CN106564610A - Auxiliary taking-off and landing system for rotor unmanned plane - Google Patents
Auxiliary taking-off and landing system for rotor unmanned plane Download PDFInfo
- Publication number
- CN106564610A CN106564610A CN201610946093.6A CN201610946093A CN106564610A CN 106564610 A CN106564610 A CN 106564610A CN 201610946093 A CN201610946093 A CN 201610946093A CN 106564610 A CN106564610 A CN 106564610A
- Authority
- CN
- China
- Prior art keywords
- landing
- landing platform
- aerial vehicle
- unmanned aerial
- rotor wing
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/007—Helicopter portable landing pads
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D3/00—Control of position or direction
- G05D3/12—Control of position or direction using feedback
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Toys (AREA)
Abstract
The invention discloses an auxiliary taking-off and landing system for a rotor unmanned plane. The auxiliary taking-off and landing system for a rotor unmanned plane includes a pedestal and a taking-off and landing platform, wherein the taking-off and landing platform is arranged on the pedestal; a detection assembly is arranged on the taking-off and landing platform for detecting flight parameters and flight attitude of a rotor unmanned plane; a lifting assembly and an inclination assembly are arranged between the pedestal and the taking-off and landing platform; the lifting assembly is used for lifting of the taking-off and landing platform; the inclination assembly is used for adjusting the inclined state of the inclination assembly; and the lifting assembly and the inclination assembly are mutually coordinated to adjust the height and the inclined state of the taking-off and landing platform so as to accord with the flight attitude of the rotor unmanned plane, so that taking-off and landing becomes convenient. The auxiliary system for a rotor unmanned plane has the advantage of improving the taking-off and landing reliability of the unmanned plane.
Description
Technical field
The invention mainly relates to aerospace craft technical field, refers in particular to a kind of rotor wing unmanned aerial vehicle auxiliary landing system.
Background technology
With the fast development of rotor wing unmanned aerial vehicle application technology in world wide, rotor wing unmanned aerial vehicle obtains more and more extensive
Using the application particularly in terms of logistics is already close to practicality.But because weather is received in the flight and landing of rotor wing unmanned aerial vehicle
It is very big with the impact of small range sinuous flow, the how application even more a great problem under urban area complexity flow conditions.It is existing
Flight performance of the rotor wing unmanned aerial vehicle under complicated weather and sinuous flow environment has had certain lifting, and in complicated weather and unrest
Landing under stream environment then never has effective solution.
The content of the invention
The technical problem to be solved in the present invention is that：For the technical problem that prior art is present, the present invention provides one
Plant the rotor wing unmanned aerial vehicle auxiliary landing system for improving landing reliability.
To solve above-mentioned technical problem, technical scheme proposed by the present invention is：
A kind of rotor wing unmanned aerial vehicle aids in landing system, including base and landing platform, and the landing stage+module is in the base
On, the detection components for detecting rotor wing unmanned aerial vehicle flight parameter and flight attitude, the bottom are installed on the landing platform
The lifting assembly for being lifted to landing platform is provided between seat and the landing platform and is put down for adjusting landing
The tilt component of platform heeling condition；The lifting assembly and tilt component cooperate adjust the landing platform height and
Heeling condition is easy to landing so that the flight attitude with the rotor wing unmanned aerial vehicle matches.
As the further improvement of above-mentioned technical proposal：
Fixation kit for being fixed to rotor wing unmanned aerial vehicle is installed on the landing platform.
The fixation kit includes motor, drive mechanism and two pieces of fixture blocks, and described rising is stretched out in the upper end of the fixture block
Drop platform, two pieces of fixture blocks are connected by drive mechanism with the motor, and move under the driving of motor with
Clamp the undercarriage of the rotor wing unmanned aerial vehicle.
Three-dimensional localization component is provided with the base, for realizing landing platform movement in the horizontal plane and vertically
Rotary motion on direction.
The three-dimensional localization component includes X-axis moving cell, Y-axis moving cell and Z axis rotary unit, the X-axis motion
Unit and Y-axis moving cell are used to cooperate to realize the movement in the horizontal plane of landing platform, and the Z axis rotary unit is used
In the rotation for realizing the landing platform in the vertical direction.
The lifting assembly includes elevator, the lower surface middle part phase of one end of the elevator and the landing platform
Even, the other end is connected with the base.
It is connected by universal joint between the elevator and the landing platform.
The tilt component includes being installed on multiple line wheels of the landing platform the week side of boss, and the line wheel is flat with the landing
Connected by line between platform, the line wheel drives rotation and realizes the flexible of line by servomotor.
The detection components include multiple ultrasonic sensors and multiple radar sensors, multiple ultrasonic sensors
Be installed on the week side of boss of the landing platform, for monitoring flight attitude during rotor wing unmanned aerial vehicle landing；Multiple radar sensings
Device is annularly uniformly installed on the landing platform, for detecting to the flight parameter of rotor wing unmanned aerial vehicle.
Be provided with display module on the landing platform, for show the landing platform state and realize warning and
Guiding function.
Compared with prior art, it is an advantage of the current invention that：
The rotor wing unmanned aerial vehicle auxiliary landing system of the present invention, the flight ginseng of the rotor wing unmanned aerial vehicle of landing is treated by detection components detection
Number and flight attitude, are adjusted to the height of landing platform with tilt component by lifting assembly with heeling condition, so as to rise
The flying height of drop platform and unmanned plane, flight attitude match, so as to facilitate the landing operation of unmanned plane, raising unmanned plane to exist
Landing reliability under complicated weather and sinuous flow environment.
Description of the drawings
Fig. 1 is the main structure diagram of the present invention.
Fig. 2 is the landing platform overlooking the structure diagram of the present invention.
Fig. 3 is the structural representation of the fixation kit of the present invention.
Fig. 4 is the structural representation of the three-dimensional localization component of the present invention.
Fig. 5 is the structural representation of the tilt component of the present invention.
Fig. 6 is one of the operating diagram of the present invention in concrete application embodiment.
Fig. 7 is the two of operating diagram of the present invention in concrete application embodiment.
Fig. 8 is the three of operating diagram of the present invention in concrete application embodiment.
Fig. 9 is the four of operating diagram of the present invention in concrete application embodiment.
Figure 10 is the five of operating diagram of the present invention in concrete application embodiment.
Figure 11 is the six of operating diagram of the present invention in concrete application embodiment.
Label is represented in figure：1st, landing platform；2nd, tilt component；21st, line；22nd, directive wheel；23rd, line wheel；24th, servo electricity
Machine；3rd, three-dimensional localization component；31st, X-axis moving cell；32nd, Y-axis moving cell；33rd, Z axis rotary unit；4th, fixation kit；41、
Fixture block；42nd, connecting rod；43rd, camshaft；44th, shaft coupling；45th, installing plate；46th, support bar；47th, motor；5th, display module；
6th, detection components；61st, radar sensor；62nd, ultrasonic sensor；7th, lifting assembly；71st, elevator；8th, unmanned plane；81st, rise
Fall frame.
Specific embodiment
Below in conjunction with Figure of description and specific embodiment, the invention will be further described.
As shown in Figure 1 to 11, the rotor wing unmanned aerial vehicle auxiliary landing system of the present embodiment, including base and landing platform 1,
Landing platform 1 is installed on base, is provided with landing platform 1 for detecting the flight parameter of rotor wing unmanned aerial vehicle 8 and flight attitude
Detection components 6, be provided between base and landing platform 1 lifting assembly 7 for being lifted to landing platform 1 and
For adjusting the tilt component 2 of the heeling condition of landing platform 1；Lifting assembly 7 and tilt component 2 cooperate and adjust landing platform
1 height and heeling condition are easy to landing so that the flight attitude with rotor wing unmanned aerial vehicle 8 matches.The present invention rotor nobody
Machine aids in landing system, and the flight parameter and flight attitude of the rotor wing unmanned aerial vehicle 8 of landing are treated by the detection of detection components 6, passes through
Lifting assembly 7 is adjusted to the height of landing platform 1 with tilt component 2 with heeling condition, so that landing platform 1 and unmanned plane
8 flying height, flight attitude match, so as to facilitate the landing operation of unmanned plane 8, improve unmanned plane 8 in complicated weather and
Landing reliability under sinuous flow environment.
As shown in Fig. 3, Fig. 6 to Fig. 8, in the present embodiment, it is provided with landing platform 1 for carrying out to rotor wing unmanned aerial vehicle 8
Fixed fixation kit 4.Fixation kit 4 includes motor 47, drive mechanism and two pieces of fixture blocks 41, and drive mechanism includes connecting rod
42nd, camshaft 43 and shaft coupling 44, the lower section both sides of wherein landing platform 1 are provided with gripper shoe, peace are provided between gripper shoe
Dress plate 45, installing plate 45 is supported in gripper shoe by support bar 46, and motor 47 is then installed on installing plate 45, drives electricity
The rotating shaft of machine 47 is connected by shaft coupling 44 with camshaft 43, and camshaft 43 passes through the bottom phase of connecting rod 42 and two fixture blocks 41
Even, the top of two fixture blocks 41 then projects landing platform 1.When fastening to unmanned plane 8, motor 47 is rotated, and is driven
Camshaft 43 is rotated, and by connecting rod 42 two left and right directions of fixture block 41 movements are driven, and makes two fixture blocks 41 clamp unmanned plane 8 respectively
Sledge type undercarriage 81, realize fixation of the unmanned plane 8 in landing platform 1, the wherein front end of fixture block 41 contacts with undercarriage 81
The curved shape in position, when two fixture blocks 41 are clamped undercarriage 81 and moved outward, 8 undercarriage of unmanned plane 81 can in arc
Run downwards in the presence of shape fixture block 41, so that it is fastened after contacting with landing platform 1, it is ensured that the reliability of fastening.
Wherein fixation kit 4 could be arranged to multigroup, the front-end and back-end of landing platform 1 is respectively arranged in, to ensure that unmanned plane 8 can
Also can reliably fix in heeling condition.
As shown in Fig. 2 in the present embodiment, detection components 6 include four ultrasonic sensors 62 and four radar sensors
61, four ultrasonic sensors 62 are installed at the corner of landing platform 1, for monitoring flight during 8 landing of rotor wing unmanned aerial vehicle
Posture；Four radar sensors 61 are annularly uniformly installed on four side centers of landing platform 1 and away from side certain distance,
It arranges between radar sensor 61 in 45 degree angles, for the flight parameter to rotor wing unmanned aerial vehicle 8（Including quantity, position, fly
Line direction, flying height, flight speed etc.）Detected.Radar sensor 61 and the collective effect of ultrasonic sensor 62 are mutual
Supplement, it is ensured that flight attitude of the rotor wing unmanned aerial vehicle 8 during landing can real-time and accurately be monitored to and feed back to control
In system.In addition display module 5 is provided with landing platform 1, using LED light group and H-shaped arrangement, with small volume, power consumption
Less, brightness is high and the characteristics of various color, and different color and luminance can be utilized to combine show the state of landing platform 1
And realize warning and guiding function.
As shown in Figure 1 and Figure 4, in the present embodiment, three-dimensional localization component 3 is provided with base, for realizing landing platform 1
Rotary motion in movement in the horizontal plane and vertical direction, functions simultaneously as base and plays a supporting role.It is wherein three-dimensional fixed
Hyte part 3 includes X-axis moving cell 31, Y-axis moving cell 32 and Z axis rotary unit 33, and X-axis moving cell 31 and Y-axis are moved
Unit 32 is used to cooperate to realize the movement in the horizontal plane of landing platform 1, and Z axis rotary unit 33 is used to realize that landing is put down
The rotation of the in the vertical direction of platform 1.Wherein X-axis moving cell 31 includes X-axis slide rail and sliding sleeve, and X-axis slide rail is along as shown in Figure 4
X-direction arranges that sliding sleeve is then slidedly arranged in X-axis slide rail the movement for realizing X-direction；Y-axis moving cell 32 is then installed on X-axis fortune
On moving cell 31, with X-axis moving cell 31, its glide direction is Y direction to its structure；X-axis rotary unit is then installed on Y-axis fortune
On moving cell 32, including rotary shaft, rotary shaft is being rotated so as to drive the rotation of landing platform 1, to be further ensured that landing is put down
The state of platform 1 matches with the landing posture of unmanned plane 8.
As shown in Figure 1 and Figure 5, in the present embodiment, lifting assembly 7 includes elevator 71, one end of elevator 71 and landing
The lower surface middle part of platform 1 is connected, and the other end is connected with base, and Universal connector is passed through wherein between elevator 71 and landing platform 1
Head is connected, and ensure that the smooth inclination of landing platform 1.
As shown in figure 5, in the present embodiment, tilt component 2 includes being installed on multiple line wheels 23 of the week side of boss of landing platform 1, line
Pass through line 21 between wheel 23 and landing platform 1（Superpower tension clue）Connection, wherein one end of superpower tension clue has been fixed on
On the drop bottom corner location of platform 1, the other end directive wheel 22 that then Jing is bypassed in gripper shoe is connected with line wheel 23, wherein line wheel 23
Then rotation is driven by servomotor 24 and realize the contraction of line 21, be ensure that using servomotor 24 and be precisely controlled.By right
The length of line 21 is controlled such that it is able to realize the inclination control of landing platform 1.When detection components 6 detect rotor nobody
Machine 8 near landing platform 1 and because weather or air-flow reason cannot voluntarily land when, first rotor wing unmanned aerial vehicle 8 is aided in into landing system
The control system of system then sends instruction allows the motion of three-dimensional localization component 3 to make landing platform 1 be located at the lower section of unmanned plane 8, Ran Houtong
Cross elevator 71 landing platform 1 to be risen at the position of unmanned plane 8, while driving landing platform 1 and coupled device one
Rise and lifted, and quick slant difference angle is realized on 360 ° of directions of surrounding using tilt component 2, with reach with rotor nobody
The landing angle identical purpose of machine 8, enables rotor wing unmanned aerial vehicle 8 to drop in the specified location on the top of landing platform 1, is easy to solid
Determine component 4 to be fixed the undercarriage 81 of rotor wing unmanned aerial vehicle 8.
The above is only the preferred embodiment of the present invention, protection scope of the present invention is not limited merely to above-described embodiment,
All technical schemes belonged under thinking of the present invention belong to protection scope of the present invention.It should be pointed out that for the art
For those of ordinary skill, some improvements and modifications without departing from the principles of the present invention should be regarded as the protection of the present invention
Scope.
Claims (10)
1. a kind of rotor wing unmanned aerial vehicle aids in landing system, it is characterised in that including base and landing platform（1）, the landing put down
Platform（1）It is installed on the base, the landing platform（1）On be provided with for detecting rotor wing unmanned aerial vehicle（8）Flight parameter and
The detection components of flight attitude（6）, the base and the landing platform（1）Between be provided with for landing platform（1）Enter
The lifting assembly of row lifting（7）And for adjusting landing platform（1）The tilt component of heeling condition（2）；The lifting assembly
（7）And tilt component（2）Cooperate the adjustment landing platform（1）Height and heeling condition with the rotor nobody
Machine（8）Flight attitude match and be easy to landing.
2. rotor wing unmanned aerial vehicle according to claim 1 aids in landing system, it is characterised in that the landing platform（1）On
It is provided with for rotor wing unmanned aerial vehicle（8）The fixation kit being fixed（4）.
3. rotor wing unmanned aerial vehicle according to claim 2 aids in landing system, it is characterised in that the fixation kit（4）Bag
Include motor（47）, drive mechanism and two pieces of fixture blocks（41）, the fixture block（41）Upper end stretch out the landing platform（1）,
Two pieces of fixture blocks（41）By drive mechanism and the motor（47）It is connected, and in motor（47）Driving under transport
Move to clamp the rotor wing unmanned aerial vehicle（8）Undercarriage（81）.
4. rotor wing unmanned aerial vehicle as claimed in any of claims 1 to 3 aids in landing system, it is characterised in that described
Three-dimensional localization component is provided with base（3）, for realizing landing platform（1）In movement in the horizontal plane and vertical direction
Rotary motion.
5. rotor wing unmanned aerial vehicle according to claim 4 aids in landing system, it is characterised in that the three-dimensional localization component
（3）Including X-axis moving cell（31）, Y-axis moving cell（32）With Z axis rotary unit（33）, the X-axis moving cell（31）With
Y-axis moving cell（32）For cooperating to realize landing platform（1）Movement in the horizontal plane, the Z axis rotary unit
（33）For realizing the landing platform（1）The rotation of in the vertical direction.
6. rotor wing unmanned aerial vehicle as claimed in any of claims 1 to 3 aids in landing system, it is characterised in that described
Lifting assembly（7）Including elevator（71）, the elevator（71）One end and the landing platform（1）Lower surface middle part phase
Even, the other end is connected with the base.
7. rotor wing unmanned aerial vehicle according to claim 6 aids in landing system, it is characterised in that the elevator（71）With institute
State landing platform（1）Between by universal joint be connected.
8. rotor wing unmanned aerial vehicle according to claim 7 aids in landing system, it is characterised in that the tilt component（2）Bag
Include and be installed on the landing platform（1）Multiple line wheels of the week side of boss（23）, the line wheel（23）With the landing platform（1）Between lead to
Cross line（21）Connection, the line wheel（23）By servomotor（24）Drive rotation and realize line（21）It is flexible.
9. rotor wing unmanned aerial vehicle as claimed in any of claims 1 to 3 aids in landing system, it is characterised in that described
Detection components（6）Including multiple ultrasonic sensors（62）With multiple radar sensors（61）, multiple ultrasonic sensors
（62）It is installed on the landing platform（1）The week side of boss, for monitoring rotor wing unmanned aerial vehicle（8）Flight attitude during landing；Multiple institutes
State radar sensor（61）Annularly uniformly it is installed on the landing platform（1）Above, for rotor wing unmanned aerial vehicle（8）Flight ginseng
Number is detected.
10. rotor wing unmanned aerial vehicle as claimed in any of claims 1 to 3 aids in landing system, it is characterised in that described
Landing platform（1）On be provided with display module（5）, for showing the landing platform（1）State and realize warning and draw
Lead effect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610946093.6A CN106564610B (en) | 2016-10-26 | 2016-10-26 | A kind of rotor wing unmanned aerial vehicle auxiliary landing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610946093.6A CN106564610B (en) | 2016-10-26 | 2016-10-26 | A kind of rotor wing unmanned aerial vehicle auxiliary landing system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106564610A true CN106564610A (en) | 2017-04-19 |
| CN106564610B CN106564610B (en) | 2019-02-15 |
Family
ID=58535126
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610946093.6A Active CN106564610B (en) | 2016-10-26 | 2016-10-26 | A kind of rotor wing unmanned aerial vehicle auxiliary landing system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106564610B (en) |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106976566A (en) * | 2017-04-27 | 2017-07-25 | 东莞市丸红电子有限公司 | Level can be kept automatically and adjusts the aircraft landing platform of height |
| CN107161343A (en) * | 2017-04-26 | 2017-09-15 | 海南大学 | A kind of rotor wing unmanned aerial vehicle and its replacing battery system |
| CN108146649A (en) * | 2018-02-10 | 2018-06-12 | 清远韶兴新能源科技有限公司 | A kind of unmanned plane Portable lifting platform |
| CN108149593A (en) * | 2018-01-18 | 2018-06-12 | 长沙修恒信息科技有限公司 | A kind of light-emitting control method for roadmarking based on Internet of Things |
| CN108221730A (en) * | 2018-01-18 | 2018-06-29 | 长沙修恒信息科技有限公司 | A kind of luminous terminal and system for roadmarking based on Internet of Things |
| CN108275282A (en) * | 2018-03-29 | 2018-07-13 | 江苏建筑职业技术学院 | A kind of air-ground complementary remote sensing survey device |
| CN109018355A (en) * | 2018-07-04 | 2018-12-18 | 牛威 | A kind of highway rescue mode |
| CN109131922A (en) * | 2018-08-30 | 2019-01-04 | 上海复亚智能科技有限公司 | A kind of automatic airport system of unmanned plane |
| CN109279040A (en) * | 2018-11-07 | 2019-01-29 | 钟夏欣 | A kind of mobile landing gear of multi-functional unmanned plane |
| WO2019085152A1 (en) * | 2017-10-30 | 2019-05-09 | 深圳市大疆创新科技有限公司 | Clamping device and a base station having same, and unmanned aerial vehicle system |
| WO2019084811A1 (en) * | 2017-10-31 | 2019-05-09 | 深圳市大疆创新科技有限公司 | Position setting mechanism, unmanned aerial vehicle base station, and unmanned aerial vehicle system |
| CN110254736A (en) * | 2019-06-18 | 2019-09-20 | 哈尔滨工程大学 | A kind of sea is tethered at unmanned plane automatic accomodation device and its control system |
| CN110386257A (en) * | 2018-07-30 | 2019-10-29 | 魏荣亮 | For vertical translation aircraft warship device and naval vessel |
| CN111552304A (en) * | 2020-06-03 | 2020-08-18 | 中国人民解放军96901部队25分队 | Unmanned aerial vehicle recovery system and recovery method |
| CN112124610A (en) * | 2019-10-29 | 2020-12-25 | 魏荣亮 | Ship landing device for vertical take-off and landing aircraft and ship |
| CN112706937A (en) * | 2020-04-08 | 2021-04-27 | 江苏方天电力技术有限公司 | Flexible and accurate autonomous take-off and landing device for unmanned aerial vehicle and control method |
| CN113247287A (en) * | 2021-05-17 | 2021-08-13 | 武汉理工大学 | Many rotor unmanned aerial vehicle take off and land platform |
| JPWO2021210136A1 (en) * | 2020-04-16 | 2021-10-21 | ||
| CN114003049A (en) * | 2020-07-28 | 2022-02-01 | 丰田自动车株式会社 | Flying object takeoff control system |
| CN114486149A (en) * | 2022-01-19 | 2022-05-13 | 山东交通学院 | Wind field simulation generation device and method based on unmanned aerial vehicle test |
| CN117550126A (en) * | 2024-01-11 | 2024-02-13 | 华慧科技(长春)有限公司 | Unmanned aerial vehicle is with platform that takes off and land |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202574627U (en) * | 2012-04-01 | 2012-12-05 | 王显兵 | Vertical take-off assisting platform for carrier aircraft |
| CN105019367A (en) * | 2015-07-08 | 2015-11-04 | 何春旺 | Parking device for aircraft, and control method of parking device |
| CN105059539A (en) * | 2015-07-14 | 2015-11-18 | 成都育芽科技有限公司 | Novel efficient drone |
| WO2016059555A1 (en) * | 2014-10-13 | 2016-04-21 | Systems Engineering Associates Corporation | Systems and methods for deployment and operation of vertical take-off and landing (vtol) unmanned aerial vehicles |
| CN105644774A (en) * | 2016-02-02 | 2016-06-08 | 吴燕 | Multi-rotor flight vehicle undercarriage based on Stewart six-degree-of-freedom parallel mechanism |
-
2016
- 2016-10-26 CN CN201610946093.6A patent/CN106564610B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202574627U (en) * | 2012-04-01 | 2012-12-05 | 王显兵 | Vertical take-off assisting platform for carrier aircraft |
| WO2016059555A1 (en) * | 2014-10-13 | 2016-04-21 | Systems Engineering Associates Corporation | Systems and methods for deployment and operation of vertical take-off and landing (vtol) unmanned aerial vehicles |
| CN105019367A (en) * | 2015-07-08 | 2015-11-04 | 何春旺 | Parking device for aircraft, and control method of parking device |
| CN105059539A (en) * | 2015-07-14 | 2015-11-18 | 成都育芽科技有限公司 | Novel efficient drone |
| CN105644774A (en) * | 2016-02-02 | 2016-06-08 | 吴燕 | Multi-rotor flight vehicle undercarriage based on Stewart six-degree-of-freedom parallel mechanism |
Cited By (32)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107161343A (en) * | 2017-04-26 | 2017-09-15 | 海南大学 | A kind of rotor wing unmanned aerial vehicle and its replacing battery system |
| CN106976566A (en) * | 2017-04-27 | 2017-07-25 | 东莞市丸红电子有限公司 | Level can be kept automatically and adjusts the aircraft landing platform of height |
| WO2019085152A1 (en) * | 2017-10-30 | 2019-05-09 | 深圳市大疆创新科技有限公司 | Clamping device and a base station having same, and unmanned aerial vehicle system |
| CN109890703B (en) * | 2017-10-30 | 2022-08-19 | 深圳市大疆创新科技有限公司 | Clamping device and have clamping device's basic station and unmanned aerial vehicle system |
| CN109890703A (en) * | 2017-10-30 | 2019-06-14 | 深圳市大疆创新科技有限公司 | Clamping device and base station and UAV system with clamping device |
| WO2019084811A1 (en) * | 2017-10-31 | 2019-05-09 | 深圳市大疆创新科技有限公司 | Position setting mechanism, unmanned aerial vehicle base station, and unmanned aerial vehicle system |
| CN108221730A (en) * | 2018-01-18 | 2018-06-29 | 长沙修恒信息科技有限公司 | A kind of luminous terminal and system for roadmarking based on Internet of Things |
| CN108149593A (en) * | 2018-01-18 | 2018-06-12 | 长沙修恒信息科技有限公司 | A kind of light-emitting control method for roadmarking based on Internet of Things |
| CN108146649A (en) * | 2018-02-10 | 2018-06-12 | 清远韶兴新能源科技有限公司 | A kind of unmanned plane Portable lifting platform |
| CN108275282A (en) * | 2018-03-29 | 2018-07-13 | 江苏建筑职业技术学院 | A kind of air-ground complementary remote sensing survey device |
| CN108275282B (en) * | 2018-03-29 | 2024-03-08 | 江苏建筑职业技术学院 | Ground-air complementary remote sensing measurement device |
| CN109018355B (en) * | 2018-07-04 | 2022-01-07 | 上海哲匠交通科技有限公司 | Expressway rescue method |
| CN109018355A (en) * | 2018-07-04 | 2018-12-18 | 牛威 | A kind of highway rescue mode |
| CN110386257A (en) * | 2018-07-30 | 2019-10-29 | 魏荣亮 | For vertical translation aircraft warship device and naval vessel |
| CN110386257B (en) * | 2018-07-30 | 2024-06-04 | 魏荣亮 | Ship landing device for vertical lifting aircraft and ship |
| CN109131922A (en) * | 2018-08-30 | 2019-01-04 | 上海复亚智能科技有限公司 | A kind of automatic airport system of unmanned plane |
| CN109279040A (en) * | 2018-11-07 | 2019-01-29 | 钟夏欣 | A kind of mobile landing gear of multi-functional unmanned plane |
| CN110254736A (en) * | 2019-06-18 | 2019-09-20 | 哈尔滨工程大学 | A kind of sea is tethered at unmanned plane automatic accomodation device and its control system |
| CN112124610A (en) * | 2019-10-29 | 2020-12-25 | 魏荣亮 | Ship landing device for vertical take-off and landing aircraft and ship |
| CN112706937A (en) * | 2020-04-08 | 2021-04-27 | 江苏方天电力技术有限公司 | Flexible and accurate autonomous take-off and landing device for unmanned aerial vehicle and control method |
| WO2021210136A1 (en) * | 2020-04-16 | 2021-10-21 | 日本電気株式会社 | Landing facility, aircraft system, and landing control method |
| JPWO2021210136A1 (en) * | 2020-04-16 | 2021-10-21 | ||
| JP7405247B2 (en) | 2020-04-16 | 2023-12-26 | 日本電気株式会社 | Landing facilities, aircraft systems, and landing control methods |
| CN111552304B (en) * | 2020-06-03 | 2024-03-05 | 中国人民解放军96901部队25分队 | Unmanned aerial vehicle recycling system and recycling method |
| CN111552304A (en) * | 2020-06-03 | 2020-08-18 | 中国人民解放军96901部队25分队 | Unmanned aerial vehicle recovery system and recovery method |
| CN114003049A (en) * | 2020-07-28 | 2022-02-01 | 丰田自动车株式会社 | Flying object takeoff control system |
| CN114003049B (en) * | 2020-07-28 | 2024-04-26 | 丰田自动车株式会社 | Flying object take-off control system |
| CN113247287A (en) * | 2021-05-17 | 2021-08-13 | 武汉理工大学 | Many rotor unmanned aerial vehicle take off and land platform |
| CN114486149A (en) * | 2022-01-19 | 2022-05-13 | 山东交通学院 | Wind field simulation generation device and method based on unmanned aerial vehicle test |
| CN114486149B (en) * | 2022-01-19 | 2023-11-24 | 山东交通学院 | Wind field simulation generation device and method based on unmanned aerial vehicle test |
| CN117550126A (en) * | 2024-01-11 | 2024-02-13 | 华慧科技(长春)有限公司 | Unmanned aerial vehicle is with platform that takes off and land |
| CN117550126B (en) * | 2024-01-11 | 2024-04-02 | 华慧科技(长春)有限公司 | Unmanned aerial vehicle is with platform that takes off and land |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106564610B (en) | 2019-02-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106564610A (en) | Auxiliary taking-off and landing system for rotor unmanned plane | |
| CN105667779B (en) | Intelligent flying robot capable of perching on walls at different inclination angles | |
| CN106864766B (en) | The battery clamp device and replacement device and method independently continued a journey applied to unmanned plane | |
| CN107065924A (en) | The vehicle-mounted landing system of unmanned plane, can vehicle-mounted landing unmanned plane and landing method | |
| CN110261849B (en) | Tunnel lining structure detection device | |
| CN109516120A (en) | A kind of the omnidirectional's conveyer system and working method of three-wheel drive | |
| CN107284653B (en) | A kind of multi-rotor aerocraft horizontal take-off regulating system and multi-rotor aerocraft | |
| CN108832885B (en) | Photovoltaic module cleaning robot | |
| CN104590557B (en) | A kind of many rotors and the flight control method of fixed-wing composite aircraft and device | |
| CN108382591A (en) | The air-ground inspection Detecting Robot system and operating method applied in complex environment | |
| CN207309951U (en) | A kind of intelligent ball collecting robot | |
| US11426862B2 (en) | Guiderail for underslung robot, underslung robot and operating system thereof | |
| CN207163422U (en) | A kind of section of jurisdiction automatic identification grabbing device | |
| CN105691606B (en) | A kind of the unmanned plane device and control method in high cruise duration | |
| CN203825466U (en) | Airborne-sensor-based small-sized four rotor aircraft control system | |
| CN207374661U (en) | Multi-rotor unmanned aerial vehicle | |
| CN104843177B (en) | Aircraft | |
| CN204623835U (en) | Multi-axis aircraft | |
| CN204172030U (en) | A kind of robot manipulator structure | |
| CN109981042A (en) | A kind of clean intelligent robot of solar panel based on more rotors | |
| CN112706937B (en) | Flexible and accurate autonomous take-off and landing device for unmanned aerial vehicle and control method | |
| CN107414823A (en) | According to the method and device of torque adjustment balance | |
| CN209306382U (en) | A kind of omnidirectional's conveyer system of three-wheel drive | |
| CN103851315A (en) | Parallel connection fast direction pointing mechanism with virtual rotating center characteristic | |
| CN105571520B (en) | A kind of intelligent 3 D stereo scanner head |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |