CN106043728A - Helicopter landing system and landing method - Google Patents
Helicopter landing system and landing method Download PDFInfo
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- CN106043728A CN106043728A CN201610466466.XA CN201610466466A CN106043728A CN 106043728 A CN106043728 A CN 106043728A CN 201610466466 A CN201610466466 A CN 201610466466A CN 106043728 A CN106043728 A CN 106043728A
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- helicopter
- parking area
- calutron
- airplane parking
- landing
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- 238000000034 method Methods 0.000 title claims description 16
- 238000009434 installation Methods 0.000 claims description 17
- 230000008859 change Effects 0.000 claims description 13
- 230000001143 conditioned effect Effects 0.000 claims description 13
- 238000004891 communication Methods 0.000 claims description 8
- 230000006698 induction Effects 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 5
- 230000005611 electricity Effects 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 230000009471 action Effects 0.000 claims description 3
- 230000005389 magnetism Effects 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 abstract description 7
- 230000000694 effects Effects 0.000 description 5
- 230000033001 locomotion Effects 0.000 description 4
- 230000007797 corrosion Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 2
- 239000011157 advanced composite material Substances 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 239000013535 sea water Substances 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 1
- KGWWEXORQXHJJQ-UHFFFAOYSA-N [Fe].[Co].[Ni] Chemical compound [Fe].[Co].[Ni] KGWWEXORQXHJJQ-UHFFFAOYSA-N 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000003064 anti-oxidating effect Effects 0.000 description 1
- 230000003260 anti-sepsis Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
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- 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
- B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a helicopter landing system. The helicopter landing system comprises a landing auxiliary mechanism installed at the bottom of a helicopter body, and a parking apron arranged on a ship deck. The landing auxiliary mechanism comprises an electromagnet attracting to a helicopter undercarriage. The parking apron is round. A plurality of evenly distributed electromagnetic devices are arranged in the parking apron. The helicopter landing system further comprises a slideway arranged on the ship deck. The parking apron is installed on the slideway. When landing, a helicopter slides to a preset position along the slideway. After landing, the helicopter slides to a helicopter warehouse along the slideway. The helicopter landing system is simple in structure and convenient to use and has good reliability and wide applicability and universality. The helicopter can land safely and stably under the circumstance of strong light and poor sea conditions. Helicopter of different models and sizes can be suitable for the helicopter landing system after improved slightly.
Description
Technical field
The present invention relates to technical field of aerospace, particularly relate to a kind of helicopter and stablize carrier landing system and warship method.
Background technology
Helicopter, according to activity classification, can be divided into and have people, pilotless helicopter；According to the energy classify, can be divided into electric energy,
Chemical energy helicopter.Generally, manned versions of helicopter build is relatively big, mostly is chemical energy source, and mechanical stability is obvious；Unmanned
Helicopter has electric energy, two kinds of energy modes of chemical energy, and average physique is less, and mechanical stability is poor, and anti-Caulis Piperis Kadsurae, mechanical are disturbed
Ability.
And relative to the stable land of physical features, helicopter VTOL aboard ship is done by following uncertain factor
Disturb: marine aerodynamic parameter change is exceedingly fast and is difficult to prediction；The motion on deck makes the face of rising and falling unstable；Seawater corrosion helicopter
Metal device.
At present, engineering still uses traditional draw fall formula warship device warship device with " harpoon-grid " formula.Fall formula is drawn
Warship device uses rope to be fixed together with naval vessel by helicopter, and the range of activity of helicopter and mobility receive rope length
Impact with toughness；" harpoon-grid " formula warship device and is required high, meanwhile, on helicopter to the precision of helicopter landing
Rigidity and the intensity of " harpoon " parts directly determine the quality of warship quality, under the round-the-clock Mechanical shock conditions of naval vessels easily
In fatigue, and the repellence difference to powerful Caulis Piperis Kadsurae.
Chinese patent CN201410775156.7 discloses a kind of helicopter helicopter Zhe Jian mechanism, this Patent design one
Plant machinery shaft type helicopter carrier landing system, at this actuator base, electric magnet is installed so that it is absorption is on naval vessel.This mechanism has
Simple in construction, the feature such as easy for installation.This mechanism is plug-in mechanism, and versatility is relatively strong, but this system is at severe weather conditions
Descend warship second-rate.
Chinese patent CN201310262315.9 discloses a kind of Novel helicopter carrier landing system, is provided with on helicopter
Several hydraulic means, and be furnished with quantity, electric magnet that position is mated with hydraulic means.When helicopter falls and close to deck
Time, throwing electric magnet is to deck, and electric magnet has opened the attraction to helicopter afterwards, hydraulic means make it put down with deck
OK.But, this patent is only applicable to iron-cobalt-nickel and the deck of alloy material thereof, if deck is not magnetic medium, but some
Advanced composite material (ACM), electric magnet cannot complete absorption with deck.
Summary of the invention
In order to overcome the problems referred to above, present inventor has performed and study with keen determination, design a kind of helicopter carrier landing system, this is
System includes the electric magnet being arranged on bottom helicopter body and the airplane parking area being arranged on ship deck, and described electric magnet is arranged on
On the undercarriage of helicopter, be internally provided with calutron in described airplane parking area, this system also, be used for controlling magnetic on calutron
The calutron control portion of field and the calculating part of control helicopter descent, described calutron control portion includes for controlling
The electric supply installation of magnetic field size and for controlling the supply unit of magnetic direction on calutron and pre-meeting on calutron
Set the tone part time the repulsion between airplane parking area and helicopter is become suction, also by described calculating part calculate control described helicopter
Descent, reduce the workload of chip in helicopter, it is provided that the processing speed of chip in helicopter, thus complete this
Bright.
In particular it is object of the present invention to offer following aspect:
(1) a kind of helicopter carrier landing system, it is characterised in that this system includes the electromagnetism being arranged on bottom helicopter body
Ferrum and the airplane parking area 1 being arranged on ship deck,
Described electric magnet is arranged on the undercarriage of helicopter,
It is internally provided with calutron 2 in described airplane parking area 1.
(2) according to the system described in above-mentioned (1), it is characterised in that this system also includes the cunning being arranged on ship deck
Road 3, described airplane parking area 1 is installed on slideway 3, and when helicopter lands, described airplane parking area 1 slides to precalculated position along slideway 3,
After helicopter has landed, described airplane parking area 1 carries helicopter and slides to hangar along slideway.
(3) according to the system described in above-mentioned (1) or (2), it is characterised in that
This system also include the spacing for sensing helicopter and airplane parking area distance induction part 4, for airplane parking area and
The communication unit 5 of helicopter communication, for controlling the calutron control portion 6 in magnetic field on calutron 2 and controlling helicopter landing
The calculating part 7 of process.
(4) according to the system described in above-mentioned (3), it is characterised in that described calutron control portion 6 includes for controlling electricity
On magnetic device magnetic field size electric supply installation 61 and for controlling the supply unit 62 of magnetic direction on calutron.
(5) according to the system described in above-mentioned (4), it is characterised in that described calutron 2 includes cylindrical metal core and twines
It is wound on the loop of the multiturn naked skin in described metal-cored outside,
Described electric supply installation 61 includes brush, and it electrically connects with the loop of described naked skin, and described brush may move,
Change the number of turn of hot-wire coil by changing the position of brush, thus control magnetic field force between calutron 2 and electric magnet
Size.
(6) according to the system described in above-mentioned (5), it is characterised in that described supply unit 62 is for warship mistake at helicopter
Cheng Zhong, when helicopter meets pre-conditioned, changes the stream of electric current in the loop of described calutron by supply unit 62
Dynamic direction, and then make the magnetic repulsion between magnetic device 2 and electric magnet become magnetic pull.
(7) according to the system described in above-mentioned (6), it is characterised in that described pre-conditioned include helicopter and airplane parking area 1 it
Between distance less than 5m, and the speed of helicopter is less than 1m/s.
(8) according to the system described in above-mentioned (3), it is characterised in that described calculating part 7 is connected with electric supply installation 61, described
Calculating part for by electric supply installation change magnetism intensity on calutron control described unmanned plane warship speed so that it is at the uniform velocity
Warship.
(9) according to the system described in above-mentioned (1), it is characterised in that set between described electric magnet and helicopter landing gear
It is equipped with spring vibration damper.
(10) a kind of helicopter warship method, it is characterised in that the method is to use if above-mentioned (1) is to being as described in (9)
System,
Preferably, the method comprises the following steps:
Step 1): helicopter is incited somebody to action warship signal and is transferred to airplane parking area 1, and airplane parking area 1 slides to precalculated position along slideway 3；
Step 2): obtain the magnetic field force needed for helicopter lands and the sinking speed of helicopter, now electricity by calculating part
Magnetic field force between magnetic device 2 and electromagnet is repulsion；
Step 3): the sinking speed that helicopter obtains according to calculating part lands, meanwhile, the motion of real-time judge helicopter
It is pre-conditioned whether state meets, and when meeting pre-conditioned, changes the magnetic field force between calutron 2 and electromagnet so that it is
Show as gravitation；
Step 4): helicopter drops on airplane parking area 1, and airplane parking area 1 carries helicopter and slides to hangar along slideway 3.
The present invention is had the advantage that to include:
(1) this system structure is simple, easy to use, has good reliability, it is possible at light, strongly and sea situation is poor
In the case of safe and stable warship；
(2) this system has wide applicability and a versatility, and the helicopter of different model and volume improves a little,
It is adapted to native system；
(3) this system includes calculating part, reduces the dependence to the microcomputer system on helicopter when warship.
Accompanying drawing explanation
Fig. 1 illustrates the helicopter carrier landing system structural representation according to a kind of preferred implementation of the present invention.
Fig. 2 illustrates the plan structure schematic diagram of the airplane parking area according to a kind of preferred implementation of the present invention；
Fig. 3 illustrates the side-looking structural representation of the airplane parking area according to a kind of preferred implementation of the present invention；
Fig. 4 illustrates the structural representation of the calutron according to a kind of preferred implementation of the present invention.
Drawing reference numeral illustrates:
1-airplane parking area
2-calutron
21-is metal-cored
The loop of 22-naked skin
3-slideway
4-distance induction part
5-communication unit
6-calutron control portion
61-electric supply installation
62-supply unit
7-calculating part
Detailed description of the invention
Below by drawings and Examples, the present invention is described in more detail.Illustrated by these, the feature of the present invention
To become more apparent from clearly with advantage.
The most special word " exemplary " means " as example, embodiment or illustrative ".Here as " exemplary "
Illustrated any embodiment should not necessarily be construed as preferred or advantageous over other embodiments.Although embodiment shown in the drawings is each
Kind aspect, but unless otherwise indicated, it is not necessary to accompanying drawing drawn to scale.
A kind of helicopter carrier landing system provided according to the present invention, as shown in Figure 1, Figure 2 and Figure 3, this system includes installing
Electric magnet bottom helicopter body and the airplane parking area 1 being arranged on ship deck,
Wherein, described electric magnet is preferably adsorbed on helicopter landing gear,
Described airplane parking area 1 is circular, has several calutrons 2 uniformly arranged inside it.
Anti-oxidation and antisepsis corrosion material it is coated with outside described electromagnet mechanism and airplane parking area, in case seawater corrosion.
In one preferred embodiment, as shown in Figure 4, described calutron 1 is for including cylindrical metal core and twining
Be wound on the loop of the multiturn/N circle naked skin in described metal-cored outside, the number of turn of described coil according to metal-cored size and
The thickness of coil determines.
In one preferred embodiment, as it is shown on figure 3, this system also includes the slideway 3 being arranged on ship deck,
Described airplane parking area 1 is installed on slideway 3, when helicopter lands, slides to precalculated position along slideway 3, when helicopter has landed
Cheng Hou, slides to hangar along slideway, it is preferred that be provided with hydraulic fixing device in airplane parking area, with the position of fixing airplane parking area.
Another preferred embodiment in, ship deck is offered groove and removable switch, helicopter flight
Time, airplane parking area places with in groove, when helicopter land, opens removable switch, airplane parking area rise to parallel with deck for
Helicopter lands.
In one preferred embodiment, as shown in fig. 1, this system also includes for sensing helicopter and airplane parking area
The distance induction part 4 of spacing, the communication unit 5 communicated with helicopter for airplane parking area, be used for controlling magnetic field on calutron 2
Calutron control portion 6 and control the calculating part 7 of helicopter descent.
Specifically, described communication unit includes wireless transmission device and radio receiver, it is therefore preferable to wireless telecommunications system,
Can receive in nearer distance/transmit information, helicopter when warship, the distance between deck with helicopter compares
Little so that described wireless telecommunications system can normally work；
Described distance induction part 4 can use the parts of multiple principle, such as infrared induction equipment, ultrasonic range finder, light
Learn diastimeter etc., due to helicopter when warship, the distance between deck and helicopter is smaller, and the said equipment can
Realize the effect of range finding, the present invention is preferably optical rangefinder.
Calculating part is able to receive that each information passed out by described communication section 5, and it is described to calculate control according to this information
The descent of helicopter, specifically, described calculating part 7 is connected with electric supply installation 61, and described calculating part is for by power supply
Device change magnetism intensity on calutron control described unmanned plane warship speed so that it is steadily warship, how controlling power is
One empirical process, in electric supply installation, electric current perseverance is certain certain value, and now, the single-turn circular coil of the single electromagnet on airplane parking area carries
Force determines, and can be obtained by reality measurement, and the power that airplane parking area provides is by live wire on the electromagnet number that is energized, each electromagnet
Circle number determines, also relevant with the difference in height on deck with helicopter, along with the landing of helicopter, its difference in height changes the most therewith,
Meanwhile, the speed of unmanned plane is likely to change, described steadily warship refer to according to fixing, less acceleration movement,
Stably drop to the process on deck eventually.So, by calculating part control the size of magnetic field force over time with the change of distance
Change and change, it is possible to realize unmanned plane steadily warship.
In one preferred embodiment, described calutron control portion 6 includes for controlling magnetic field on calutron
The electric supply installation 61 of size and for controlling the supply unit 62 of magnetic direction on calutron, electric supply installation 61 is used for changing stream
Enter the electric current of calutron, and then change the magnetic field force between calutron 2 and electric magnet,
Preferably, described electric supply installation is naval vessel built-in power.
As it is shown on figure 3, described electric supply installation includes brush, it electrically connects with the loop of described naked skin, by changing
The position of power transformation brush changes the number of turn of hot-wire coil, thus changes the magnetic field force between calutron 2 and electric magnet.
Further, described supply unit 62, for during helicopter warship, changes when helicopter meets pre-conditioned
Become the flow direction of electric current in the loop of described calutron, and then make the repulsion in magnetic field between magnetic device 2 and electric magnet
Become gravitation.
The described pre-conditioned distance included between helicopter and airplane parking area 1 is less than 5m, and the speed of helicopter is less than
1m/s。
Specific operation process is, when helicopter starts to land, the magnetic field force between calutron 2 and electric magnet shows as
Repulsion, until judging when the kinestate of helicopter meets pre-conditioned, changing the electric current flowing into calutron 2, making electromagnetism
Magnetic field force between device 2 and electric magnet shows as gravitation.
In one preferred embodiment, described Zhe Jian auxiliary body also includes spring vibration damper and the anti-side of undercarriage
Turning-up devices.Wherein, described spring vibration damper is arranged between electric magnet and helicopter landing gear.
In one preferred embodiment, described spring vibration damper one end is connected with bottom helicopter body, one end
Be connected with electric magnet, be drawn onto with calutron 2 at electric magnet together with moment play the effect of damping.
Warship method according to a kind of helicopter that the present invention provides, the method comprises the following steps:
Step 1): helicopter is incited somebody to action warship signal and is transferred to airplane parking area 1, and airplane parking area 1 slides to precalculated position along slideway 3；
Step 2): obtain the magnetic field force needed for helicopter lands and the sinking speed of helicopter, now electricity by calculating part
Magnetic field force between magnetic device 2 and electromagnet is repulsion；
Step 3): the sinking speed that helicopter obtains according to calculating part lands, meanwhile, the motion of real-time judge helicopter
It is pre-conditioned whether state meets, and when meeting pre-conditioned, changes the magnetic field force between calutron 2 and electromagnet so that it is
Show as gravitation；
Step 4): helicopter drops on airplane parking area 1, and drives airplane parking area 1 to carry helicopter to slide to machine along slideway 3
Storehouse.
In one preferred embodiment, this system can also include angular-rate sensor and the first barometertic altimeter,
Second barometertic altimeter, wherein, angular-rate sensor is for measuring the angular velocity in roll of ship deck, and the first barometertic altimeter is used
In the height above sea level of measurement helicopter, the second barometertic altimeter is for measuring the height above sea level of ship deck.
Wherein, when two groups of ship deck height above sea level the most in the same time that the second barometertic altimeter being positioned on deck records continuously
When highly differing by more than or be equal to warning height difference, or, the angular velocity sensing on the second electromagnet on be set forth in deck
Two groups of naval vessel angular velocity in rolls the most in the same time that device records continuously differ by more than or equal to when guarding against swing speed value, it is believed that institute
Stating helicopter and be unsatisfactory for steadily the condition of warship, the conditional information that helicopter is now unsatisfactory for steadily warship sends to calculating
Portion, by calculating part control helicopter wouldn't warship, until after the above-mentioned condition being unsatisfactory for steadily warship changes；
Wherein, described two groups differ 0.1～0.5s the most in the same time, preferably 0.2s；Described warning height difference be 0.5～
1.5m, preferably 1m；5m/s～15m/s, preferably 10m/s during described warning swing speed value.
Above in association with preferred embodiment describing the present invention, but these embodiments are only exemplary
, only play illustrative effect.On this basis, the present invention can be carried out multiple replacement and improvement, these each fall within this
In the protection domain of invention.
Claims (10)
1. a helicopter carrier landing system, it is characterised in that this system include being arranged on the electric magnet bottom helicopter body and
The airplane parking area (1) being arranged on ship deck,
Described electric magnet is arranged on the undercarriage of helicopter,
It is internally provided with calutron (2) in described airplane parking area (1).
System the most according to claim 1, it is characterised in that this system also includes the slideway being arranged on ship deck
(3), described airplane parking area (1) is installed on slideway (3), when helicopter lands, described airplane parking area (1) along slideway (3) slide to
Precalculated position, after helicopter has landed, described airplane parking area (1) carries helicopter and slides to hangar along slideway.
System the most according to claim 1 and 2, it is characterised in that
This system also includes the distance induction part (4) of the spacing for sensing helicopter and airplane parking area, for airplane parking area and straight
The communication unit (5) of the machine of liter communication, the calutron control portion (6) being used for controlling the upper magnetic field of calutron (2) and control helicopter
The calculating part (7) of descent.
System the most according to claim 3, it is characterised in that described calutron control portion (6) includes for controlling electricity
On magnetic device magnetic field size electric supply installation (61) and for controlling the supply unit (62) of magnetic direction on calutron.
System the most according to claim 4, it is characterised in that described calutron (2) includes cylindrical metal core (21)
With the loop (22) of the multiturn naked skin being wrapped in described metal-cored outside,
Described electric supply installation (61) includes brush, and it electrically connects with the loop of described naked skin, and described brush may move, logical
Cross and change the position of brush to change the number of turn of hot-wire coil, thus control magnetic field force between calutron (2) and electric magnet
Size.
System the most according to claim 5, it is characterised in that described supply unit (62) is for warship process at helicopter
In, when helicopter meets pre-conditioned, changed the stream of electric current in the loop of described calutron by supply unit (62)
Dynamic direction, and then make the magnetic repulsion between magnetic device (2) and electric magnet become magnetic pull.
System the most according to claim 6, it is characterised in that described pre-conditioned include:
Distance between helicopter and airplane parking area (1) is less than 5m, and the speed of helicopter is less than 1m/s.
System the most according to claim 3, it is characterised in that described calculating part (7) is connected with electric supply installation (61), described
Calculating part for by electric supply installation change magnetism intensity on calutron control described unmanned plane warship speed so that it is steadily
Warship.
System the most according to claim 1, it is characterised in that be provided with between described electric magnet and helicopter landing gear
Spring vibration damper.
10. a helicopter warship method, it is characterised in that the method is to use the system as described in claim 1 to 9,
Preferably, the method comprises the following steps:
Step 1): helicopter is incited somebody to action warship signal and is transferred to airplane parking area (1), and airplane parking area (1) slides to precalculated position along slideway (3)；
Step 2): obtain the magnetic field force needed for helicopter lands and the sinking speed of helicopter, now electromagnetic installing by calculating part
Putting the magnetic field force between (2) and electromagnet is repulsion；
Step 3): the sinking speed that helicopter obtains according to calculating part lands, meanwhile, the kinestate of real-time judge helicopter
Whether meet pre-conditioned, when meeting pre-conditioned, change the magnetic field force between calutron (2) and electromagnet so that it is table
It is now gravitation；
Step 4): helicopter drops on airplane parking area (1), and drives airplane parking area (1) to carry helicopter to slide to machine along slideway (3)
Storehouse.
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| CN201610466466.XA CN106043728B (en) | 2016-06-23 | 2016-06-23 | Helicopter carrier landing system and warship method |
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|---|---|---|---|
| CN201610466466.XA CN106043728B (en) | 2016-06-23 | 2016-06-23 | Helicopter carrier landing system and warship method |
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| Publication Number | Publication Date |
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| CN106043728A true CN106043728A (en) | 2016-10-26 |
| CN106043728B CN106043728B (en) | 2018-09-28 |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428538A (en) * | 2016-10-27 | 2017-02-22 | 济南新吉纳远程测控股份有限公司 | Novel rotorcraft system and landing and charging method |
| CN107323678A (en) * | 2017-08-18 | 2017-11-07 | 中国科学院沈阳自动化研究所 | A kind of depopulated helicopter landing servicing unit |
| CN107539492A (en) * | 2017-10-11 | 2018-01-05 | 上海融军科技有限公司 | A kind of small-sized carrier-borne depopulated helicopter helps drop mooring device |
| CN109003342A (en) * | 2018-07-12 | 2018-12-14 | 广州光强障碍灯航空设备有限公司 | A kind of intelligence airplane parking area management system |
| CN109116866A (en) * | 2018-09-20 | 2019-01-01 | 四川腾盾科技有限公司 | A kind of unmanned plane is two-way independently to drive into control method |
| CN109709972A (en) * | 2018-12-28 | 2019-05-03 | 上海鹄恩信息科技有限公司 | A kind of Internet of Things network communication system and method based on unmanned plane |
| CN109782791A (en) * | 2017-11-14 | 2019-05-21 | 长城汽车股份有限公司 | A kind of landing method and device of unmanned plane |
| CN109850177A (en) * | 2018-11-29 | 2019-06-07 | 中国船舶工业系统工程研究院 | A method of being quickly tethered at operation on the sea helicopter |
| CN110386257A (en) * | 2018-07-30 | 2019-10-29 | 魏荣亮 | For vertical translation aircraft warship device and naval vessel |
| CN111532440A (en) * | 2020-04-16 | 2020-08-14 | 广东工业大学 | Multi-adaptive electromagnetic adsorption unmanned aerial vehicle recovery system |
| CN114516400A (en) * | 2022-03-25 | 2022-05-20 | 四川腾盾科技有限公司 | Carrier landing device, carrier landing system and carrier landing method of unmanned helicopter |
| CN115897440A (en) * | 2023-01-14 | 2023-04-04 | 武汉理工大学 | Intelligent parking apron and construction method thereof |
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