CN207225642U - More rotor balance aircraft and flight equipment - Google Patents
More rotor balance aircraft and flight equipment Download PDFInfo
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- CN207225642U CN207225642U CN201721119530.3U CN201721119530U CN207225642U CN 207225642 U CN207225642 U CN 207225642U CN 201721119530 U CN201721119530 U CN 201721119530U CN 207225642 U CN207225642 U CN 207225642U
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Abstract
The utility model provides a kind of more rotor balance aircraft and flight equipment, is related to the technical field of aircraft.More rotor balance aircraft include rotor control unit, cabin control unit and load-bearing limiter；Rotor control unit includes controller and rotor, and the quantity of rotor is multiple, and multiple rotors are connected with controller, and controller can control the keying of multiple rotors；Cabin control unit includes cabin housing, console and seat portion, and console and seat portion are both connected in cabin shell body；First spacing ball of load-bearing limiter is connected to the inside of the second spacing ball, and one end of the second spacing ball is connected with controller, and the other end is connected with cabin housing.Aircraft is solved when running into emergency case, rotor head is bigger than fuselage angle of inclination, the technical problem of stability difference.The utility model sets load-bearing limiter between rotor control unit and cabin control unit, and load-bearing limiter timely adjusts the impact force of aircraft, makes the stability of whole aircraft good.
Description
Technical field
The technical field of aircraft is the utility model is related to, is set more particularly, to a kind of more rotor balance aircraft and flight
It is standby.
Background technology
Aircraft, is manufactured by the mankind, can fly away from ground, is controlled in space flight and by people, can be in atmosphere
Interior or extra-atmospheric flight apparatus flying object.Aircraft is broadly divided into five major classes：Aircraft, spacecraft, rocket, guided missile and system
Lead weapon；In endoatmosphere, the aircraft of flight is known as aircraft, such as balloon, aerodone, dirigible, aircraft, helicopter, they
The air force that quiet buoyancy or air relative motion by ground effect vehicle air produces, which is gone up to the air, flies；In extraatmospheric flight
Device is known as spacecraft, such as artificial earth satellite, manned spaceship, space probe, space shuttle, they are pushed away carrier rocket
The dynamic lower necessary speed of acquisition enters space, then completes track motion under graviational interaction；Rocket be using rocket engine as
The aircraft of power, can be in endoatmosphere, can also be in extra-atmospheric flight；Guided missile is equipped with the controllable fire of warhead
Arrow, is divided into the ballistic missile in extra-atmospheric flight and the surface-to-air ballistic missile, the cruise missile etc. that fly equipped with aerofoil in endoatmosphere；
Guided weapon be can be carried out according to certain rule, fly in an atmosphere, high hit rate weapon, such as Terminal munition, guidance big gun
Bullet etc..
It is above-mentioned in the prior art, people it is common mainly manned vehicle, for disaster escape, emergency relief, road
Reconnoitre and low-latitude flying.The primary structure of aircraft includes rotor and fuselage, and rotor is generally connected to the upper end of fuselage, starter motor
After motor in body, rotor wing rotation while, can drive fuselage to fly.But aircraft is when taking off, landing, flying speed
It will change, and during flying at a constant speed, often since aerial barrier needs to hide, the speed of flight will
Occur declining or raise suddenly, small relative motion just occurs in the junction between rotor and fuselage, i.e.,：Fuselage with
The flare maneuver of aircraft is tilted accordingly, and rotor head angle more inclined than fuselage is big, causes the flat of whole aircraft
Stability is poor, when driver is especially taken in fuselage, can threaten to the personal safety of driver.
Utility model content
It is existing in the prior art to solve the purpose of this utility model is to provide a kind of more rotor balance aircraft,
Use mechanical connection mode between rotor and cabin, during the flying speed suddenly change of aircraft, rotor head inclines than fuselage
Oblique angle is big, makes the stationarity of whole aircraft poor, the technical problem to threaten to the driving safety of driver.
The utility model also provides a kind of flight equipment, and to solve in the prior art, the stationarity of aircraft is poor, whole to fly
The technical problem of the driving effect difference of row equipment.
A kind of more rotor balance aircraft provided by the utility model, including rotor control unit, cabin control unit and load-bearing
Limiter；
The rotor control unit includes controller and horizontally disposed rotor, and the quantity of the rotor is multiple, Duo Gesuo
State rotor to be connected with the controller, the controller can control the keying of multiple rotors；
The cabin control unit includes cabin housing, console and seat portion, and the console and the seat portion connect
It is connected in the cabin shell body；
The load-bearing limiter includes the first spacing ball and the second spacing ball, and first spacing ball is connected to described second
The inside of spacing ball, one end of second spacing ball are connected with the controller, the other end of second spacing ball and institute
State the connection of cabin housing.
Further, second spacing ball is equipped with limiting slot, and the quantity of the limiting slot is multiple, first limit
Position ball is equipped with gag lever post, bearing is connected with the gag lever post, the quantity of the gag lever post is multiple；
The bearing and each limiting slot of each gag lever post are in mating connection, make first spacing ball spacing described second
Moved in the space that ball is limited.
Further, the rotor control unit is connected with motor support bar, and the rotor includes the horizontally disposed first rotation
The wing and horizontally disposed second rotor, first rotor are connected to the one side of the motor support bar, second rotor
The another side of the motor support bar is connected to, the motor support bar is arranged on first rotor and second rotation
Between the wing；
Control motor is connected with the motor support bar, one end of the control motor is connected with first rotor,
The other end of the control motor is connected with second rotor.
Further, one end of the motor support bar is connected with the rotor control unit, the motor support bar it is another
One end is connected with baffle；
Whether be connected with the baffle has the ultrasonic sensor of object around detection.
Further, the console is connected with gyroscope, and the seat portion is connected with cushioning supportive bar；
The cushioning supportive bar includes hydraulic stem and elastic component, and one end of the hydraulic stem is connected with the seat portion, institute
The other end for stating hydraulic stem is connected with the elastic component, and the gyroscope can adjust institute according to the pressure of the cushioning supportive bar
State the length of cushioning supportive bar.
Further, one end of the cushioning supportive bar is connected with the seat portion, the other end of the cushioning supportive bar
Movable pulley is connected with, the starter for controlling the movable pulley to open and close is connected with the movable pulley.
Further, the first magnetic block is connected with the rotor, horizontally disposed rotation is connected with the cabin housing
Wing fixed link, is connected with the second magnetic block in the rotor fixed link；
When the rotor folds, the rotor is vertically arranged, and first magnetic block and second magnetic block are engaged,
The rotor is connected with the rotor fixed link.
Further, the rotor control unit is connected with parachute and compressed gas cylinder；
The controller is connected with the gas outlet of the compressed gas cylinder, and the controller controls the compressed gas cylinder gas outlet
Keying；The gas outlet of the compressed gas cylinder is connected with the air inlet of the parachute, and the compressed gas cylinder is the parachute
Interior supply gas.
Further, the seat portion is connected with the buffer air bag of protection driver safety.
The utility model also provides a kind of flight equipment, including body and more rotors balance aircraft；
More rotor balance aircraft are connected on the body.
A kind of more rotor balance aircraft provided by the utility model, the rotor control unit are connected to the cabin control
The upper end in portion, driving force is provided for the cabin control unit, drives the cabin control unit to move；During the controller is arranged on
Between position, to be horizontally disposed multiple, multiple rotors are uniformly connected to around the controller rotor, are made described
Controller can control the keying of multiple rotors at the same time, so as to drive the cabin control unit to move；The console and
Seat portion is both connected in the cabin shell body, and the console is controlled the control unit, so as to fly to aircraft
Line direction is controlled；The load-bearing limiter is connected between the rotor control unit and the cabin control unit, when described
During the flying speed suddenly change of aircraft, the load-bearing limiter can adjust the rotor control unit and cabin control
Impact force between portion, makes the operation of whole aircraft more steady；It is spacing that first spacing ball is connected to described second
Inside ball, the upper end of second spacing ball is connected with the controller, lower end and the cabin shell of second spacing ball
Body connects, and using the connection mode of spacing ball, makes the tune of the impact force between the rotor control unit and the cabin control unit
Whole effect is more stable.
The utility model also provides a kind of flight equipment, and above-mentioned more rotor balance aircraft are installed on to the machine of flight equipment
On body, whole flight equipment stationarity during flight is good, and the safety coefficient of flight is high.
Brief description of the drawings
, below will be right in order to illustrate more clearly of the utility model embodiment or technical solution of the prior art
Embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, describe below
In attached drawing be the utility model some embodiments, for those of ordinary skill in the art, do not paying creativeness
On the premise of work, other attached drawings can also be obtained according to these attached drawings.
Fig. 1 is the structure diagram that more rotors that the utility model embodiment provides balance aircraft unfolded state；
Fig. 2 is the structure diagram that more rotors that the utility model embodiment provides balance aircraft folded state；
Fig. 3 is that more rotors that the utility model embodiment provides balance the schematic front view after aircraft folds；
Fig. 4 is that more rotors that the utility model embodiment provides balance the schematic top plan view after aircraft folds；
Fig. 5 is that more rotors that the utility model embodiment provides balance the elevational schematic view after aircraft folds；
Fig. 6 is the structure diagram for the rotor control unit that the utility model embodiment provides；
Fig. 7 is the structure diagram for the seat portion that the utility model embodiment provides；
Fig. 8 is the structure diagram for the load-bearing limiter that the utility model embodiment provides；
Fig. 9 is the inside partial structural diagram for the rotor control unit that the utility model embodiment provides.
Icon：100- rotor control units；200- cabin control units；300- load-bearing limiters；101- controllers；
102- rotors；103- motor support bars；104- controls motor；105- baffles；106- parachutes；107- compressed gas cylinders；
201- cabin housings；202- consoles；203- seat portions；204- cushioning supportive bars；205- movable pulleies；206- rotors are consolidated
Fixed pole；207- buffer air bags；The first spacing balls of 301-；The second spacing balls of 302-；303- limiting slots；304- gag lever posts.
Embodiment
The technical solution of the utility model is clearly and completely described below in conjunction with attached drawing, it is clear that described
Embodiment is the utility model part of the embodiment, instead of all the embodiments.Based on the embodiment in the utility model, sheet
Field those of ordinary skill all other embodiments obtained without making creative work, belong to this practicality
Novel protected scope.
, it is necessary to explanation in the description of the utility model, term " " center ", " on ", " under ", it is "left", "right", " perpendicular
Directly ", the orientation of the instruction such as " level ", " interior ", " outer " or position relationship are based on orientation shown in the drawings or position relationship, are only
Described for the ease of description the utility model and simplifying, rather than instruction or imply signified device or element must have it is specific
Orientation, with specific azimuth configuration and operation, therefore it is not intended that limitation to the utility model.In addition, term " the
One ", " second ", " the 3rd " are only used for description purpose, and it is not intended that instruction or hint relative importance.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in the description of the utility model
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can mechanically connect or be electrically connected；It can be directly connected, can also be indirectly connected by intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
Concrete meaning of the language in the utility model.
Fig. 1 is the structure diagram that more rotors that the utility model embodiment provides balance aircraft unfolded state；Fig. 2 is
The structure diagram for more rotors balance aircraft folded state that the utility model embodiment provides；Fig. 3 is real for the utility model
Schematic front view after more rotors balance aircraft folding of example offer is provided；Fig. 4 is more rotations that the utility model embodiment provides
Schematic top plan view after wing balance aircraft folding；Fig. 5 is that more rotors that the utility model embodiment provides balance aircraft folding
The elevational schematic view of poststack；Fig. 6 is the structure diagram for the rotor control unit that the utility model embodiment provides；Fig. 7 is this reality
The structure diagram of the seat portion provided with new embodiment；Fig. 8 is the load-bearing limiter that the utility model embodiment provides
Structure diagram；Fig. 9 is the inside partial structural diagram for the rotor control unit that the utility model embodiment provides.
As shown in Fig. 1~9, a kind of more rotor balance aircraft provided by the utility model, including rotor control unit 100,
Cabin control unit 200 and load-bearing limiter 300；
The rotor control unit 100 includes controller 101 and horizontally disposed rotor 102, and the quantity of the rotor 102 is
Multiple, multiple rotors 102 are connected with the controller 101, and the controller 101 can control multiple rotors
102 keying；
The cabin control unit 200 includes cabin housing 201, console 202 and seat portion 203,202 He of console
The seat portion 203 is both connected in the cabin housing 201；
The load-bearing limiter 300 includes the first spacing ball 301 and the second spacing ball 302, and first spacing ball 301 connects
The inside of second spacing ball 302 is connected on, one end of second spacing ball 302 is connected with the controller 101, and described
The other end of two spacing balls 302 is connected with the cabin housing 201.
As shown in Figure 1, mainboard, control mainboard are used to receive control instruction and are passed after compiling the controller 101 in order to control
Defeated to arrive motor and miscellaneous part, the normal flight for ensureing equipment controls, and control mainboard is connected with camera using electric wire, surpasses
Sonic sensor, control camera is taken pictures, keep in obscurity a series of relevant actions such as control；The rotor 102 is rectangular-shape, the rotation
The inner opposite end of the wing 102 is electrically connected with the control mainboard, the quantity of the rotor 102 be it is multiple, multiple rotors 102
Inner opposite end is electrically connected with the control mainboard, so that the control mainboard can control multiple rotors 102 to be revolved at the same time
Turn or movement of stopping rotating；In the present embodiment, the quantity of the rotor 102 is four, and four rotors 102 are uniformly connected to
In control mainboard, and four 102 perpendicular modes of rotor are set, and during actual use, the quantity of rotor 102 can be with
For other quantity, such as three, five etc., as long as rotor 102 is uniformly connected around control mainboard, make rotor control unit 100
Keep balance；Air-conditioning system is housed, for air pressure adjustment, ventilation, cabin housing 201 inside cabin on cabin housing 201
It is connected with camera；The outside of 202 position of console is equipped with the searchlight of changeable distance-light, and left side is equipped with flashing red light, right
Side is equipped with green flashing lamp；Cabin housing 201 can be designed as above opening the door or side is opened the door, and cabin housing 201 above uses
Monolithic glass or macromolecule transparent material, the visual field for open driver.201 upper end of cabin housing and the rotor control unit
100 lower part connection, is connected with console 202 and seat portion 203 in the cabin housing 201, and the console 202 can be with
Manual manipulation is carried out to whole aircraft, automatic manipulation can also be switched to, the state of flight of aircraft is divided into road surface pattern
And offline mode, 202 connecting valve of console, control lever, display screen, route planning, equipment all directions image viewing, regard
The functional hardwares such as angle switching, and the console 202 is electrically connected with the control mainboard, so that driver is in console 202
Position the operating status of control mainboard can be just controlled；The seat portion 203 is rested easy to driver, described
Seat portion 203 is seat, and seat can carry out front and rear adjusting using adjusting rod, and seat can also be connected with backrest, add and drive
The comfort level of the person's of sailing seat；The lower part of the seat portion 203 is connected with power source, and the power source can use driven by engine to send out
Motor, can also use battery；The load-bearing limiter 300 is used for aircraft to during all directions flight, ensures nacelle and ground
Face is vertical, prevents in flight, and nacelle is tilted and tilted with rotor flying direction, is added the comfort level of people, is played at the same time
The holder function of camera in nacelle；First spacing ball 301 is spherical interior ball, and second spacing ball 302 is spherical
Outer ball, interior ball and outer ball make of metal material, for example, can use steel material, aviation aluminium, titanium alloy,
Carbon fiber etc., chassis is equipped with the lower end of interior ball, and chassis is fixedly connected on the upper end of cabin housing 201 using bolt, nut,
Rotor fixed shell is externally connected in controller 101, the upper end of outer ball is equipped with connector, and the upper end of outer ball passes through company
Interface is connected with rotor fixed shell, is had certain gap between interior ball and outer ball, is allow interior ball in outer ball
Interior rotation；A through hole is respectively provided with the top and bottom of interior ball, a through hole is provided with the top of outer ball, three through holes are equal
For accommodating the cable of connection electric wire；During actual use, outer ball can also be two semi-round balls, two semi-round balls
Between be fixedly connected with bolt, form an outer ball.
Further, second spacing ball 302 is equipped with limiting slot 303, the quantity of the limiting slot 303 be it is multiple,
First spacing ball 301 is equipped with gag lever post 304, and bearing, the number of the gag lever post 304 are connected with the gag lever post 304
Measure to be multiple；
The bearing and each limiting slot 303 of each gag lever post 304 are in mating connection, make first spacing ball 301 in institute
State in the space that the second spacing ball 302 is limited and move.
As shown in figure 8, outer ball it is horizontal and vertical on respectively have a limiting slot 303, the limiting slot 303 is perforate
Groove, is connected with gag lever post 304 on the outer circumferential surface of interior ball, and the gag lever post 304 is fixed column, and fixed column passes through outer ball
Opening slot；During actual use, in order to make that more firm, the position of fixed column is connected between fixed column and opening slot
Two fixed columns can be set, at this moment, in each opening slot can accommodate two fixed columns；It is respectively connected with each fixed column
Bearing, can reduce the friction between fixed column and opening slot using bearing, avoid the loss between part；On outer ball
The effect in mating connection of fixed column on opening slot and interior ball is：Allow outer ball along front, rear, left and right, left front, right
Before, it is left back, right after eight directions rotate, prevent the lateral rotation of rotor 102；The length of opening slot can exist according to rotor 102
The gradient design of eight direction flight.The limiting slot 303 set on interior ball can solve aircraft awing laterally
The problem of rotation, i.e.,：Prevent the relative position between the position of rotor control unit 100 and cabin control unit 200 from changing, make
Load-bearing limiter 300 can ensure stationarity of the aircraft in flight, reduce the probability that aircraft is overturn, solve
In flight, fuselage is tilted existing aircraft accordingly with the flare maneuver of aircraft, rotor head is tilted than fuselage
Angle is 30 degree big, the technical problem of the having a smooth flight property difference of whole aircraft.
Further, the rotor control unit 100 is connected with motor support bar 103, and the rotor 102 includes horizontally disposed
The first rotor and horizontally disposed second rotor, first rotor be connected to the one side of the motor support bar 103, institute
The another side that the second rotor is connected to the motor support bar 103 is stated, the motor support bar 103 is arranged on described first
Between rotor and second rotor；
Control motor 104, one end and described first of the control motor 104 are connected with the motor support bar 103
Rotor connects, and the other end of the control motor 104 is connected with second rotor.
As shown in Figure 1,103 inner opposite end of motor support bar is fixedly connected by fixed pin with rotor fixed shell,
When motor support bar 103 rotates to horizontal position, the effect of fixed pin is seized motor supporting rod 103, prevents motor branch
Strut 103 rotates down, and when motor support bar 103 rotates to upright position, the effect of fixed pin is seized motor supporting rod
103, prevent motor support bar 103 to be rotated up, so as to ensure that the position that motor support bar 103 is supported is fixed；In the electricity
Shaft is also associated between machine supporting rod 103 and rotor fixed shell, for driving the rotation of the motor support bar 103；Institute
State that the structure of the first rotor and the second rotor is identical, and the first rotor is arranged on above motor support bar 103, the second rotor is set
Below motor support bar 103, control motor 104, the control motor are connected with the centre position of motor support bar 103
104 upper end connects the first rotor, and the lower end of control motor 104 connects the second rotor, can when making the startup of control motor 104
Two rotor operations are driven at the same time；The control motor 104 uses DC brushless outer rotor motor, is carried using above-mentioned power source
Rotor 102 is rotated for power, so as to produce lift, realizes the flight of whole aircraft.
Further, one end of the motor support bar 103 is connected with the rotor control unit 100, the motor support
The other end of bar 103 is connected with baffle 105；
Whether be connected with the baffle 105 has the ultrasonic sensor of object around detection.
As shown in Figure 1, the inner opposite end of the motor support bar 103 is connected with rotor control unit 100, the motor support
The lateral ends of bar 103 are connected with baffle 105, the square plate being vertically arranged for baffle 105, and baffle 105 is used as rotor 102
The guard block of lateral ends, the lateral ends for preventing rotor 102 bump to object, the lateral ends of rotor 102 are made
Into damage；Ultrasonic sensor is connected on the baffle 105, ultrasonic sensor is used to detect neighbouring barrier, is automatic
Barrier thing provides related data, after being transferred to control mainboard, then is transferred to console 202, driver is at console 202
It can be operated, avoidant disorder thing.
Further, the console 202 is connected with gyroscope, and the seat portion 203 is connected with cushioning supportive bar 204；
The cushioning supportive bar 204 includes hydraulic stem and elastic component, and one end of the hydraulic stem connects with the seat portion 203
Connect, the other end of the hydraulic stem is connected with the elastic component, and the gyroscope can be according to the pressure of the cushioning supportive bar 204
Power adjusts the length of the cushioning supportive bar 204.
In the present embodiment, the quantity of the cushioning supportive bar 204 is four, during actual use, the buffering branch
The quantity of strut 204 can also be other quantity；The hydraulic stem is connected to upper position, it is possible to achieve stretching motion, from
And the height of whole cushioning supportive bar 204 is adjusted, the elastic component is connected to lower position, and the elastic component can be
Spring, or buffer air bag, the damping during decline for aircraft；The gyroscope can use multiaxis gyro
Instrument, such as three-axis gyroscope, four axis gyroscopes, six axis gyroscopes etc., the gyroscope can be according to four cushioning supportive bars 204
Pressure condition, automatically adjust four hydraulic cylinders length, ensure the verticality of cabin, be particularly suitable between cabin and ground
Angle of inclination be less than 60 degree of inclined-plane, or with settling the hollow of the height on ground less than the length of cushioning supportive bar 204
Face.
Further, one end of the cushioning supportive bar 204 is connected with the seat portion 203, the cushioning supportive bar 204
The other end be connected with movable pulley 205, the starter for controlling the movable pulley 205 to open and close is connected with the movable pulley 205.
The upper end of the cushioning supportive bar 204 is connected with the seat portion 203, and the lower end of the cushioning supportive bar 204 connects
Movable pulley 205 is connect, the movable pulley 205 is load-bearing tire, and starter, the starter are connected on the load-bearing tire
For brushless electric machine, or stepper motor, starter controls the speed of travel of load-bearing tire, is travelled easy to aircraft on road,
So as to save the energy；When aircraft lands, load-bearing tire can provide branch as the fulcrum of aircraft lower end for aircraft
Support force, when aircraft uses road mode, load-bearing tire drives aircraft walking as rotation tire used.
Further, the first magnetic block is connected with the rotor 102, being connected with level on the cabin housing 201 sets
The rotor fixed link 206 put, is connected with the second magnetic block in the rotor fixed link 206；
When the rotor 102 folds, the rotor 102 is vertically arranged, first magnetic block and second magnetic block
It is engaged, the rotor 102 is connected with the rotor fixed link 206.
The lateral ends of the rotor 102 are connected with the first magnet piece, and the lower end of the cabin housing 201 connects four water
The flat rotor fixed link 206 set, the inner opposite end of the rotor fixed link 206 are connected with cabin housing 201, and the rotor is consolidated
The lateral ends of fixed pole 206 are connected with the second magnet piece；When the rotor 102 folds, rotor 102 is vertically arranged, and rotor is fixed
Bar 206 is horizontally disposed, the first magnet piece of 206 lateral ends of the second magnet piece and rotor fixed link of 102 lateral ends of rotor
Mutually adsorb, prevent that rotor 102 rotates after folding.
As shown in figure 9, further, the rotor control unit 100 is connected with parachute 106 and compressed gas cylinder 107；
The controller 101 is connected with the gas outlet of the compressed gas cylinder 107, and the controller 101 controls the compression
The keying of 107 gas outlet of gas cylinder；The gas outlet of the compressed gas cylinder 107 is connected with the air inlet of the parachute 106, the pressure
Contracting gas cylinder 107 is supply gas in the parachute 106.The controller 101, parachute 106 and compressed gas cylinder 107 are respectively provided with
In rotor fixed shell.
Further, the seat portion 203 is connected with the buffer air bag 207 of protection driver safety；The seat portion 203
Seat can be used, the buffer air bag 207 can use air bag, and air bag is connected to the lower position of seat.
When aircraft flight runs into emergency case more than 100 meters of high-altitudes, such as equipment runs out of steam or loses suddenly control
When processed, 106 function of a key parachute can be used, after key pressing, the air in compressed gas cylinder 107 is emitted into parachute 106,
Due to air pressure relation, the open-top protection cap above of parachute 106, while parachute 106 is impacted be subject to compressed gas, acceleration is beaten
Parachute 106 is driven, so that aircraft security drops to ground；When aircraft runs into emergency case below 25 meters of low latitude
When, the buffer air bag 207 below seat can be opened with a key, wound of the equipment landing to human body is reduced using buffer air bag 207
Evil, ensures the safe landing of people and equipment.
The utility model also provides a kind of flight equipment, including body and more rotors balance aircraft；
More rotor balance aircraft are connected on the body；Utilize load-bearing limiter, cushioning supportive bar and buffering
Air bag respectively protects the operating status of whole equipment, and the operating status of whole equipment is steady, and when use is more safe.
Finally it should be noted that：Various embodiments above is only to illustrate the technical solution of the utility model, rather than it is limited
System；Although the utility model is described in detail with reference to foregoing embodiments, those of ordinary skill in the art should
Understand：It can still modify the technical solution described in foregoing embodiments, either to which part or whole
Technical characteristic carries out equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from this practicality newly
The scope of each embodiment technical solution of type.
Claims (10)
1. a kind of more rotor balance aircraft, it is characterised in that including rotor control unit (100), cabin control unit (200) and hold
Weight limiter (300)；
The rotor control unit (100) includes controller (101) and horizontally disposed rotor (102), the number of the rotor (102)
Measure to be multiple, multiple rotors (102) are connected with the controller (101), and the controller (101) can control multiple
The keying of the rotor (102)；
The cabin control unit (200) includes cabin housing (201), console (202) and seat portion (203), the console
(202) it is both connected to the seat portion (203) in the cabin housing (201)；
The load-bearing limiter (300) includes the first spacing ball (301) and the second spacing ball (302), first spacing ball
(301) inside of second spacing ball (302), one end and the controller of second spacing ball (302) are connected to
(101) connect, the other end of second spacing ball (302) is connected with the cabin housing (201).
2. more rotor balance aircraft according to claim 1, it is characterised in that set on second spacing ball (302)
There is limiting slot (303), the quantity of the limiting slot (303) is multiple, and first spacing ball (301) is equipped with gag lever post
(304), bearing is connected with the gag lever post (304), the quantity of the gag lever post (304) is multiple；
The bearing and each limiting slot (303) of each gag lever post (304) are in mating connection, first spacing ball (301) is existed
Moved in the space that second spacing ball (302) is limited.
3. more rotor balance aircraft according to claim 1, it is characterised in that rotor control unit (100) connection
There is motor support bar (103), the rotor (102) includes horizontally disposed first rotor and horizontally disposed second rotor, institute
The one side that the first rotor is connected to the motor support bar (103) is stated, second rotor is connected to the motor support bar
(103) another side, makes the motor support bar (103) be arranged between first rotor and second rotor；
Control motor (104), one end of the control motor (104) and described the are connected with the motor support bar (103)
One rotor connects, and the other end of the control motor (104) is connected with second rotor.
4. more rotor balance aircraft according to claim 3, it is characterised in that the one of the motor support bar (103)
End is connected with the rotor control unit (100), and the other end of the motor support bar (103) is connected with baffle (105)；
Whether be connected with the baffle (105) has the ultrasonic sensor of object around detection.
5. more rotor balance aircraft according to claim 1, it is characterised in that the console (202) is connected with top
Spiral shell instrument, the seat portion (203) are connected with cushioning supportive bar (204)；
The cushioning supportive bar (204) includes hydraulic stem and elastic component, and one end of the hydraulic stem connects with the seat portion (203)
Connect, the other end of the hydraulic stem is connected with the elastic component, and the gyroscope can be according to the cushioning supportive bar (204)
Pressure adjusts the length of the cushioning supportive bar (204).
6. more rotor balance aircraft according to claim 5, it is characterised in that the one of the cushioning supportive bar (204)
End is connected with the seat portion (203), and the other end of the cushioning supportive bar (204) is connected with movable pulley (205), the slip
The starter for controlling the movable pulley (205) to open and close is connected with wheel (205).
7. more rotors balance aircraft according to claim 1, it is characterised in that the is connected with the rotor (102)
One magnetic block, is connected with horizontally disposed rotor fixed link (206), the rotor fixed link on the cabin housing (201)
(206) the second magnetic block is connected with；
When the rotor (102) folds, the rotor (102) is vertically arranged, first magnetic block and second magnetic block
It is engaged, the rotor (102) is connected with the rotor fixed link (206).
8. more rotor balance aircraft according to claim 1, it is characterised in that rotor control unit (100) connection
There are parachute (106) and compressed gas cylinder (107)；
The controller (101) is connected with the gas outlet of the compressed gas cylinder (107), and the controller (101) controls the pressure
The keying of contracting gas cylinder (107) gas outlet；The gas outlet of the compressed gas cylinder (107) connects with the air inlet of the parachute (106)
Connect, the compressed gas cylinder (107) is supply gas in the parachute (106).
9. more rotor balance aircraft according to claim 1, it is characterised in that the seat portion (203) is connected with guarantor
Protect the buffer air bag (207) of driver safety.
10. a kind of flight equipment, it is characterised in that put down including body and more rotors as claimed in any one of claims 1-9 wherein
Weigh aircraft；
More rotor balance aircraft are connected on the body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721119530.3U CN207225642U (en) | 2017-09-01 | 2017-09-01 | More rotor balance aircraft and flight equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721119530.3U CN207225642U (en) | 2017-09-01 | 2017-09-01 | More rotor balance aircraft and flight equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207225642U true CN207225642U (en) | 2018-04-13 |
Family
ID=61860313
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| CN201721119530.3U Expired - Fee Related CN207225642U (en) | 2017-09-01 | 2017-09-01 | More rotor balance aircraft and flight equipment |
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| Country | Link |
|---|---|
| CN (1) | CN207225642U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110329499A (en) * | 2019-07-29 | 2019-10-15 | 谌薏冰 | A kind of multifunctional intellectual aircraft |
-
2017
- 2017-09-01 CN CN201721119530.3U patent/CN207225642U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110329499A (en) * | 2019-07-29 | 2019-10-15 | 谌薏冰 | A kind of multifunctional intellectual aircraft |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180413 Termination date: 20200901 |