CN106379550A - Take-off and landing platform for aircraft - Google Patents
Take-off and landing platform for aircraft Download PDFInfo
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- CN106379550A CN106379550A CN201610882801.4A CN201610882801A CN106379550A CN 106379550 A CN106379550 A CN 106379550A CN 201610882801 A CN201610882801 A CN 201610882801A CN 106379550 A CN106379550 A CN 106379550A
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- landing platform
- undercarriage
- aircraft
- fixed plate
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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
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- E—FIXED CONSTRUCTIONS
- E01—CONSTRUCTION OF ROADS, RAILWAYS, OR BRIDGES
- E01C—CONSTRUCTION OF, OR SURFACES FOR, ROADS, SPORTS GROUNDS, OR THE LIKE; MACHINES OR AUXILIARY TOOLS FOR CONSTRUCTION OR REPAIR
- E01C9/00—Special pavings; Pavings for special parts of roads or airfields
- E01C9/008—Paving take-off areas for vertically starting aircraft
-
- E—FIXED CONSTRUCTIONS
- E01—CONSTRUCTION OF ROADS, RAILWAYS, OR BRIDGES
- E01F—ADDITIONAL WORK, SUCH AS EQUIPPING ROADS OR THE CONSTRUCTION OF PLATFORMS, HELICOPTER LANDING STAGES, SIGNS, SNOW FENCES, OR THE LIKE
- E01F3/00—Landing stages for helicopters, e.g. located above buildings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention provides a take-off and landing platform for assisting an aircraft to take off and land in a bumpy environment. The take-off and landing platform comprises a fixing plate and an attitude adjustment seat, wherein the fixing plate is used as a platform where the aircraft takes off and lands, and is used for fixing the aircraft before the aircraft takes off; the attitude adjustment seat is mounted on the lower side of the fixing plate and is used for stabilizing a space attitude of the fixing plate; and the attitude adjustment seat is at least provided with two degrees of freedom capable of rotating around the X axis and the Y axis. The multi-axis aircraft is fixed on the fixing plate before taking off, and the attitude adjustment seat dynamically stabilizes the attitude of the aircraft, so that the aircraft can be prevented from swinging back and forth, and good take-off conditions are supplied to taking off; and the stable fixing plate can supply a good landing environment to the multi-axis aircraft.
Description
Technical field
The present invention relates to the landing platform of the landing platform of aircraft, more particularly, to Multi-axis aircraft.
Background technology
Multi-axis aircraft generally includes fuselage, horn, flies control device, power supply, electric tune, motor, rotor and feature sensing
Device.
Electric helicopter generally also include empennage and lock tail gyroscope, control rotary wing changing away from feathering and always away from control
Device processed, this control device includes the components such as steering wheel, pitch, connecting rod.
Multi-axis aircraft and electric helicopter all should not take off under strong wind atmosphere.At present, four-axle aircraft can be in strong breeze
Hereinafter fly；Six axle aircraft can fly in 6 to fresh gale reluctantly.The wind speed of strong breeze between 8 to 10.7 metre per second (m/s)s, 6 grades
, between 10.8 to 13.8 metre per second (m/s)s, the wind speed of fresh gale is between 13.9 to 17.1 metre per second (m/s)s for the wind speed of wind.But multiaxis flight
Device needs weaker in wind-force and steady air current local landing, and under Limit of Wind Speed and sinuous flow, landing is extremely hazardous.Helicopter is 7
It is difficult to take off under level wind-force.When typically taking off or landing, the wind speed of 8 metre per second (m/s)s just belongs to than relatively hazardous environment bar
Part, during force 7 wind, generally requires and makes preparation for dropping.
Notification number discloses a kind of landing system of unmanned boat-carrying unmanned plane, its purpose for CN105059558A patent application
It is to solve the problems, such as that how unmanned plane safely takes off and landing on indefinite unmanned boat deck jolting, this unmanned plane is multiaxis
Aircraft.Under good weather environment, cancel the electromagnetic force between unmanned boat and unmanned plane, let unmanned plane fly away.Obviously, unmanned plane
Take off and depend on weather conditions, still cannot take off under strong wind atmosphere.This system can only solve under good weather environment
Unmanned plane take off problem, in the environment of wind and waves, the landing problem of unmanned plane does not still solve.Additionally, being fixed on ship
On for plate electromagnet and the solenoid actuated module that is attached thereto, being fixed on unmanned plane foot rest is magnetic conductive board, due to
The foot rest span of unmanned plane is larger, needs larger bearing-surface, the therefore area of plate electromagnet can be very big, and not only weight is relatively
Greatly, manufacturing cost is high, and needs more electric energy could maintain the fixation of unmanned plane, poor practicability.Landing platform is arranged on land
When on mobile devices, it is indefinite that the fluctuating on road surface leads to mobile devices and landing platform jolts, and is unfavorable for the landing of Multi-axis aircraft.
Existing Multi-axis aircraft only to adjust flight attitude by changing variable rotor speed substantially, and translation flight needs dumper
Body, thus increased the front face area of fuselage, lead to the increase of flight resistance, make the movement response of Multi-axis aircraft slow, motor-driven
Property poor, frequently acceleration and deceleration make kinetic energy rejection big to motor, and motor thermal losses is big, and efficiency is low.It is difficult to pacify under action of high-speed airflow
Full landing.Before taking off on the landing platform impacted by high velocity air, Multi-axis aircraft unprotect measure, not only easily by a high speed
Air-flow blows off, but also does not enable the mobile takeoff and landing of safety and stability.
Content of the invention
The present invention is intended to provide a kind of landing platform of auxiliary Multi-axis aircraft landing under the environment that jolts.
In order to realize above-mentioned main purpose, the landing platform of the present invention includes fixed plate and pose adjustment seat.Fixed plate conduct
The platform of aircraft landing, is used for fixing aircraft before take-off；Pose adjustment seat is arranged on the downside of fixed plate, for stable
The spatial attitude of fixed plate, pose adjustment seat is minimum to possess two degree of freedom verting around X-axis and Y-axis.
From above scheme, Multi-axis aircraft is fixed in fixed plate before take-off, dynamically steady by pose adjustment seat
Determine the attitude of aircraft, can prevent aircraft from rocking back and forth, provide good takeoff condition for taking off.Initial when fixed plate
When being positioned against high velocity air inclination, the rotor using Multi-axis aircraft absorbs the air-flow rushing at Multi-axis aircraft, reduces multiaxis
Windage in front of aircraft, is conducive to improving the security and stability taking off.The fixed plate of horizontal attitude can dynamically be kept simultaneously,
Be conducive to providing, for Multi-axis aircraft, the environment that stably lands, when minimizing will be landed, flow perturbation on the downside of Multi-axis aircraft or
When the situation of cataclysm, vehicle or ship jolt, it is to avoid Multi-axis aircraft is clashed with landing platform, lead to aircraft quilt
Upspring and crash.
Further, the base of pose adjustment seat be Three Degree Of Freedom base, base include added, undercarriage and connect added
And three expansion links of undercarriage, the upper end of expansion link with added between be connected by universal joint or ball pivot；The lower end of expansion link with
Undercarriage is hinged, and its hinge is horizontally disposed.Fixed plate can be verted around X and Y-axis with added, and moves up and down along Z axis, only needs three
Expansion link can ensure that attitude fixed plate tilts in any direction and lifts, structure simpler reliable it is easy to control, cost
Low.
Further, the base of pose adjustment seat be binary base, base include added, undercarriage and connect added
And three expansion links of undercarriage, the upper end of expansion link with added between be connected by universal joint or ball pivot, the lower end of expansion link with
Undercarriage is hinged, and its hinge is horizontally disposed, and the upside at the middle part of undercarriage is provided with pillar, and the upper end of pillar is passed through with added downside
Universal joint or ball pivot connect.Effectively improve the bearing capacity of base.
Further, added serve as fixed plate.Fixed plate need not be separately provided, advantageously reduce the weight of landing platform.
Further, described pose adjustment seat be six degree of freedom Stewart formula base, described base include added,
Undercarriage and the six roots of sensation expansion link connecting described added and described undercarriage.The understructure intensity of the Stewart formula of six degree of freedom is high,
High precision, fast response time, can effectively stablize the attitude of fixed plate with full angle ground.
Further, buffer part, be arranged on fixed plate and described added between.Not only can cut down from pose adjustment seat to
The vibrations of fixed plate transmission, can also absorb impact during Multi-axis aircraft landing, enter row buffering.
Further, buffer part is the cushion rubber bumper of ring-type.Shock attenuation result is good, and structure is simply easily installed.
Further, buffer part is Acetabula device.It is easy to the installation and removal of fixed plate.
Further, Acetabula device includes support and minimum two suckers, and sucker is rack-mount, the axis of sucker with
The axial offset of support.Be conducive to extending conduct vibrations path, slacken vibration transmission.
Further, Acetabula device includes dropping-proof bracket, and dropping-proof bracket includes snap ring and connection part, and snap ring is stuck in sucker
The downside of main body, the work surface of the main body of sucker is abutted with fixed plate, together with connection part is removably attachable to fixed plate.Carry
The reliability that high fixed plate is installed.
Further, support is provided with the first cylinder, added on be provided with the second cylinder, first cylinder at least a portion
In embedded second cylinder.It is lined with damping rubber between the diapire of the diapire of the first cylinder and the second cylinder.Be conducive to extending vibration biography
Guiding path, slackens vibration transmission.
Further, the quantity of Acetabula device is more than or equal to three, expansion link and added connecting portion and Acetabula device
Stagger with added connecting portion.Be conducive to extending conduct vibrations path, slacken vibration transmission.
Further, the downside of undercarriage is provided with multiple cushion pads, and the connecting portion of expansion link and undercarriage is wrong with cushion pad
Open.Be conducive to extending conduct vibrations path, slacken vibration transmission.
Brief description
Fig. 1 is the top view of the omission shell of the Multi-axis aircraft embodiment one of the present invention；
Fig. 2 is the partial schematic diagram of the second tilting drive of the Multi-axis aircraft embodiment one of the present invention；
Fig. 3 is the partial schematic diagram of Multi-axis aircraft embodiment one first tilting drive of the present invention；
Fig. 4 is the side view of Multi-axis aircraft embodiment one of the present invention；
Fig. 5 is the partial schematic diagram of the first tilting drive of Multi-axis aircraft embodiment two of the present invention；
Fig. 6 is the partial schematic diagram of the second tilting drive of Multi-axis aircraft embodiment two of the present invention；
Fig. 7 is the structural representation of landing platform embodiment one of the present invention；
Fig. 8 is the installment state zoomed-in view of the mechanical lock mechanism of landing platform embodiment one of the present invention；
Fig. 9 is the A-A sectional view of Fig. 8；
Figure 10 is the axonometric chart of landing platform embodiment two of the present invention；
Figure 11 is the axonometric chart of the Acetabula device of landing platform embodiment two of the present invention；
Figure 12 is the generalized section of the installment state of Acetabula device of landing platform embodiment two of the present invention；
Figure 13 is the axonometric chart of landing platform embodiment three of the present invention；
Figure 14 is the axonometric chart of landing platform example IV of the present invention；
Figure 15 is original state schematic diagram when Multi-axis aircraft is on the landing platform of movement；
Figure 16 is view during standby for takeoff when Multi-axis aircraft is on the landing platform of movement.
Specific embodiment
The reference frame of the degree of freedom described in the present invention is rectangular coordinate system in space, and X-axis therein and Y-axis are located at water
In plane, Z axis are vertical.
Multi-axis aircraft embodiment one
As shown in figure 1, Multi-axis aircraft includes fuselage, power set, tilting drive and take-off and landing device.The main function of fuselage
It is to load power supply, fly the equipment such as control device, Multi-axis aircraft is connected integral effect simultaneously, including frame 1010, fly control
Pallet 103, battery mounting 102, the first horn 1020 and the second horn 1030.Frame 1010 includes two supervisor's 1011 Hes
1012, connect the connector 1013 of two supervisors and cover the casing 130 in supervisor outside（Referring to Fig. 3）.Casing can be effective
Protection inner member.Fly control pallet 103 to be used for loading winged control plate（In figure is not shown）, frame 1010 is fixed on by pipe clamp 1015
On.Battery mounting 102 is used for loading battery, is symmetrically fixed on the both sides of frame 1010 width, both sides by screw
Fixture 1021,1022 pass through limited post 1023 and pass through limited post 1023 bolt（Not shown）Carry out installing and fix, knot
Structure is simple, intensity is high and lightweight.First horn 1020 includes the first duct power unit 104, the second duct power unit
105th, fix bar 1021 and the first chuck 1022, the first duct power unit 104 and the second duct power unit 105 are by fix bar
Support, and can vert in front and back under the first tilting drive 107 drives.
As shown in Fig. 2 the second horn 1030 includes the 3rd duct power unit 106, the second chuck 116, installing plate 125 and
Rotating shaft 115.Chuck 116 is fixed by screws on installing plate 125, and chuck 116 rotatably supports the 3rd along its width
Duct power unit 106, rotating shaft 115 is rotatably mounted in the mounting seat 1014 of frame 1010.
First duct power unit 104, the second duct power unit 105 and the 3rd duct power unit 106 are as this reality
Apply the power set of example.
In conjunction with Fig. 2-3, described tilting drive includes the first tilting drive 107 and the second tilting drive
108.First tilting drive 107 includes fixed mount 112, steering wheel 124, anchor ear 113, and fixed mount 112 first end passes through bearing
110 rotatable supporting the first horns 1020, screw and frame 1010 are passed through in second end relative with first end of fixed mount 112
Connect, the 3rd end of fixed mount 112 is that downside is connected with the top connection 126 of foot rest by screw, and steering wheel 124 passes through fixed block
127 are fixed on fixed mount 112, and steering wheel output steering wheel arm 114 passes through push rod 111 and the anchor ear being fixed on the first horn 1020
113 connections, thus driving the first horn 1020 to vert, drive the first duct power unit 104 and the second duct power list simultaneously
Unit 105 verts.As preferred, the structure of the double push rods of push rod 111 selection, it is more uniformly stressed, structural strength is higher, work is more
Stable.Second tilting drive 108 includes rear steering wheel 121, the second chuck 116.Steering wheel 121 passes through screw and the second chuck afterwards
116 and installing plate 125 connect, rear steering wheel 121 output steering wheel arm is connected with rocking arm 123 by push rod 122, rocking arm 123 respectively with
Duct bucket, the second chuck 116 connect, so that the second duct power unit 105 verts.As preferred, push rod 122 selection pair
The structure of push rod, is more uniformly stressed, and structural strength is higher, and work is more steady.
First tilting drive 107 drives the first duct power unit 104 and the second duct power unit 105 towards leaning forward
Turn and front air-flow can be absorbed by the rotor of two power units, weaken the windage to flow towards head, it is to avoid high velocity air pair
Multi-axis aircraft is thrown by the windage that Multi-axis aircraft produces.Further second tilting drive 108 drives the 3rd duct
Power unit 106 tilts forward and can further weaken the windage to flow, and improves the attitude anterior-posterior balance of Multi-axis aircraft
Stability.
Further, tilting drive also includes the 3rd tilting drive 109.Including fixed block 128, front steering wheel
119th, pivot block 117, rotating shaft 115, front steering wheel 119 are fixed by screws on fixed block 128, and fixed block leads to 128 crosses screw admittedly
It is scheduled on pipe clamp 1013, front steering wheel 119 output steering wheel arm 120 is connected with pivot block 117 by push rod 118, and pivot block 117 passes through
Screw is fixed in rotating shaft 115, and rotating shaft 115 is fixed by screws on the second chuck 116, so that the second duct power unit
105 vert along the length direction of fuselage.
First duct power unit 104 and the second duct power unit 105 vert forward or backward can quickly produce to
Front or Level Promoting component backward.3rd duct power unit 106 verts forward or backward and equally can quickly produce forward
Or Level Promoting component backward, the quick anterior-posterior translation realizing flight.3rd duct power unit 106 can also be around fuselage
The axis that is located of length direction to the left or Right deviation turns, in the quick horizontal thrust producing to the left or to the right of tail, fast to realize
Speed driftage.First, second, and third duct power unit vert forward or backward simultaneously just can realize high speed anterior-posterior translation fly
OK.Because translation flight does not need dumper body, greatly reduce front face area, horizontal windage is less.
As shown in figure 4, take-off and landing device 140 Main Function of Multi-axis aircraft is to carry during Multi-axis aircraft take-off and landing
For supporting role, it includes undercarriage 141 and fixture 142.Undercarriage 141 is used for supporting Multi-axis aircraft, solid by screw
It is scheduled in frame 1010, undercarriage 141 is provided with T font bracing piece 143, structure is simple, lightweight, intensity is high.Fixture 142
It is fixed on the downside of undercarriage 141, Multi-axis aircraft relies on fixture 142 to be fixed on landing platform 150 before movement is taken off, will not
Because the impact of high velocity air is dropped from landing platform.When landing platform is mobile, tilting drive driving power device is towards landing
Vert to predetermined angular in the direction of platform movement, fixture 142 reaches in the rotor rotating speed of power unit, the thrust producing or throttle
After predetermined value, release the fixation to landing platform for the Multi-axis aircraft.Preferably, fixture 142 bottom is provided with electric magnet, landing platform
The side of 150 supporting Multi-axis aircrafts is iron plate.The rotation axiss of the rotor of power set vert towards the direction of landing platform movement
Predetermined angular between 15 degree to 45 degree.Landing platform translational speed is faster, predetermined tilt angle bigger it is preferred that predetermined
Square being directly proportional of tilt angle and the speed of landing platform movement.
Multi-axis aircraft embodiment two
The present embodiment is the first tilting drive and the second tilting drive with the difference of embodiment one.
As shown in figure 5, the first tilting drive 200 includes：Fixed mount 201, steering wheel 202, steering wheel output synchronous pulley
203rd, Timing Belt 204, synchronous pulley 205, fixed mount 201 first end passes through bearing 206 rotatable supporting the first horn 2020,
Second end relative with first end of fixed mount 201 is connected with frame 2010 by screw, fixed mount 201 positioned at the of downside
Three ends are connected with foot rest by screw, and steering wheel 202 is connected with fixed mount 201 by locating dowel, and steering wheel output synchronous pulley 203 leads to
Cross Timing Belt 204 and be connected with the synchronous pulley 205 being fixed on the first horn 2020, so that the first horn 2020 verts, and then
The first duct power unit 211 and the first duct power unit 212 is driven to vert.Preferably, the first horn 2020 has independence
The left horn verting and right arm, the first duct power unit 211 and the first duct power unit 212 are separately mounted to left horn
On right arm, two groups of steering wheels and synchronous belt device are arranged in the first tilting drive, drive left horn and right machine respectively
Arm independently verts so that the regulation of Multi-axis aircraft air-flow is more flexible.Device for regulating tightness of synchronous belt 207 passes through screw scalable
Be arranged on inside fixed mount, play regulation tightness of synchronous belt effect.Timing Belt overload can be skidded, and can play protection multiaxis flight
The effect of device tilting drive.
As shown in fig. 6, the second tilting drive includes rear steering wheel 231, rear steering wheel output synchronous pulley 232, Timing Belt
233, synchronous pulley 234.Synchronous pulley 234 is coupled with duct bucket and is rotatably mounted on chuck 216.Afterwards steering wheel 231 according to
Secondary synchronous pulley 232 is exported by rear steering wheel, Timing Belt 233 and synchronous pulley 234 driving the 3rd duct power unit 213 inclines
Turn.Device for regulating tightness of synchronous belt 235 is adjustably mounted at the inner side of chuck 216 by screw, rises and adjusts tightness of synchronous belt
Effect.Timing Belt overload can be skidded, and plays the effect of protection Multi-axis aircraft tilting drive.
Landing platform embodiment one
As shown in fig. 7, landing platform 1000 includes fixed plate 810 and pose adjustment seat 900.Pose adjustment seat 900 has one six
The base 910 of the Stewart formula of degree of freedom.It is provided with the ring-type as buffer part between fixed plate 810 and pose adjustment seat 900
Cushion rubber bumper 920.Base 910 includes lower ring stand 911 as undercarriage, six roots of sensation expansion link 912 and as added upper ring stand
913.Upper ring stand 913 and fixed plate 810 are connected by bolt 914, and bolt passes through the via in cushion rubber bumper 920, cushion rubber bumper
920 pads are between upper ring stand 913 and fixed plate 810.Preferably, six roots of sensation expansion link 912 is electric cylinders or hydraulic cylinder.Obviously, buffer
Portion is not limited to cushion rubber bumper 920, and the silica gel shock-absorption ball parallel connection that can also be had via by multiple middle parts is constituted.Under fixed plate 810
Side is provided with three mechanical lock mechanisms 410.Preferably, it is provided with the rubber of annular between the head of bolt 914 and upper ring stand
Pad, so advantageously reduces the vibration transmitted from base 910 to fixed plate 810.
As shown in Figure 8 and Figure 9, the mechanical lock mechanism 410 with housing 430 is arranged on the downside of fixed plate 810, fixture
142 are fixed on the upside of fixed plate 810.Fixture 142 includes set casing 440 and electric magnet 450.Electric magnet includes iron core 451 line
Circle 452 and shell 453.Screwed hole 454 is had, upside is provided with installing hole 455 on the downside of iron core.Electric magnet 450 passes through installing hole
455 and screw be arranged in set casing 440.Electric magnet 450 is fixed with the silicagel pad 456 as cushion.Mechanical lock mechanism
410 have a motor 411, back-moving spring 412, sliding sleeve 413, screw rod 414, motor cabinet 415 and mounting seat 416.Mounting seat 416 is led to
Cross screw and be arranged on the downside of fixed plate 810, motor cabinet 415 is fixed by screws on the downside of mounting seat 416.The output of motor 411
Axle is D profile shaft, is provided with D type hole, D type hole is enclosed within D profile shaft in sliding sleeve 413.The upper end of sliding sleeve 413 is led to the lower end of screw rod 414
Cross flange and mode connects for screw.The output shaft of motor 411 can to while sliding sleeve 413 transmitting torque in the direction of its rotation axis
Upper slip relative with sliding sleeve 413.When the fixture 142 of Multi-axis aircraft is not placed in fixed plate 810, sliding sleeve 413 and screw rod
414 pass upwards from the perforate of fixed plate 810 under the promotion of spring 412；When the screwed hole 454 of fixture 142 is directed at screw rod
When being placed in fixed plate 810, the elastic force of back-moving spring 412 is overcome to push screw rod 414.Motor 411 is driven by sliding sleeve 413
Screw rod 414 rotates, and screw rod 414 screws in screwed hole 454 thus being fixed on electric magnet 450 under the pushing of back-moving spring 412
In fixed board 810, thus realizing the mechanical caging of fixture 142.When motor 411 drive screw 414 reversely rotates, screw rod 414
Back-moving spring 412 elastic force is overcome to screw out from screwed hole 454, thus realizing the mechanical release of fixture 142.Obviously, electric magnet 450
Iron core 451 serve as mechanical locking portions.Screwing and outwarding winding of screw thread can effectively realize mechanical caging and unblock, and structure is simple
Single, compact.
Obviously, mechanical lock mechanism not limited to this, can also be can folding gripper, by the folding of gripper to solid
Determine part and carry out mechanical caging and unblock, now fixture itself is as mechanical locking portions.Certainly, mechanical lock mechanism can also be
Latch that can be transversely opened and closed, fixture is provided with the pin hole with latch cooperation, now fixture itself is as mechanical caging
Portion.
Landing platform embodiment two
As shown in Figure 10, landing platform 2000 includes fixed plate 2810 and pose adjustment seat 2900.Pose adjustment seat 2900 has one
The base 2910 of the Stewart formula of individual six degree of freedom.It is provided with as buffering between fixed plate 2810 and pose adjustment seat 2900
The Acetabula device 2920 in portion.Base 2910 includes lower ring stand 2911 as undercarriage, six roots of sensation expansion link 2912 and as added
Upper ring stand 2913.Preferably, six roots of sensation expansion link 2912 is electric cylinders or hydraulic cylinder.It is provided with three mechanical locks on the downside of fixed plate 2810
Determine mechanism 2410.
Three Acetabula devices 2920 are evenly arranged on ring stand 2913.The downside of Acetabula device 2920 is by bolt even
Connect and be arranged on ring stand 2913.The connecting portion of expansion link 2912 and upper ring stand 2913 and Acetabula device 2920 and upper ring stand
2913 connecting portion staggers, and is so conducive to extending conduct vibrations path, is conducive to eliminating vibration.Set on the downside of lower ring stand 2911
It is equipped with the cushion pad 2915 that multiple middle parts are provided with via, the connecting portion of expansion link 2912 and lower ring stand 2911 and cushion pad 2915
Stagger, be so conducive to extending conduct vibrations path, be conducive to eliminating vibration.
As is illustrated by figs. 11 and 12, it is provided with three opening up suckers 2940 on the upside of Acetabula device 2920, downside sets
It is equipped with the support 2950 including cylinder portion 2951 and cantilever 2952, middle part is provided with dropping-proof bracket 2960.The lower end of sucker 2940 leads to
Cross bolt connection to be arranged on cantilever 2952, the work surface of sucker 2940 main body is used for adsorbing fixed plate 2810, that is, work surface with
Fixed plate 2810 abuts.The axis of sucker 2940 and the axial offset in cylinder portion 2951, i.e. the axis of sucker 2940 and support 2950
Axial offset, further extend conduct vibrations path, be conducive to eliminate vibration.Dropping-proof bracket 2960 includes snap ring
2961st, the cylinder 2963 as connection part of arm 2962 and the embedded silicagel pad 2964 positioned at middle part.Snap ring 2961 is stuck in suction
The downside of the main body of disk 2940, screw 2965 passes through fixed plate 2810 and cylinder 2963 and is locked by nut 2966, not only prevents
Fixed plate 2810 gets loose from sucker 2940, improves security reliability, also effectively realizes Acetabula device 2920 and fixed plate
2810 be flexible coupling, effectively reduces the interference to fixed plate 2810 for the dither.Upper ring stand 2913 is provided with cylinder 2914, cylinder
In the embedded cylinder 2914 of 2951 at least a portion, effectively extend conduct vibrations path, be conducive to eliminating vibration.The bottom of cylinder 2951
It is lined with damping rubber 2954, cylinder 2951 and cylinder 2914 pass through bolt 2955 and nut 2956 between the diapire of wall and cylinder 2914
It is attached.Preferably, it is lined with buffering adhesive 2953 between the diapire of the head of bolt 2955 and cylinder 2951.Effectively realize inhaling
Being flexible coupling of disk device 2920 and upper ring stand 2913, effectively reduces the transmission of dither.
Landing platform embodiment three
As shown in figure 13, the present embodiment and the difference of landing platform embodiment two are, the base of pose adjustment seat be one three from
By the base 3910 spent.Base 3910 includes as added upper ring stand 3920, undercarriage 3930 and connect upper ring stand 3920 and under
The expansion link 3940 of frame 3930.Upper ring stand 3920 can vert around X and Y-axis, and moves up and down along Z axis.Expansion link 3940 upper
End is connected by universal joint or ball pivot between upper ring stand 3920；The lower end of expansion link 3940 is hinged with undercarriage 3930, its hinge
3931 is horizontally disposed.
Landing platform example IV
As shown in figure 14, the present embodiment and the difference of landing platform embodiment three are, can be direct as added iron plate 4920
As the fixed plate for Multi-axis aircraft landing.The upside at undercarriage 4930 middle part is provided with pillar 4950.The upper end of pillar 4950
It is connected by universal joint or ball pivot with the downside of iron plate 4920.The present embodiment has lacked and has moved down along along Z axis compared with landing platform embodiment three
Dynamic degree of freedom, but bearing strength is higher.
Before Multi-axis aircraft takes off on the landing platform of high-speed mobile, if no fixation will be blown off by high velocity air,
Electric magnet as fixture is installed on undercarriage, electric magnet energising can be fixed on high speed landing platform Multi-axis aircraft
Above it is ensured that it is not blown off by high velocity air.The operation principle of the present invention is as follows：Multiaxis is flown by the electric magnet being arranged on undercarriage
Row device is fixed on landing platform, so that power set is verted to predetermined angular by tilting drive, starts power set and increase
Put english the rotating speed of the wing, when rotor rotating speed, the pulling force that produces or throttle be when reaching predetermined value, and electric magnet unlocks, and multiaxis flies
Device departs from landing platform and takes off.Power set effectively absorb oncoming air-flow, thus improve stability and safety.
As shown in Figure 15 and Figure 16, Multi-axis aircraft 700 has power set 710, and foot rest is provided with fixture 750.
Landing platform 2000 moves along direction V1, and high velocity air rushes at Multi-axis aircraft 700 along V2 direction.
The method that the Multi-axis aircraft that the present invention provides takes off under gas shock：
S1, Multi-axis aircraft 700 are fixed on landing platform 2000 by fixture 750；
S2, come to tilt power device 710 towards air-flow so as to rotor wing rotation axis is towards flowing；
S3, the rotating speed of the rotor of increase power set 710, the rotor rotating speed of power set 710, the thrust producing or throttle reach
After predetermined value, release the locking to landing platform 2000 for the fixture 750 of Multi-axis aircraft 700.
Preferably, it is provided with pressure transducer as on the upside of the electric magnet of fixture 750 and each foot rest support bar between,
Described pressure transducer is electrically connected with the winged control device of Multi-axis aircraft 700, when winged control device detects each pressure transducer
Detected value difference two-by-two within a predetermined range when, electric magnet power-off, release locking to landing platform 2000, release multiaxis flies
Row device 700.Now, the top of landing platform 2000 is made up of the carbon fiber plate that iron plate or top cover ferrous material, and it serves as landing
The fixed plate 2810 of platform 2000.
Further, fixed plate 2810 also includes mechanical lock mechanism 2820；Pass through mechanical lock mechanism before take-off
2820 locking Multi-axis aircrafts 700；When will take off, electric magnet energising absorption iron plate, mechanical lock mechanism 2820 releases to many
Axle aircraft 700 locks；Electric magnet power-off simultaneously, discharges Multi-axis aircraft 700.
Verted by way of the horn that verts power set 710 when, vert equal positioned at the power set 710 of front side or rear side
The absorbable air-flow rushing at Multi-axis aircraft 700, cuts down windage, realizes safe take-off.Preferably, vert front side power set
The security reliability taken off can be improved, the power set positioned at front side and rear side that simultaneously vert can further improve
Winged security reliability.
The controller of pose adjustment seat 2900 is led to by way of wireless telecommunications with the winged control device of Multi-axis aircraft
News, fly to be provided with the inertial navigation list including three axis accelerometer and three-axis gyroscope for testing machine figure state in control device
Unit.Fly control device according to fuselage attitude detection data genaration control signal, send to the controller of pose adjustment seat 2900, attitude
Adjustment seat 2900 dynamically adjusts length of telescopic bar to stablize the fuselage attitude of Multi-axis aircraft.The invention is not restricted to this it is also possible to
Fuselage attitude parameter is obtained from winged control device by the controller of pose adjustment seat 2900, calculates the control parameter of expansion link, adjust
Whole length of telescopic bar, thus stablize fuselage attitude.Improve as a kind of, the downside of landing platform 2800 is provided with gyroscope, attitude
The controller of adjustment seat 2900 reads the gyroscope signal on landing platform 2000, calculates the control parameter of expansion link, adjustment is stretched
Contracting pole length, thus stablize fuselage attitude.So pose adjustment seat 2900 can compensate to inclination earlier, realizes rapid
Effectively pose adjustment.Obviously, pose adjustment seat 2900 is by stablizing the spatial attitude of fixed plate 2810, you can stablizes multiaxis and flies
The spatial attitude of row device.When expansion link is for electric cylinders, the circuit module of controller is electrically connected with electric cylinders.When expansion link is hydraulic cylinder
When, controller also includes pumping plant, and the circuit part of controller is electrically connected with the electromagnetic valve of pumping plant, and pumping plant passes through oil pipe and hydraulic cylinder
Connect.
The initial position of the fixed plate 2810 of pose adjustment seat 2900 is in horizontality.Before taking off, pose adjustment seat
2900 locus that can greatly revise adjustment fixed plate 2810, eliminate significantly low-frequency oscillation, as buffering
The Acetabula device 2920 in portion and cushion rubber bumper 2915 can effectively eliminate the dither of little amplitude, thus effectively ensureing fuselage
Attitude stabilization, greatly improves the security reliability that movement is taken off.Low-frequency vibration can be risen and fallen by the entirety of road surface or wave and cause；High
Frequency vibration can be patted ship by itself vibration of road surface thin portion roughness, the vehicle of carrying landing platform or ship or wave and cause.
The type that can not vert for power set 710, can be realized by the initial position of adjustment fixing plate 2810
Power set 710 coming to inclination towards air-flow.
The power unit of the present invention possesses rotor it is preferred that being provided with duct or guard circle outside rotor.Rotor is not limited to
By Motor drive, can also be driven by oil machine.
It is many that the Multi-axis aircraft of the present invention is not limited to three axle aircraft or four-axle aircraft, six axle aircraft etc.
Axle aircraft.For example, the 3rd duct power unit 213 in embodiment two is substituted by two duct power units arranged side by side, that is,
Become four-axle aircraft.
The landing platform of the present invention can be used on vehicle or the ship of high-speed mobile, by arranging the initial position of landing platform
It is also possible that the rotor of Multi-axis aircraft tilts, allow rotor aspirate oncoming air-flow, reduce windage, improve the peace taken off
Total stability.
Embodiment described above is simply presently preferred embodiments of the present invention, not limits the practical range of the present invention with this,
The equivalence changes that all shapes according to the present invention, construction and principle are made, all should be covered by protection scope of the present invention.
Claims (13)
1. a kind of aircraft landing platform it is characterised in that：Including,
Fixed plate, as the platform of aircraft landing, is used for fixing aircraft before take-off；
Pose adjustment seat, is arranged on the downside of described fixed plate, for stablizing the spatial attitude of described fixed plate；
Described pose adjustment seat is minimum to possess two degree of freedom verting around X-axis and Y-axis.
2. landing platform as claimed in claim 1 it is characterised in that：
The base of pose adjustment seat is the base of Three Degree Of Freedom, and described base includes added, undercarriage and connects described added and institute
State three expansion links of undercarriage, the upper end of described expansion link with described added between be connected by universal joint or ball pivot；Described stretch
The lower end of contracting bar is hinged with described undercarriage, and its hinge is horizontally disposed.
3. landing platform as claimed in claim 1 it is characterised in that：
The base of pose adjustment seat is binary base, and described base includes added, undercarriage and connects described added and institute
State three expansion links of undercarriage, the upper end of described expansion link with described added between be connected by universal joint or ball pivot, described stretch
The lower end of contracting bar is hinged with described undercarriage, and its hinge is horizontally disposed, and the upside at the middle part of described undercarriage is provided with pillar, described
The upper end of post is connected by universal joint or ball pivot with described added downside.
4. landing platform as claimed in claim 2 or claim 3 it is characterised in that：
Described added serve as described fixed plate.
5. landing platform as claimed in claim 1 it is characterised in that：
Described pose adjustment seat is the base of the Stewart formula of six degree of freedom, and described base includes added, undercarriage and connects described
The six roots of sensation expansion link of added and described undercarriage.
6. described landing platform as arbitrary in claim 1 to 5 it is characterised in that：
Buffer part, be arranged on described fixed plate and described added between.
7. landing platform as claimed in claim 6 it is characterised in that：
Described buffer part is the cushion rubber bumper of ring-type.
8. landing platform as claimed in claim 6 it is characterised in that：
Described buffer part is Acetabula device.
9. landing platform as claimed in claim 8 it is characterised in that：
Described Acetabula device includes support and minimum two suckers, and described sucker is installed on the bracket, the axle of described sucker
Line and the axial offset of described support.
10. landing platform as claimed in claim 9 it is characterised in that：
Described Acetabula device includes dropping-proof bracket, and described dropping-proof bracket includes snap ring and connection part, and described snap ring is stuck in described suction
The downside of the main body of disk, the work surface of the main body of described sucker is abutted with fixed plate, and described connection part is removable with described fixed plate
That unloads links together.
11. landing platforms as claimed in claim 9 it is characterised in that：
First cylinder is provided with described support, described added on be provided with the second cylinder, described first cylinder at least a portion
Embed in described second cylinder, between the diapire of the diapire of described first cylinder and described second cylinder, be lined with damping rubber.
12. landing platforms as claimed in claim 8 it is characterised in that：
The quantity of described Acetabula device is more than or equal to three, described expansion link and added connecting portion and Acetabula device and added
Connecting portion stagger.
13. landing platforms as claimed in claim 6 it is characterised in that：
The downside of described undercarriage is provided with multiple cushion pads, the connecting portion of described expansion link and described undercarriage and described cushion pad
Stagger.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2016104371298 | 2016-06-15 | ||
| CN201610437129 | 2016-06-15 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106379550A true CN106379550A (en) | 2017-02-08 |
Family
ID=57937132
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610882801.4A Withdrawn CN106379550A (en) | 2016-06-15 | 2016-10-07 | Take-off and landing platform for aircraft |
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| CN106945817A (en) * | 2017-05-02 | 2017-07-14 | 珠海市双捷科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN106970649A (en) * | 2017-04-25 | 2017-07-21 | 华南农业大学 | A kind of unmanned plane wireless charging automatic control platform and control method |
| CN107240328A (en) * | 2017-06-27 | 2017-10-10 | 珠海磐磊智能科技有限公司 | Three-degree-of-freedom motion platform, control moment gyroscope and aircraft landing platform |
| CN107323680A (en) * | 2017-07-06 | 2017-11-07 | 上海复亚通信科技有限公司 | Elastomer interviews recycle bin |
| CN107416225A (en) * | 2017-08-07 | 2017-12-01 | 洛阳理工学院 | A kind of vehicle-mounted landing platform of aircraft |
| CN107943063A (en) * | 2017-11-15 | 2018-04-20 | 广东容祺智能科技有限公司 | A kind of unmanned plane landing is from steady platform and its method of work |
| CN110171546A (en) * | 2019-06-28 | 2019-08-27 | 上海大学 | A kind of unmanned plane recycling charging unit based on parallel institution |
| CN110239685A (en) * | 2019-07-09 | 2019-09-17 | 上海大学 | It is a kind of for unmanned boat platform based on parallel four-bar linkage from steady multiple no-manned plane landing-gear |
| CN110816865A (en) * | 2019-10-21 | 2020-02-21 | 燕山大学 | Compensation type four-degree-of-freedom ship-based take-off and landing platform |
| CN110844053A (en) * | 2019-10-10 | 2020-02-28 | 中国直升机设计研究所 | Unmanned helicopter ship surface take-off and landing auxiliary system and control method |
| CN110844099A (en) * | 2019-10-21 | 2020-02-28 | 燕山大学 | Carrier-based stable platform with liftable and separable table top |
| CN111007866A (en) * | 2019-12-26 | 2020-04-14 | 桂林航天工业学院 | Marine unmanned aerial vehicle take-off and landing platform and working method thereof |
| CN111284720A (en) * | 2018-12-10 | 2020-06-16 | 邯郸市复兴区宏昌科技有限公司 | Auxiliary take-off device with pneumatic control system for airplane |
| 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 |
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| CN106970649A (en) * | 2017-04-25 | 2017-07-21 | 华南农业大学 | A kind of unmanned plane wireless charging automatic control platform and control method |
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| CN107240328B (en) * | 2017-06-27 | 2019-11-12 | 珠海磐磊智能科技有限公司 | Three-degree-of-freedom motion platform, control moment gyroscope and aircraft landing platform |
| CN107323680A (en) * | 2017-07-06 | 2017-11-07 | 上海复亚通信科技有限公司 | Elastomer interviews recycle bin |
| CN107323680B (en) * | 2017-07-06 | 2020-11-13 | 上海复亚智能科技有限公司 | Elastic fiber surface type recovery station for unmanned aerial vehicle |
| CN107416225A (en) * | 2017-08-07 | 2017-12-01 | 洛阳理工学院 | A kind of vehicle-mounted landing platform of aircraft |
| CN107943063A (en) * | 2017-11-15 | 2018-04-20 | 广东容祺智能科技有限公司 | A kind of unmanned plane landing is from steady platform and its method of work |
| CN111284720A (en) * | 2018-12-10 | 2020-06-16 | 邯郸市复兴区宏昌科技有限公司 | Auxiliary take-off device with pneumatic control system for airplane |
| CN110171546A (en) * | 2019-06-28 | 2019-08-27 | 上海大学 | A kind of unmanned plane recycling charging unit based on parallel institution |
| CN110239685A (en) * | 2019-07-09 | 2019-09-17 | 上海大学 | It is a kind of for unmanned boat platform based on parallel four-bar linkage from steady multiple no-manned plane landing-gear |
| CN110844053A (en) * | 2019-10-10 | 2020-02-28 | 中国直升机设计研究所 | Unmanned helicopter ship surface take-off and landing auxiliary system and control method |
| CN110844099A (en) * | 2019-10-21 | 2020-02-28 | 燕山大学 | Carrier-based stable platform with liftable and separable table top |
| CN110816865B (en) * | 2019-10-21 | 2020-12-29 | 燕山大学 | Compensation type four-degree-of-freedom ship-based take-off and landing platform |
| CN110816865A (en) * | 2019-10-21 | 2020-02-21 | 燕山大学 | Compensation type four-degree-of-freedom ship-based take-off and landing platform |
| CN111007866A (en) * | 2019-12-26 | 2020-04-14 | 桂林航天工业学院 | Marine unmanned aerial vehicle take-off and landing platform and working method thereof |
| 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 |
| CN113844670A (en) * | 2021-11-09 | 2021-12-28 | 北京航空航天大学 | Disconnect-type folding oil moves duct aircraft and starts platform |
| CN113844670B (en) * | 2021-11-09 | 2023-07-14 | 北京航空航天大学 | Separated foldable oil-driven ducted aircraft starting platform |
| CN117779639A (en) * | 2024-02-23 | 2024-03-29 | 烟台市北海海洋工程技术有限公司 | Lightweight helicopter deck |
| CN117779639B (en) * | 2024-02-23 | 2024-04-30 | 烟台市北海海洋工程技术有限公司 | Lightweight helicopter deck |
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Application publication date: 20170208 |