CN111284721A - Aircraft take-off and landing platform - Google Patents
Aircraft take-off and landing platform Download PDFInfo
- Publication number
- CN111284721A CN111284721A CN202010219064.6A CN202010219064A CN111284721A CN 111284721 A CN111284721 A CN 111284721A CN 202010219064 A CN202010219064 A CN 202010219064A CN 111284721 A CN111284721 A CN 111284721A
- Authority
- CN
- China
- Prior art keywords
- platform
- aircraft
- landing
- module
- landing gear
- 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
- 238000001179 sorption measurement Methods 0.000 claims abstract description 105
- 230000005347 demagnetization Effects 0.000 claims description 34
- 238000010521 absorption reaction Methods 0.000 claims description 25
- 238000013016 damping Methods 0.000 claims description 16
- 230000035939 shock Effects 0.000 claims description 12
- 230000000712 assembly Effects 0.000 claims description 4
- 238000000429 assembly Methods 0.000 claims description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 230000005389 magnetism Effects 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 230000001681 protective effect Effects 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000004804 winding Methods 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 2
- 239000000741 silica gel Substances 0.000 claims description 2
- 229910002027 silica gel Inorganic materials 0.000 claims description 2
- 230000001360 synchronised effect Effects 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 229910000976 Electrical steel Inorganic materials 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Images
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
-
- 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
- B64F1/12—Ground or aircraft-carrier-deck installations for anchoring aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
The invention discloses an aircraft take-off and landing platform, which comprises an aircraft and a take-off and landing platform. The aircraft comprises a flying machine body and a landing gear assembly. The take-off and landing platform can fix the aircraft on the platform in a bumping mode, so that the adsorption force can be kept all the time, and when the aircraft is required to be released, a plurality of adsorption points can be released simultaneously. The return accuracy of the existing aircraft has tolerance, and the landing slots at three angles of the take-off and landing platform can guide return deviation with certain error. The existing mechanical fixed type lifting platform has extremely large volume, needs time for releasing a locking structure, and has extremely poor synchronism; the aircraft releasing device has excellent aircraft releasing performance, and when the aircraft is released during takeoff, the releasing time of a plurality of fixed positions is more synchronous; even the aircraft can be started first and then released synchronously, and the task efficiency is improved.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a take-off and landing platform.
Background
The take-off and landing platform is a key auxiliary device of an aviation aircraft, and is mainly used in some environments without basic take-off and landing conditions, such as sea, air and vehicle driving. Or some require precise take-off and landing location scenarios in order to achieve automatic charging, perform tasks automatically, etc. Some disclosed mechanical structure locking take-off and landing platforms have the disadvantages of large weight, high manufacturing cost and high manufacturing difficulty; moreover, as the mechanical structure is difficult to achieve the uniformity of a plurality of locking points, the locking mechanism needs to be released first and then takes off; the takeoff has certain risks and flight accidents occur. In the existing some magnetic-type take-off and landing platforms, the fact that the attractive force of a magnet cannot resist larger torque and shearing force is not considered, and an aircraft is easy to fall off when the aircraft inclines or jolts; some existing magnetic-type take-off and landing platforms adopt electromagnets for power-off degaussing; the electromagnet needs to be independently powered for a long time, and once the power is insufficient, the aircraft can fall off; the existing take-off and landing platforms of most of the aircrafts taking off and landing vertically do not consider that the existing aircrafts have position deviation and course angle deviation in return flight precision, and are not well processed.
Disclosure of Invention
The invention aims to overcome the problems and provide a lifting platform.
In order to achieve the purpose, the method adopted by the invention is as follows: an aircraft take-off and landing platform comprises an aircraft and a take-off and landing platform; the aircraft comprises a flying body and a landing gear assembly; the landing gear assembly comprises a landing gear adapter, a supporting cantilever, a lifting slide block, a landing gear adsorption module and a demagnetization control assembly; the lifting platform comprises a platform base, a guiding and positioning assembly, a platform adsorption module and a floating damping module. The aircraft lands above the take-off and landing platform; the landing gear assembly is arranged below the aircraft body; the lifting slide block is arranged at the middle section of the supporting cantilever; one end of the supporting cantilever is fixedly connected to the landing gear adapter; the other end of the landing gear is fixedly connected with the landing gear adsorption module; at least three supporting cantilevers, three lifting slide blocks and three landing gear adsorption modules are uniformly distributed around the landing gear adapter; a platform adsorption module is arranged at the position, corresponding to the landing gear adsorption module, on the lifting platform; at least three groups of the guiding and positioning assemblies are fixedly arranged on the platform base, and the number of the groups of the guiding and positioning assemblies is equal to that of the take-off and landing sliding blocks on the aircraft; and are uniformly distributed in 360 degrees around the center of the lifting platform; the guide positioning assembly is in the shape of an inverted triangular groove with a large top opening, the surface of the guide positioning assembly is smooth, and the lifting slide block can freely slide in the groove of the guide positioning assembly; an adsorption surface at one end of a platform adsorption module correspondingly installed on the platform base penetrates through the upper surface of the take-off and landing platform, faces the aircraft and is parallel to the upper surface of the take-off and landing platform; the other end of the platform adsorption module is fixedly connected with one end of the floating damping module, and the other end of the floating damping module is fixedly connected with the lower surface of the lifting platform; the platform adsorption module is controlled to be disconnected through the power supply control assembly;
preferably, the platform adsorption module is an electromagnet for power-off demagnetization, and is cylindrical; the outermost layer is a metal protective shell, the middle layer is an enameled wire winding coil, and the inner layer is a strong-magnetic magnet; the power is supplied to the positive electrode and the negative electrode of the platform adsorption module, and a magnetic field which is mutually offset with the inner layer magnet can be formed so as to achieve the aim of eliminating magnetism; the landing gear adsorption module is made of alloy materials which are magnetic conductive and are not easy to magnetize; the positive pole of the demagnetization control assembly is connected with one landing gear adsorption module (temporarily called as a positive landing gear adsorption module), and the negative pole of the demagnetization control assembly is connected with the other landing gear adsorption module (temporarily called as a negative landing gear adsorption module); positive leads of all the platform adsorption modules on the lifting platform are connected with the platform adsorption module conductive shell corresponding to the positive landing gear adsorption module; the negative leads of all the platform adsorption modules on the lifting platform are connected with the platform adsorption module conductive shell corresponding to the negative landing gear adsorption module; through the connection, after the aircraft is started, the demagnetization control assembly can electrify and demagnetize the platform adsorption module through the contact point of the platform adsorption module and the landing gear adsorption module;
as a preferred choice of the invention, the floating shock absorption module is one of a steel wire shock absorption ball or a silica gel damping shock absorption ball; the floating damping module eliminates micro displacement and deformation in 6 degrees of freedom; when the platform bumps and shakes, the floating shock absorption module reduces the impact force at the joint of the platform absorption module and the landing gear absorption module; the influences of uneven contact points and uneven stress are eliminated;
as a preferred aspect of the present invention, the platform suction module and the landing gear suction module may be, but are not limited to, one of the following five configurations:
a. a platform adsorption module: an electromagnet capable of controlling demagnetization; landing gear absorption module: a magnetizer;
b. a platform adsorption module: an electromagnet capable of controlling demagnetization; landing gear absorption module: a magnet;
c. a platform adsorption module: an electromagnet capable of controlling demagnetization; landing gear absorption module: an electromagnet capable of controlling demagnetization;
d. a platform adsorption module: a magnetizer; landing gear absorption module: an electromagnet capable of controlling demagnetization;
e. a platform adsorption module: a magnet; landing gear absorption module: an electromagnet capable of controlling demagnetization;
as a preferable aspect of the present invention, the demagnetization control assembly may also be installed in the lifting platform to directly control the platform adsorption assembly; the demagnetization control component can be a wireless remote control device or a simple power-on switch;
preferably, the aircraft take-off and landing platform is applied to a vehicle-mounted unmanned aerial vehicle or a shipborne take-off and landing platform;
as a preferred aspect of the present invention, the aircraft may be, but is not limited to, one of a multi-rotor aircraft, a coaxial dual-rotor aircraft, a single-rotor helicopter, a vertical take-off and landing fixed wing, and a launch vehicle.
Has the advantages that:
compared with a plurality of mechanical take-off and landing platforms, the invention greatly simplifies the manufacturing difficulty and the processing difficulty of the platform, reduces the material cost and the maintenance difficulty, and the simple structure provides greater safety guarantee for the aircraft. Compared with a plurality of lifting platforms adsorbed by electromagnets, the landing guide assembly disclosed by the invention can allow flying return, has certain course angle deflection and horizontal position offset, and can accurately land at a take-off position. Compared with the lifting platforms of a plurality of electromagnets, the aircraft can be released only by electrifying for a short time when demagnetization is needed without maintaining power supply; the take-off and landing platform does not need a power supply and control component and is completely powered and controlled by the aircraft; compared with most of magnetic-type take-off and landing platforms, the magnetic-type take-off and landing platform can process high-frequency and large-amplitude bumping impact to protect the aircraft from falling off, and release time of a plurality of fixed positions is more synchronous when the magnetic-type take-off and landing platform releases the aircraft; even the aircraft can be started first and then released synchronously, and the task efficiency is improved.
Drawings
FIG. 1 is a schematic diagram illustrating the overall effect of the present invention;
FIG. 2 is a functional structure diagram of the landing platform of the present invention;
FIG. 3 is a schematic structural view of the present invention;
FIG. 4 is a schematic view of an aircraft landing alignment axis of the present invention;
FIG. 5 is a schematic top plan view of the aircraft landing alignment of the present invention;
in the figure, each component comprises 1 an aircraft, 2a take-off and landing platform;
the aircraft 1 comprises: 1a, an aircraft body, 1b, a landing gear assembly;
the landing platform 2 includes: 2a, a platform base, 2b, a guiding and positioning component, 2c, a platform adsorption module, 2d and a floating damping module;
the landing gear assembly 1b comprises a supporting cantilever 1b1, a supporting cantilever 1b2, a landing gear adsorption module 1b3, a lifting slider 1b4, a landing gear adapter, a degaussing control assembly 2d and a degaussing control assembly.
Detailed Description
The present invention will be further illustrated with reference to the accompanying drawings and specific examples, which are carried out on the premise of the technical solution of the present invention, and it should be understood that these examples are only for illustrating the present invention and are not intended to limit the scope of the present invention.
Example 1:
referring to fig. 1, an aircraft landing platform 1 is shown, wherein the aircraft 1 lands above the landing platform 2, and the landing gear assembly 1b is installed below the aircraft body 1 a.
As shown in fig. 2 and 3, the landing gear assembly 1b is mounted below the aircraft body 1 a; the lifting slider 1b3 is arranged at the middle section of the supporting suspension arm 1b 1; one end of the supporting cantilever 1b1 is fixedly connected to the landing gear adapter 1b 4; the other end is fixedly connected with the landing gear adsorption module 1b 1; three supporting cantilevers 1b1, three lifting sliders 1b3 and three landing gear adsorption modules 1b1 are uniformly distributed around the landing gear adapter 1b 4; a platform adsorption module 2c is arranged at the position, corresponding to the landing gear adsorption module 1b1, on the lifting platform 2; the three groups of guiding and positioning components 2b are fixedly arranged on the platform base 2 a; and are evenly distributed in 360 degrees around the center of the lifting platform 2; the guiding and positioning component 2b is in the shape of an inverted triangular groove with a large top opening and has a smooth surface; an adsorption surface at one end of a platform adsorption module 2c, which is arranged on the platform base 2a corresponding to the landing gear adsorption module 1b1, penetrates through a round hole on the upper surface of the take-off and landing platform 2 and faces the direction of the aircraft 1, and the adsorption surface is parallel to the upper surface of the take-off and landing platform 2; the other end of the platform adsorption module 2c is fixedly connected with one end of a floating damping module 2d, and the other end of the floating damping module 2d is fixedly connected below the lifting platform 2; the multi-degree-of-freedom shock absorption and buffering of the floating shock absorption module 2d prevents the aircraft 1 from falling off due to the fact that the overlarge shock force exceeds the adsorption force of the adsorption module.
As shown in fig. 4, when the aircraft lands, the aircraft has a heading deviation, and during the landing process, the take-off and landing slider 1b3 can slide in the groove of the guide positioning assembly 2 b; when the aircraft 1 lands, the position deviation and the course deviation exist, and the position deviation and the course deviation do not exceed the range of the groove of the guiding and positioning assembly 2b, the starting sliding block 1b3 can slide in the groove to an accurate position, so that the landing gear adsorption module 1b1 is aligned with the platform adsorption module 2 c;
the platform adsorption module 2c is an electromagnet for power failure demagnetization and is cylindrical; the outermost layer is a metal protective shell, the middle layer is an enameled wire winding coil, and the inner layer is a strong-magnetic magnet; when the positive and negative electrodes of the platform adsorption module 2c are electrified, a magnetic field which is mutually offset with the inner layer magnet is formed so as to eliminate the magnetism of the inner layer strong magnet; the landing gear adsorption module 1b1 is made of magnetic conductive and non-magnetized alloy material (such as silicon steel); the degaussing control assembly 2d has its positive pole connected to one landing gear attachment module 1b1 (referred to for the moment as positive landing gear attachment module 1b 1) and its negative pole connected to the other landing gear attachment module 1b1 (referred to for the moment as negative landing gear attachment module 1b 1); the positive leads of all platform adsorption modules 2c on the lifting platform 2 are connected with the conductive shell of the platform adsorption module 2c corresponding to the positive landing gear adsorption module 1b 1; the negative leads of all the platform adsorption modules 2c on the lifting platform 2 are connected with the conductive shell of the platform adsorption module 2c corresponding to the negative landing gear adsorption module 1b 1; through the connection, after the aircraft 1 is started, the demagnetization control assembly 2d on the landing gear assembly 1b can perform electrification and demagnetization control on all the platform adsorption modules 2c through contact points of the platform adsorption modules 2c and the landing gear adsorption modules 1b 1;
the floating damping module 2d is a steel wire damping ball; the floating damping module 2d eliminates micro displacement and deformation in 6 degrees of freedom; when the landing platform 2 bumps and shakes, the floating shock absorption module 2d absorbs and reduces the impact force at the joint of the platform adsorption module 2c and the landing gear adsorption module 1b1, and eliminates the influences of uneven contact points and uneven stress caused by the stress deformation of the landing gear assembly 1b due to manufacturing tolerance and assembly tolerance.
The platform suction module 2c and the landing gear suction module 1b1 may be, but are not limited to, one of the following five configurations:
1. platform adsorption module 2 c: an electromagnet capable of controlling demagnetization; landing gear adsorption module 1b 1: a magnetizer;
2. platform adsorption module 2 c: an electromagnet capable of controlling demagnetization; landing gear adsorption module 1b 1: a magnet;
3. platform adsorption module 2 c: an electromagnet capable of controlling demagnetization; landing gear adsorption module 1b 1: an electromagnet capable of controlling demagnetization;
4. platform adsorption module 2 c: a magnetizer; landing gear adsorption module 1b 1: an electromagnet capable of controlling demagnetization;
5. platform adsorption module 2 c: a magnet; landing gear adsorption module 1b 1: can control the demagnetizing electromagnet.
Example 2:
the difference between the embodiment and the embodiment 1 is that the demagnetization control component 2d is installed in the take-off and landing platform 2 and directly controls the platform adsorption component; the degaussing control assembly 2d may then be a radio remote control device or a simple power-on switch.
The take-off and landing platform 2 of the aircraft 1 is applied to a vehicle-mounted unmanned aerial vehicle or a shipborne take-off and landing platform;
the aircraft 1 may be, but is not limited to, one of a multi-rotor aircraft, a coaxial twin-rotor aircraft, a single-rotor helicopter, a vertical take-off and landing fixed wing, and a launch vehicle.
The technical means disclosed by the scheme of the invention are not limited to the technical means disclosed by the technical means, and the technical scheme also comprises the technical scheme formed by any combination of the technical characteristics. While the foregoing is directed to embodiments of the present invention, it will be appreciated by those skilled in the art that various changes may be made in the embodiments without departing from the principles of the invention, and that such changes and modifications are intended to be included within the scope of the invention.
Claims (7)
1. An aircraft take-off and landing platform, comprising: comprises an aircraft and a take-off and landing platform; the aircraft comprises a flying body and a landing gear assembly; the landing gear assembly comprises a landing gear adapter, a supporting cantilever, a lifting slide block, a landing gear adsorption module and a demagnetization control assembly; the lifting platform comprises a platform base, a guiding and positioning assembly, a platform adsorption module and a floating damping module; the aircraft lands above the take-off and landing platform; the landing gear assembly is arranged below the aircraft body; the lifting slide block is arranged at the middle section of the supporting cantilever; one end of the supporting cantilever is fixedly connected to the landing gear adapter; the other end of the landing gear is fixedly connected with the landing gear adsorption module; at least three supporting cantilevers, three lifting slide blocks and three landing gear adsorption modules are uniformly distributed around the landing gear adapter; a platform adsorption module is arranged at the position, corresponding to the landing gear adsorption module, on the lifting platform; at least three groups of the guiding and positioning assemblies are fixedly arranged on the platform base, and the number of the groups of the guiding and positioning assemblies is equal to that of the take-off and landing sliding blocks on the aircraft; and are uniformly distributed in 360 degrees around the center of the lifting platform; the top of the guiding and positioning component is provided with an inverted triangular groove in shape and smooth in surface, and the lifting slide block can freely slide in the groove of the guiding and positioning component; an adsorption surface at one end of a platform adsorption module correspondingly installed on the platform base penetrates through the upper surface of the take-off and landing platform, faces the aircraft and is parallel to the upper surface of the take-off and landing platform; the other end of the platform adsorption module is fixedly connected with one end of the floating damping module, and the other end of the floating damping module is fixedly connected to the lower surface of the lifting platform.
2. An aircraft takeoff and landing platform according to claim 1, wherein: the platform adsorption module is an electromagnet for power failure demagnetization and is cylindrical; the outermost layer is a metal protective shell, the middle layer is an enameled wire winding coil, and the inner layer is a strong-magnetic magnet; the power is supplied to the positive electrode and the negative electrode of the platform adsorption module, and a magnetic field which is mutually offset with the inner layer magnet can be formed so as to achieve the aim of eliminating magnetism; the landing gear adsorption module is made of alloy materials which are magnetic conductive and are not easy to magnetize; the positive pole of the demagnetization control assembly is connected with one landing gear adsorption module, and the negative pole of the demagnetization control assembly is connected with the other landing gear adsorption module; positive leads of all the platform adsorption modules on the lifting platform are connected with the platform adsorption module conductive shell corresponding to the positive landing gear adsorption module; the negative leads of all the platform adsorption modules on the lifting platform are connected with the platform adsorption module conductive shell corresponding to the negative landing gear adsorption module; after the aircraft is started, the demagnetization control assembly can electrify and demagnetize the platform adsorption module through the contact point of the platform adsorption module and the landing gear adsorption module.
3. An aircraft takeoff and landing platform according to claim 1, wherein: the floating shock absorption module is one of a steel wire shock absorption ball or a silica gel damping shock absorption ball; the floating damping module eliminates micro displacement and deformation in 6 degrees of freedom; when the platform bumps and shakes, the floating shock absorption module reduces the impact force at the joint of the platform absorption module and the landing gear absorption module; and eliminate the influence of uneven contact points and uneven stress.
4. An aircraft takeoff and landing platform according to claim 2, wherein: the platform adsorption module and the landing gear adsorption module comprise one of the following five configurations:
a platform adsorption module: an electromagnet capable of controlling demagnetization; landing gear absorption module: a magnetizer;
a platform adsorption module: an electromagnet capable of controlling demagnetization; landing gear absorption module: a magnet;
a platform adsorption module: an electromagnet capable of controlling demagnetization; landing gear absorption module: an electromagnet capable of controlling demagnetization;
a platform adsorption module: a magnetizer; landing gear absorption module: an electromagnet capable of controlling demagnetization;
a platform adsorption module: a magnet; landing gear absorption module: can control the demagnetizing electromagnet.
5. An aircraft takeoff and landing platform according to claim 1, wherein: the demagnetization control component is arranged in the lifting platform and directly controls the platform adsorption component; the degaussing control component is a wireless remote control device or a power-on switch.
6. An aircraft takeoff and landing platform according to claim 1, wherein: the aircraft take-off and landing platform is applied to a vehicle-mounted unmanned aerial vehicle or a shipborne take-off and landing platform.
7. An aircraft takeoff and landing platform according to claim 1, wherein: the aircraft comprises one of a multi-rotor aircraft, a coaxial double-rotor aircraft, a single-rotor helicopter, a vertical take-off and landing fixed wing and a carrier rocket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010219064.6A CN111284721A (en) | 2020-03-25 | 2020-03-25 | Aircraft take-off and landing platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010219064.6A CN111284721A (en) | 2020-03-25 | 2020-03-25 | Aircraft take-off and landing platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111284721A true CN111284721A (en) | 2020-06-16 |
Family
ID=71017922
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010219064.6A Pending CN111284721A (en) | 2020-03-25 | 2020-03-25 | Aircraft take-off and landing platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111284721A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928144A (en) * | 2021-04-22 | 2022-01-14 | 南京韬讯航空科技有限公司 | Mobile unmanned aerial vehicle take-off and landing platform and take-off and landing control method |
-
2020
- 2020-03-25 CN CN202010219064.6A patent/CN111284721A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928144A (en) * | 2021-04-22 | 2022-01-14 | 南京韬讯航空科技有限公司 | Mobile unmanned aerial vehicle take-off and landing platform and take-off and landing control method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10953999B2 (en) | Unmanned aerial vehicle docking system | |
| CN107054641B (en) | Magnetic directional brake | |
| CN110481769B (en) | Unmanned aerial vehicle device based on coaxial double rotors | |
| US9429954B2 (en) | Flight control for an airborne wind turbine | |
| CN109436314A (en) | A kind of unmanned vehicle | |
| CN108327926B (en) | Modular spacecraft capable of on-orbit allosteric | |
| CN109533329B (en) | Magnetic suspension positioning device for unmanned aerial vehicle charging, unmanned aerial vehicle and charging method | |
| CN212243865U (en) | Aircraft take-off and landing platform | |
| CN110155265B (en) | A unmanned aerial vehicle descending device for unmanned ship platform based on electromagnetism | |
| CN212243873U (en) | Unmanned aerial vehicle ejection rack unit and flexible combined unmanned aerial vehicle row-connected track ejection rack thereof | |
| CN114878197B (en) | Ground test method for verifying low-impact emission and reliability attachment of space | |
| CN111284721A (en) | Aircraft take-off and landing platform | |
| CN115676674A (en) | Magnetic-gas mixed suspension gravity unloading device and system | |
| CN110228598B (en) | Rapid recovery system applied to fixed-wing unmanned aerial vehicle and recovery control method thereof | |
| CN205022853U (en) | Many rotors flight equipment | |
| CN205022916U (en) | Portable flight equipment | |
| CN205022914U (en) | Undercarriage is fixed flight equipment | |
| CN205022908U (en) | Attachment mechanism | |
| CN107757914A (en) | Double dynamical VTOL fixed-wing unmanned plane | |
| KR102336741B1 (en) | Unmanned aerial vehicle having apparatus for control take off | |
| CN214986016U (en) | Modularized replaceable tail wing | |
| CN205022905U (en) | Undercarriage is telescopic flight equipment | |
| CN205022865U (en) | Folding flight equipment of rotor | |
| CN211001835U (en) | Unmanned aerial vehicle positioner that charges | |
| CN208705679U (en) | UAV Flight Control analogue system |
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 |