CN104326078B - Manned Electric aircraft - Google Patents
Manned Electric aircraft Download PDFInfo
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- CN104326078B CN104326078B CN201410532901.5A CN201410532901A CN104326078B CN 104326078 B CN104326078 B CN 104326078B CN 201410532901 A CN201410532901 A CN 201410532901A CN 104326078 B CN104326078 B CN 104326078B
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- driving cabin
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Abstract
The invention belongs to manned technical field of aerospace, be specifically related to a kind of manned Electric aircraft；This aircraft includes mechanical part and circuit control part, a, mechanical part include the driving cabin connected in the middle part of balloon eyelid covering, the ultrathin flexible solar energy pad pasting of balloon eyelid covering top setting, balloon eyelid covering by hanger rope, b, circuit control part include ultrathin flexible solar energy pad pasting, ultrathin flexible solar energy pad pasting is connected with accumulator by charge switch, described accumulator is provided with external charge socket, and accumulator is connected with rotating blower fan with controller by battery main switch；Having simple in construction, cheap, environmental protection, clean energy resource, loading capacity adjustable, operating flexibility is good, the advantage of shipping cost guarantee navigation safety low, many-sided.
Description
Technical field
The invention belongs to manned technical field of aerospace, be 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 France Robert brother is flushed with hydrogen taking a flight test of gas HIKOUSEN.French engineer Ji Faer in 1852 manufactured and designed air bag be 2500 cubic metres, handling of promoting with steam engine that propeller is onward impulse be flushed with hydrogen gas dirigible.Later, soft balloon dirigible was replaced by the rigid airship of metal, timber frame covering eyelid covering again.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.De Laige dirigible airline of Germany was only achieved that the achievement of dirigible aviation 2,140,000 kilometers, safe carrying 35000 person-times from 1910 to 1914.Germany manufactures successful Hindenburg dirigible length 245 meters for 1936, diameter 41 meters, total bag volume are 20 ten thousand steres, gross weight 230 tons, the electromotor that power is 4 610 kilowatts, carrying 75, the speed of a ship or plane reaches 130 kilometers/hour, cruising time 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 prominent effect.But the termination of dirigible aircraft industry, also have an accident for mark with Hindenburg dirigible unexpected blast on fire when New Jersey lands on May 6 nineteen thirty-seven just.But dirigible aviation is replaced not accidentally by emerging aircraft aviation, and its necessity is in that two big defects of inflation airship at that time: one be most of dirigible institute inflatable body is flammable explosive hydrogen；Two it is bulky dirigible malfunction, is difficult to cope with contingencies.20 century 70s, inflatable vehicle starts again recovery, but there is the defect of loading capacity, shipping cost and safety still cannot overcome, especially the energy of its consumption is substantially oil product, when world energy sources, oil shortage are day by day serious, undoubtedly the fast development of the industry is also existed serious restriction；And such aircraft pollution on the environment is also very important.
Summary of the invention
It is an object of the invention to overcome defect of the prior art, and provide a kind of loading capacity adjustable, operating flexibility is good, the manned Electric aircraft of shipping cost guarantee navigation safety low, many-sided.
The object of the present invention is achieved like this: this aircraft includes mechanical part and circuit control part,
A, mechanical part includes balloon eyelid covering, the ultrathin flexible solar energy pad pasting that balloon eyelid covering top is arranged, the driving cabin connected by hanger rope in the middle part of balloon eyelid covering, the outer wall top of described driving cabin be respectively provided on two sides with the wire drawing ring that casts anchor, cast anchor wire drawing ring wire drawing one end of casting anchor with tensile force of belt instrument first hook be connected, the other end of wire drawing of casting anchor is provided with the second hook, the outer bottom of described driving cabin is provided with landing shock absorption device, the side of described driving cabin outer wall offers cockpit door, the inside of driving cabin is provided with control panel, the fixing bar being connected with driving cabin, fan operation hands handle, balancing weight, accumulator and blower fan wind speed foot controling pedal；Described fixing bar is provided with blower fan wind speed manual control cruise handle, 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 eyelid covering is provided with several helium capsules, wherein, each helium capsule is correspondingly arranged on a charge and discharge QI KOU, several charge and discharge QI KOU described are respectively arranged at the bottom of balloon eyelid covering, wherein, at least one charge and discharge QI KOU extends exhaustor 24 with air bag and is connected, this air bag extends exhaustor and is arranged on the inside of driving cabin, described air bag extends the tail end of exhaustor and is provided with exhaust pipe mouth safety helmet, what have at least a charge and discharge QI KOU in other several charge and discharge QI KOU is provided externally with the reinforcing annular pad and metal rack cover that are arranged on balloon eyelid covering outer surface, this charge and discharge QI KOU described is provided with sealing-plug, sealing-plug is connected with the driving cabin internal upper part safety draw ring with catch by steel wire drawing, between the inner bottom part of sealing-plug and metal rack cover, stage clip is installed, it is provided with wire drawing pipe between metal rack cover and the outer top of driving cabin, described steel wire drawing traverse stage clip, wire drawing pipe is connected with the safety draw ring with catch with extension spring, described extension spring is arranged between catch and driving cabin internal upper part, the outer surface of described metal rack cover offers several exhaust holes；Described driving cabin be provided externally with anemobiagraph, described driving cabin is provided with illuminating lamp；
B, circuit control part includes ultrathin flexible solar energy pad pasting, ultrathin flexible solar energy pad pasting is connected with accumulator by charge switch, described accumulator is provided with external charge socket, accumulator is connected with rotating blower fan with controller by battery main switch, described blower fan wind speed manual control cruise handle is connected with controller respectively with blower fan wind speed foot controling pedal, described controller respectively with the back on control panel, forwarding button, turn left button and be connected with button of turning right, described control panel is provided with the electricity display instrument being connected with accumulator, altimeter, variometer, horizontal velocity instrument and navigator；Described accumulator is connected with illuminating lamp by headlamp switch, and described charge switch, battery main switch and headlamp switch are respectively provided on control panel；Described accumulator, controller 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 first corresponding alarm, the second alarm and the 3rd alarm respectively through wire with three-temperature sensor, and described first alarm, the second alarm and the 3rd alarm are respectively provided on control panel.
Described hanger rope is at least three；Described landing shock absorption device is at least three；Described accumulator is at least one；Described sealing-plug is taper type sealing-plug, adopts hinge to be connected between described cockpit door and driving cabin, and cockpit door top offers clear glass window；The top of described balancing weight is provided with portable handle.Said two charge and discharge QI KOU extends exhaustor with two air bags respectively and is connected.Described rotating blower fan is two, it is separately positioned on the both sides outside driving cabin, 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, said two rotating blower fan is connected with two corresponding controllers respectively, said two controller is connected with blower fan wind speed manual control cruise handle and blower fan wind speed foot controling pedal respectively, said two controller is respectively equipped with the second temperature sensor, and the second temperature sensor is connected with the second alarm.It is respectively provided on two sides with two rotating blower fans outside described driving cabin, described blower fan connecting shaft is two, it is shaped as yi word pattern, two blower fan connecting shafts be respectively arranged at two ends with rotating blower fan, said two blower fan connecting shaft is connected with the bottom of two corresponding fan operation handles respectively, four rotating blower fans are connected with four corresponding controllers respectively, described four controllers are connected with blower fan wind speed manual control cruise handle and blower fan wind speed foot controling pedal respectively, described four controllers are respectively equipped with the second temperature sensor, and second temperature sensor be connected with the second alarm.The inside of described driving cabin is provided with driver seat, and described accumulator is arranged on the bottom of driver seat.The outer bottom of described driving cabin is provided with the standby rope safety collar of integrative-structure, described standby rope safety collar is connected with one end of standby rope, the other end of standby rope is provided with anti-drop hook, and described anti-drop hook is connected with the standby rope curling device arranged on driving cabin wall outer surface.Described anemobiagraph is connected with the anemobiagraph display instrument on control panel by wire.Described lever journey disk offers the first gear, the second gear, third gear, fourth speed position, fifth speed position and sixth speed position respectively.Described accumulator is lithium battery group.
According to the manned Electric aircraft that such scheme is made, in use owing to the quantity of balloon eyelid covering helium gas inside capsule is relative with volume stable, therefore realize the stochastic equilibrium of gross buoyancy and gross weight by adjusting the weight of balancing weight, create the condition that this aircraft is weightless；By arranging air bag extends exhaustor, steel wire drawing connects sealing-plug and safety draw ring with catch and standby rope ensures the flight safety of aircraft；Realize the advance of aircraft, retrogressing, rise by positive and negative the transferring changing the air blower position of rotating blower fan and fan blade, land, turn left curved or turn right curved；Having simple in construction, cheap, environmental protection, clean energy resource, loading capacity adjustable, operating flexibility is good, the advantage of shipping cost guarantee navigation safety low, many-sided.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the structural representation of side of the present invention；
Fig. 3 is the structural scheme of mechanism of lever journey disk of the present invention and fan operation handle；
Fig. 4 is the control panel structural representation of the present invention；
Fig. 5 is the structural representation of balancing weight of the present invention；
Fig. 6 is the structural representation of cockpit door of the present invention；
Fig. 7 is the structural representation of cockpit of the present invention；
Fig. 8 is the structural representation of steel wire drawing of the present invention and safety draw ring；
Fig. 9 is the structural representation of metal rack cover of the present invention；
The circuit that Figure 10 is the present invention controls frame principle figure；
Figure 11 is the structural representation within balloon eyelid covering of the present invention；
Figure 12 is the structural representation of four rotating blower fans of the present invention.
Detailed description of the invention
As shown in Fig. 1,2,3,4,5,6,7,8,9,10,11, the manned Electric aircraft of the present invention, this aircraft includes mechanical part and circuit control part,
A, mechanical part includes balloon eyelid covering 1, the ultrathin flexible solar energy pad pasting 2 that balloon eyelid covering 1 top is arranged, the driving cabin 4 connected by hanger rope 3 in the middle part of balloon eyelid covering 1, the outer wall top of described driving cabin 4 be respectively provided on two sides with the wire drawing ring 5 that casts anchor, first hook of wire drawing ring 5 wire drawing 7 one end of casting anchor with tensile force of belt instrument 6 of casting anchor 11 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 cabin 4 is provided with landing shock absorption device 9, the side of described driving cabin 4 outer wall offers cockpit door 10, the inside of driving cabin 4 is provided with control panel 12, the fixing bar 13 being connected with driving cabin 4, fan operation handle 14, balancing weight 15, accumulator 16 and blower fan wind speed foot controling pedal 17；Described fixing bar 13 is provided with blower fan wind speed manual control cruise handle 18, 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 eyelid covering 1 is provided with several helium capsules 22, wherein, each helium capsule is correspondingly arranged on a charge and discharge QI KOU 23 respectively, several charge and discharge QI KOU 23 described are respectively arranged at the bottom of balloon eyelid covering 1, wherein, at least one charge and discharge QI KOU extends exhaustor 24 with air bag and is connected, this air bag extends exhaustor 24 and is arranged on the inside of driving cabin 4, described air bag extends the tail end of exhaustor 24 and is provided with exhaust pipe mouth safety helmet 25, what have at least a charge and discharge QI KOU in other several charge and discharge QI KOU 23 is provided externally with the reinforcing annular pad 26 and metal rack cover 27 that are arranged on balloon eyelid covering 1 outer surface, this charge and discharge QI KOU described is provided with sealing-plug 28, sealing-plug 28 is connected with driving cabin 4 internal upper part safety draw ring 30 with catch 33 by steel wire drawing 29, stage clip 32 is installed between the inner bottom part of sealing-plug 28 and metal rack cover 27, it is provided with wire drawing pipe 31 between metal rack cover 27 and the outer top of driving cabin 4, described steel wire drawing 29 traverse stage clip 32, wire drawing pipe 31 is connected with the safety draw ring 30 with catch 33 with extension spring 34, described extension spring 34 is arranged between catch 33 and driving cabin 4 internal upper part, the outer surface of described metal rack cover 27 offers several exhaust holes 38；Described driving cabin 4 be provided externally with anemobiagraph 40, described driving cabin 4 is provided with illuminating lamp 41；
B, circuit control part includes ultrathin flexible solar energy pad pasting 2, ultrathin flexible solar energy pad pasting 2 is connected with accumulator 16 by charge switch 45, described accumulator 16 is provided with external charge socket 42, accumulator 16 is connected with rotating blower fan 21 with controller 44 by battery main switch 43, described blower fan wind speed manual control cruise handle 18 is connected with controller 44 respectively with blower fan wind speed foot controling pedal 17, described controller 44 respectively with the back 46 on control panel 12, forwarding button 47, turn left button 48 and be connected with button 49 of turning right, described control panel 12 is provided with the electricity display instrument 51 being connected with accumulator 16, altimeter 35, variometer 36, horizontal velocity instrument 37 and navigator 39；Described accumulator 16 is connected with illuminating lamp 41 by headlamp switch 57, and described charge switch 45, battery main switch 43 and headlamp switch 57 are respectively provided on control panel 12；Described accumulator 16, controller 44 and rotating blower fan 21 are respectively equipped with first temperature sensor the 58, second temperature sensor 59 and three-temperature sensor 60, described first temperature sensor the 58, second temperature sensor 59 is connected with first corresponding alarm the 61, second alarm 62 and the 3rd alarm 63 respectively through wire with three-temperature sensor 60, and described first alarm the 61, second alarm 62 and the 3rd alarm 63 are respectively provided on control panel 12.
Described hanger rope 3 is at least three；Described landing shock absorption device 9 is at least three；Described accumulator 16 is at least one；Described sealing-plug 28 is taper type sealing-plug, adopts hinge 50 to be connected between described cockpit door 10 and driving cabin 4, and cockpit door 10 top offers clear glass window 52；The top of described balancing weight 15 is provided with portable handle 53.Said two charge and discharge QI KOU 23 extends exhaustor 24 with two air bags respectively and is connected.Described rotating blower fan 21 is two, it is separately positioned on the both sides outside driving cabin 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, said two rotating blower fan 21 is connected with corresponding two controllers 44 respectively, said two controller 44 is connected with blower fan wind speed manual control cruise handle 18 and blower fan wind speed foot controling pedal 17 respectively, said two controller 44 is respectively equipped with the second temperature sensor 59, and second temperature sensor 59 be connected with the second alarm.It is respectively provided on two sides with two rotating blower fans 21 outside described driving cabin 4, described blower fan connecting shaft 20 is two, it is shaped as yi word pattern, two blower fan connecting shafts 20 be respectively arranged at two ends with rotating blower fan 21, said two blower fan connecting shaft 20 is connected with the bottom of two corresponding fan operation handles 14 respectively, four rotating blower fans 21 are connected with corresponding four controllers 44 respectively, described four controllers 44 are connected with blower fan wind speed manual control cruise handle 18 and blower fan wind speed foot controling pedal 17 respectively, described four controllers 44 are respectively equipped with the second temperature sensor 59, and second temperature sensor 59 be connected with the second alarm.The inside of described driving cabin 4 is provided with driver seat 54, and described accumulator 16 is arranged on the bottom of driver seat 54.The outer bottom of described driving cabin 4 is provided with the standby rope safety collar 55 of integrative-structure, described standby rope safety collar 55 is connected with one end of standby rope 56, the other end of standby rope 56 is provided with anti-drop hook 66, and described anti-drop hook 66 is connected with the standby rope curling device 64 arranged on driving cabin 4 wall outer surface.Described anemobiagraph 40 is connected with the anemobiagraph display instrument 65 on control panel 12 by wire.Described lever journey disk 19 offers first gear the 67, second gear 68, third gear 69, fourth speed position 70, fifth speed position 71 and sixth speed position 72 respectively.Described accumulator 16 is lithium battery group.
As shown in Fig. 1,2,11, several helium capsules 22 heretofore described all can realize filling simultaneously, putting helium by several corresponding charge and discharge QI KOU 23, or wherein helium capsule is only carried out independent inflation, bleed air operation by a certain moment；In the present invention, 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 eyelid covering 1 and helium capsule 22 foldable transportation, balloon eyelid covering 1 and helium capsule 22 molding tympanites during sufficient gas, it can be made aloft to increase by the effect of buoyancy, several helium capsules 22 multiple primarily serve two effects: first, it is able to ensure that under the fortuitous event of Local Damaged, the unlikely runaway condition making manned device be in rapidly decline because of rapid blow-down helium of balloon；Second, can arbitrarily determine the loading capacity of the present invention, when needs loading capacity increases, multiple large-scale helium capsule 22 is set, when need not too load capacity time, multiple less helium capsule 22 is set.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 ropes form the cylindrical net cylinder that stands upside down, and air bag extends exhaustor and wire drawing pipe can be hidden in above-mentioned net cylinder.
As shown in Figure 8, heretofore described wire drawing pipe 31 is nonelastic, flexible, and as motor brake cable spool, wire drawing pipe 31 upper end is connected in the lower outside of metal rack cover 27, dismantled and assembled, lower end extend after with drive cabin roof appearance be connected, it is possible to dismounting；Metal rack cover 27 plays a supportive role, hard nonelastic, the outer surface of metal rack cover 27 offers several exhaust holes 38, can freely take a breath with the external world；Metal rack cover 27 top is fixedly attached to the lower outside surface of reinforcing annular pad 26, detachably；Reinforcing annular pad 26, outside balloon eyelid covering 1, is provided with sealing-plug 28 in corresponding charge and discharge QI KOU, sealing-plug 28 enters outside charge and discharge QI KOU and imbeds in charge and discharge QI KOU, and during compression, gas can not release, and when unclamping, helium freely can be discharged in helium capsule 22；Stage clip 32 is provided in sealing-plug 28 and a spring in metal rack cover 27, and effect is to compress sealing-plug 28；Steel wire drawing 29 upper end is connected with sealing-plug 28, and the other end is driven cabin roof entrance drive inside cabin through stage clip 32 endoporus, wire drawing pipe 31 endoporus, traverse, is connected through extension spring 34 with the safety draw ring 30 with catch 33；Catch 33 acts the effect stopping extension spring 34.Human pilot pulls safety draw ring 30, extension spring 34 is stretched, stage clip 32 in metal rack cover is compressed, owing to steel wire drawing 29 and wire drawing pipe 31 are all nonelastic, not flexible, taper type sealing-plug is unclamped downwards in charge and discharge QI KOU, but will not drop out, and in helium capsule 22, the circular gap between helium end count blocking 28 and charge and discharge QI KOU enters in metal rack cover 27 and is excreted in air by exhaust hole 38；Driver unclamps safety draw ring 30, and sealing-plug is under the effect of stage clip 32 and extension spring 34 restoring force, and plug is tightened on the position that charge and discharge QI KOU is original again, and helium gas emission process terminates immediately.
Such as Fig. 2, shown in 7, heretofore described driver seat 54 is arranged in driving cabin 4, and described driver seat 54 fills seat belt, and bottom it, four feet 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 sets lever journey disk 19, and lever journey disk 19 is parallel with the left and right bulkhead of driving cabin 4.Described blower fan connecting shaft 20 is hard metal rotating shaft, and it is connected through driving cabin 4 with outside rotating blower fan 21, and described blower fan connecting shaft and fan operation handle 14 are vertically connected.Described accumulator 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 accumulator has lightweight, volume is little, capacity is big and safe and reliable as far as possible, the not perishable feature with burning, for lithium battery, or the accumulator battery more more excellent than lithium battery；Its main purpose is to provide power for the present invention；Control panel 12 is specifically located at the dead ahead of driver seat 54, the bottom of control panel 12 is provided with blower fan wind speed foot controling pedal 17, heretofore described blower fan wind speed foot controling pedal 17 adopts right crus of diaphragm to manipulate, described control panel 12 top is provided with one and laterally fixes bar 13, driver's right-hand operated blower fan wind speed manual control cruise handle 18, heretofore described blower fan wind speed foot controling pedal 17, blower fan wind speed manual control cruise handle 18 and controller 44 all adopt the control pedal in electric motor car, manual cruise handle and controller, it commercially can directly be purchased, therefore its structure repeats no more；Described controller 44 is without Hall type with volt (voltage) number same specification, has cruise function.Each controller 44 connects a rotating blower fan 21, and controller 44 is supporting with the voltage of rotating blower fan 21.When rotating blower fan 21 is several, driver's right hand holds blower fan wind speed manual control cruise handle 18 rotation or foot steps on blower fan wind speed foot controling pedal 17, several controllers 44 drive rotating blower fan 21 synchronous axial system in accumulator 16 under the effect of electric energy, and fan blade increases rotating speed with handle degree of rotation and increases therewith；Change the electric current of any portion blower fan in several rotating blower fans 21 and pass through direction, it may be achieved multiple blower fans synchronize incorgruous rotation.The outer bottom of described driving cabin 4 is provided with standby rope safety collar 55, and described standby rope safety collar 55 is provided with standby rope 56, and standby rope 56 has pliable and tough nonelastic and resistance burning weather resistance feature, and the length of described standby rope safety collar 55 is less than the length of landing shock absorption device 9.
Such as Fig. 4, shown in 10, the described altimeter 35 in the present invention is for the residing aloft instant height of this aircraft of Dynamic Announce and height change；Described variometer 36 is used for speed and the change that this aircraft of Dynamic Announce rises or falls；Described horizontal velocity instrument 37 is used for the advance of this aircraft of Dynamic Announce or the speed retreated and change；Described navigator 39 plays the effect that compass is navigated；Described electricity display instrument 51 is used for electricity and the electric quantity change of accumulator 16 in this aircraft of Dynamic Announce；Described charge switch 45 is for when the electricity display instrument 51 of this aircraft shows electricity deficiency, opening charge switch 45, it is achieved the ultrathin flexible solar energy pad pasting 2 automatic charging to accumulator 16 in flight course；During turn off charge switch 45, charging terminates.Accumulator 16 is provided with external charge socket 42 to facilitate this aircraft when ground is overcast and rainy, uses external power supply to be charged.Described headlamp switch 57 is used for controlling illuminating lamp 41.Heretofore described illuminating lamp 41 penetrate before including illuminating lamp, under penetrate illuminating lamp, interior light, outside clearance lamps and steering indicating light etc..
Such as Fig. 3, shown in 7, heretofore described lever journey disk 19 offers first gear the 67, second gear 68, third gear 69, fourth speed position 70, fifth speed position 71 and sixth speed position 72, two are had for rotating blower fan 21, two rotating blower fans 21 are separately positioned on the both sides outside driving cabin 4, namely as shown in Figure 3, when fan operation handle 14 is in the third gear 69 of lever journey disk 19, the blower fan mouth of two rotating blower fans 21 is straight down；When fan operation handle 14 is in the second gear 68 of lever journey disk 19, the blower fan mouth of two rotating blower fans 21 is 45 degree, lower section diagonally forward；When fan operation handle 14 is in the first gear 67 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 speed position 70 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 speed position 71 of lever journey disk 19, the horizontal saliva of blower fan mouth of two rotating blower fans 21 is flat backward.Sixth speed position 72 is a trim locations, the likely side of fourth speed position 70 in fifth speed position 71 is slightly partial to when it is actually used, it is also possible to be slightly partial to outer side in fifth speed position 71.Reason is: owing to the error of surface personnel or balancing weight weight regulate improper, actual manned vehicle helium gross buoyancy is impossible with total force 100% equal.When buoyancy is slightly smaller than gravity, altimeter 35 can show that this aircraft is overall downward trend in horizontally advancing process, when moving the position that the position of fan operation handle 14 to fifth speed position 71 is retracted into sixth speed position 72 slightly, two rotating blower fan 21 place planes of driving cabin 4 left and right sides and they straight down time place plane between angle, it is slightly smaller than 90 degree, rotating blower fan 21 can produce a downward aerofluxus component, offsets the gravity that manned device is superfluous；When buoyancy is a bit larger tham gravity, this aircraft is the upper parabolic motion of trace, move lever and exceed the position of fifth speed position 71, two rotating blower fan 21 place planes and they straight down time place plane between angle, it is a bit larger tham 90 degree, rotating blower fan 21 produces an aerofluxus component upwards, offsets superfluous buoyancy, it is ensured that the horizontal flight that the present invention can be stable.Therefore, before taking off, accurately read tensiometer numerical value, it is determined that the overall net buoyancy of this invention, and accurately weigh driver and carrying object weight, accomplish accurately to configure balancing weight, particularly significant.When described forwarding button 47 is pressed, moving fan operation handle 14 makes the blower fan mouth of rotating blower fan 21 straight down, rotating blower fan 21 makes the downward aerofluxus of blade synchronization of rotating blower fan 21 under the effect of blower fan wind speed manual control cruise handle 18 or blower fan wind speed foot controling pedal 17, this aircraft does ascending motion, when move fan operation handle 14 make the horizontal saliva of blower fan mouth of rotating blower fan 21 flat backward time, this aircraft forwards moves；When described back 46 is pressed, fan operation handle 14 controls the blower fan mouth of rotating blower fan 21 straight down, rotating blower fan 21 makes the downward air-breathing of blade synchronization of rotating blower fan 21 under the effect of blower fan wind speed manual control cruise handle 18 or blower fan wind speed foot controling pedal 17, this aircraft does descending motion, when the horizontal saliva of blower fan mouth that fan operation handle 14 controls rotating blower fan 21 is put down backward, this aircraft rearward moves；When described button 48 of turning left is pressed, the horizontal saliva of blower fan mouth that fan operation handle 14 controls rotating blower fan 21 is flat backward, rotating blower fan 21 makes the blade air-breathing of left side rotating blower fan 21 under the effect of blower fan wind speed manual control cruise handle 18 or blower fan wind speed foot controling pedal 17, make the blade aerofluxus of right side rotating blower fan 21, thus the curved flight that realizes turning left；When described button 49 of turning right is pressed, the horizontal saliva of blower fan mouth that fan operation handle 14 controls rotating blower fan 21 is flat backward, rotating blower fan 21 makes the blade aerofluxus of left side rotating blower fan 21 under the effect of blower fan wind speed manual control cruise handle 18 or blower fan wind speed foot controling pedal 17, make the blade air-breathing of right side rotating blower fan 21, thus the curved flight that realizes turning right.Described balancing weight 15 is a kind of special making, for increasing and regulate the total force of the present invention.Needing to use the material that density is relatively big, hard is inexpensive to make, such as sand hill, cement block or ordinary metallic material make.Before taking off after metering, be accurately placed on the idle position of driving cabin 4 internal backplane or driver seat 54 bottom.Balancing weight using priciple: balance this invention surplus buoyancy, make this aircraft can realize air suspension in unpowered situation.Neatly and having a smooth flight for pendulum code, balancing weight makes the square that fragment of brick is the same as far as possible, has certain proportion between length；Weight also has plurality of specifications and rank, and the top of its balancing weight 15 is provided with portable handle 53, picks and places to facilitate.As shown in figure 12, the operating process of four heretofore described rotating blower fans 21 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 to keep synchronizing, and its operational approach repeats no more.
Such as Fig. 4, shown in 10, first described alarm the 61, second alarm 62 and the 3rd alarm 63 are respectively used to the temperature conditions of monitoring accumulator 16, controller 44 and rotating blower fan 21, when the temperature of accumulator 16, controller 44 and rotating blower fan 21 is too high, first alarm the 61, second alarm 62 and the 3rd alarm 63 and alarm, the mode reported 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 controller 44, each controller 44 is all connected with the second alarm 62, and when there are several rotating blower fans 21, each rotating blower fan 21 is connected respectively at the 3rd alarm 63, to ensure the flight safety of this aircraft.
The operation principle of the present invention is: when static in time flying, and the landing shock absorption device 9 below driving cabin 4 steadily contacts with ground；The outer wall top of described driving cabin 4 be respectively provided on two sides with the wire drawing ring 5 that casts anchor, first hook of wire drawing ring 5 wire drawing 7 one end of casting anchor with tensile force of belt instrument 6 of casting anchor 11 is connected, the other end of wire drawing 7 of casting anchor is provided with the second hook 8, two draw rings of the ad hoc cement flooring of aircraft service area of this aircraft and the second hook 8 are connected, by casting anchor, the tensiometer 6 in wire drawing 7 reads the pulling force that wire drawing 7 of casting anchor is born, calculate the relation of various tensiometer reading and corresponding manned device's buoyancy in advance and be fabricated to 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 driver body weight G1, all take articles for use weight G2, the difference of three is need to driving the balancing weight total amount G increased in cabin, it may be assumed that G=F-G1-G2.This work, is generally completed by ground flying device service area staff.Entrance is driven after cabin takes a seat, and the person of driving adjusts the elevation angle and the front and back position of driver seat 54 according to oneself stature, after obtaining optimal performance position and foot hands manipulation state, fastens seat belt, checks whether fan operation handle 14 is in the position of third gear 69；Ground flying service area staff helps removing to cast anchor wire drawing 7, and namely this aircraft can be at free suspended state；Driver connects total power switch 43, press the forwarding button 47 on control panel 12, the right hand hold blower fan wind speed manual control cruise handle 18 and slowly rotate or foot step on blower fan wind speed foot controling pedal 17, rotating blower fan 21 starts air port and synchronizes downwards aerofluxus, and this aircraft begins to ramp up；Blower fan wind speed manual control cruise handle 18 anglec of rotation increase or foot step on blower fan wind speed foot controling pedal 17 put more effort wind speed strengthen, vertical velocity is accelerated therewith.After reaching predetermined altitude, unclamp blower fan wind speed manual control cruise handle 18 or blower fan wind speed foot controling pedal 17, the right hand moves the position of fan operation handle 14 to fifth speed position 71, then the right hand hold blower fan wind speed manual control cruise handle 18 and slowly rotate or foot step on blower fan wind speed foot controling pedal 17, making 21 mouthfuls of horizontal saliva of rotating blower fan put down to final vacuum, this aircraft starts flight forward.If the gross buoyancy of this aircraft does not have 100% definitely equal with total force, having a kind of trend totally somewhat risen or fallen in-flight, this can be seen that from altimeter 35 change in value.Time in rising trend, fine setting fan operation handle 14 makes blower fan mouth slightly below horizontal line, offsets superfluous buoyancy with the aerofluxus component that blower fan is downward；Time on a declining curve, fine setting fan operation handle 14 makes blower fan mouth slightly above horizontal line, offsets superfluous gravity with aerofluxus component upwards, it is ensured that aircraft steadily advances in the horizontal direction.Owing to controller 44 has cruise function, driver's hand-screw blower fan wind speed manual control cruise handle 18 or foot are stepped on blower fan wind speed foot controling pedal 17 and are only needed several seconds transfixion, and namely this aircraft enters automatic cruising flight.Driver observes on control panel except various flight parameters and change, understanding flight dynamically except paying attention to, hands and foot can it goes without doing anything.When turning round, first right hand rotation blower fan wind speed manual control cruise handle 18 or foot step on blower fan wind speed foot controling pedal 17, cruise is made to lose efficacy, press turn left button 48 or button 49 of turning right, turn blower fan wind speed manual control cruise handle 18 or foot step on blower fan wind speed foot controling pedal 17 again, and namely this aircraft enters curved or curved state of turning right of turning left.When pressing back 46, and rotation blower fan wind speed manual control cruise handle 18 or foot step on blower fan wind speed foot controling pedal 17 again, and this aircraft advancing can slow down voluntarily, and continued deceleration can realize aerial static suspension subsequently or retreat flight.When blower fan wind speed manual control cruise handle 18 is out of order, blower fan wind speed foot controling pedal 17 can be used.When flight terminates, move fan operation handle 14 to third gear 69, make back 46 in running order, rotate blower fan wind speed manual control cruise handle 18 or foot is stepped on blower fan wind speed foot controling pedal 17 and can be realized vertical landing or the landing of lower parabola of the present invention.External bottom driving cabin 4 have landing amortisseur 9, the shock produced when can effectively cushion landing.After grease it in, ground flying service area staff, the 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 are separately fixed at and cast anchor on wire drawing ring 5 and ground draw ring, the person of driving just can unload seat belt, open hatch door, walk out out of my cabin, take off balancing weight.The present invention is equipped with two set hydrodynamic regulation systems: i.e. blower fan wind speed manual control cruise handle 18 and blower fan wind speed foot controling pedal 17, it is achieved the power of this aircraft rises, flies and returns, to guarantee safety.The two backups each other, but can not operate simultaneously.And air bag is set and extends exhaustor 24 and safety draw ring 30 liang set self-rescue escape device, when running into the fault of weather reason or this aircraft itself, when this aircraft aloft persistently rises or suspension is not dropped, air bag can be opened and extend the exhaust pipe mouth safety helmet 25 bottom exhaustor 24 or pull safety draw ring 30 implementation to save oneself；When declining occurs in this aircraft, exhaust pipe mouth safety helmet 25 can be closed or allow safety draw ring 30 reset, to ensure landing flight safety.When this aircraft is when non-flight service area emergency landing, after this aircraft can be connected with neighbouring fixture by driver by the anti-drop hook 66 of standby rope 56 other end, human pilot gets final product safe land, relieved leaves.The present invention has safety and environmental protection and the cheap feature of flight cost, without burning petroleum product, weight by the buoyancy of self, balancing weight regulates and the power of rotating blower fan 21 gets final product follow-on mission, and power resources can directly use solar energy, to ensure the flying power of this aircraft.
Claims (10)
1. a manned Electric aircraft, this aircraft includes mechanical part and circuit control part, it is characterised in that:
A, mechanical part includes balloon eyelid covering (1), ultrathin flexible solar energy pad pasting (2) that balloon eyelid covering (1) top is arranged, the driving cabin (4) that balloon eyelid covering (1) middle part is connected by hanger rope (3), the outer wall top of described driving cabin (4) be respectively provided on two sides with the wire drawing ring (5) that casts anchor, cast anchor wire drawing ring (5) wire drawing of casting anchor (7) one end with tensile force of belt instrument (6) first hook (11) be connected, the other end of wire drawing (7) of casting anchor is provided with the second hook (8), the outer bottom of described driving cabin (4) is provided with landing shock absorption device (9), the side of described driving cabin (4) outer wall offers cockpit door (10), the inside of driving cabin (4) is provided with control panel (12), the fixing bar (13) being connected with driving cabin (4), fan operation handle (14), balancing weight (15), accumulator (16) and blower fan wind speed foot controling pedal (17)；Described fixing bar (13) is provided with blower fan wind speed manual control cruise handle (18), 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 eyelid covering (1) is provided with several helium capsules (22), wherein, each helium capsule is correspondingly arranged on a charge and discharge QI KOU (23), several charge and discharge QI KOU (23) described are respectively arranged at the bottom of balloon eyelid covering (1), wherein, at least one charge and discharge QI KOU extends exhaustor (24) with air bag and is connected, this air bag extends exhaustor (24) and is arranged on the inside of driving cabin (4), described air bag extends the tail end of exhaustor (24) and is provided with exhaust pipe mouth safety helmet (25), what have at least a charge and discharge QI KOU in other several charge and discharge QI KOU (23) is provided externally with the reinforcing annular pad (26) and metal rack cover (27) that are arranged on balloon eyelid covering (1) outer surface, this charge and discharge QI KOU described is provided with sealing-plug (28), sealing-plug (28) is connected with driving cabin (4) internal upper part safety draw ring (30) with catch (33) by steel wire drawing (29), stage clip (32) is installed between the inner bottom part of sealing-plug (28) and metal rack cover (27), wire drawing pipe (31) it is provided with between metal rack cover (27) and driving cabin (4) outer top, described steel wire drawing (29) traverse stage clip (32), wire drawing pipe (31) is connected with the safety draw ring (30) with catch (33) with extension spring (34), described extension spring (34) is arranged between catch (33) and driving cabin (4) internal upper part, the outer surface of described metal rack cover (27) offers several exhaust holes (38)；Described driving cabin (4) be provided externally with anemobiagraph (40), described driving cabin (4) is provided with illuminating lamp (41)；
B, circuit control part includes ultrathin flexible solar energy pad pasting (2), ultrathin flexible solar energy pad pasting (2) is connected with accumulator (16) by charge switch (45), described accumulator (16) is provided with external charge socket (42), accumulator (16) is connected with rotating blower fan (21) with controller (44) by battery main switch (43), described blower fan wind speed manual control cruise handle (18) is connected with controller (44) respectively with blower fan wind speed foot controling pedal (17), described controller (44) respectively with the back (46) on control panel (12), forwarding button (47), button (48) of turning left is connected with button of turning right (49), described control panel (12) is provided with the electricity display instrument (51) being connected with accumulator (16), altimeter (35), variometer (36), horizontal velocity instrument (37) and navigator (39)；Described accumulator (16) is connected with illuminating lamp (41) by headlamp switch (57), and described charge switch (45), battery main switch (43) and headlamp switch (57) are respectively provided on control panel (12)；Described accumulator (16), controller (44) 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 through wire and corresponding the first alarm (61), second alarm (62) is connected with the 3rd alarm (63), described first alarm (61), second alarm (62) and the 3rd alarm (63) are respectively provided on control panel (12).
2. manned Electric aircraft according to claim 1, it is characterised in that: described hanger rope (3) is at least three；Described landing shock absorption device (9) is at least three；Described accumulator (16) is at least one；Described sealing-plug (28) is taper type sealing-plug, adopting hinge (50) to be connected between described cockpit door (10) with driving cabin (4), cockpit door (10) top offers clear glass window (52)；The top of described balancing weight (15) is provided with portable handle (53).
3. manned Electric aircraft according to claim 1, it is characterised in that: two charge and discharge QI KOU (23) in described charge and discharge QI KOU (23) extend exhaustor (24) with two air bags respectively and are connected.
4. manned Electric aircraft according to claim 1, it is characterized in that: described rotating blower fan (21) is two, it is separately positioned on the both sides that driving cabin (4) is 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), said two rotating blower fan (21) is connected with two corresponding controllers (44) respectively, said two controller (44) is connected with blower fan wind speed manual control cruise handle (18) and blower fan wind speed foot controling pedal (17) respectively, said two controller (44) is respectively equipped with the second temperature sensor (59), and second temperature sensor (59) be connected with the second alarm (62).
5. manned Electric aircraft according to claim 1, it is characterized in that: what described driving cabin (4) was outside is respectively provided on two sides with two rotating blower fans (21), described blower fan connecting shaft (20) is two, it is shaped as yi word pattern, two blower fan connecting shafts (20) be respectively arranged at two ends with rotating blower fan (21), said two blower fan connecting shaft (20) is connected with the bottom of two corresponding fan operation handles (14) respectively, four rotating blower fans (21) are connected with four corresponding controllers (44) respectively, described four controllers (44) are connected with blower fan wind speed manual control cruise handle (18) and blower fan wind speed foot controling pedal (17) respectively, described four controllers (44) are respectively equipped with the second temperature sensor (59), and second temperature sensor (59) be connected with the second alarm (62).
6. manned Electric aircraft according to claim 1, it is characterised in that: the inside of described driving cabin (4) is provided with driver seat (54), and described accumulator (16) is arranged on the bottom of driver seat (54).
7. manned Electric aircraft according to claim 1, it is characterized in that: the outer bottom of described driving cabin (4) is provided with the standby rope safety collar (55) of integrative-structure, described standby rope safety collar (55) is connected with one end of standby rope (56), the other end of standby rope (56) is provided with anti-drop hook (66), and described anti-drop hook (66) is connected with the standby rope curling device (64) arranged on driving cabin (4) wall outer surface.
8. manned Electric aircraft according to claim 1, it is characterised in that: described anemobiagraph (40) is connected with the anemobiagraph display instrument (65) on control panel (12) by wire.
9. manned Electric aircraft according to claim 1, it is characterised in that: described lever journey disk (19) offers the first gear (67), the second gear (68), third gear (69), fourth speed position (70), fifth speed position (71) and sixth speed position (72) respectively.
10. manned Electric aircraft according to claim 1, it is characterised in that: described accumulator (16) is lithium battery group.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410532901.5A CN104326078B (en) | 2014-09-22 | 2014-09-22 | Manned Electric aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410532901.5A CN104326078B (en) | 2014-09-22 | 2014-09-22 | Manned Electric aircraft |
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| CN104326078A CN104326078A (en) | 2015-02-04 |
| CN104326078B true CN104326078B (en) | 2016-06-29 |
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| CN201410532901.5A Expired - Fee Related CN104326078B (en) | 2014-09-22 | 2014-09-22 | Manned Electric aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105363204B (en) * | 2015-11-20 | 2018-08-28 | 郑州中德美游乐设备有限公司 | The production method of golden flying saucer |
| CN105363203B (en) * | 2015-11-20 | 2018-03-30 | 郑州中德美游乐设备有限公司 | The application method of golden flying saucer |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CA2568861C (en) * | 2004-06-05 | 2010-08-10 | Phu Nguyen | Device and method for sealing and lighting a balloon |
| CN1721273A (en) * | 2004-07-15 | 2006-01-18 | 陈明 | Safety automatic deflation device for balloon when out of control and rising |
| CN202481301U (en) * | 2012-03-06 | 2012-10-10 | 刘波 | Fire balloon falling prevention supporting frame with airbag |
| US9033274B2 (en) * | 2012-07-11 | 2015-05-19 | Google Inc. | Balloon altitude control using density adjustment and/or volume adjustment |
| CN203601557U (en) * | 2013-12-09 | 2014-05-21 | 北方信息控制集团有限公司 | Aerostat pressure regulator allowing aerostat to be deflated through manual intervention |
| CN204173151U (en) * | 2014-09-22 | 2015-02-25 | 杜晓东 | Manned Electric aircraft |
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