CN206318029U - The landing platform of aircraft - Google Patents
The landing platform of aircraft Download PDFInfo
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- CN206318029U CN206318029U CN201621108761.XU CN201621108761U CN206318029U CN 206318029 U CN206318029 U CN 206318029U CN 201621108761 U CN201621108761 U CN 201621108761U CN 206318029 U CN206318029 U CN 206318029U
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- landing platform
- restocking
- fixed plate
- undercarriage
- aircraft
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Abstract
The utility model provides a kind of landing platform of aircraft.Landing platform includes fixed plate and pose adjustment seat.Fixed plate as aircraft landing platform, before take-off for fixing aircraft；Pose adjustment seat is arranged on the downside of fixed plate, and the spatial attitude for stablizing fixed plate, pose adjustment seat at least possesses two frees degree verted around X-axis and Y-axis.Multi-axis aircraft is fixed in fixed plate before take-off, by the attitude of pose adjustment seat dynamic stability aircraft, can prevent that aircraft from rocking back and forth, good takeoff condition is provided to take off.Stable fixed plate can provide good landing environment for Multi-axis aircraft.
Description
Technical field
The utility model is related to the landing platform of aircraft, more particularly to Multi-axis aircraft landing platform.
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, the control device includes the components such as steering wheel, pitch, connecting rod.
Multi-axis aircraft and electric helicopter should not all take off under strong wind atmosphere.At present, four-axle aircraft can be in strong breeze
Fly below；Six axle aircraft can reluctantly fly 6 into fresh gale.The wind speed of strong breeze is between 8 to 10.7 metre per second (m/s)s, 6 grades
The wind speed of wind is between 10.8 to 13.8 metre per second (m/s)s, and the wind speed of fresh gale is between 13.9 to 17.1 metre per second (m/s)s.But multiaxis flies
Device is needed wind-force is weaker and local landing of steady air current, and landing is extremely hazardous under Limit of Wind Speed and sinuous flow.Helicopter is 7
It is difficult to take off under level wind-force.When typically taking off or land, 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 applications
It is to solve the problems, such as how unmanned plane safely takes off and landing jolting on indefinite unmanned boat deck, the unmanned plane is multiaxis
Aircraft.Under good weather environment, the electromagnetic force between revocation unmanned boat and unmanned plane lets unmanned plane fly away.Obviously, unmanned plane
Take off dependent on weather conditions, can not still be taken off under strong wind atmosphere.The system can only be solved under good weather environment
Unmanned plane take off problem, in the environment of wind and waves, the landing problem of unmanned plane is not solved still.In addition, being fixed on ship
On for plate electromagnet and the solenoid actuated module that is attached thereto, it is magnetic conductive board to be fixed on unmanned plane foot stool, due to
The foot stool span of unmanned plane is larger, it is necessary to larger bearing-surface, therefore the area of plate electromagnet can be very big, not only weight compared with
Greatly, it is more expensive to manufacture, and the more electric energy of needs could maintain the fixation of unmanned plane, poor practicability.Landing platform is arranged on land
When on mobile devices, the fluctuating on road surface causes mobile devices and landing platform to jolt indefinite, is unfavorable for the landing of Multi-axis aircraft.
Existing Multi-axis aircraft only adjusts flight attitude by changing variable rotor speed substantially, and translation flight needs dumper
Body, thus the front face area of fuselage is added, cause the increase of flight resistance, make the movement response of Multi-axis aircraft slow, it is motor-driven
Property it is poor, frequently acceleration and deceleration make kinetic energy rejection big to motor, and motor thermal losses is big, and efficiency is low.Under action of high-speed airflow, it is difficult to pacify
Full landing.Before being taken 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 can not realize the mobile takeoff and landing of safety and stability.
The content of the invention
The utility model aims 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, landing platform of the present utility model includes fixed plate and pose adjustment seat.Fixed plate
As the platform of aircraft landing, before take-off for fixing aircraft；Pose adjustment seat is arranged on the downside of fixed plate, is used for
The spatial attitude of stable fixed plate, pose adjustment seat at least possesses two frees degree verted around X-axis and Y-axis.
From above scheme, Multi-axis aircraft is fixed in fixed plate before take-off, steady by pose adjustment seat dynamic
Determine the attitude of aircraft, can prevent that aircraft from rocking back and forth, good takeoff condition is provided to take off.It is initial when fixed plate
When being positioned against high velocity air inclination, the air-flow for rushing at Multi-axis aircraft is absorbed using the rotor of Multi-axis aircraft, multiaxis is reduced
Windage in front of aircraft, is conducive to improving the security and stability taken off.The fixed plate of horizontal attitude can be dynamically kept simultaneously,
Be conducive to providing stable landing environment for Multi-axis aircraft, when reduction will land, 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 clashes with landing platform, cause aircraft quilt
Upspring and crash.
Further, the base of pose adjustment seat is the base of Three Degree Of Freedom, and base includes restocking, undercarriage and connection restocking
And three expansion links of undercarriage, connected between the upper end of expansion link and restocking 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 vert with restocking around X and Y-axis, and be moved up and down along Z axis, only need three
Expansion link can ensure that attitude fixed plate is tilted and lifted in any direction, the simpler reliability of structure, it is easy to control, cost
It is low.
Further, the base of pose adjustment seat is the base of two degrees of freedom, and base includes restocking, undercarriage and connection restocking
And three expansion links of undercarriage, connected between the upper end of expansion link and restocking by universal joint or ball pivot, the lower end of expansion link with
Undercarriage is hinged, and its hinge is horizontally disposed, is provided with the downside of pillar, the upper end of pillar and restocking and is passed through on the upside of the middle part of undercarriage
Universal joint or ball pivot connection.Effectively improve the bearing capacity of base.
Further, fixed plate is served as in restocking.Fixed plate need not be separately provided, the weight of landing platform is advantageously reduced.
Further, pose adjustment seat for the Stewart formulas of six degree of freedom base, the base include restocking,
Undercarriage and the six roots of sensation expansion link for connecting the restocking and the undercarriage.The understructure intensity of the Stewart formulas of six degree of freedom is high,
High precision, fast response time can effectively stablize the attitude of fixed plate with full angle.
Further, buffer part, between fixed plate and the restocking.Can not only 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, simple in construction to be 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 extension 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 working face 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, it is provided with support in the first cylinder, restocking and is provided with the second cylinder, the first cylinder is at least partially
In embedded second cylinder.Damping rubber is lined between the bottom wall of the bottom wall of first cylinder and the second cylinder.Extension vibration is conducive to pass
Guiding path, slackens vibration transmission.
Further, the quantity of Acetabula device is more than or equal to three, the connecting portion and Acetabula device of expansion link and restocking
Stagger with the connecting portion of restocking.Be conducive to extension conduct vibrations path, slacken vibration transmission.
Further, the connecting portion and cushion pad mistake of multiple cushion pads, expansion link and undercarriage are provided with the downside of undercarriage
Open.Be conducive to extension conduct vibrations path, slacken vibration transmission.
Brief description of the drawings
Fig. 1 is the top view of the omission shell of Multi-axis aircraft embodiment one of the present utility model；
Fig. 2 is the partial schematic diagram of the second tilting drive of Multi-axis aircraft embodiment one of the present utility model；
Fig. 3 is the partial schematic diagram of the tilting drive of Multi-axis aircraft embodiment one first of the present utility model；
Fig. 4 is the side view of the utility model Multi-axis aircraft embodiment one；
Fig. 5 is the partial schematic diagram of the first tilting drive of the utility model Multi-axis aircraft embodiment two；
Fig. 6 is the partial schematic diagram of the second tilting drive of the utility model Multi-axis aircraft embodiment two；
Fig. 7 is the structural representation of the utility model landing platform embodiment one；
Fig. 8 is the installment state zoomed-in view of the mechanical lock mechanism of the utility model landing platform embodiment one；
Fig. 9 is Fig. 8 A-A sectional views；
Figure 10 is the stereogram of the utility model landing platform embodiment two；
Figure 11 is the stereogram of the Acetabula device of the utility model landing platform embodiment two；
Figure 12 is the diagrammatic cross-section of the installment state of the Acetabula device of the utility model landing platform embodiment two；
Figure 13 is the stereogram of the utility model landing platform embodiment three；
Figure 14 is the stereogram of the utility model landing platform example IV；
Original state schematic diagram when Figure 15 is on landing platform of the Multi-axis aircraft in movement；
Figure 16 is view when Multi-axis aircraft is in standby for takeoff when on mobile landing platform.
Embodiment
The reference frame of the free degree described in the utility model is rectangular coordinate system in space, X-axis and Y-axis position therein
In on horizontal plane, Z axis is 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.Fuselage is main
Function is to load power supply, fly the equipment such as control device, while Multi-axis aircraft is connected to integral effect, including frame 1010,
Fly control pallet 103, battery mounting 102, the first horn 1020 and the second horn 1030.Frame 1010 includes two supervisors 1011
With 1012, connectors 1013 and be covered in the casing 130 on the outside of being responsible for that connection two is responsible for（Referring to Fig. 3）.Casing can have
Effect protection inner member.Flying control pallet 103 is used to load winged control plate（Not shown in figure）, frame is fixed on by pipe clamp 1015
On 1010.Battery mounting 102 is used to load battery, and the both sides of the width of frame 1010 are symmetrically fixed on by screw,
The fixture 1021,1022 of both sides passes through limited post 1023 and the bolt through limited post 1023（It is not shown）Progress is installed solid
Fixed, simple in construction, intensity is high and lightweight.First horn 1020 includes the first duct power unit 104, the second duct power list
Member 105, the chuck 1022 of fix bar 1021 and first, the first duct power unit 104 and the second duct power unit 105 are by fixing
Bar is supported, and front and rear under the driving of the first tilting drive 107 can be verted.
As shown in Fig. 2 the second horn 1030 includes the 3rd duct power unit 106, the second chuck 116, the and of installing plate 125
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 used as this reality
Apply the power set of example.
With reference to Fig. 2-3, the 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 the first end of fixed mount 112 passes through bearing
110 the first horns 1020 of rotatable supporting, second end relative with first end of fixed mount 112 passes through screw and frame 1010
Connection, the 3rd end of fixed mount 112 is that downside is connected by the top connection 126 of screw and foot stool, 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 for being fixed on the first horn 1020
113 connections, so as to drive the first horn 1020 to vert, while driving the first duct power unit 104 and the second duct power list
Member 105 is verted.As preferred, the structure of the double push rods of the selection of push rod 111, it is more uniformly stressed, structural strength is higher, work is more
It is 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 by push rod 122 with rocking arm 123, rocking arm 123 respectively with
Duct bucket, the second chuck 116 are connected, so that the second duct power unit 105 verts.It is used as preferred, the selection pair of push rod 122
The structure of push rod, is more uniformly stressed, and structural strength is higher, works more steady.
First tilting drive 107 drives the first duct power unit 104 and the second duct power unit 105 towards leaning forward
Turn that front air-flow can be absorbed by the rotor of two power units, weaken the windage flowed towards head, it is to avoid high velocity air pair
The windage that Multi-axis aircraft is produced throws Multi-axis aircraft.Further second tilting drive 108 drives the 3rd duct
Power unit 106 tilts forward the windage that further can weaken 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, preceding steering wheel
119th, pivot block 117, rotating shaft 115, preceding steering wheel 119 are fixed by screws on fixed block 128, and fixed block logical 128 is crossed screw and consolidated
It is scheduled on pipe clamp 1013, the preceding output steering wheel of steering wheel 119 arm 120 is connected by push rod 118 with pivot block 117, 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
Preceding or Level Promoting component backward.3rd duct power unit 106 verts equally can quickly produce forward forward or backward
Or Level Promoting component backward, the quick anterior-posterior translation for realizing flight.3rd duct power unit 106 can also be around fuselage
Length direction where axis to the left or Right deviation turns, leftward or rightward horizontal thrust is quickly produced in tail, it is 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 need not tilt fuselage, front face area is greatly reduced, horizontal windage is smaller.
As shown in figure 4, the main function of take-off and landing device 140 of Multi-axis aircraft is carried when being Multi-axis aircraft take-off and landing
For supporting role, it includes undercarriage 141 and fixture 142.Undercarriage 141 is used to support Multi-axis aircraft, solid by screw
It is scheduled in frame 1010, undercarriage 141 is provided with T fonts bracing piece 143, simple in construction, lightweight, and intensity is high.Fixture 142
The downside of undercarriage 141 is fixed on, Multi-axis aircraft is fixed on landing platform 150 before mobile take off by fixture 142, will not
Because the influence of high velocity air is dropped from landing platform.When landing platform is moved, tilting drive driving power device is towards landing
The direction of platform movement is verted to predetermined angular, and fixture 142 reaches in the rotor rotating speed of power unit, the thrust of generation or throttle
After predetermined value, fixation of the Multi-axis aircraft to landing platform is released.It is preferred that, the bottom of fixture 142 is provided with electromagnet, landing platform
The side of 150 supporting Multi-axis aircrafts is iron plate.The rotation axis of the rotor of power set verts towards the direction that landing platform is moved
Predetermined angular between 15 degree to 45 degree.Landing platform translational speed is faster, and predetermined tilt angle is bigger, it is preferred that predetermined
The speed that is moved to landing platform of tilt angle square be directly proportional.
Multi-axis aircraft embodiment two
The difference of the present embodiment and embodiment one is the first tilting drive and the second tilting drive.
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, the first end of fixed mount 201 support the first horn 2020 by the way that bearing 206 is rotatable,
Second end relative with first end of fixed mount 201 is connected by screw with frame 2010, and be located at downside the of fixed mount 201
Three ends are connected by screw with foot stool, and steering wheel 202 is connected by locating dowel with fixed mount 201, and steering wheel output synchronous pulley 203 leads to
Cross Timing Belt 204 and be connected with being fixed on the synchronous pulley 205 of 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.It is preferred that, the first horn 2020 has independent
The left horn and right arm verted, 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, and left horn and right machine are driven 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 is adjustable by screw
Be arranged on fixed mount on the inside of, serve adjust tightness of synchronous belt.Timing Belt overload can skid, 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 couples and is rotatably mounted on chuck 216 with duct bucket.Afterwards steering wheel 231 according to
It is secondary to drive the 3rd duct power unit 213 to incline by rear steering wheel output synchronous pulley 232, Timing Belt 233 and synchronous pulley 234
Turn.Device for regulating tightness of synchronous belt 235 is adjustably mounted at the inner side of chuck 216 by screw, plays regulation tightness of synchronous belt
Effect.Timing Belt overload can skid, and play a part of to protect 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
The base 910 of the Stewart formulas of individual six degree of freedom.It is provided between fixed plate 810 and pose adjustment seat 900 as buffer part
The cushion rubber bumper 920 of ring-type.Base 910 includes as the lower ring stand 911 of undercarriage, six roots of sensation expansion link 912 and is used as the upper of restocking
Ring stand 913.Upper ring stand 913 and fixed plate 810 are connected by bolt 914, and bolt is buffered through the via in cushion rubber bumper 920
Rubber cushion 920 is padded between upper ring stand 913 and fixed plate 810.It is preferred that, six roots of sensation expansion link 912 is electric cylinders or hydraulic cylinder.Obviously,
Buffer part is not limited to cushion rubber bumper 920, and the silica gel shock-absorption ball parallel connection that via can also be provided with by multiple middle parts is constituted.Fixed plate
810 downsides are provided with three mechanical lock mechanisms 410.It is preferred that, annular is provided between the head of bolt 914 and upper ring stand
Rubber sheet gasket, 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 electromagnet 450.Electromagnet includes the line of iron core 451
Circle 452 and shell 453.Screwed hole 454 is provided with the downside of iron core, upside is provided with mounting hole 455.Electromagnet 450 passes through mounting hole
455 and screw be arranged on set casing 440 in.Electromagnet 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
Screw is crossed installed in the downside of fixed plate 810, motor cabinet 415 is fixed by screws in the downside of mounting seat 416.The output of motor 411
Axle is that D type holes are provided with D profile shafts, sliding sleeve 413, and D type holes are enclosed within D profile shafts.The upper end of sliding sleeve 413 leads to the lower end of screw rod 414
Cross flange and mode connects for screw.The output shaft of motor 411 can to while 413 transmitting torque of sliding sleeve in the direction of its rotation axis
Upper and sliding sleeve 413 is relative to be slided.When the fixture 142 of Multi-axis aircraft is not placed in fixed plate 810, sliding sleeve 413 and screw rod
414 pass upwards under the promotion of spring 412 from the perforate of fixed plate 810；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 to be fixed on electromagnet 450 under the pushing of back-moving spring 412
In fixed board 810, so as to realize the mechanical caging of fixture 142.When the drive screw 414 of motor 411 is reversely rotated, screw rod 414
The elastic force of back-moving spring 412 is overcome to be screwed out from screwed hole 454, so as to realize the mechanical release of fixture 142.Obviously, electromagnet 450
Iron core 451 serve as mechanical locking portions.Screwing and outwarding winding for screw thread can effectively realize mechanical caging and unblock, and structure letter
It is single, it is compact.
Obviously, mechanical lock mechanism not limited to this, can also be retractable gripper, by the folding of gripper to solid
Determine part and carry out mechanical caging and unblock, now fixture is in itself as mechanical locking portions.Certainly, mechanical lock mechanism can also be
The pin hole coordinated with latch is provided with latch that can be transversely opened and closed, fixture, now fixture is in itself 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
There is the base 2910 of the Stewart formulas of a six degree of freedom.Conduct is provided between fixed plate 2810 and pose adjustment seat 2900
The Acetabula device 2920 of buffer part.Base 2910 is included as the lower ring stand 2911 of undercarriage, six roots of sensation expansion link 2912 and as upper
The upper ring stand 2913 of frame.It is preferred that, six roots of sensation expansion link 2912 is electric cylinders or hydraulic cylinder.The downside of fixed plate 2810 is provided with three machines
Tool locking mechanism 2410.
Three Acetabula devices 2920 are evenly arranged on ring stand 2913.The downside of Acetabula device 2920 is connected by bolt
Connect on upper 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 extension conduct vibrations path, is conducive to eliminating and vibrates.The lower downside of ring stand 2911 is set
It is equipped with the connecting portion and cushion pad 2915 of the cushion pad 2915 that multiple middle parts are provided with via, expansion link 2912 and lower ring stand 2911
Stagger, be so conducive to extension conduct vibrations path, be conducive to eliminating and vibrate.
As is illustrated by figs. 11 and 12, the upside of Acetabula device 2920 is provided with three opening up suckers 2940, and downside is set
The support 2950 including cylinder portion 2951 and cantilever 2952 is equipped with, middle part is provided with dropping-proof bracket 2960.The lower end of sucker 2940 leads to
Bolt connection is crossed on the cantilever 2952, the working face of the main body of sucker 2940 be used to adsorbing fixed plate 2810, i.e. working face with
Fixed plate 2810 is abutted.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 vibrate.Dropping-proof bracket 2960 includes snap ring
2961st, arm 2962 and the cylinder 2963 as connection part of 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 is locked through fixed plate 2810 and cylinder 2963 and by nut 2966, is not only prevented
Fixed plate 2810 is released from sucker 2940, improves security reliability, also effectively realizes Acetabula device 2920 and fixed plate
2810 be flexible coupling, effectively reduces interference of the dither to fixed plate 2810.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 and vibrate.The bottom of cylinder 2951
Damping rubber 2954 is lined between the bottom wall of wall and cylinder 2914, cylinder 2951 and cylinder 2914 pass through bolt 2955 and nut 2956
It is attached.It is preferred that, it is lined with buffering adhesive 2953 between the head of bolt 2955 and the bottom wall of cylinder 2951.Effective realize is inhaled
Being flexible coupling for 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 is that the base of pose adjustment seat is one
The base 3910 of Three Degree Of Freedom.Base 3910 includes the upper ring stand 3920 as restocking, undercarriage 3930 and the upper ring stand 3920 of connection
And the expansion link 3940 of undercarriage 3930.Upper ring stand 3920 can vert around X and Y-axis, and be moved up and down along Z axis.Expansion link 3940
Upper end and upper ring stand 3920 between pass through universal joint or ball pivot and connect；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 be, can be with as the iron plate 4920 of restocking
Directly as the fixed plate for Multi-axis aircraft landing.The upside at the middle part of undercarriage 4930 is provided with pillar 4950.Pillar 4950
Upper end is connected with the downside of iron plate 4920 by universal joint or ball pivot.The present embodiment has lacked along along Z axis compared with landing platform embodiment three
The free degree of lower movement, but bearing strength is higher.
Before Multi-axis aircraft takes off on the landing platform of high-speed mobile, if will be blown off without fixation by high velocity air,
Electromagnet as fixture is installed on undercarriage, electromagnet, which is powered, can be fixed on Multi-axis aircraft high speed landing platform
On, it is ensured that it is not blown off by high velocity air.Operation principle of the present utility model is as follows：Electromagnet on undercarriage will be many
Axle aircraft is fixed on landing platform, power set is verted to predetermined angular by tilting drive, is started power set
And increase the rotating speed of rotor, when rotor rotating speed, the pulling force produced or throttle reach predetermined value, electromagnet unlocks, multiaxis
Aircraft departs from landing platform and taken off.Power set effectively absorb the air-flow come head-on, so as to improve stability and security.
As shown in Figure 15 and Figure 16, Multi-axis aircraft 700, which has, be provided with fixture 750 on power set 710, foot stool.
Landing platform 2000 is moved along direction V1, and high velocity air rushes at Multi-axis aircraft 700 along V2 directions.
The method that the Multi-axis aircraft that the utility model is provided 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, make its rotor wing rotation axis towards flowing；
S3, the rotor of increase power set 710 rotating speed, the rotor rotating speed of power set 710, the thrust produced or throttle
Reach after predetermined value, release locking of the fixture 750 of Multi-axis aircraft 700 to landing platform 2000.
It is preferred that, pressure sensor is provided with as between the electromagnet upside of fixture 750 and each foot stool support bar,
The pressure sensor is electrically connected with the winged control device of Multi-axis aircraft 700, and each pressure sensor is detected when flying control device
Detected value difference two-by-two within a predetermined range when, electromagnet power-off releases locking to landing platform 2000, and release multiaxis flies
Row device 700.Now, the carbon fiber plate that the top of landing platform 2000 covers ferrous material by iron plate or top is made, 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, electromagnet, which is powered, adsorbs iron plate, and mechanical lock mechanism 2820 is released to many
Axle aircraft 700 is locked；Electromagnet is powered off simultaneously, discharges Multi-axis aircraft 700.
Verted by way of the horn that verts power set 710 when, the power set 710 verted positioned at front side or rear side are equal
The absorbable air-flow for rushing at Multi-axis aircraft 700, cuts down windage, realizes safe take-off.It is preferred that, the power set for front side of verting
The security reliability taken off can be improved, while the power set verted positioned at front side and rear side can have been improved further
Winged security reliability.
Pose adjustment 2900 controller of seat and the winged control device of Multi-axis aircraft are led to by way of wireless telecommunications
News, fly to be provided with control device includes the inertial navigation list of three axis accelerometer and three-axis gyroscope for detection machine figure state
Member.Fly control device and generate control signal according to fuselage attitude detection data, send to the controller of pose adjustment seat 2900, attitude
The dynamic of adjustment seat 2900 adjusts length of telescopic bar to stablize the fuselage attitude of Multi-axis aircraft.The utility model not limited to this,
Fuselage attitude parameter can be obtained from winged control device by the controller of pose adjustment seat 2900, calculate the control ginseng of expansion link
Number, adjusts length of telescopic bar, so that stable fuselage attitude.As one kind improvement, the downside of landing platform 2800 is provided with gyroscope,
The controller of pose adjustment seat 2900 reads the gyroscope signal on landing platform 2000, calculates the control parameter of expansion link, adjusts
Whole length of telescopic bar, so that stable fuselage attitude.What so pose adjustment seat 2900 can be earlier compensates to inclination, realizes
Rapid effective pose adjustment.Obviously, pose adjustment seat 2900 is by stablizing the spatial attitude of fixed plate 2810, you can stable many
The spatial attitude of axle aircraft.When expansion link is electric cylinders, the circuit module of controller is electrically connected with electric cylinders.When expansion link is liquid
During cylinder pressure, controller also includes pumping plant, and the circuit part of controller is electrically connected with the magnetic valve of pumping plant, and pumping plant passes through oil pipe and liquid
Cylinder pressure is connected.
The initial position of the fixed plate 2810 of pose adjustment seat 2900 is in horizontality.Before taking off, pose adjustment seat
2900 can greatly correct the locus of adjustment fixed plate 2810, eliminate significantly low-frequency oscillation, are used as buffering
The Acetabula device 2920 and cushion rubber bumper 2915 in portion can effectively eliminate the dither of small amplitude, so as to effectively ensure fuselage
Attitude stabilization, greatly improves the mobile security reliability taken off.Low-frequency vibration can be caused by overall rise and fall of road surface or wave；It is high
Frequency vibration can be caused by itself vibration or wave beating ship of road surface thin portion roughness, the vehicle of carrying landing platform or ship.
The type that can not be verted for power set 710, can be realized by the initial position of adjustment fixing plate 2810
Power set 710 come to inclination towards air-flow.
Power unit of the present utility model possesses rotor, it is preferred that be provided with duct or guard circle on the outside of rotor.Rotor is not
It is limited to be driven by motor, can also be driven by oil machine.
Multi-axis aircraft of the present utility model is not limited to three axle aircraft or four-axle aircraft, six axle aircraft
Deng Multi-axis aircraft.For example, the 3rd duct power unit 213 in embodiment two is replaced by two duct power units arranged side by side
Generation, you can become four-axle aircraft.
Landing platform of the present utility model can be with the vehicle or ship of high-speed mobile, by setting the initial of landing platform
Position is also possible that the air-flow that the rotor of Multi-axis aircraft is tilted, and allows rotor suction to come head-on, and reduces windage, and raising is taken off
Security and stability.
Embodiment described above is simply preferred embodiment of the present utility model, not limits reality of the present utility model with this
Scope is applied, all equivalence changes made according to the shape of the utility model, construction and principle all should be covered by guarantor of the present utility model
In the range of shield.
Claims (13)
1. a kind of landing platform of aircraft, it is characterised in that：Including,
Fixed plate, as the platform of aircraft landing, before take-off for fixing aircraft；
Pose adjustment seat, installed in the downside of the fixed plate, the spatial attitude for stablizing the fixed plate；
The pose adjustment seat at least possesses two frees degree verted 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 the base includes restocking, undercarriage and connects the restocking and institute
Three expansion links of undercarriage are stated, are connected between the upper end of the expansion link and the restocking by universal joint or ball pivot；It is described to stretch
The lower end of contracting bar is hinged with the 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 the base of two degrees of freedom, and the base includes restocking, undercarriage and connects the restocking and institute
Three expansion links of undercarriage are stated, are connected between the upper end of the expansion link and the restocking by universal joint or ball pivot, it is described to stretch
The lower end of contracting bar is hinged with the undercarriage, and its hinge is horizontally disposed, and pillar, the branch are provided with the upside of the middle part of the undercarriage
The upper end of post is connected with the downside of the restocking by universal joint or ball pivot.
4. landing platform as claimed in claim 2 or claim 3, it is characterised in that：
The fixed plate is served as in the restocking.
5. landing platform as claimed in claim 1, it is characterised in that：
The pose adjustment seat is the base of the Stewart formulas of six degree of freedom, and it is described that the base includes restocking, undercarriage and connection
Restocking and the six roots of sensation expansion link of the undercarriage.
6. the landing platform as described in claim 2,3 or 5 are any, it is characterised in that：
Buffer part, between the fixed plate and the restocking.
7. landing platform as claimed in claim 6, it is characterised in that：
The buffer part is the cushion rubber bumper of ring-type.
8. landing platform as claimed in claim 6, it is characterised in that：
The buffer part is Acetabula device.
9. landing platform as claimed in claim 8, it is characterised in that：
The Acetabula device includes support and minimum two suckers, and the sucker is installed on the bracket, the axle of the sucker
The axial offset of line and the support.
10. landing platform as claimed in claim 9, it is characterised in that：
The Acetabula device includes dropping-proof bracket, and the dropping-proof bracket includes snap ring and connection part, and the snap ring is stuck in the suction
The downside of the main body of disk, the working face of the main body of the sucker is abutted with fixed plate, and the connection part and the fixed plate are removable
That unloads links together.
11. landing platform as claimed in claim 9, it is characterised in that：
It is provided with the support in the first cylinder, the restocking and is provided with the second cylinder, first cylinder is at least partially
In embedded second cylinder, damping rubber is lined between the bottom wall of the bottom wall of first cylinder and second cylinder.
12. landing platform as claimed in claim 8, it is characterised in that：
The quantity of the Acetabula device is more than or equal to three, the connecting portion and Acetabula device and restocking of the expansion link and restocking
Connecting portion stagger.
13. landing platform as claimed in claim 6, it is characterised in that：
The connecting portion and the cushion pad of multiple cushion pads, the expansion link and the undercarriage are provided with the downside of the undercarriage
Stagger.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620590710 | 2016-06-15 | ||
| CN2016205907109 | 2016-06-15 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206318029U true CN206318029U (en) | 2017-07-11 |
Family
ID=59262341
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621108761.XU Active CN206318029U (en) | 2016-06-15 | 2016-10-07 | The landing platform of aircraft |
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| CN (1) | CN206318029U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106379550A (en) * | 2016-06-15 | 2017-02-08 | 珠海市磐石电子科技有限公司 | Take-off and landing platform for aircraft |
| CN110077595A (en) * | 2019-04-28 | 2019-08-02 | 北京理工大学 | Unmanned automated spacecraft lands and recovery system automatically under the conditions of complicated dynamic is jolted |
| CN113928560A (en) * | 2021-10-21 | 2022-01-14 | 中煤航测遥感集团有限公司 | Unmanned aerial vehicle platform for aerial photogrammetry and photography method |
-
2016
- 2016-10-07 CN CN201621108761.XU patent/CN206318029U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106379550A (en) * | 2016-06-15 | 2017-02-08 | 珠海市磐石电子科技有限公司 | Take-off and landing platform for aircraft |
| CN110077595A (en) * | 2019-04-28 | 2019-08-02 | 北京理工大学 | Unmanned automated spacecraft lands and recovery system automatically under the conditions of complicated dynamic is jolted |
| CN113928560A (en) * | 2021-10-21 | 2022-01-14 | 中煤航测遥感集团有限公司 | Unmanned aerial vehicle platform for aerial photogrammetry and photography method |
| CN113928560B (en) * | 2021-10-21 | 2024-02-27 | 中煤航测遥感集团有限公司 | Unmanned aerial vehicle platform for aerial photogrammetry and shooting method |
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