CN204173152U - A kind of manned Electric aircraft - Google Patents
A kind of manned Electric aircraft Download PDFInfo
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- CN204173152U CN204173152U CN201420587428.6U CN201420587428U CN204173152U CN 204173152 U CN204173152 U CN 204173152U CN 201420587428 U CN201420587428 U CN 201420587428U CN 204173152 U CN204173152 U CN 204173152U
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Abstract
The utility model belongs to manned technical field of aerospace, is specifically related to a kind of manned Electric aircraft; This aircraft comprises mechanics and circuit control part, the driving compartment connected by hanger rope in the middle part of the ultrathin flexible solar power pad pasting that a, mechanics comprise balloon covering, balloon covering top is arranged, balloon covering, b, circuit control part comprise ultrathin flexible solar power pad pasting, and ultrathin flexible solar power pad pasting is connected with storage battery by charge switch; Have that structure is simple, cheap, environmental protection, clean energy resource, load carrying ability adjustable, flexibility of operation is good, low, the many-sided advantage ensureing safety of navigation of shipping cost.
Description
Technical field
The utility model belongs to manned technical field of aerospace, is specifically related to a kind of manned Electric aircraft.
Background technology
The enforcement the earliest of balloon flighter can be traced back to 1784, and the manual feed fish shape of French Robert brother fills taking a flight test of hydrogen HIKOUSEN.French engineer Ji Faer in 1852 has manufactured and designed that air bag is 2500 cubic meters, to promote screw propeller be onward impulse handles and fill hydrogen dirigible with steam engine.Afterwards, soft balloon dirigible again by metal, timber frame cover covering rigid airship replace.To 20 beginnings of the century, airship technology is ripe day by day.Significant contribution is made in the neat Berlin of inventor by Germany, makes dirigible aviation become the leading trend of 20th century initial World Airways industry.Germany De Laige dirigible airline company only just achieved the achievement of dirigible aviation 2,140,000 kilometers, safe carrying 35000 person-times from 1910 to 1914.Germany manufactures long 245 meters of successful Hindenburg dirigible for 1936, diameter 41 meters, always bag volume are 20 ten thousand steres, gross weight 230 tons, the driving engine that power is 4 610 kilowatts, carrying 75, the speed of a ship or plane reaches 130 kilometers/hour, cruise duration is 200 hours, the luxurious and equipment of inside fitting comfortable not second to " Titanic " number luxurious passenger steamer.This ship carries out 63 commercial aviation altogether.In the World War I, dirigible is also widely used in military affairs by various countries, and obtains outstanding effect.But the termination of dirigible aircraft industry, also have an accident for mark with the unexpected blast on fire when New Jersey lands of Hindenburg dirigible on May 6 nineteen thirty-seven just.But dirigible aviation replace by emerging aircraft aviation not accidentally, its certainty is two of inflation airship at that time large defects: one be most of dirigible institute inflatable body is flammable explosive hydrogen; Two are bulky dirigible malfunctions, are difficult to cope with contingencies.20 century 70s, inflatable vehicle starts again recovery, but there is load carrying ability, the defect of shipping cost and safety still cannot overcome, especially its energy consumed is petroleum products substantially, when world energy sources, oil shortage are day by day serious, undoubtedly serious restriction is also existed to the fast development of the industry; And such aircraft pollution on the environment is also very important.
Utility model content
The purpose of this utility model is to overcome defect of the prior art, and provides a kind of load carrying ability adjustable, and flexibility of operation is good, low, the many-sided manned Electric aircraft of one ensureing safety of navigation of shipping cost.
The purpose of this utility model is achieved in that this aircraft comprises mechanics and circuit control part,
A, mechanics comprises balloon covering, the ultrathin flexible solar power pad pasting that balloon covering top is arranged, by driving compartment that hanger rope connects in the middle part of balloon covering, the both sides on the outer wall top of described driving compartment are respectively equipped with the wire drawing ring that casts anchor, to cast anchor first the linking up with and be connected of wire drawing one end of casting anchor of wire drawing ring and tensile force of belt instrument, the other end of wire drawing of casting anchor is provided with the second hook, the outer bottom of described driving compartment is provided with landing shock absorption device, the side of described driving compartment outer wall offers cockpit door, the inside of driving compartment is provided with control panel, two-direction switch, governor, fan operation handle, clump weight, storage battery, described fan operation handle is located at the inside of lever journey disk, the bottom of fan operation handle is connected with rotating blower fan by blower fan connecting shaft, the inside of described balloon covering is provided with several helium capsules, wherein, each helium capsule correspondence is provided with a charge and discharge gas port, several charge and discharge gas ports described are arranged at the bottom of balloon covering respectively, wherein, at least one charge and discharge gas port and air bag extend freeing pipe and are connected, this air bag extends the inside that freeing pipe is arranged on driving compartment, the tail end that described air bag extends freeing pipe is provided with exhaust pipe mouth safety cap, have the outside of a charge and discharge gas port to be provided with in other several charge and discharge gas ports to be arranged on reinforcing annular pad and the metallic support cover of balloon covering outside face at least, sealing plug is provided with in this charge and discharge gas port described, sealing plug is connected with the safety draw ring of driving compartment internal upper part band catch by steel wire drawing, between the inner bottom part of sealing plug and metallic support cover, stage clip is installed, wire drawing pipe is provided with between metallic support cover and the outer top of driving compartment, described steel wire drawing is through stage clip, wire drawing pipe is connected with the safety draw ring of extension spring with band catch, described extension spring is arranged between catch and driving compartment internal upper part, the outside face of described metallic support cover offers several exhaust holes, the outside of described driving compartment is provided with anemoscope, and described driving compartment is provided with illuminating lamp,
B, circuit control part comprise ultrathin flexible solar power pad pasting, ultrathin flexible solar power pad pasting is connected with storage battery by charge switch, described storage battery is provided with external charge socket, storage battery is connected with two-direction switch with governor by battery isolator control, described two-direction switch is connected with rotating blower fan by inverter, and described control panel is provided with the electricity display instrument, altitude instrument, variometer, horizontal velocity instrument and the navigating instrument that are connected with storage battery; Described storage battery is connected with illuminating lamp by headlamp switch, and described charge switch, battery isolator control and headlamp switch are established on the control panel respectively; Described storage battery, inverter and rotating blower fan are respectively equipped with the first temperature sensor, the second temperature sensor and three-temperature sensor, described first temperature sensor, the second temperature sensor are connected with the 3rd annunciator with the first corresponding annunciator, the second annunciator respectively by wire with three-temperature sensor, and described first annunciator, the second annunciator and the 3rd annunciator are established on the control panel respectively.
Described hanger rope is at least three; Described landing shock absorption device is at least three; Described storage battery is at least one; Described sealing plug is taper type sealing plug, and described cockpit door is connected with adopting hinge between driving compartment, and cockpit door top offers clear glass window; The top of described clump weight is provided with portable handle.Described two charge and discharge gas ports extend freeing pipe with two air bags respectively and are connected.Described rotating blower fan is two, it is separately positioned on the both sides of driving compartment outside, blower fan connecting shaft is yi word pattern, two rotating blower fans are separately positioned on the two ends of blower fan connecting shaft, blower fan connecting shaft is provided with fan operation handle, described two rotating blower fans are connected with corresponding two inverters respectively, described two inverters are connected with corresponding two two-direction switchs respectively, two two-direction switchs are connected with storage battery with battery isolator control respectively by governor, described two inverters are respectively equipped with the second temperature sensor, and two the second temperature sensors are connected with the second annunciator respectively.The both sides of described driving compartment outside are respectively equipped with two rotating blower fans, described blower fan connecting shaft is two, its shape is yi word pattern, the two ends of two blower fan connecting shafts are respectively equipped with rotating blower fan, described two blower fan connecting shafts are connected with the bottom of corresponding two fan operation handles respectively, four rotating blower fans are connected with corresponding four inverters respectively, described four inverters are connected with corresponding four two-direction switchs respectively, four two-direction switchs are connected with storage battery with battery isolator control respectively by governor, described four inverters are respectively equipped with the second temperature sensor, and four the second temperature sensors are connected with the second annunciator respectively.The inside of described driving compartment is provided with driver seat, and described storage battery is arranged on the bottom of driver seat.The outer bottom of described driving compartment is provided with the rope safety link for subsequent use of integrative-structure, described rope safety link for subsequent use is connected with one end of rope for subsequent use, the other end of rope for subsequent use is provided with anti-drop hook, and described anti-drop hook is connected with the rope curling device for subsequent use that driving compartment wall outer surface is arranged.Described anemoscope is connected with the anemoscope display instrument on control panel by wire.Described lever journey disk offers the first gear, the second gear, third gear position, fourth gear position, fifth gear position and sixth gear position respectively.Described storage battery is lithium cell group.
The manned Electric aircraft of the one made according to such scheme, in use due to the quantity of balloon covering helium gas inside capsule and volume relatively stable, therefore the weight by adjusting clump weight realizes the stochastic equilibrium of gross buoyancy and total weight, creates the condition of this aircraft weightlessness; The sealing plug that air bag extends freeing pipe by arranging, steel wire drawing connects and the band safety draw ring of catch and rope for subsequent use ensure the flight safety of aircraft; By change the air blower position of rotating blower fan and the positive and negative of fan blade transfer realize aircraft advance, retrogressing, rise, land, turn left curved or turn right curved; Have that structure is simple, cheap, environmental protection, clean energy resource, load carrying ability adjustable, flexibility of operation is good, low, the many-sided advantage ensureing safety of navigation of shipping cost.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the structural representation of the utility model side;
Fig. 3 is the structural scheme of mechanism of the utility model lever journey disk and fan operation handle;
Fig. 4 is control panel structural representation of the present utility model;
Fig. 5 is the structural representation of the utility model clump weight;
Fig. 6 is the structural representation of the utility model cockpit door;
Fig. 7 is the structural representation of the utility model cockpit;
Fig. 8 is the structural representation of the wire drawing of the utility model steel and safety draw ring;
Fig. 9 is the structural representation of the utility model metallic support cover;
Figure 10 is control circui frame principle figure of the present utility model;
Figure 11 is the structural representation of the utility model balloon covering inside;
Figure 12 is the structural representation of four rotating blower fans of the present utility model.
Detailed description of the invention
As shown in Fig. 1,2,3,4,5,6,7,8,9,10,11, the utility model is a kind of manned Electric aircraft, and this aircraft comprises mechanics and circuit control part,
A, mechanics comprises balloon covering 1, the ultrathin flexible solar power pad pasting 2 that balloon covering 1 top is arranged, by driving compartment 4 that hanger rope 3 connects in the middle part of balloon covering 1, the both sides on the outer wall top of described driving compartment 4 are respectively equipped with the wire drawing ring 5 that casts anchor, the wire drawing ring 5 that casts anchor is linked up with 11 with first of wire drawing 7 one end of casting anchor of tensile force of belt instrument 6 and is connected, the other end of wire drawing 7 of casting anchor is provided with the second hook 8, the outer bottom of described driving compartment 4 is provided with landing shock absorption device 9, the side of described driving compartment 4 outer wall offers cockpit door 10, the inside of driving compartment 4 is provided with control panel 12, two-direction switch 13, governor 17, fan operation handle 14, clump weight 15, storage battery 16, described fan operation handle 14 is located at the inside of lever journey disk 19, the bottom of fan operation handle 14 is connected with rotating blower fan 21 by blower fan connecting shaft 20, the inside of described balloon covering 1 is provided with several helium capsules 22, wherein, each helium capsule correspondence is provided with a charge and discharge gas port 23, several charge and discharge gas ports 23 described are arranged at the bottom of balloon covering 1 respectively, wherein, at least one charge and discharge gas port and air bag extend freeing pipe 24 and are connected, this air bag extends the inside that freeing pipe 24 is arranged on driving compartment 4, the tail end that described air bag extends freeing pipe 24 is provided with exhaust pipe mouth safety cap 25, have the outside of a charge and discharge gas port to be provided with in other several charge and discharge gas ports 23 to be arranged on reinforcing annular pad 26 and the metallic support cover 27 of balloon covering 1 outside face at least, sealing plug 28 is provided with in this charge and discharge gas port described, sealing plug 28 is connected with the safety draw ring 30 of driving compartment 4 internal upper part band catch 33 by steel wire drawing 29, stage clip 32 is installed between the inner bottom part of sealing plug 28 and metallic support cover 27, wire drawing pipe 31 is provided with between metallic support cover 27 and the outer top of driving compartment 4, described steel wire drawing 29 is through stage clip 32, wire drawing pipe 31 is connected with the safety draw ring 30 of extension spring 34 with band catch 33, described extension spring 34 is arranged between catch 33 and driving compartment 4 internal upper part, the outside face of described metallic support cover 27 offers several exhaust holes 38, the outside of described driving compartment 4 is provided with anemoscope 40, and described driving compartment 4 is provided with illuminating lamp 41,
B, circuit control part comprise ultrathin flexible solar power pad pasting 2, ultrathin flexible solar power pad pasting 2 is connected with storage battery 16 by charge switch 45, described storage battery 16 is provided with external charge socket 42, storage battery 16 is connected with two-direction switch 13 with governor 17 by battery isolator control 43, described two-direction switch 13 is connected with rotating blower fan 21 by inverter 18, and described control panel 12 is provided with the electricity display instrument 51, altitude instrument 35, variometer 36, horizontal velocity instrument 37 and the navigating instrument 39 that are connected with storage battery 16; Described storage battery 16 is connected with illuminating lamp 41 by headlamp switch 57, and described charge switch 45, battery isolator control 43 and headlamp switch 57 are located on control panel 12 respectively; Described storage battery 16, inverter 18 and rotating blower fan 21 are respectively equipped with the first temperature sensor 58, second temperature sensor 59 and three-temperature sensor 60, described first temperature sensor 58, second temperature sensor 59 is connected with the 3rd annunciator 48 with the first corresponding annunciator 61, second annunciator 49 respectively by wire with three-temperature sensor 60, and described first annunciator 61, second annunciator 49 and the 3rd annunciator 48 are located on control panel 12 respectively.
Described hanger rope 3 is at least three; Described landing shock absorption device 9 is at least three; Described storage battery 16 is at least one; Described sealing plug 28 is taper type sealing plug, and described cockpit door 10 is connected with adopting hinge 50 between driving compartment 4, and cockpit door 10 top offers clear glass window 52; The top of described clump weight 15 is provided with portable handle 53.Described two charge and discharge gas ports 23 extend freeing pipe 24 with two air bags respectively and are connected.Described rotating blower fan 21 is two, it is separately positioned on the both sides of driving compartment 4 outside, blower fan connecting shaft 20 is yi word pattern, two rotating blower fans 21 are separately positioned on the two ends of blower fan connecting shaft 20, blower fan connecting shaft 20 is provided with fan operation handle 14, described two rotating blower fans 21 are connected with corresponding two inverters 18 respectively, described two inverters 18 are connected with corresponding two two-direction switchs 13 respectively, two two-direction switchs 13 are connected with storage battery 16 with battery isolator control 43 respectively by governor 17, described two inverters 18 are respectively equipped with the second temperature sensor 59, and two the second temperature sensors 59 are connected with the second annunciator 49 respectively.The both sides of described driving compartment 4 outside are respectively equipped with two rotating blower fans 21, described blower fan connecting shaft 20 is two, its shape is yi word pattern, the two ends of two blower fan connecting shafts 20 are respectively equipped with rotating blower fan 21, described two blower fan connecting shafts 20 are connected with the bottom of corresponding two fan operation handles 14 respectively, four rotating blower fans 21 are connected with corresponding four inverters 18 respectively, described four inverters 18 are connected with corresponding four two-direction switchs 13 respectively, four two-direction switchs 13 are connected with storage battery 16 with battery isolator control 43 respectively by governor 17, described four inverters 18 are respectively equipped with the second temperature sensor 59, and four the second temperature sensors 59 are connected with the second annunciator 49 respectively.The inside of described driving compartment 4 is provided with driver seat 54, and described storage battery 16 is arranged on the bottom of driver seat 54.The outer bottom of described driving compartment 4 is provided with the rope safety link 55 for subsequent use of integrative-structure, described rope safety link 55 for subsequent use is connected with one end of rope 56 for subsequent use, the other end of rope 56 for subsequent use is provided with anti-drop hook 44, and described anti-drop hook 44 is connected with the rope curling device 47 for subsequent use that driving compartment 4 wall outer surface is arranged.Described anemoscope 40 is connected with the anemoscope display instrument 46 on control panel 12 by wire.Described lever journey disk 19 offers the first gear 62, second gear 63, third gear position 64, fourth gear position 65, fifth gear position 66 and sixth gear position 67 respectively.Described storage battery 16 is lithium cell group.Several helium capsules 22 described all realize filling simultaneously, putting helium by several corresponding charge and discharge gas ports 23, or a certain moment only carries out independent inflation, bleed air operation to wherein helium capsule; In the utility model, use is lighter than air and overweights the ellipse property gas helium of hydrogen as special gas, can be ensured to fly its flight safety, during vent gas, balloon covering 1 and helium capsule 22 foldable transportation, balloon covering 1 and helium capsule 22 shaping bulging during sufficient gas, it can be made aloft to increase by the effect of buoyancy, several helium capsules 22 multiple mainly play two effects: first, can guarantee under the unforeseen circumstances of Local Damaged, balloon is unlikely makes manned device be in rapidly the runaway condition of decline because of rapid blow-down helium; The second, can arbitrarily determine load carrying ability of the present utility model, when needs load carrying ability increases, the volume of several helium capsules 22 be become maximum, when do not need too load capacity time, arrange make several helium capsules 22 be filled with part helium.Described hanger rope 3 has light weight soft and tough, weather resistance, Resisting fractre, nonflammable feature.After the inflation of several helium capsules 22 is risen, whole hanger rope forms the cylindrical net cylinder that stands upside down, and air bag extends freeing pipe and wire drawing pipe can be hidden in above-mentioned net cylinder.
As shown in Figure 8, wire drawing pipe 31 described in the utility model is nonelastic, flexible, and as motor brake cable spool, wire drawing pipe 31 upper end is connected in the lower outside of metallic support cover 27, dismantled and assembled, after lower end extends with drive cabin roof appearance and be connected, also dismantled and assembled; Metallic support cover 27 plays a supportive role, hard nonelastic, the outside face of metallic support cover 27 offers several exhaust holes 38, can freely take a breath with the external world; Metallic support cover 27 top is firmly arranged on the lower outside surface of reinforcing annular pad 26, detachably; Reinforcing annular pad 26, outside balloon covering 1, is provided with sealing plug 28 in corresponding charge and discharge gas port, and sealing plug 28 enters and imbeds in charge and discharge gas port outside charge and discharge gas port, and during compression, gas can not release, and when unclamping, helium freely can be discharged in helium capsule 22; Stage clip 32 is arranged on sealing plug 28 and a spring in metallic support cover 27, and effect is press seal plug 28; Steel wire drawing 29 upper end and sealing plug 28 are connected, and the other end through stage clip 32 endoporus, wire drawing pipe 31 endoporus, enter drive inside, cabin through driving cabin roof, is connected through the safety draw ring 30 of extension spring 34 with band catch 33; Catch 33 plays a part to stop extension spring 34.Navigating mate pulls safety draw ring 30, extension spring 34 is stretched, stage clip 32 in metallic support cover is compressed, because steel wire drawing 29 and wire drawing pipe 31 are all nonelastic, not flexible, taper type sealing plug is unclamped downwards by charge and discharge gas port, but can not drop out, and in helium capsule 22, helium to enter through the circular gap between sealing plug 28 and charge and discharge gas port in metallic support cover 27 and to be excreted in air by exhaust hole 38; Chaufeur unclamps safety draw ring 30, and sealing plug is under the effect of stage clip 32 and extension spring 34 restoring force, and jam-pack is on the original position of charge and discharge gas port again, and helium gas emission process stops immediately.
As shown in Fig. 2,7, the driver seat 54 described in the utility model is arranged in driving compartment 4, and described driver seat 54 fills safety strap, and bottom it, four pin are fixed on chassis, the tiltable of driver seat 54, and front and back position can move; Chassis on the right side of driver seat 54 is established lever journey disk 19, and lever journey disk 19 is parallel with the left and right bulkhead of driving compartment 4.Described blower fan connecting shaft 20 is hard metal rotating shaft, and it is connected with the rotating blower fan 21 of outside through driving compartment 4, and described blower fan connecting shaft 20 is connected with fan operation handle 14 is vertical.Described storage battery 16 is arranged on the neutral gear place, bottom of driver seat 54, do not affect the adjustment at driver seat 54 front and back position and the elevation angle, described storage battery has lightweight, volume is little, capacity is large as far as possible, and safe and reliable, the not perishable feature with burning, for lithium cell, or the battery pack more outstanding than lithium cell; Its main purpose is for the utility model provides power; Control panel 12 is specifically arranged on the dead ahead of driver seat 54, and the side of described control panel 12 is provided with governor 17 and several two-direction switchs 13, and the quantity of two-direction switch 13 is identical with the quantity of rotating aircraft 21; Governor 17 described in the utility model is fan governor, and it commercially can directly be purchased, and therefore its structure repeats no more; Described two-direction switch 13 and inverter 18 all can commercially can directly be purchased, and therefore its structure repeats no more; Described governor 17 controls all rotating blower fans 21, drive synchronous rotating in same direction or synchronous different to rotation under making the effect of its electric energy in storage battery 16, the synchronous rotating in same direction of rotating blower fan 21 or synchronous different carry out specific implementation to rotation by two-direction switch 13; The outer bottom of described driving compartment 4 is provided with rope safety link 55 for subsequent use, and described rope safety link 55 for subsequent use is provided with rope 56 for subsequent use, and rope 56 for subsequent use has the pliable and tough nonelastic feature with hindering burning weather resistance, and the length of described rope safety link 55 for subsequent use is less than the length of landing shock absorption device 9.
As shown in Figure 4, the described altitude instrument 35 in the utility model is for the residing aloft instant height of this aircraft of Dynamic Announce and height change; The speed that described variometer 36 rises for this aircraft of Dynamic Announce or declines and change; Described horizontal velocity instrument 37 for this aircraft of Dynamic Announce advance or retreat speed and change; Described navigating instrument 39 plays compass and navigates; Described electricity display instrument 51 is for the electricity of storage battery 16 in this aircraft of Dynamic Announce and electric quantity change; Described charge switch 45 is for showing electricity deficiency during when the electricity display instrument 51 of this aircraft, opens charge switch 45, realizing the automatic charging of ultrathin flexible solar power pad pasting 2 pairs of storage batterys 16 in flight course; During turn off charge switch 45, charging terminates.Storage battery 16 is provided with external charge socket 42 to facilitate this aircraft when ground is overcast and rainy, uses external source to charge.Described headlamp switch 57 is for controlling illuminating lamp 41.Penetrate before illuminating lamp 41 described in the utility model comprises illuminating lamp, under penetrate illuminating lamp, interior light, outside flank indicator and steering indicating light etc.
As shown in Fig. 3,7, lever journey disk 19 described in the utility model offers the first gear 62, second gear 63, third gear position 64, fourth gear position 65, fifth gear position 66, sixth gear position 67, two are had for rotating blower fan 21, two rotating blower fans 21 are separately positioned on the both sides of driving compartment 4 outside, namely as shown in Figure 3, when fan operation handle 14 is in the third gear position 64 of lever journey disk 19, the blower fan mouth of two rotating blower fans 21 straight down; When fan operation handle 14 is in the second gear 63 of lever journey disk 19,45 degree, the oblique front lower place of blower fan mouth of two rotating blower fans 21; When fan operation handle 14 is in the first gear 62 of lever journey disk 19, the blower fan mouth of two rotating blower fans 21 is horizontal forward; When fan operation handle 14 is in the fourth gear position 65 of lever journey disk 19,45 degree, the oblique back lower place of blower fan mouth of two rotating blower fans 21; When fan operation handle 14 is in the fifth gear position 66 of lever journey disk 19, the horizontal saliva of blower fan mouth of two rotating blower fans 21 is flat backward.Sixth gear position 67 is trim locations, it is actual when using the likely side of fourth gear position 65 in fifth gear position 66 is slightly partial to, and also slightly may be partial to outer side in fifth gear position 66.Reason is: because the error of surface personnel or clump weight weight regulate improper, actual manned craft helium gross buoyancy and total force are impossible 100% equal.When buoyancy is slightly smaller than gravity, altitude instrument 35 can show this aircraft in level advance process in overall downswing, when the position of moving fan operation handle 14 to fifth gear position 66 is retracted into the position of sixth gear position 67 slightly, two rotating blower fan 21 place planes of driving compartment 4 left and right sides and they straight down time place plane between angle, be slightly smaller than 90 degree, rotating blower fan 21 can produce a downward exhaust component, offsets the gravity of manned device's surplus; When buoyancy is a bit larger tham gravity, this aircraft is in the upper parabolic motion of trace, move the position that lever exceedes fifth gear position 66, two rotating blower fan 21 place planes and they straight down time place plane between angle, be a bit larger tham 90 degree, rotating blower fan 21 produces an exhaust component upwards, offsets superfluous buoyancy, guarantees the horizontal flight that the utility model can be stable.Therefore, before taking off, accurately read tensiometer numerical value, determine the overall net buoyancy of this utility model, and accurately take chaufeur and carrying object weight, accomplish accurately to configure clump weight, very important.When needs the utility model rises, move fan operation handle 14 and make the blower fan mouth of rotating blower fan 21 straight down, rotating blower fan 21 makes rotating blower fan 21 blade synchronization be vented downwards under the effect of governor 17 and two-direction switch 13, now this aircraft does upward movement, when moving fan operation handle 14 and making the horizontal saliva of blower fan mouth of rotating blower fan 21 put down backward, rotating blower fan 21 makes rotating blower fan 21 blade synchronization to final vacuum under the effect of governor 17 and two-direction switch 13, now this aircraft does forward movement, when needs the utility model declines, move fan operation handle 14 and make the blower fan mouth of rotating blower fan 21 straight down, move all two-direction switchs 13, rotating blower fan 21 makes the downward air-breathing of rotating blower fan 21 blade synchronization under the effect of governor 17, this aircraft is made to do descending motion, when moving fan operation handle 14 and making the horizontal saliva of blower fan mouth of rotating blower fan 21 put down backward, rotating blower fan 21 makes rotating blower fan 21 blade synchronization air-breathing backward under the effect of governor 17, and this aircraft is rearward moved, when needs the utility model is turned left, the horizontal saliva of blower fan mouth that fan operation handle 14 controls rotating blower fan 21 is flat backward, move the two-direction switch 13 that rotating blower fan in left side is corresponding, make left side rotating blower fan 21 under the effect of governor 17, make rotating blower fan 21 blade air-breathing, make right side rotating blower fan 21 under the effect of governor 17, make rotating blower fan 21 blade be vented, thus realize turning left curved flight, when needs the utility model is turned right, the horizontal saliva of blower fan mouth that fan operation handle 14 controls rotating blower fan 21 is flat backward, move the two-direction switch 13 that rotating blower fan in right side is corresponding, make right side rotating blower fan 21 under the effect of governor 17, make rotating blower fan 21 blade air-breathing, make left side rotating blower fan 21 under the effect of governor 17, make rotating blower fan 21 blade be vented, thus realize turning right curved flight, described clump weight 15 be a kind of special to make, for increasing with adjustment total force of the present utility model.Need to use the material that density is comparatively large, hard is inexpensive to make, such as sand hill, cement block or ordinary metallic material make.After metering, be accurately placed on the idle position of driving compartment 4 internal backplane or driver seat 54 bottom before taking off.Clump weight using priciple: balance the superfluous buoyancy of this utility model, make this aircraft can realize air suspension in unpowered situation.For pendulum code is neat and have a smooth flight, clump weight makes the same square of fragment of brick as far as possible, has certain proportion between length; Weight also has plurality of specifications and rank, and the top of its clump weight 15 is provided with portable handle 53, picks and places to facilitate.As shown in figure 12, the operating process of the rotating blower fan 21 of four described in the utility model is identical with the operating process of two rotating blower fans 21, and two fan operation handles 14 in four rotating blower fans 21 need keep synchronous, and its method of operation repeats no more.
As shown in Figure 10, the first annunciator 61, second annunciator 49 described in the utility model and the 3rd annunciator 48 are respectively used to the temperature conditions monitoring storage battery 16, inverter 18 and rotating blower fan 21, when the temperature of storage battery 16, inverter 18 and rotating blower fan 21 is too high, first annunciator 61, second annunciator 49 and the 3rd annunciator 48 and alarm, the mode of reporting to the police is buzzing warning, light warning, music alarm or vibration alarming, or the group alarm of described any two or three type of alarm; When there is multiple inverter 18, each inverter 18 is all connected with the second annunciator 49, and when there are several rotating blower fans 21, each rotating blower fan 21 is connected respectively at the 3rd annunciator 48, to ensure the flight safety of this aircraft.
Principle of work of the present utility model is: when static in time flying, and the landing shock absorption device 9 below driving compartment 4 steadily contacts with ground, the both sides on the outer wall top of described driving compartment 4 are respectively equipped with the wire drawing ring 5 that casts anchor, the wire drawing ring 5 that casts anchor is linked up with 11 with first of wire drawing 7 one end of casting anchor of tensile force of belt instrument 6 and is connected, the other end of wire drawing 7 of casting anchor is provided with the second hook 8, two draw rings and second of the ad hoc cement flooring, aircraft service zone of this aircraft are linked up with 8 and are connected, the pulling force that wire drawing 7 of casting anchor bears is read by the tensiometer 6 cast anchor in wire drawing 7, calculate the relation of various tensiometer reading and corresponding manned device's buoyancy in advance and be made into table, table look-up according to tensiometer 6 reading during practical application, at once know that the overall clean buoyancy of current manned device is how many.Read tensiometer 6 data, table look-up and know buoyancy net value F; Electronic scale claim chaufeur body weight G1, all take articles for use weight G2, the difference of three is need to driving the clump weight total amount G increased in cabin, that is: G=F-G1-G2.This work, is generally completed by ground flying device service zone staff.Enter and drive after cabin takes a seat, the person of driving, according to the elevation angle of oneself stature adjustment driver seat 54 and front and back position, when after acquisition optimum operation position and pin hand manipulation state, fastens safety strap, checks whether fan operation handle 14 is in the position of third gear position 64; Ground flying service zone staff helps removing to cast anchor wire drawing 7, and this aircraft can be in free suspended state; Chaufeur connects total power switch 43, this aircraft is made to enter propradation, move fan operation handle 14 and make the blower fan mouth of rotating blower fan 21 straight down, rotating blower fan 21 makes rotating blower fan 21 blade synchronization be vented downwards under the effect of governor 17 and two-direction switch 13, and this aircraft starts to rise; Tune up the gear of governor 17, rotating blower fan 21 blade rotary speed is accelerated, and wind speed strengthens, and vertical velocity is accelerated thereupon.After reaching predetermined altitude, this aircraft is made to enter forward travel state, when moving fan operation handle 14 and making the horizontal saliva of blower fan mouth of rotating blower fan 21 put down backward, rotating blower fan 21 makes rotating blower fan 21 blade synchronization to final vacuum under the effect of governor 17 and two-direction switch 13, and this aircraft starts to advance.If the gross buoyancy of this aircraft and total force do not have 100% definitely equal, have a kind of totally to rise a little or downward trend in-flight, this is as can be seen from altitude instrument 35 numerical value change.Time in rising trend, fine setting fan operation handle 14 makes blower fan mouth a little less than horizon, and the exhaust component downward with blower fan offsets superfluous buoyancy; Time on a declining curve, fine setting fan operation handle 14 makes blower fan mouth a little more than horizon, offsets superfluous gravity, guarantee that aircraft steadily advances in the horizontal direction with exhaust component upwards.When this aircraft enters forward flight state, chaufeur is observed except various flight parameter and change on control panel, understanding flight dynamically except paying attention to, hand and pin can it goes without doing anything.When needs the utility model is turned left, the horizontal saliva of blower fan mouth that fan operation handle 14 controls rotating blower fan 21 is flat backward, move the two-direction switch 13 that rotating blower fan in left side is corresponding, make left side rotating blower fan 21 under the effect of governor 17, make rotating blower fan 21 blade air-breathing, make right side rotating blower fan 21 under the effect of governor 17, make rotating blower fan 21 blade be vented, thus realize turning left curved flight; When needs the utility model is turned right, the horizontal saliva of blower fan mouth that fan operation handle 14 controls rotating blower fan 21 is flat backward, move the two-direction switch 13 that rotating blower fan in right side is corresponding, make right side rotating blower fan 21 under the effect of governor 17, make rotating blower fan 21 blade air-breathing, make left side rotating blower fan 21 under the effect of governor 17, make rotating blower fan 21 blade be vented, thus realize turning right curved flight; When moving fan operation handle 14 and making the horizontal saliva of blower fan mouth of rotating blower fan 21 put down backward, rotating blower fan 21 makes rotating blower fan 21 blade synchronization air-breathing backward under the effect of governor 17, this aircraft advancing can slow down voluntarily, and continued deceleration can realize aerial static suspension subsequently or retreat flight.At the end of flight, move fan operation handle 14 to third gear position 64, move fan operation handle 14 and make the blower fan mouth of rotating blower fan 21 straight down, move all two-direction switchs 13, rotating blower fan 21 makes the downward air-breathing of rotating blower fan 21 blade synchronization under the effect of governor 17, can realize the utility model vertical landing or the landing of lower parabola.External bottom driving compartment 4 have landing bumper 9, the shock produced when effectively can cushion landing.After grease it in, ground flying service zone staff, is separately fixed at first of wire drawing 7 two ends of casting anchor of tensile force of belt instrument 6 the hook 11 and the second hook 8 and casts anchor on wire drawing ring 5 and ground draw ring, the person of driving just can unload safety strap, open hatch door, walk out out of my cabin, take off clump weight.The utility model arranges air bag and extends freeing pipe 24 and safety draw ring 30 liang cover self-rescue escape device, when running into the fault of weather reason or this aircraft itself, this aircraft aloft continues to rise or suspend when not falling, and can open air bag and extend the exhaust pipe mouth safety cap 25 bottom freeing pipe 24 or pull safety draw ring 30 to carry out and save oneself; When declining appears in this aircraft, exhaust pipe mouth safety cap 25 can be closed or allow safety draw ring 30 reset, to ensure landing flight safety.When this aircraft is in non-flight service zone emergency landing, after this aircraft is connected with neighbouring fixture by the anti-drop hook 44 of rope 56 other end for subsequent use by chaufeur, navigating mate can safe land, relievedly leave.The utility model has safety and environmental protection and the cheap feature of flight cost, without burning petroleum product, by the buoyancy of self, the weight of clump weight regulates and the power of rotating blower fan 21 gets final product follow-on mission, and power resources directly can use solar power, to ensure the flying power of this aircraft.
Claims (10)
1. a manned Electric aircraft, this aircraft comprises mechanics and circuit control part, it is characterized in that:
A, mechanics comprises balloon covering (1), the ultrathin flexible solar power pad pasting (2) that balloon covering (1) top is arranged, the driving compartment (4) that balloon covering (1) middle part is connected by hanger rope (3), the both sides on the outer wall top of described driving compartment (4) are respectively equipped with the wire drawing ring (5) that casts anchor, to cast anchor first the linking up with (11) and be connected of wire drawing of casting anchor (7) one end of wire drawing ring (5) and tensile force of belt instrument (6), the other end of wire drawing (7) of casting anchor is provided with the second hook (8), the outer bottom of described driving compartment (4) is provided with landing shock absorption device (9), the side of described driving compartment (4) outer wall offers cockpit door (10), the inside of driving compartment (4) is provided with control panel (12), two-direction switch (13), governor (17), fan operation handle (14), clump weight (15), storage battery (16), described fan operation handle (14) is located at the inside of lever journey disk (19), the bottom of fan operation handle (14) is connected with rotating blower fan (21) by blower fan connecting shaft (20), the inside of described balloon covering (1) is provided with several helium capsules (22), wherein, each helium capsule correspondence is provided with a charge and discharge gas port (23), several charge and discharge gas ports (23) described are arranged at the bottom of balloon covering (1) respectively, wherein, at least one charge and discharge gas port and air bag extend freeing pipe (24) and are connected, this air bag extends the inside that freeing pipe (24) is arranged on driving compartment (4), the tail end that described air bag extends freeing pipe (24) is provided with exhaust pipe mouth safety cap (25), have the outside of a charge and discharge gas port to be provided with in other several charge and discharge gas ports (23) to be arranged on reinforcing annular pad (26) and the metallic support cover (27) of balloon covering (1) outside face at least, sealing plug (28) is provided with in this charge and discharge gas port described, sealing plug (28) is connected with the safety draw ring (30) of driving compartment (4) internal upper part band catch (33) by steel wire drawing (29), stage clip (32) is installed between the inner bottom part of sealing plug (28) and metallic support cover (27), wire drawing pipe (31) is provided with between metallic support cover (27) and driving compartment (4) outer top, described steel wire drawing (29) is through stage clip (32), wire drawing pipe (31) is connected with the safety draw ring (30) of extension spring (34) with band catch (33), described extension spring (34) is arranged between catch (33) and driving compartment (4) internal upper part, the outside face of described metallic support cover (27) offers several exhaust holes (38), the outside of described driving compartment (4) is provided with anemoscope (40), and described driving compartment (4) is provided with illuminating lamp (41),
B, circuit control part comprises ultrathin flexible solar power pad pasting (2), ultrathin flexible solar power pad pasting (2) is connected with storage battery (16) by charge switch (45), described storage battery (16) is provided with external charge socket (42), storage battery (16) is connected with two-direction switch (13) with governor (17) by battery isolator control (43), described two-direction switch (13) is connected with rotating blower fan (21) by inverter (18), described control panel (12) is provided with the electricity display instrument (51) be connected with storage battery (16), altitude instrument (35), variometer (36), horizontal velocity instrument (37) and navigating instrument (39), described storage battery (16) is connected with illuminating lamp (41) by headlamp switch (57), and described charge switch (45), battery isolator control (43) and headlamp switch (57) are located on control panel (12) respectively, described storage battery (16), inverter (18) and rotating blower fan (21) are respectively equipped with the first temperature sensor (58), second temperature sensor (59) and three-temperature sensor (60), described first temperature sensor (58), second temperature sensor (59) and three-temperature sensor (60) are respectively by wire and corresponding the first annunciator (61), second annunciator (49) is connected with the 3rd annunciator (48), described first annunciator (61), second annunciator (49) and the 3rd annunciator (48) are located on control panel (12) respectively.
2. the manned Electric aircraft of one according to claim 1, is characterized in that: described hanger rope (3) is at least three; Described landing shock absorption device (9) is at least three; Described storage battery (16) is at least one; Described sealing plug (28) is taper type sealing plug, adopt hinge (50) to be connected between described cockpit door (10) with driving compartment (4), cockpit door (10) top offers clear glass window (52); The top of described clump weight (15) is provided with portable handle (53).
3. the manned Electric aircraft of one according to claim 1, is characterized in that: described two charge and discharge gas ports (23) extend freeing pipe (24) with two air bags respectively and are connected.
4. the manned Electric aircraft of one according to claim 1, it is characterized in that: described rotating blower fan (21) is two, it is separately positioned on the outside both sides of driving compartment (4), blower fan connecting shaft (20) is yi word pattern, two rotating blower fans (21) are separately positioned on the two ends of blower fan connecting shaft (20), blower fan connecting shaft (20) is provided with fan operation handle (14), described two rotating blower fans (21) are connected with corresponding two inverters (18) respectively, described two inverters (18) are connected with corresponding two two-direction switchs (13) respectively, two two-direction switchs (13) are connected with storage battery (16) with battery isolator control (43) respectively by governor (17), described two inverters (18) are respectively equipped with the second temperature sensor (59), and two the second temperature sensors (59) are connected with the second annunciator (49) respectively.
5. the manned Electric aircraft of one according to claim 1, it is characterized in that: the both sides of described driving compartment (4) outside are respectively equipped with two rotating blower fans (21), described blower fan connecting shaft (20) is two, its shape is yi word pattern, the two ends of two blower fan connecting shafts (20) are respectively equipped with rotating blower fan (21), described two blower fan connecting shafts (20) are connected with the bottom of corresponding two fan operation handles (14) respectively, four rotating blower fans (21) are connected with corresponding four inverters (18) respectively, described four inverters (18) are connected with corresponding four two-direction switchs (13) respectively, four two-direction switchs (13) are connected with storage battery (16) with battery isolator control (43) respectively by governor (17), described four inverters (18) are respectively equipped with the second temperature sensor (59), and four the second temperature sensors (59) are connected with the second annunciator (49) respectively.
6. the manned Electric aircraft of one according to claim 1, it is characterized in that: the inside of described driving compartment (4) is provided with driver seat (54), and described storage battery (16) is arranged on the bottom of driver seat (54).
7. the manned Electric aircraft of one according to claim 1, it is characterized in that: the outer bottom of described driving compartment (4) is provided with the rope safety link (55) for subsequent use of integrative-structure, described rope safety link (55) for subsequent use is connected with one end of rope for subsequent use (56), the other end of rope for subsequent use (56) is provided with anti-drop hook (44), and described anti-drop hook (44) is connected with the rope curling device (47) for subsequent use that driving compartment (4) wall outer surface is arranged.
8. the manned Electric aircraft of one according to claim 1, is characterized in that: described anemoscope (40) is connected with the anemoscope display instrument (46) on control panel (12) by wire.
9. the manned Electric aircraft of one according to claim 1, is characterized in that: described lever journey disk (19) offers the first gear (62), the second gear (63), third gear position (64), fourth gear position (65), fifth gear position (66) and sixth gear position (67) respectively.
10. the manned Electric aircraft of one according to claim 1, is characterized in that: described storage battery (16) is lithium cell group.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420587428.6U CN204173152U (en) | 2014-09-22 | 2014-09-22 | A kind of manned Electric aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420587428.6U CN204173152U (en) | 2014-09-22 | 2014-09-22 | A kind of manned Electric aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN204173152U true CN204173152U (en) | 2015-02-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420587428.6U Expired - Fee Related CN204173152U (en) | 2014-09-22 | 2014-09-22 | A kind of manned Electric aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN204173152U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106218853A (en) * | 2016-09-30 | 2016-12-14 | 德保县实验小学 | A kind of hot air balloon device |
-
2014
- 2014-09-22 CN CN201420587428.6U patent/CN204173152U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106218853A (en) * | 2016-09-30 | 2016-12-14 | 德保县实验小学 | A kind of hot air balloon device |
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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: 20150225 Termination date: 20170922 |