Utility model content
The purpose of this utility model is that providing a kind of more rotors of combined type is tethered at UAS, it is intended to solves existing skill
It is tethered at that unmanned plane hovering efficiency is low and wind resistance is poor, the inflexible technical problem of folding and unfolding in art.
In order to solve the above technical problems, the technical solution of the utility model is:A kind of more rotors of combined type are provided and are tethered at nothing
Man-machine system, including unmanned aerial vehicle platform and ground power supply system are tethered at, the unmanned aerial vehicle platform that is tethered at includes fuselage, located at described
Dynamical system on fuselage, the airborne equipment in the fuselage and the load below the fuselage, the power
System includes setting up and down along the fuselage and turns to two opposite main rotor systems on same axis and be distributed in institute
Four posture oar systems of fuselage surrounding are stated, four posture oar systems are in cross arranged in a crossed manner.
Alternatively, each main rotor system includes main motor and main screw, and each main motor is respectively positioned on described
In fuselage, each main screw is fixed on the motor shaft of each main motor and is located at the fuselage outer side.
Alternatively, main motor seat is provided with the fuselage, two main motors of two main rotor systems are stood by a motor
Post is fixedly connected, and the motor column is passed vertically through and is fixed on the main motor seat.
Alternatively, each posture oar system includes posture motor, posture propeller and guard ring, each posture motor
It is fixed on respectively by a motor beam on the main motor seat, each posture propeller is fixed on the electricity of each posture motor
On arbor, each guard ring is enclosed outside each posture propeller, the motor beam position for the two posture motors being oppositely arranged
It is opposite in the rotation direction for the two posture propellers on same straight line, being disposed adjacent.
Alternatively, the fuselage includes skeleton and the parcel skeleton and forms the fuselage skin in cabin, the fuselage
Covering is provided with heat emission hole.
Alternatively, the load is located at below the main rotor system, is set between the load and the main rotor system
There is switching cabin, be provided with multiple load beams on the switching cabin, each load beam passes through a fuselage support arm and the appearance respectively
State oar system connects.
Alternatively, a pull bar is provided with the fuselage, the pull bar extends downwardly from and is placed through the main rotation of lower section
The pull bar bottom is fixed in wing system, the switching cabin.
Alternatively, a load hanger is provided with below the switching cabin, the load is fixed in the load hanger.
Alternatively, undercarriage is equipped with each load beam, the load hanger is highly less than the height of the undercarriage
Degree.
Alternatively, the ground power supply system includes generator, the alternating current of generator can be converted into the straight of direct current
Stream power supply and the winch being connected with the dc source, the winch are put down by composite optical/electrical cable and the unmanned plane that is tethered at
Platform connects.
In the utility model, lifting drive is provided using two main rotor systems that are coaxially disposed and invert, hovering efficiency compared with
Height, it can for a long time hover and perform task in predetermined altitude, and this dynamical system improves the ability of inorganic spot hover, makes it not
That unmanned plane flies loss because out of control be present;And main rotor system more compact structure setting up and down, in landing not
The fuselage for conventional more rotors easily occur such as rocks at the wild effect, moreover, four posture oar systems are responsible for unmanned aerial vehicle platform behaviour
The stability of control, compared with being routinely tethered at more rotors, hoverning stability is higher, though in extreme conditions, unmanned plane machine according to
So there is stable and reliable maneuvering performance;Meanwhile load is arranged at below fuselage, effective utilization space is compact-sized, tears open
Dress is convenient.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation
Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only explaining
The utility model, it is not used to limit the utility model.
It should be noted that when element is referred to as " being fixed on " or " being arranged at " another element, it can be directly another
On one element or it may be simultaneously present centering elements.When an element is referred to as " being connected to " another element, it can be with
It is directly to another element or may be simultaneously present centering elements.
It should also be noted that, the orientation term such as left and right, upper and lower in the present embodiment, be only each other relative concept or
Using the normal operating condition of product as reference, and should not be regarded as restrictive.
Reference picture 1, Fig. 2, the more rotors of a kind of combined type that the utility model embodiment provides are tethered at UAS, including
It is tethered at unmanned aerial vehicle platform 100 and ground power supply system 200.Being tethered at unmanned aerial vehicle platform 100 includes fuselage 110, on fuselage 110
Dynamical system 120, the airborne equipment (not shown) in fuselage 110 and the load located at the lower section of fuselage 110
130.Wherein, dynamical system 120 includes setting up and down along fuselage 110 and turns to two opposite main rotor systems on same axis
System 121 and four posture oar systems 122 for being distributed in the surrounding of fuselage 110, four posture oar systems 122 are set in cross intersection
Put.
In the utility model, lifting drive, hovering efficiency are provided using two main rotor systems 121 for being coaxially disposed and inverting
It is higher, it can for a long time hover and perform task in predetermined altitude, and this dynamical system 120 improves the ability of inorganic spot hover,
Make its situation about losing of being flown in the absence of unmanned plane because out of control;And main rotor system more compact structure setting up and down, dropping
The fuselage 110 for being not easy to occur conventional more rotors when falling such as rocks at the wild effect, moreover, four posture oar systems 122 are responsible for
The stability of unmanned aerial vehicle platform manipulation, compared with being routinely tethered at more rotors, hoverning stability is higher, even in extreme condition
Under, unmanned plane machine still has stable and reliable maneuvering performance;Meanwhile load 130 is arranged at the lower section of fuselage 110, effectively profit
It is compact-sized with space, convenient disassembly.
Reference picture 3, in the present embodiment, fuselage 110 includes skeleton (not shown) and wrapping frame and forms cabin
Fuselage skin 111.Skeleton encloses the fuselage 110 to be formed with fuselage skin 111 and is cylindrical in shape structure, and tubular structure is broad in the middle,
Upper and lower ends are small.The two ends of fuselage 110 have opening, for installing two main rotor systems 121.Airborne equipment is located at cabin
Interior, fuselage skin 111 is provided with heat emission hole 1111.Specifically, heat emission hole 1111 is located at the middle part of fuselage skin 111, and circumferentially
Uniformly divide rich, so, air-flow when can be rotated using two main rotor systems 121 is radiated to airborne equipment in cabin.
Reference picture 4 is to Fig. 6, and in the present embodiment, two groups of structures of main rotor system 121 are identical, but two groups of main rotor systems 121
Contrarotation, prevailing lift is provided to be tethered at unmanned aerial vehicle platform 100.Every group of main rotor system 121 include main motor 1211 and
Main screw 1212.One of which main rotor system 121 is at the upper end open of fuselage 110.Specifically, main motor 1211
In in fuselage 110, outside motor-shaft extending to the fuselage 110 of main motor 1211, main screw 1212 is fixed on the electricity of main motor 1211
On arbor and positioned at the outside of fuselage 110.Another group of main rotor system 121 is at the lower ending opening of fuselage 110.Specifically, should
The main motor 1211 of group main rotor system 121 also is located on the inside of lower ending opening, i.e., in fuselage 110, the electricity of main motor 1211
Arbor is extended outside fuselage 110, and main screw 1212 is fixed on the motor shaft of main motor 1211 and positioned at the outside of fuselage 110.Ginseng
According to Fig. 6, main motor seat 1213 is provided with fuselage 110, two main motors 1211 of two groups of main rotor systems 121 pass through a motor column
1214 are fixedly connected, and motor column 1214 passes vertically through and is fixed on main motor seat 1213.So, main motor seat is passed through
1213 and motor column 1214 realize two groups of main rotor systems 121 main motor 1211 fixation, certainly, motor column 1214
Effect in addition to fixed main motor 1211, be also responsible for main motor 1211 lifting certain altitude.
Reference picture 4 is to Fig. 6, and in the present embodiment, four groups of structures of posture oar system 122 are identical.Every group of posture oar system 122 wraps
Include posture motor 1221, posture propeller 1222 and guard ring 1223.Every group of posture motor 1221 passes through a motor beam respectively
1224 are fixed on the main motor seat 1213 in fuselage 110.Specifically, fuselage 110 is provided with four mounting holes 1112, Mei Ge electricity
Machine beam 1224 is horizontally disposed, and one end of motor beam 1224 is stretched into fuselage 110 by mounting hole 1112 and is fixed on main motor seat
On 1213, posture motor 1221 is fixed on the other end of motor beam 1224, and posture propeller 1222 is fixed on posture motor
On 1221 motor shaft, and guard ring 1223 is enclosed outside each posture propeller 1222.In the present embodiment, two postures that are oppositely arranged
The motor beam 1224 of motor 1221 is located along the same line, and the rotation direction for two posture propellers 1222 being disposed adjacent is opposite.
In the present embodiment, four groups of posture oar systems 122 for being distributed in the surrounding of fuselage 110 are responsible for the transverse direction and longitudinal direction stabilization of tethered platform
Property, so both ensure the higher hovering efficiency of coaxial double main rotors, and also improve the manipulation stability of tethered platform.
In the present embodiment, load 130 is located at the lower section of two main rotor system 121, specifically being located under fuselage 110
The lower section of that group of main rotor system 121 of port.Switching cabin 140 is additionally provided between load 130 and the main rotor system 121.Specifically
Ground, fuselage 110 is interior to be provided with a pull bar 135, and pull bar 135 extends downwardly from and is placed through the main rotor system 121 of lower section, cabin of transferring
140 are fixed on the bottom of pull bar 135.Switching is provided with multiple load beams 131 on cabin 140, and each load beam 131 passes through a fuselage respectively
Support arm 134 is connected with each posture oar system 122.Specifically, load beam 131 omits slant setting, and its higher one end with putting vertically
The bottom of fuselage support arm 134 connection put, relatively low one end is connected with switching cabin 140, and the top of fuselage support arm 134 is fixedly connected on
In motor beam 1224.Undercarriage 132 is equipped with each load beam 131.The lower section of switching cabin 140 is provided with a load hanger 133, load
130 are fixed in load hanger 133.The height of load hanger 133 is less than the height of undercarriage 132, so, ensures that unmanned plane utilizes
When undercarriage 132 drops to the state of ground, load 130 is not contacted to earth.
Referring again to Fig. 1, Fig. 2, ground power supply system 200 includes generator 210, can turn the alternating current of generator 210
The winch 230 for being changed to the dc source 220 of direct current and being connected with dc source 220, winch 230 pass through composite optical/electrical cable
240 are connected with being tethered at unmanned aerial vehicle platform 100.In the present embodiment, the operation principle that more rotors are tethered at UAS is:Ground
Generator 210 in electric power system 200 is responsible for unmanned plane power supply is tethered at, and generator 210 exports the exchange that rated power needs
Electricity, the direct current for becoming high pressure is converted through dc source 220, high voltage direct current is by the composite optical/electrical cable 240 on winch 230
It is conveyed to and is tethered at unmanned aerial vehicle platform 100, and be tethered at unmanned aerial vehicle platform 100 and be responsible for hanging load 130, and hovers over for a long time predetermined
Highly, the manipulation of unmanned aerial vehicle platform 100 and the data communication of load 130 etc. are tethered at ground is then transferred to by optical fiber.In nothing
During man-machine long-time hovering, four posture oar systems 122 are responsible for the transverse direction and longitudinal direction stability of tethered platform, so as to ensure
The hovering efficiency of unmanned plane.
Preferred embodiment of the present utility model is these are only, it is all in this practicality not to limit the utility model
All any modification, equivalent and improvement made within new spirit and principle etc., should be included in guarantor of the present utility model
Within the scope of shield.