CN104691758A - Rotor wing vertical lift electric unmanned machine of linkage fixed wing - Google Patents
Rotor wing vertical lift electric unmanned machine of linkage fixed wing Download PDFInfo
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- CN104691758A CN104691758A CN201510091079.8A CN201510091079A CN104691758A CN 104691758 A CN104691758 A CN 104691758A CN 201510091079 A CN201510091079 A CN 201510091079A CN 104691758 A CN104691758 A CN 104691758A
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- 239000002775 capsule Substances 0.000 claims description 11
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 9
- 229910052799 carbon Inorganic materials 0.000 claims description 9
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- 238000004806 packaging method and process Methods 0.000 claims description 9
- 239000000203 mixture Substances 0.000 claims description 8
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 6
- 229910052744 lithium Inorganic materials 0.000 claims description 6
- 230000009467 reduction Effects 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 4
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- 239000003638 chemical reducing agent Substances 0.000 claims description 3
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- 238000005265 energy consumption Methods 0.000 abstract description 7
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- 230000003042 antagnostic effect Effects 0.000 description 1
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- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention discloses a rotor wing vertical lift electric unmanned machine of a linkage fixed wing. A machine body is internally provided with a storage battery bin, a control bin and a freight bin, wherein the top end of the machine body is provided with a movable connecting frame; the upper end of the connecting frame is provided with a bogie; a bearing inner circle in left and right rotation direction in the bogie is provided with a fixed wing steering shaft; the fixed wing steering shaft and a rotor wing steering shaft are both hollow shafts and are perpendicular to each other to form a T-shaped steering shaft; the upper end of the rotor wing steering shaft is provided with a linkage rotor wing; the T-shaped steering shaft is provided with a linkage fixed wing; the linkage fixed wing is vertical to the linkage rotor wing; the rear upper end of the machine body is provided with a perpendicular tail wing, and the rear lower end of the machine body is provided with a horizontal tail wing; the lower end of the machine body is provided with a power supply socket and a power supply plug; the power supply plug is connected with the head end of a double-hinge electric cable; the tail end of the double-hinge electric cable is provided with a wire take-off device. The rotor wing vertical lift electric unmanned machine not only is simple in structure, but also can send the electric unmanned machine to a high altitude by utilizing a power supply on the ground, and then fly with low energy consumption depending on the power supply, or can glide to the target place without energy consumption, not only can glide to land, but also can land perpendicularly when approaching the terminal.
Description
Technical field
The present invention relates to a kind of aircraft, is specifically a kind of interlock fixed-wing rotor electric vertical lifting unmanned plane.
Background technology
The unmanned plane of current whole world various uses is developing rapidly, and China is also unwilling to be lag behind, and no matter unmanned plane is military or civilian, and all playing great role, therefore the unmanned plane of superior performance, the market demand is very large.As everyone knows, fixed wing aircraft speed is fast, energy consumption is low, manoevreability is good, need runway, rise and fall restricted, helicopter is then contrary with it, especially helicopter is maximum at vertical uplift discrete consuming energy, therefore the fixed-wing that both advantages all possess goes straight up to unmanned plane also in constantly research and development, be " 201310543988.1 " title at number of patent application be in the application for a patent for invention of " a kind of vertical takeoff and landing model plane unmanned plane ", the left-and-right spiral oar that can turn to is installed in its fixed-wing front end, tail is equipped with fan-type duct, the shortcoming of this version is: this unmanned plane can not do large because screw propeller is subject to fixed-wing restriction, so lift is little, aircraft can not load-carrying, it is three rotor structures in addition, can not balance well during vertical lift, easily spin, and complex structure.
Summary of the invention
Therefore, in order to overcome the deficiency of existing unmanned air vehicle technique, actively promote the upsurge of modern Development of UAV, the open a kind of interlock fixed-wing rotor electric vertical lifting unmanned plane of the present invention, not only structure is simple for it, and employ wired device that takes off, utilize ground power supply that this electronic unmanned plane is served high-altitude, then the power supply of self is relied on, low energy consumption is flown, or Non-energy-consumption glides destination, during close to terminal, can dead-stick landing, again can vertical landing, therefore, achieve a small amount of electric energy of this electronic unmanned plane, leap longer mileage, complete the object of carrying duty.
Technical scheme of the present invention is by fuselage, link span, bogie truck, interlock fixed-wing, interlock rotor, tailplane, vertical tail, wired device composition that takes off, its constructional feature is: described interlock fixed-wing rotor electric vertical lifting unmanned plane is provided with fleetline fuselage, large before fuselage, little below, cross section is triangular in shape, be provided with battery compartment in fuselage below and control storehouse, the above is cargo transport storehouse, fuselage top is provided with link span, link span is pre-large post-small stream line pattern hollow pillar, cross section is triangular in shape, link span is installed tressel by fixed mount upper end and is formed, fixed mount lower end is welded with fuselage top, left end between fixed mount and tressel is equipped with lower hinge, right-hand member is equipped with upper hinge, L-type gear frame is installed in upper hinge lower end, gear frame lower end is provided with nut bore, lead screw is provided with in nut bore, lead screw lower end is provided with driving motor, driving motor axle drive shaft and lead screw are one, driving motor is fastened on fixed mount bottom righthand side, described link span upper end is provided with bogie truck, described bogie truck is by cartridge type bearing frame, fixed-wing steering shaft, rotor steering shaft forms, described link span upper end is welded in the middle of cartridge type bearing frame lower end, hold close-fitting that steering bearing is installed about cartridge type bearing frame inner circle, left and right turn bearing inner circle installs fixed-wing steering shaft, mounting hole is shaped with in the middle part of fixed-wing steering shaft, in mounting hole, close-fitting installs rotor steering shaft, rotor steering shaft is less than fixed-wing steering shaft, both hollow shafts, both orthogonal formation Т type steering shafts, the described front upper end of cartridge type bearing frame is shaped with and turns to groove, rotor steering shaft turns to the action radius of 90 degree before and after turning in groove, cartridge type bearing frame cylindrical close-fitting is installed and is turned to gear ring, driving turns to gear ring that fixed-wing steering shaft and rotor steering shaft can be made synchronously to turn to, rotor steering shaft upper end is provided with interlock rotor, described Т type steering shaft is provided with interlock fixed-wing, interlock fixed-wing is perpendicular to interlock rotor, after described fuselage, upper end is provided with vertical tail, posterior end is provided with tailplane, and the front lower end of fuselage is provided with left and right front-wheel, middle lower end is provided with trailing wheel, left and right front-wheel and trailing wheel are used for unmanned plane dead-stick landing, fuselage lower end is provided with battery socket, being provided with attaching plug in socket, the connection of plug and socket of power source, is rely on the friction force between the spring pressure in battery socket and plugs and sockets to be of coupled connections, attaching plug connects two hinge cable head end, two hinge cable tail end arranges wired device that takes off, and described wired device that takes off is arranged on ground, and wired device right-hand member that takes off arranges ground intelligent control capsule.
Described interlock fixed-wing is connected to form by upper limb box and bottom wing box and some spiral nails, by turning to window up and down in the middle part of upper bottom wing box, synthesize wing and turn to window, wing turns to window lower end to be provided with link span passage breach, in upper bottom wing box, about wing turns to window, end is respectively equipped with upper left right semicircle type fixed-wing pedestal and bottom left right semicircle type fixed-wing pedestal, semi-circular fixed-wing pedestal holds fastening packaging by about fixed-wing steering shaft up and down, wing turns to upper end in window to be respectively equipped with first round rotor shaft frame and second round rotor shaft frame, upper and lower semi-circular rotor pedestal is by fastening for rotor steering shaft packaging, described cartridge type bearing frame turns in the middle of window at wing, described cartridge type bearing frame is arranged on wing and turns in the middle of window, described interlock fixed-wing has the steering range of 90 degree on cartridge type bearing frame, wing turns to window upper end to be provided with first round motor rack and second round motor rack, the fastening packaging steer motor of upper and lower semi-circular motor rack, steer motor axle drive shaft is shaped with driven wheel, driven wheel engages with the described gear ring that turns to, composition gear reduction, installation left and right, described interlock fixed-wing lower end slave wing motor, left and right slave wing motor is respectively equipped with left and right axle drive shaft, the left and right axle drive shaft of left and right slave wing motor is installed respectively the left slave wing and the right slave wing.
The structure of described interlock rotor installs rotor bearing in rotor steering shaft upper end, rotor steering shaft on rotor bearing upper and lower side position is shaped with upper and lower jump-ring slot, upper and lower jump-ring slot installs outer jump ring respectively, rotor bearing top circle close-fitting installs rotor shaft bolster, rotor shaft bolster circumference lower end is shaped with rotor internally toothed annulus, rotor internally toothed annulus cylindrical upper end is shaped with the blade of 4 deciles, mounted motor support on rotor steering shaft below rotor bearing, rotor motor is installed in electric machine support front end, rotor motor driving shaft is shaped with rotor clutch gear, rotor clutch gear engages with rotor internally toothed annulus, composition gear reduction driver train, between rotor clutch gear and rotor motor driving shaft, unidirectional needle bearing is set, during rotor electric machine rotation, drive unidirectional needle bearing, rotor clutch gear, rotor internally toothed annulus, the blade of 4 deciles, make interlock rotor rotational, when described interlock fixed-wing rotor electric vertical lifting unmanned vehicle is in level glide state, rotor motor stalls, unidirectional needle bearing skids, rotor clutch gear dallies with rotor internally toothed annulus and engages, described interlock rotor is unloaded in atmosphere to rotate, reduce air resistance.
Described tailplane is held about being arranged on the fuselage back lower place, the secondary empennage motor of level is installed in tailplane rear end, about level secondary empennage motor, end is provided with left and right axle drive shaft, the secondary empennage of level that left and right axle drive shaft is installed, described vertical tail is arranged on upper end after fuselage, vertical secondary empennage motor is installed in vertical tail rear end, and vertical secondary empennage motor upper and lower side is provided with upper and lower axle drive shaft, upper and lower axle drive shaft is installed vertical secondary empennage.
Described wired device that takes off is provided with base, installation left and right, base upper end pedestal, pedestal upper end, left and right arranges left and right axis hole, left and right axis hole is built with drum shaft, drum shaft installs spool, spool is plastic product, about spool, end arranges left and right end cap, about the end cap of left and right, end arranges left and right conducting slip ring, left end cap circumference arranges external toothing, spool is wrapped described two hinge cable, two hinge cable tail end connects left and right conducting slip ring respectively, left and right brush holder is set inside the pedestal of left and right, left and right carbon brush is provided with in the brush holder of left and right, left and right carbon brush and left and right conducting slip ring moving contact, on the left of the left and right pedestal of described wired device that takes off, spool motor is installed, right side installation ground intelligent control box, left and right carbon brush output line connects intelligent control box, the power lead of ground intelligent control capsule connects 220V source of AC, ground intelligent control capsule has and charges to lithium cell group, the functions such as rotor electric motor starting and wireless reception of signals control, spool motor driving shaft arranges driven wheel, and driven wheel passes through the axis hole of left pedestal, engage with the external toothing of left end cap circumference, described wired device that takes off is provided with hand-held remote controller.
Below in described fuselage, in battery compartment, lithium cell group is set; Control radio receiver and emitter that the contact of navigating instrument, sensing gyroscope instrument, airborne intelligent controller and remote-control communication is set in storehouse, the load carrying ability lade that cargo transport logical sequence above in fuselage sets according to unmanned plane, the permanent magnet DC motor of gear reducer selected by the secondary empennage motor of described left and right slave wing motor, steer motor, level, vertical secondary empennage motor, permanent magnet DC motor selected by described driving motor, spool motor, and high-speed permanent magnetic DC machine selected by described rotor motor.
The gesture stability principle of described interlock fixed-wing rotor electric vertical lifting unmanned plane when vertical lift and high-speed flight is: during described interlock fixed-wing vertical ground, described interlock rotor level is in ground, hand-held remote controller control signal is transmitted to ground intelligent controller, ground intelligent controller opens startup power supply is to rotor feeding electric motors, rotor motor drives rotor rotational, this electronic unmanned plane slowly takes off, described sensing gyroscope instrument exports various control signal to airborne intelligent controller according to fuselage attitude, airborne intelligent controller output voltage drives various electric machine rotation, when controlling left and right slave wing motor, action before and after the slave wing of left and right, air rate on fixed-wing can make fixed-wing produce the antagonistic force contrary with rotor rotational, fuselage can be kept not rotate, when controlling steer motor, action before and after interlock fixed-wing rotor, can keep not drifting about before and after unmanned plane, control driving motor, the action of link span left and right, do not drift about about keeping unmanned plane, when unmanned plane rises to setting height, in spool, two hinge cable discharges, two attaching plug of hinge cable upper end and the battery socket of fuselage lower end, pulling force because of unmanned plane exceeds the coupling elastic force of plugs and sockets and shakes off, after two hinge cable lands, spool motor drives clutch gear to drive the external toothing of left end cap circumference, spool rotates and is reclaimed by two hinge cable, the lift-off of taking off of the unmanned plane of surface power supply is higher, course continuation mileage is far away, now this electronic unmanned plane relies on self-contained storage battery electric energy to work on, unmanned plane vertical lift patten transformation is horizontal flight pattern by airborne intelligent controller, control interlock fixed-wing rotor to rotate forward, progressively be transitioned into level flight condition, airborne intelligent controller controls the left and right slave wing, the secondary empennage of level, vertical secondary empennage realizes the posture balancing of unmanned plane and turns to flight, control navigating instrument in storehouse and send command signal to airborne intelligent controller every now and then, automatically unmanned plane is led to arrive the route of destination, during close to terminal, unmanned plane can dead-stick landing, again can vertical landing, therefore, achieve this electronic unmanned plane and only use a small amount of electric energy, leap longer mileage, complete the object of carrying duty.
The beneficial effect of interlock fixed-wing rotor electric vertical lifting unmanned plane is reasonable in design, and not only structure is simple for it, and employs wired device that takes off, utilize ground power supply that this electronic unmanned plane is served high-altitude, then rely on the power supply of self, low energy consumption is flown, or Non-energy-consumption glides destination, during close to terminal, can dead-stick landing, again can vertical landing, therefore, achieve this electronic unmanned plane and only use a small amount of electric energy, leap longer mileage, complete the object of carrying duty.Interlock fixed-wing rotor of the present invention turns to as horizontality or plumbness 90 degree of scope inter-syncs, the vertical equity degree control torque of unmanned plane is large, good stability, promptly can enter horizontal flight or vertical floating state flexibly, in the switching process of vertical lift pattern and horizontal flight pattern, interlock fixed-wing rotor does not cause air-flow resistance, air-flow guiding is steadily controlled, do not produce air-flow vortex, guarantee that aircraft security is reliable, once running down of battery, unmanned function relies on large and wide interlock fixed-wing gliding flight, safe landing.
Accompanying drawing explanation
Xia face is Zuo Jin mono-Walk explanation by reference to the accompanying drawings.
Fig. 1 is interlock fixed-wing rotor electric vertical lifting unmanned plane vertical lift state forward sight structural representation.
Fig. 2 is the right TV structure schematic diagram of interlock fixed-wing rotor electric vertical lifting unmanned plane vertical lift state.
Fig. 3 is the right TV structure schematic diagram of interlock fixed-wing rotor electric vertical lifting unmanned plane level flight condition.
Fig. 4 is interlock fixed-wing rotor electric vertical lifting unmanned plane level flight condition plan structure schematic diagram.
Detailed description of the invention
In Fig. 1, Fig. 2, Fig. 3, Fig. 4, described interlock fixed-wing rotor electric vertical lifting unmanned plane is provided with fleetline fuselage 1, large before fuselage, little below, cross section is triangular in shape, be provided with battery compartment 2 in fuselage below and control storehouse 3, the above is cargo transport storehouse 4, fuselage top is provided with link span, link span is pre-large post-small stream line pattern hollow pillar, and cross section is triangular in shape, and link span is installed tressel 6 by fixed mount 5 upper end and formed, fixed mount lower end is welded with fuselage top, and the left end between fixed mount and tressel is equipped with lower hinge 7, right-hand member is equipped with upper hinge 8, L-type gear frame 9 is installed in upper hinge lower end, gear frame lower end is provided with nut bore, lead screw 10 is provided with in nut bore, lead screw lower end is provided with driving motor 11, driving motor axle drive shaft and lead screw are one, driving motor is fastened on fixed mount bottom righthand side, described link span upper end is provided with bogie truck, described bogie truck is by cartridge type bearing frame 12, fixed-wing steering shaft 13, rotor steering shaft 14 forms, described link span upper end is welded in the middle of cartridge type bearing frame lower end, hold close-fitting that left and right turn bearing 15 is installed about cartridge type bearing frame inner circle, left and right turn bearing inner circle installs fixed-wing steering shaft, mounting hole is shaped with in the middle part of fixed-wing steering shaft, in mounting hole, close-fitting installs rotor steering shaft, rotor steering shaft is less than fixed-wing steering shaft, both hollow shafts, both orthogonal formation Т type steering shafts, the described front upper end of cartridge type bearing frame is shaped with and turns to groove 16, rotor steering shaft turns to the action radius of 90 degree before and after turning in groove, cartridge type bearing frame cylindrical close-fitting is installed and is turned to gear ring 17, driving turns to gear ring that fixed-wing steering shaft and rotor steering shaft can be made synchronously to turn to, rotor steering shaft upper end is provided with interlock rotor 18, described Т type steering shaft is provided with interlock fixed-wing 19, interlock fixed-wing is perpendicular to interlock rotor, after described fuselage, upper end is provided with vertical tail 20, posterior end is provided with tailplane 21, and the front lower end of fuselage is provided with left and right front-wheel 22, middle lower end is provided with trailing wheel 23, left and right front-wheel and trailing wheel are used for unmanned plane dead-stick landing, fuselage lower end is provided with battery socket 24, being provided with attaching plug 25 in socket, the connection of plug and socket of power source, is rely on the friction force between the spring pressure in battery socket and plugs and sockets to be of coupled connections, attaching plug connects two hinge cable 26 head end, two hinge cable tail end arranges wired device 27 that takes off, and described wired device that takes off is arranged on ground, and wired device right-hand member that takes off arranges ground intelligent control capsule 28.
Described interlock fixed-wing is connected to form by upper limb box 29 and bottom wing box 30 and some spiral nails, be provided with in the middle part of upper bottom wing box and turn to window up and down, synthesize wing and turn to window 31, wing turns to window lower end to be provided with link span passage breach 32, in upper bottom wing box, about wing turns to window, end is respectively equipped with upper left right semicircle type fixed-wing pedestal 33 and bottom left right semicircle type fixed-wing pedestal 34, semi-circular fixed-wing pedestal holds fastening packaging by about fixed-wing steering shaft up and down, wing turns to upper end in window to be respectively equipped with first round rotor shaft frame 35 and second round rotor shaft frame 36, upper and lower semi-circular rotor pedestal is by fastening for rotor steering shaft packaging, described cartridge type bearing frame is arranged on wing and turns in the middle of window, described interlock fixed-wing has the steering range of 90 degree on cartridge type bearing frame, wing turns to window upper end to be provided with first round motor rack and second round motor rack, the fastening packaging steer motor 37 of upper and lower semi-circular motor rack, steer motor axle drive shaft is shaped with driven wheel 38, driven wheel engages with the described gear ring that turns to, composition gear reduction, installation left and right, described interlock fixed-wing lower end slave wing motor 39, 40, left and right slave wing motor is respectively equipped with left and right axle drive shaft 41, 42, the left and right axle drive shaft of left and right slave wing motor is installed respectively the left slave wing 43 and the right slave wing 44.
The structure of described interlock rotor installs rotor bearing 45 in rotor steering shaft upper end, rotor steering shaft on rotor bearing upper and lower side position is shaped with upper and lower jump-ring slot, upper and lower jump-ring slot installs outer jump ring 46 respectively, 47, rotor bearing top circle close-fitting installs rotor shaft bolster 48, rotor shaft bolster circumference lower end is shaped with rotor internally toothed annulus 49, rotor internally toothed annulus cylindrical upper end is shaped with the blade 50 of 4 deciles, mounted motor support 51 on rotor steering shaft below rotor bearing, rotor motor 52 is installed in electric machine support front end, rotor motor driving shaft is shaped with rotor clutch gear 53, rotor clutch gear engages with rotor internally toothed annulus, composition gear reduction, between rotor clutch gear and rotor motor driving shaft, unidirectional needle bearing is set, during rotor electric machine rotation, drive unidirectional needle bearing, rotor clutch gear, rotor internally toothed annulus, the blade of 4 deciles, make interlock rotor rotational, when described interlock fixed-wing rotor electric vertical lifting unmanned vehicle is in level glide state, rotor motor stalls, unidirectional needle bearing skids, rotor clutch gear dallies with rotor internally toothed annulus and engages, described interlock rotor is unloaded in atmosphere to rotate, reduce air resistance.
Described tailplane is held about being arranged on the fuselage back lower place, the secondary empennage motor 54 of level is installed in tailplane rear end, about level secondary empennage motor, end is provided with left and right axle drive shaft, the secondary empennage 55 of level that left and right axle drive shaft is installed, described vertical tail is arranged on upper end after fuselage, vertical secondary empennage motor 56 is installed in vertical tail rear end, and vertical secondary empennage motor upper and lower side is provided with upper and lower axle drive shaft, upper and lower axle drive shaft is installed vertical secondary empennage 57.
Described wired device that takes off is provided with base 58, installation left and right, base upper end pedestal 59, 60, pedestal upper end, left and right arranges left and right axis hole, left and right axis hole is built with drum shaft 61, drum shaft installs spool, spool is plastic product, about spool, end arranges left and right end cap 62, about the end cap of left and right, end arranges left and right conducting slip ring 63, left end cap circumference arranges external toothing 64, spool is wrapped described two hinge cable, two hinge cable tail end connects left and right conducting slip ring respectively, left and right brush holder 65 is set inside the pedestal of left and right, left and right carbon brush 66 is provided with in the brush holder of left and right, left and right carbon brush and left and right conducting slip ring moving contact, on the left of the left and right pedestal of described wired device that takes off, spool motor 67 is installed, right side installation ground intelligent control box, left and right carbon brush output line connects ground intelligent control capsule, the power lead 68 of ground intelligent control capsule connects 220V source of AC, ground intelligent control capsule has and charges to lithium cell group, the functions such as rotor electric motor starting and wireless reception of signals control, spool motor driving shaft arranges transmission gear 69, and transmission gear passes through the axis hole of left pedestal, engage with the external toothing of left end cap circumference, described wired device that takes off is provided with hand-held remote controller.
In battery compartment below in described fuselage, lithium cell group is set; Control radio receiver and emitter that the contact of navigating instrument, sensing gyroscope instrument, airborne intelligent controller and remote-control communication is set in storehouse, cargo transport logical sequence above in fuselage, according to the load carrying ability lade of unmanned plane setting, the permanent magnet DC motor of gear reducer selected by the secondary empennage motor of described left and right slave wing motor, steer motor, level, vertical secondary empennage motor, permanent magnet DC motor selected by described driving motor, spool motor, and high-speed permanent magnetic DC machine selected by described rotor motor.
Claims (6)
1. an interlock fixed-wing rotor electric vertical lifting unmanned plane, by fuselage, link span, bogie truck, interlock fixed-wing, interlock rotor, tailplane, vertical tail, wired device composition that takes off, it is characterized in that: described interlock fixed-wing rotor electric vertical lifting unmanned plane is provided with fleetline fuselage (1), large before fuselage, little below, cross section is triangular in shape, be provided with battery compartment (2) in fuselage below and control storehouse (3), the above is cargo transport storehouse (4), fuselage top is provided with link span, link span is pre-large post-small stream line pattern hollow pillar, cross section is triangular in shape, link span is installed tressel (6) by fixed mount (5) upper end and is formed, fixed mount lower end is welded with fuselage top, left end between fixed mount and tressel is equipped with lower hinge (7), right-hand member is equipped with upper hinge (8), L-type gear frame (9) is installed in upper hinge lower end, gear frame lower end is provided with nut bore, lead screw (10) is provided with in nut bore, lead screw lower end is provided with driving motor (11), driving motor axle drive shaft and lead screw are one, driving motor is fastened on fixed mount bottom righthand side, described link span upper end is provided with bogie truck, described bogie truck is by cartridge type bearing frame (12), fixed-wing steering shaft (13), rotor steering shaft (14) forms, described link span upper end is welded in the middle of cartridge type bearing frame lower end, hold close-fitting that left and right turn bearing (15) is installed about cartridge type bearing frame inner circle, left and right turn bearing inner circle installs fixed-wing steering shaft, mounting hole is shaped with in the middle part of fixed-wing steering shaft, in mounting hole, close-fitting installs rotor steering shaft, rotor steering shaft is less than fixed-wing steering shaft, both hollow shafts, both orthogonal formation Т type steering shafts, the described front upper end of cartridge type bearing frame is shaped with and turns to groove (16), rotor steering shaft turns to the action radius of 90 degree before and after turning in groove, cartridge type bearing frame cylindrical close-fitting is installed and is turned to gear ring (17), driving turns to gear ring that fixed-wing steering shaft and rotor steering shaft can be made synchronously to turn to, rotor steering shaft upper end is provided with interlock rotor (18), described Т type steering shaft is provided with interlock fixed-wing (19), interlock fixed-wing is perpendicular to interlock rotor, after described fuselage, upper end is provided with vertical tail (20), posterior end is provided with tailplane (21), and the front lower end of fuselage is provided with left and right front-wheel (22), middle lower end is provided with trailing wheel (23), left and right front-wheel and trailing wheel are used for unmanned plane dead-stick landing, fuselage lower end is provided with battery socket (24), attaching plug (25) is provided with in socket, the connection of plug and socket of power source, rely on the friction force between the spring pressure in battery socket and plugs and sockets to be of coupled connections, attaching plug connects two hinge cable (26) head end, two hinge cable tail end arranges wired device that takes off (27), described wired device that takes off is arranged on ground, and wired device right-hand member that takes off arranges ground intelligent control capsule (28).
2. according to described interlock fixed-wing rotor electric vertical lifting unmanned plane, it is characterized in that: described interlock fixed-wing is connected to form by upper limb box (29) and bottom wing box (30) and some spiral nails, be provided with in the middle part of upper bottom wing box and turn to window up and down, synthesize wing and turn to window (31), wing turns to window lower end to be provided with link span passage breach (32), in upper bottom wing box, about wing turns to window, end is respectively equipped with upper left right semicircle type fixed-wing pedestal (33) and bottom left right semicircle type fixed-wing pedestal (34), semi-circular fixed-wing pedestal holds fastening packaging by about fixed-wing steering shaft up and down, wing turns to upper end in window to be respectively equipped with first round rotor shaft frame (35) and second round rotor shaft frame (36), upper and lower semi-circular rotor pedestal is by fastening for rotor steering shaft packaging, described cartridge type bearing frame is arranged on wing and turns in the middle of window, described interlock fixed-wing has the steering range of 90 degree on cartridge type bearing frame, wing turns to window upper end to be provided with first round motor rack and second round motor rack, the fastening packaging steer motor (37) of upper and lower semi-circular motor rack, steer motor axle drive shaft is shaped with driven wheel (38), driven wheel engages with the described gear ring that turns to, composition gear reduction, described installation left and right slave wing motor, interlock fixed-wing lower end (39), (40), left and right slave wing motor is respectively equipped with left and right axle drive shaft (41), (42), the left and right axle drive shaft of left and right slave wing motor installs the left slave wing (43) and the right slave wing (44) respectively.
3. according to described interlock fixed-wing rotor electric vertical lifting unmanned plane, it is characterized in that: the structure of described interlock rotor installs rotor bearing (45) in rotor steering shaft upper end, rotor steering shaft on rotor bearing upper and lower side position is shaped with upper and lower jump-ring slot, upper and lower jump-ring slot installs outer jump ring (46) respectively, (47), rotor bearing top circle close-fitting installs rotor shaft bolster (48), rotor shaft bolster circumference lower end is shaped with rotor internally toothed annulus (49), rotor internally toothed annulus cylindrical upper end is shaped with the blade (50) of 4 deciles, mounted motor support (51) on rotor steering shaft below rotor bearing, rotor motor (52) is installed in electric machine support front end, rotor motor driving shaft is shaped with rotor clutch gear (53), rotor clutch gear engages with rotor internally toothed annulus, composition gear reduction, between rotor clutch gear and rotor motor driving shaft, unidirectional needle bearing is set, during rotor electric machine rotation, drive unidirectional needle bearing, rotor clutch gear, rotor internally toothed annulus, the blade of 4 deciles, make interlock rotor rotational, rotor motor stalls, unidirectional needle bearing skids, rotor clutch gear dallies with rotor internally toothed annulus and engages, described interlock rotor is unloaded in atmosphere to rotate.
4. according to described interlock fixed-wing rotor electric vertical lifting unmanned plane, it is characterized in that: described tailplane is held about being arranged on the fuselage back lower place, secondary empennage motor (54) of level is installed in tailplane rear end, about level secondary empennage motor, end is provided with left and right axle drive shaft, the secondary empennage (55) of level that left and right axle drive shaft is installed, described vertical tail is arranged on upper end after fuselage, vertical secondary empennage motor (56) is installed in vertical tail rear end, vertical secondary empennage motor upper and lower side is provided with upper and lower axle drive shaft, upper and lower axle drive shaft is installed vertical secondary empennage (57).
5. according to described interlock fixed-wing rotor electric vertical lifting unmanned plane, it is characterized in that: described wired device that takes off is provided with base (58), installation left and right, base upper end pedestal (59), (60), pedestal upper end, left and right arranges left and right axis hole, left and right axis hole is built with drum shaft (61), drum shaft installs spool, spool is plastic product, about spool, end arranges left and right end cap (62), about the end cap of left and right, end arranges left and right conducting slip ring (63), left end cap circumference arranges external toothing (64), spool is wrapped described two hinge cable, two hinge cable tail end connects left and right conducting slip ring respectively, left and right brush holder (65) is set inside the pedestal of left and right, left and right carbon brush (66) is provided with in the brush holder of left and right, left and right carbon brush and left and right conducting slip ring moving contact, on the left of the left and right pedestal of described wired device that takes off, spool motor (67) is installed, right side installation ground intelligent control box, left and right carbon brush output line connects ground intelligent control capsule, the power lead (68) of ground intelligent control capsule connects 220V source of AC, ground intelligent control capsule has and charges to lithium cell group, the functions such as rotor electric motor starting and wireless reception of signals control, spool motor driving shaft arranges transmission gear (69), and transmission gear passes through the axis hole of left pedestal, engage with the external toothing of left end cap circumference, described wired device that takes off is provided with hand-held remote controller.
6. according to described interlock fixed-wing rotor electric vertical lifting unmanned plane, it is characterized in that: in the battery compartment below in described fuselage, lithium cell group is set; Control radio receiver and emitter that the contact of navigating instrument, sensing gyroscope instrument, airborne intelligent controller and remote-control communication is set in storehouse, cargo transport logical sequence above in described fuselage, according to the load carrying ability lade of unmanned plane setting, the permanent magnet DC motor of gear reducer selected by the secondary empennage motor of described left and right slave wing motor, steer motor, level, vertical secondary empennage motor, permanent magnet DC motor selected by described driving motor, spool motor, and high-speed permanent magnetic DC machine selected by described rotor motor.
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| CN201510091079.8A CN104691758B (en) | 2015-03-01 | 2015-03-01 | Linkage fixed-wing rotor electric vertical lifting unmanned plane |
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| CN201510091079.8A CN104691758B (en) | 2015-03-01 | 2015-03-01 | Linkage fixed-wing rotor electric vertical lifting unmanned plane |
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| CN105652886A (en) * | 2016-03-18 | 2016-06-08 | 吴李海 | Internet unmanned aerial vehicle capable of achieving continuous endurance |
| CN107150803A (en) * | 2017-06-07 | 2017-09-12 | 天津科技大学 | Mixed layout unmanned plane and its control method |
| CN110116806A (en) * | 2019-04-28 | 2019-08-13 | 南京航空航天大学 | A kind of device docked for fixed-wing unmanned plane with rotor flat pad |
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| Publication number | Publication date |
|---|---|
| CN104691758B (en) | 2016-09-28 |
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