 3rd development mechanism is turned to be in together with the propeller hub body
One plane, now, its locked corresponding oar folder of latch-up structure in the first to the 3rd development mechanism；
Step 7）, stand spring pull propeller hub support upspring from support-folding groove so that folding rotor be in expansion shape
State；
Step 8）, as gyroplane falls, the first to the 3rd rotary blade is blown by air-flow, around propeller hub middle shaft rotation, rotor
The transform gravitational energy of machine is the kinetic energy of rotor, and gyroplane, which slows down, to fall；
Step 9）, the lift and gravitational equilibrium produced after rotary blade spin stabilization, when gyroplane at the uniform velocity falls, receiver
Electric current is distributed to the motor；
Step 10）, motor rotated, and the propeller propeller folded under the influence of centrifugal force thrown away, propeller rotation
Pulling force is produced, drives gyroplane to advance, gyroplane enters cruising condition.
Remote control transmission signal, receiver receive signal, lithium battery to electricity adjust power supply, electricity adjust distribute the current to motor and
Signal is passed to electric tune by steering wheel, receiver, and control electricity adjusts the distribution to motor and first to fourth steering wheel electric current, and then manipulates
Unmanned plane.
Gyroplane is completed after In-Flight Deployment, and ground remote control device sends signal, and fuselage interior receiver receives signal, passes through control
System electricity adjusts the electric current for distributing to motor to carry out the rotating speed of controlled motor, reaches the purpose of the flying speed of regulation gyroplane.Receiver
The steering wheel of same control folding rotor, realizes the manipulation to rotor pitching.Receiver is real by the control to fuselage vertical fin steering wheel
The control now gone off course to gyroplane.
The utility model can be reached the destination by Canon launching or the transmitting of carrying opportunity of combat not against self power flight,
And In-Flight Deployment is realized in destination overhead, into cruising condition.
As shown in Fig. 8, Fig. 9, Figure 10, the utility model includes three kinds of mode of operations, Mobile launch pattern, expansion pattern,
Cruise mode.The utility model is studied by designing to calculate, and breaks through Mobile launch Automatic-expanding control technology and full machine gas
The key technologies such as movement and motor-driven integrative design.The technological approaches that autogyro realizes Mobile launch is found, is new unmanned gyroplane
Theory and technology basis is established in the application for carrying out maneuverability.
Those skilled in the art of the present technique are it is understood that unless otherwise defined, all terms used herein（Including skill
Art term and scientific terminology）With the general understanding identical meaning with the those of ordinary skill in the utility model art
Justice.It should also be understood that those terms defined in such as general dictionary should be understood that with upper with prior art
The consistent meaning of meaning hereinafter, and unless defined as here, will not with idealization or excessively formal implication come
Explain.
Above-described embodiment, is entered to the purpose of this utility model, technical scheme and beneficial effect
One step is described in detail, be should be understood that and be the foregoing is only embodiment of the present utility model, is not used to limit
The utility model processed, all within spirit of the present utility model and principle, any modification, equivalent substitution and improvements done etc.,
It should be included within protection domain of the present utility model.
Claims (4)
1. Mobile launch formula autogyro, it is characterised in that put down comprising fuselage, radome fairing, constraint bag, the first to the second V-type
Tail, vertical fin, folding rotor, rotating shaft, stand spring, motor, propeller, propeller installation axle, first to fourth rudder be mechanical, electrical to be adjusted,
Receiver and power module；
The motor is arranged on the head end of fuselage；The first to the second V-type horizontal tail and vertical fin are correspondingly arranged at the fuselage
Afterbody；The mechanical, electrical tune of electricity, receiver, power module are arranged in fuselage；
Described propeller installation axle one end and the output shaft of the motor are fixedly linked, and the other end is used to install the propeller；
The blade of the propeller can install the axially fuselage around the propeller on its sub warhead and fold；
The folding rotor includes folding propeller hub, the first to the 3rd rotary blade, universal joint and propeller hub support；
The folding propeller hub includes propeller hub body, propeller hub axis, bearing and the first to the 3rd development mechanism；
One end of the propeller hub axis is connected by bearing with the propeller hub body so that the propeller hub body can be in propeller hub
Axle is freely rotated；
Described first to the 3rd development mechanism includes oar folder, gantry, rotor spring and latch-up structure, wherein, the oar folder is logical
Cross screw shaft and the propeller hub body is hinged, can be rotated upwardly and downwardly around the propeller hub body；Described gantry and the propeller hub body
It is fixedly linked；The rotor spring one end and described gantry are fixedly linked, and the other end and oar folder are fixedly linked, the rotor
Plane when spring and oar folder are rotated is in same plane, and in extended state；The latch-up structure is used for described
Oar folder, which is turned to, determines the oar clamp lock when being in same plane with the propeller hub body, it is not rotated further by；
Described first to the 3rd rotary blade is corresponding with the oar folder of the described first to the 3rd development mechanism respectively to be fixedly linked；
The fuselage is provided with the support-folding groove for being used for accommodating propeller hub support and correspondence accommodates the first to the 3rd rotary blade
Rotor folded slot；
One end of the propeller hub support is connected by universal joint with the other end of the propeller hub axis, and the other end is default away from end
Distance at it is side walls hinged by two of the rotating shaft and the support-folding groove so that the propeller hub support can be around described
Axis of rotation is folded in the support-folding groove, and when propeller hub support-folding is into the support-folding groove, described first
It can be separately folded into the described first to the 3rd rotor folded slot to the 3rd rotary blade；
Described stand spring one end is connected with the one end of propeller hub support away from propeller hub, and the other end is connected with fuselage, in extended state,
For by the propeller hub support from the support-folding groove pull-up, cause folding rotor be in deployed condition；
3rd steering wheel, the 4th steering wheel are arranged on the propeller hub support, pass through pull bar and the universal joint phase respectively
Even, it is respectively used to control the universal joint progress pitch and left and right to vert, and then controls the pitching of propeller hub plane with inclining
Turn；
The constraint bag includes a circular constraint circle and two restrainings；The blade of the propeller is in folded state,
The radome fairing is covered on the propeller；The constraint circle is fixed on the fuselage, for the propeller hub support to be fettered
The described first to the 3rd rotor folded slot is strapped in respectively in the support-folding groove, by the first to the 3rd rotary blade；It is described
Two equal one end of restraining are connected with the radome fairing, and the other end is connected with the radome fairing, and the radome fairing is fixed on into institute
State on the head end of fuselage；
First steering wheel is arranged in fuselage, and its output end is connected with blade by rocking arm, for receiving control electric current
After cut off it is described constraint circle, the fuselage be provided with for blade cuts off it is described constraint circle through hole；
Second steering wheel is arranged on fuselage, the driftage for controlling vertical fin and then control gyroplane；
The universal joint by steering wheel and it is described electricity adjust be electrically connected, it is described electricity adjust also respectively with motor, receiver, power supply mould
Block is electrically connected, wherein, the receiver be used for receive instruct, and by it is instruction morphing for control signal pass to it is described electricity adjust；
The electricity is adjusted according to the control signal distribution electric current for being used to receive to the motor and first to fourth steering wheel；The motor is used
In the speed for then controlling to fly before gyroplane according to the rotating speed of the current control propeller received.
2. the Mobile launch formula autogyro according to right wants 1, it is characterised in that the latch-up structure comprising snap fit and
Spring leaf, wherein, the end of the snap fit and propeller hub body is hinged, hook part can be rotated around the propeller hub body；Spring leaf one
End and the propeller hub body offset, and the end of the other end and the snap fit offsets, for being turned to and the oar in oar folder
Spring leaf promotes the hook part of the snap fit that the oar clamp lock is dead when hub body is in same plane.
3. the Mobile launch formula autogyro according to right wants 1, it is characterised in that the fuselage is streamlined.
4. the Mobile launch formula autogyro according to right wants 1, it is characterised in that the power module is using lithium electricity
Pond.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621309666.6U CN206502045U (en) | 2016-12-01 | 2016-12-01 | Mobile launch formula autogyro |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621309666.6U CN206502045U (en) | 2016-12-01 | 2016-12-01 | Mobile launch formula autogyro |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206502045U true CN206502045U (en) | 2017-09-19 |
Family
ID=59842680
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621309666.6U Expired - Fee Related CN206502045U (en) | 2016-12-01 | 2016-12-01 | Mobile launch formula autogyro |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206502045U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516147A (en) * | 2016-12-01 | 2017-03-22 | 南京航空航天大学 | Mobile launch type autogyro and control method thereof |
| CN113306710A (en) * | 2021-07-28 | 2021-08-27 | 西安羚控电子科技有限公司 | Tube type launching composite wing unmanned aerial vehicle and method for realizing roll action |
| CN113335504A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Rotor wing fairing of composite wing aircraft |
-
2016
- 2016-12-01 CN CN201621309666.6U patent/CN206502045U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516147A (en) * | 2016-12-01 | 2017-03-22 | 南京航空航天大学 | Mobile launch type autogyro and control method thereof |
| CN113306710A (en) * | 2021-07-28 | 2021-08-27 | 西安羚控电子科技有限公司 | Tube type launching composite wing unmanned aerial vehicle and method for realizing roll action |
| CN113335504A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Rotor wing fairing of composite wing aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106516147B (en) | Mobile launch formula autogyro and its control method | |
| CN109018349B (en) | Multi-rotor unmanned aerial vehicle system suitable for stable throwing under high-speed flight condition | |
| US10850835B2 (en) | Unmanned aerial vehicle with monolithic wing and twin-rotor propulsion/lift modules | |
| US10538321B2 (en) | Tri-rotor aircraft capable of vertical takeoff and landing and transitioning to forward flight | |
| US11912404B2 (en) | Vertical takeoff and landing aircraft | |
| EP3386856B1 (en) | Uav with wing-plate assemblies providing efficient vertical takeoff and landing capability | |
| CN110775264B (en) | Water-air amphibious unmanned aircraft and control method thereof | |
| CN106143911B (en) | A kind of foldable unmanned plane that individual soldier carries, can cartridge type storage and emit | |
| CN206502045U (en) | Mobile launch formula autogyro | |
| US10017278B2 (en) | Gyroscopic orbiter with vertical takeoff and vertical landing capabilities | |
| CN106005395A (en) | Tilting mechanism capable of being hidden in wing | |
| CN110386248A (en) | A kind of rotation quadrotor high-speed unmanned aerial vehicle and its control method | |
| CN108382590A (en) | Composite wing unmanned plane | |
| JP2021535028A (en) | Launch system | |
| CN108791859B (en) | Rotor unmanned aerial vehicle who supports closely fast | |
| JP2023508614A (en) | an aircraft with propellers positioned at the wingtips | |
| AU2021275719A1 (en) | A vertical take-off and landing aircraft, methods and systems for controlling a vertical take-off and landing aircraft | |
| CN113371182A (en) | Barrel-type transmitted reconnaissance attack rotor unmanned aerial vehicle | |
| CN110562448A (en) | Tailstock type unmanned aerial vehicle | |
| CN109533310B (en) | Miniature coaxial double-rotor suspension device of maneuvering launching foldable type | |
| RU2579235C1 (en) | Light convertible high-speed helicopter | |
| CN208498792U (en) | A kind of rotor wing unmanned aerial vehicle quickly approached | |
| CN112829933A (en) | Aircraft with deployable duct wings | |
| CN206394895U (en) | Oil electric mixed dynamic rotor manned aircraft | |
| CN108639334A (en) | A kind of interurban logistics transportation system based on tilting rotor shipping unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170919 Termination date: 20181201 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |