CN204606192U - Aerostatics - Google Patents
Aerostatics Download PDFInfo
- Publication number
- CN204606192U CN204606192U CN201420635862.7U CN201420635862U CN204606192U CN 204606192 U CN204606192 U CN 204606192U CN 201420635862 U CN201420635862 U CN 201420635862U CN 204606192 U CN204606192 U CN 204606192U
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- Prior art keywords
- force
- supporting belt
- aerostatics
- utricule
- supporting
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/02—Non-rigid airships
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/58—Arrangements or construction of gas-bags; Filling arrangements
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D3/00—Control of position or direction
- G05D3/12—Control of position or direction using feedback
Abstract
The utility model provides a kind of aerostatics, comprising: utricule body, draw in the net structure, bottom hanging device, gondola and solar cell system.Utricule body comprises multiple capsule lobe docked successively.Drawing in the net structure comprises hoop force-supporting belt, longitudinal force-supporting belt and equal power force-supporting belts.Hoop force-supporting belt with the top center of utricule for the center of circle is arranged; One end of longitudinal force-supporting belt is connected to the top center of utricule, and longitudinal force-supporting belt and hoop force-supporting belt angularly distribute with the top center of utricule; The two ends of equal power force-supporting belt respectively coupling link to the force-supporting belt node that be positioned at diagonal position crossing with longitudinal force-supporting belt.Bottom hanging device is connected with the other end of longitudinal force-supporting belt.Gondola is connected to the below of bottom hanging device.Solar cell system comprises polygon prism sensing device and driver train.Polygon prism sensing device is for detecting the Illumination intensity of multiple direction in space; Driver train is for driving the direction of solar panel consistent with the direction in space of maximum Illumination intensity.
Description
Technical field
The utility model relates to aerospace structure field, particularly relates to aerostatics.
Background technology
Due in technology and understanding, the strategic value of near space just causes the attention of countries in the world also to become the focus of various countries' research because of its distinguishing feature and potential dual-use value for several years up to date.A lot of country is just numerous and confused at present drops into a large amount of funds, actively develops the technology and application research of near space aerostatics.Current near space aerostatics is mainly near space dirigible, and near space dirigible adopts blimp mostly, has hang time long, the feature such as load capacity is large, flying height is high, viability is strong.
But, the utricule complex structure of near space dirigible, cause its design and cost of manufacture higher.
Therefore, this area needs a kind of design and the lower aerostatics of cost of manufacture badly.
Utility model content
In order to overcome above-mentioned defect, the utility model aims to provide a kind of lower-cost aerostatics.
According to one side of the present utility model, provide a kind of aerostatics, comprise: utricule body, the axisymmetric body of this utricule body to be bus be arc, gas is filled with to provide buoyancy in this utricule body, this utricule body comprises multiple capsule lobe docked successively, and the capsule lobe entirety that this docks successively forms axisymmetric body shape; Draw in the net structure, comprising: the hoop force-supporting belt that many diameters are different, with the top center of described utricule for the center of circle is arranged; Many longitudinal force-supporting belts, one end is connected to the top center of this utricule, and these many longitudinal force-supporting belts are with described many orthogonal settings of hoop force-supporting belt and angularly distribute with the top center of this utricule, for bearing buoyancy and longitudinal tension force; And many first equal power force-supporting belts, be arranged at adjacent ring in the region that force-supporting belt and adjacent longitudinal force-supporting belt are formed, the two ends of this first equal power force-supporting belt connect the described hoop force-supporting belt node that be positioned at diagonal position crossing with longitudinal force-supporting belt respectively; Bottom hanging device, is connected with the other end of these many longitudinal force-supporting belts; Gondola, is connected to the below of hanging device bottom this; And solar cell system, comprising: solar panel, be connected to this gondola; Polygon prism sensing device, comprises multiple optical sensor, and described multiple optical sensor is formed at the side of this polygon prism respectively with towards multiple different direction in space, to detect the Illumination intensity of multiple direction in space respectively; And driver train, being electrically connected with described polygon prism sensing device, making the direction of described solar panel consistent with the direction in space of maximum Illumination intensity for driving described solar panel to move.
In one example, the quantitative range of this capsule lobe is 60-120.
In one example, this utricule comprises further safeguards lid, comprise clip plate, outer plate, fixation clip and occlusion part, this clip plate and outer plate are annular and are arranged at the inner side and outer side of this utricule body respectively, and clip plate and outer plate interfix, the centre hole of this clip plate and outer plate communicates, and the position that utricule body corresponds to this centre hole has opening, this occlusion part and fixation clip are set in turn on this outer plate, and this fixation clip and this outer plate interfix to be fixed between this fixation clip and this outer plate by occlusion part.
In one example, the shape of this utricule body is spherical, pumpkin-shaped or drops.
In one example, this aerostatics also comprises buffer structure, and this buffer structure is connected to the side away from this utricule of this gondola.
In one example, this aerostatics also comprises the truss be arranged at bottom this between hanging device and this gondola.
In one example, the ratio of the quantity of this longitudinal force-supporting belt and the quantity of this capsule lobe is 1:2 to 1:4.
In one example, in adjacent ring in the region that force-supporting belt and adjacent longitudinal force-supporting belt limit, this draws in the net structure and comprises the second equal power force-supporting belt and the 3rd equal power force-supporting belt further, the two ends of this second equal power force-supporting belt lay respectively at the mid point of two hoop force-supporting belts in the region of corresponding restriction, and the second equal power force-supporting belt is through the joining of two first equal power force-supporting belts; The two ends of the 3rd equal power force-supporting belt are connected to two longitudinal force-supporting belts in the region of corresponding restriction, perpendicular to this second force-supporting belt and through the joining of described two first equal power force-supporting belts.
In one example, this aerostatics comprises laser signal transmit receive unit further, and comprise at least one laser signal projector and at least one laser signal receivers, this laser signal transmit receive unit is installed on this gondola.
In one example, the quantity of this laser signal transmit receive unit is multiple, around the surrounding being arranged on this gondola.
In one example, described multiple optical sensor head and the tail are connected to form described polygon prism sensing device, and the sensitive surface of the plurality of optical sensor constitutes multiple sides of this polygon prism sensing device.
In one example, described polygon prism sensing device comprises polygon prism structure-steel framing, and described multiple optical sensor is arranged at multiple sides of described polygon prism structure-steel framing respectively.
In one example, described polygon prism sensing device is regular prism shape.
In one example, described polygon prism sensing device and described solar panel axially be arranged in parallel or coaxially arrange.
The utricule of the aerostatics of the utility model embodiment is be designed to the axisymmetric body that bus is arc, and structure is simple, and designing and making cost is lower, and owing to have employed high-strength laminar composite, therefore can have the stagnant sky of longer time.In addition, adopt and draw in the net structure and carry out hanging load, hoop force-supporting belt, longitudinal force-supporting belt and the first equal power force-supporting belt make the load of whole utricule more evenly, thus avoid the problem of stress concentration of aerostatics.
Accompanying drawing explanation
After the detailed description of reading embodiment disclosed in the utility model in conjunction with the following drawings, more can understand above-mentioned feature and advantage of the present utility model better.
Fig. 1 is the schematic diagram of the aerostatics according to one side of the present utility model.
Fig. 2 is the front view of the utricule body in the aerostatics in Fig. 1.
Fig. 3 is the generalized section of the multiple-structure of utricule body in Fig. 2.
Fig. 4 is the birds-eye view of the utricule body in Fig. 2.
Fig. 5 is the upward view of the utricule body in Fig. 2.
Fig. 6 is the decomposing schematic representation of the maintenance lid of utricule body in Fig. 5.
Fig. 7 is the schematic diagram drawing in the net structure of aerostatics in Fig. 1.
Fig. 8 is the enlarged diagram of VIII part in Fig. 1.
Fig. 9 is the enlarged diagram of IX part in Fig. 1.
Figure 10 draws in the net the schematic diagram of another embodiment of structure in Fig. 1.
Figure 11 is the solar-tracking system schematic of the aerostatics in Fig. 1.
Figure 12 is the schematic diagram of the aerostatics according to another aspect of the present utility model.
Figure 13 is the schematic diagram of the intercommunication of three aerostatics as shown in figure 12.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in detail.Note, the aspects described below in conjunction with the drawings and specific embodiments is only exemplary, and should not be understood to carry out any restriction to protection domain of the present utility model.
Referring to Fig. 1, is the schematic diagram of the aerostatics 100 of the utility model first embodiment, and this aerostatics 100 can be used as advection layer aerostatics or near space aerostatics, and when being used as near space aerostatics, advantage is more obvious.This aerostatics 100 comprises utricule 10, draw in the net structure 12, bottom hanging device 14, gondola 16 and solar cell system 18.
The buoyancy that this utricule 10 is used as aerostatics 100 provides structure.Please consult this utricule 10 of Fig. 2-5 further and comprise utricule body 110 and the gas filled device 111, the valve 112 that are arranged on utricule body 110 and safeguard lid 113.It is the airbag structure that the in-built gas carrier of utricule body 110 is formed that this utricule body 110 comprises shown in multiple capsule lobe 114, Fig. 2 docked successively, and capsule lobe 114 entirety that this docks successively forms spherosome shape.The gas loaded in utricule 10 be equal air pressure lower density than the gas being less than air, be generally helium.After this utricule body 110 enters near space, its diameter range is 10-50 rice, is preferably 20-45 rice.Be understandable that, the shape of the utricule body 110 of the present embodiment can be also the axisymmetric body of arc for other buses such as pumpkin-shaped or drops, is not limited with the present embodiment.
As shown in Figure 3, the material of this utricule body 10 can adopt the skin material of dirigible, in present embodiment, this utricule body 110 is multiple-structure, comprises anti-aging layer 101, glue-line 102, tissue layer 103, basalis 104, high-obstruction 105 and weld layer 106 successively.The material of anti-aging layer 101 is be 2-4%ZnO and massfraction containing resistance to massfraction is the thermoplastic polyurethane of 3.5-5%, and thickness is 20-30 micron; The material of glue-line 102 is the adhesive for polyurethane of hot melt or the adhesive for polyurethane of coating, and thickness is 20-30 micron; The material of tissue layer 103 is polyster fibre, aramid fiber or other high-intensity fibers, and thickness is 90-140 micron; The material of basalis 104 is thermoplastic polyurethane, and thickness is 20-30 micron; The material of high-obstruction 105 is the polyvinyl alcohol containing massfraction to be 1.5-2.5% grain size the be SiO2 nano particle of 20-50 nanometer, and thickness is 1-3 micron.The material of weld layer 106 is thermoplastic polyurethane, and thickness is 20-30 micron, is combined into one between each layer by coating, dry adhered technique.Be understandable that, light reflecting material layer (not shown) can also can be formed further between the arbitrary neighborhood of the outermost of the multiple-structure of utricule body 110 or this multiple-structure is two-layer, as aluminium foil layer etc., can usable reflection sunray, reduce solar light irradiation to the damage of skin material.
In the present embodiment, the making cutting of capsule lobe 114 adopts geodesic cutting-out method, be specially: using the two ends of the two poles of the earth of the spheroid of preformed utricule body 110 as capsule lobe 114, then utilize geodesic cutting-out method to carry out cutting, and the cutting of each capsule lobe 114 is measure-alike.The number of capsule lobe 114 can calculate according to the diameter of its fabric width and spheroid.Engage after capsule lobe 114 cuts, capsule lobe 114 engages and adopts docking welding manner, is docked by adjacent capsule lobe 114 respectively by many load sealings, adopts docking welding manner can obtain higher separation resistance and good air-tightness.Other combination can certainly be adopted, as the mode of heat seal.
Form butted line 115 between adjacent bladders lobe 114, the two ends of butted line 115 are connected with the position, the two poles of the earth of utricule body 110 respectively.The number of capsule lobe 114 can be determined according to actual conditions, and very little, then the systematicness that the utricule body 110 formed is spherical is poor for the quantity of capsule lobe 114, quantity too much then manufacture difficulty and cost larger.In the present embodiment, the quantity of capsule lobe 114 is preferably 60-120, is more preferably 75-100.
This gas filled device 111 comprises appendix 116, appendix 116 is connected with utricule body 110 and is connected with the inside of utricule body 110, in the present embodiment, utricule body 110 surface forms air-filled pore, and appendix 116 directly mode that is bonding with utricule body 110 or heat seal is fixed and is communicated with air-filled pore.Certainly, appendix 116 also can adopt other mode to be connected with utricule body 110, is not limited with the present embodiment.
In the present embodiment, the quantity of valve 112 is one, is arranged at the top of utricule body 110, for regulating utricule body 110 inside and outside differential pressure, thus controls the quiet buoyancy of utricule 10.In the present embodiment, this valve 112 can be electric control valve.Certainly, the quantity of valve 112 also can be multiple, is not limited with the present embodiment.
Please consult Fig. 6 further, describedly safeguard the bottom relative with described valve 112 that lid 113 is arranged at utricule body 110, that is, safeguard that lid 113 and valve 112 lay respectively at the two poles of the earth of this utricule body 110.Describedly safeguard that lid 113 comprises clip plate 1130, outer plate 1131, fixation clip 1132 and occlusion part 1133.This clip plate 1130 and outer plate 211 are ring-type, in the present embodiment, this clip plate 1130 and outer plate 1131 are circular and centre hole and coaxially arrange, clip plate 1130 and outer plate 1131 are arranged at the inner side and outer side of utricule body 110 respectively and arrange with one heart, utricule body 110 corresponds to this clip plate 1130 and the part of outer plate 1131 centre hole and has the opening corresponding with the centre hole of this clip plate 1130 and outer plate 1131, and clip plate 1130 and outer plate 1131 are by interfixing through the bolt of utricule body 110.This occlusion part 1133 and fixation clip 1132 are set in turn on outer plate 1131.In the present embodiment, this fixation clip 1132 is also circular, and it is fixed on this outer plate 1131 by screw, and is fixed between this fixation clip 1132 and this outer plate 1131 by occlusion part 1133, and preferably, screw also have passed through this occlusion part 1133 simultaneously.In the present embodiment, the material of this occlusion part 1133 is identical with the material of utricule body 110.When needing the inside entering utricule 10 to safeguard, the screw be fixed on fixation clip 1132 can be taken off, and fixation clip 1132 and occlusion part 1133 are taken off, service personnel just can enter into utricule 10 inside from the central hole of clip plate 1130 and outer plate 1131 and safeguard.
Refer to Fig. 1, this utricule 10 comprises the explosion mouth 22, differential pressure transducer 23 and the temperature sensor 24 that are arranged at utricule body 110 surface further.This explosion mouth 22 is for releasing the gas in utricule body 110 fast in emergency situations, and the Fig. 1 in the present embodiment only draws one, can be multiple during practical application certainly.This differential pressure transducer 23 is for sensing the draught head inside and outside utricule 10, and this temperature sensor 24 is in the temperature for sensing utricule 10.
See also Fig. 7 and Fig. 8, this draws in the net structure 12 and comprises hoop force-supporting belt 120, longitudinal force-supporting belt 122 and the first equal power force-supporting belt 124.This material drawing in the net structure 12 can adopt but be not limited to individual layer aramid belt.
Hoop force-supporting belt 120 is the different reinforced rib confinement ring of multiple diameter, and with the top center of utricule 10 for arranging in the center of circle, for bearing hoop tension force, in the present embodiment, the quantity of this hoop force-supporting belt 120 is three.
Longitudinal force-supporting belt 122 is load reinforced rib, and quantity is multiple, and the number ratio scope of the capsule lobe 114 of the general and utricule 10 of its quantity is 1:2 to 1:4, in the present embodiment, its ratio is 1:3, as: when capsule lobe quantity is 90, the quantity of longitudinal force-supporting belt 122 is 30.The quantity of longitudinal force-supporting belt 122 is set to relation proportional with the quantity of capsule lobe, a corresponding integer capsule lobe of each longitudinal force-supporting belt 122 can be made, thus make the load of utricule 10 more even.One end of multiple longitudinal force-supporting belt 122 is connected to the top center of this utricule 10, the plurality of longitudinal force-supporting belt 122 setting orthogonal with hoop force-supporting belt 120 and angularly distributing with the top center of this utricule 10, for bearing buoyancy and longitudinal tension force.
This first equal power force-supporting belt 124 is multiple, be arranged at adjacent ring in the region that force-supporting belt 120 and adjacent longitudinal force-supporting belt 122 are formed, coupling link is to force-supporting belt 120 node that be positioned at diagonal position crossing with longitudinal force-supporting belt 122 respectively for the two ends of the first equal power force-supporting belt 124, and the transmission for power between node draws in the net the stressing conditions of structure 12 at the tip position of utricule 10 to improve.The two ends of the first equal power force-supporting belt 124 interfix at its node place with corresponding hoop force-supporting belt 120 and longitudinal force-supporting belt 122, and every two crossing the first equal power force-supporting belts 124 are separate, without interfixing relation.Usually, at node place, longitudinal force-supporting belt 122 or the first equal power force-supporting belt 124 adjacent with utricule 10, hoop force-supporting belt 120 is arranged on the top of longitudinal force-supporting belt 122 and the first equal power force-supporting belt 124, is fixed by sewing or the technique such as heat seal.
Please consult Fig. 9 further, bottom this, hanging device 14 comprises poly-band structure 142 and hoist cable 144.One end away from this utricule 10 of these many longitudinal force-supporting belts 122 is assembled and is fixed on this poly-band structure 142, this poly-band structure 142 be positioned at this utricule 10 side, bottom and with bottom interval and set a distance.In the present embodiment, this poly-band structure 142 is a circular plate-like shape, and its material can be corrosion-resistant steel etc.
This hoist cable 144 comprises the first lifting rope 145, hanging board 146 and the second lifting rope 147.This hanging board 146 is tabular, it is arranged one for discharging with aerostatics the through hole 148 that car is connected.In the present embodiment, the quantity of this first lifting rope 145 is four, and the opposite end of every bar first lifting rope 145 is connected with poly-band structure 142 and hanging board 146 respectively.In the present embodiment, the quantity of this second lifting rope 147 is identical with the quantity of this first lifting rope 145, and one end is connected with hanging board 146, and the other end of this second lifting rope 147 is used for being connected with the object that gondola or truss etc. are hung in advance.This first lifting rope 145 and the second lifting rope 147 can be but be not limited to steel rope, the quantity of this first lifting rope 145 and the second lifting rope 147 also can be set to one or more as required, this first lifting rope 145 can be identical with the quantity of the second lifting rope 147, also can be different.
In the present embodiment, adopt and draw in the net structure 12 and carry out hanging load, hoop force-supporting belt 120, longitudinal force-supporting belt 122 and the first equal power force-supporting belt 124 make the load of whole utricule 10 more evenly, thus avoid the problem of stress concentration of aerostatics.
Refer to Figure 10, for the utility model draws in the net another embodiment of structure, with draw in the net in above-mentioned embodiment structure 12 unlike, in adjacent ring in the region that force-supporting belt 120 and adjacent longitudinal force-supporting belt 122 limit, comprise the equal power force-supporting belt 124b of the second equal power force-supporting belt 124a and the 3rd further.The two ends of the second equal power force-supporting belt 124a lay respectively at the mid point of two hoop force-supporting belts 120 in the region of corresponding restriction, then the second equal power force-supporting belt 124a is through the joining of two first equal power force-supporting belts 124; The two ends of the 3rd equal power force-supporting belt 124a are connected to two longitudinal force-supporting belts 122 in the region of corresponding restriction, perpendicular to this second force-supporting belt and through the joining of described two first equal power force-supporting belts 124.The equal power force-supporting belt 124b of this first equal power force-supporting belt 124a and the 3rd of equal power force-supporting belt 124, second is independently structure, each other without annexation.The structure of drawing in the net of present embodiment can make the load of whole utricule 10 more even.
This gondola 16 is connected with the free end of the second lifting rope 147 of hanging device bottom this 14.This gondola 16 is for loading Aerial Electronic Equipment, flight control unit, communicator etc.
In other optional embodiment, this aerostatics 200 can also comprise truss structure and buffer structure, truss structure is connected between utricule device 100 and gondola 21, and the opposite end of this truss structure can also connect drive configuration (not shown) respectively respectively as screw propeller; Buffer structure is arranged at the below of gondola, buffering when landing for aerostatics 200, damages to prevent aerostatics 200.
See also Figure 11, this solar cell system 18 comprises polygon prism sensing device 181, driver train 182 and solar panel 183.
Solar panel 183 is arranged on dirigible or other stratosphere flight devices rotationally, thus solar panel 183 can carry out rotating to receive solar power and being converted into electric energy, thus provides it normally to run the required energy to aerostatics 100.In the present embodiment, solar panel 183 is suspended on the below of gondola 16.
Polygon prism sensing device 181 comprises multiple optical sensor 1810, and multiple optical sensor 1810 head and the tail connect, and are mounted to towards multiple different direction in space, to detect the Illumination intensity of multiple direction in space.Multiple optical sensor 1810 can be irradiation sensor, and irradiation sensor can gather solar power, and detects Intensity of the sunlight.This polygon prism sensing device 181 can be arranged on outside gondola 16, also can be arranged on the below of gondola 16.
Preferably, in order to the difference of the Illumination intensity that the difference reducing multiple optical sensor 1810 accuracy of detection causes as far as possible, multiple optical sensor 1810 is identical optical sensor.Each optical sensor 1810 adopts same size, same model, the product of same batch, and make under identical illumination condition, the direct voltage output difference of each optical sensor 1810 is within the scope of millesimal.The polygon prism sensing device 181 be made up of above-mentioned multiple optical sensor 1810 is the shape of regular prism, and the sensitive surface of the plurality of optical sensor 1810 constitutes multiple sides of this regular prism, and the sensitive surface of the corresponding optical sensor 1810 in each side.As Figure 11, in the present embodiment, polygon prism sensing device 181 comprises eight optical sensors 1810, these eight optical sensor 1810 head and the tail connect and compose eight prisms, the sensitive surface of these eight optical sensors 1810 forms eight sides of this eight prism respectively, the all corresponding optical sensor 1810 in each side, make each side towards direction in space different, eight sides detect respectively its towards direction in space on Illumination intensity.In the present embodiment, polygon prism sensing device 181 is regular prism shape.
In other optional embodiments, polygon prism sensing device comprises polygon prism structure-steel framing and multiple optical sensor, and each side of polygon prism structure-steel framing is provided with an optical sensor.In addition, be understandable that, the quantity of the rib of this polygon prism sensing device also can suitably increase and decrease as required, is not limited with eight of the present embodiment.The quantity of optical sensor 1810 is more, the Illumination intensity collected towards more, solar panel 183 is also more accurate towards the direction of maximum Illumination intensity.Certainly, the quantity of optical sensor 1810 can not be too much, and the rotation of solar panel 183 may be caused so too much to increase the out of order possibility of driver train and consume too much electric energy; When optical sensor 1810 number is very few, accuracy rate is too low, and solar conversion efficiency may be caused too low.Therefore, the number of probes of polygon prism sensing device 181 is preferably 8-12, has both decreased the out of order possibility of driver train, and has also made solar conversion efficiency high as much as possible.Due to the finiteness of the spatial direction of multiple optical sensor 181, when operating mode have change by a small margin time, the direction of the sensor that voltage is the highest there will not be change, thus the direction that solar panel can be made to keep stable, avoid the stability of unnecessary rotation and maintenance power stage.
Driver train 182 is electrically connected with polygon prism sensing device 181, makes the direction of solar panel 183 consistent with the direction in space of maximum Illumination intensity for driving solar panel 183 to move.This solar cell system 18 also comprises signal processor 1820, signal processor 200 is connected between polygon prism sensing device 181 and driver train 182, in polygon prism sensing device 181, the Illumination intensity detected is sent to signal processor 1820 by each optical sensor 1810, signal processor 1820 compares the size of the Illumination intensity of the multiple direction in spaces sent by multiple optical sensor 1810 to determine maximum Illumination intensity, using the optical sensor 1810 corresponding to maximum Illumination intensity towards direction in space as the direction in space corresponding to maximum Illumination intensity.After the direction in space determining maximum Illumination intensity, the driver train 182 that signal processor 1820 controls to be electrically connected with signal processor 1820 by control signal drives solar panel 183 to rotate, make solar panel 183 turn to direction in space corresponding to maximum Illumination intensity, thus the Illumination intensity that solar panel 183 can be received maximize.
Preferably, in order to the VREF (Voltage Reference) adopted when each optical sensor 1810 output voltage signal is identical, the negative pole of multiple optical sensor 1810 is connected, and positive pole is connected with signal processor 1820 respectively, is convenient to the Illumination intensity of the more multiple optical sensor 1810 of signal processor 1820.
Particularly, signal processor 1820 receives the Illumination intensity that in polygon prism sensing device 181, multiple optical sensor 1810 collects, wherein, Illumination intensity collects the numerical representation method of voltage analog signal, power analog signal or Illumination intensity by optical sensor 1810.Signal processor 1820 compares the Illumination intensity that multiple optical sensor 1810 collects according to the signal received, thus determines the sensor receiving maximum Illumination intensity.This receive the sensor of maximum Illumination intensity towards direction in space be the direction in space of maximum Illumination intensity, now signal processor 1820 can generate indicator signal, the sensor corresponding to maximum Illumination intensity driving solar panel 183 to turn to indicate driver train 182 to detect towards direction in space.
Preferably, driver train 182 comprises electric machine controller 1821 and motor 1822, and electric machine controller 1821 is connected with signal processor 1820, for the electric signal of Received signal strength treater 1820, and generates motor control signal; Motor 1822 is connected with electric machine controller 1821, for driving solar panel 183 to turn to the direction of maximum Illumination intensity according to motor control signal.Wherein, motor control signal can indication motor 1822 angle that drives solar panel 183 to rotate, motor 1822 drives the angle indicated by solar panel 183 rotary electric machine control signal according to the motor control signal received, and makes solar panel 183 turn to the direction of maximum Illumination intensity.Preferably, this motor 1822 can be stepping motor.
Above-described embodiment, before driving solar panel 183 rotates, the Illumination intensity on different spaces direction is detected by the multiple optical sensors 1810 in polygon prism sensing device 181, after judging the direction in space that maximum Illumination intensity is corresponding, determine the angle driving solar panel 183 to rotate, again by motor 1822 according to the angle driven indicated by solar panel 183 rotary electric machine control signal, the direction making solar panel 183 receive illumination turn to the sensor collecting maximum Illumination intensity towards direction in space.In this process, neither needing the rotation driving solar panel to continue, also without the need to driving solar panel to do tentative rotation, thus solving in prior art the problem that when adjusting solar panel, consumed energy is larger.
In other optional embodiment, this aerostatics 100 can also comprise truss structure and buffer structure, truss structure is connected between utricule 10 and gondola 16, and the opposite end of this truss structure can also connect drive configuration (not shown) respectively respectively as screw propeller; Buffer structure is arranged at the below of gondola, buffering when landing for aerostatics 100, damages to prevent aerostatics 100.This polygon prism sensing device 181 also can be arranged on truss structure.
Referring to Figure 12, is the schematic diagram of the aerostatics 200 of the utility model second embodiment.The difference of the aerostatics 100 of aerostatics 200 and the first embodiment is, aerostatics 200 comprises the laser signal transmit receive unit 40 being arranged at gondola 16 further, and this laser signal transmit receive unit 40 comprises laser signal projector 41 and laser signal receivers 42.This laser signal projector 41 is for launching two scale notation or the multi-system information communicating light signal through overcutting by high speed stroboscopic, the laser signal comprising the high speed stroboscopic of two scale notation or multi-system information that this laser signal receivers 42 sends for receiving another aerostatics 200.This laser signal receivers 42 is connected for the treater (not shown) of this laser signal of demodulation with one, with by laser signal demodulation out, thus realizes the data communication between aerostatics 200.This laser signal transmit receive unit 40 information of receiving and dispatching can be the two scale notation weaved into as prespecified methods of information such as picture, word or states or multi-system information.It should be noted that, binary modulated demodulation involved herein, and information to be carried out the method for encoding etc. be structure in order to laser signal transmit receive unit is described and effect, the not claimed scope of the utility model.In the present embodiment, quantity corresponding to the laser signal transmit receive unit 40 of an aerostatics 200 is multiple, arranges, preferably around this gondola 16, the quantity of this laser signal transmit receive unit 40 is more than or equal to four, angularly around the surrounding being arranged on this gondola 16.When the quantity of laser signal transmit receive unit 40 is more than or equal to four, then transmit receive unit can receive the laser signal of all directions from gondola 16.In the present embodiment, laser signal transmit receive unit 40 and gondola 16 together constitute nacelle device.
Please consult further shown in Figure 13, the aerostatics communication network 300 that multiple near space vehicle 200 is formed, each aerostatics 200 is by realizing data communication between installing laser signal transmit receive unit 40 thereon and other aerostatics 200.
The aerostatics 200 of the present embodiment, owing to being provided with laser signal transmit receive unit, making to fly at aerial multiple aerostatics 200 and can communicate each other, be convenient to communication network in frame empty.
Description before providing is to make any technical personnel in this area all can put into practice various aspects described herein.But should be appreciated that, protection domain of the present utility model should be as the criterion with claims, and should not be defined to concrete structure and the assembly of above explained orally embodiment.Those skilled in the art, in spirit and scope of the present utility model, can carry out various variation and amendment to each embodiment, and these variations and amendment also drop within protection domain of the present utility model.
Claims (14)
1. an aerostatics, comprising:
Utricule body, the axisymmetric body of this utricule body to be bus be arc, be filled with gas in this utricule body to provide buoyancy, this utricule body comprises multiple capsule lobe docked successively, and the capsule lobe entirety that this docks successively forms axisymmetric body shape;
Draw in the net structure, comprising:
The hoop force-supporting belt that many diameters are different, with the top center of described utricule for the center of circle is arranged;
Many longitudinal force-supporting belts, one end is connected to the top center of this utricule, and these many longitudinal force-supporting belts are with described many orthogonal settings of hoop force-supporting belt and angularly distribute with the top center of this utricule, for bearing buoyancy and longitudinal tension force; And
Many first equal power force-supporting belts, be arranged at adjacent ring in the region that force-supporting belt and adjacent longitudinal force-supporting belt are formed, the two ends of this first equal power force-supporting belt connect the described hoop force-supporting belt node that be positioned at diagonal position crossing with longitudinal force-supporting belt respectively;
Bottom hanging device, is connected with the other end of these many longitudinal force-supporting belts;
Gondola, is connected to the below of hanging device bottom this; And
Solar cell system, comprising:
Solar panel, is connected to this gondola;
Polygon prism sensing device, comprises multiple optical sensor, and described multiple optical sensor is formed at the side of this polygon prism respectively with towards multiple different direction in space, to detect the Illumination intensity of multiple direction in space respectively; And
Driver train, is electrically connected with described polygon prism sensing device, makes the direction of described solar panel consistent with the direction in space of maximum Illumination intensity for driving described solar panel to move.
2. aerostatics as claimed in claim 1, is characterized in that, the quantitative range of this capsule lobe is 60-120.
3. aerostatics as claimed in claim 1, it is characterized in that, this utricule comprises further safeguards lid, comprise clip plate, outer plate, fixation clip and occlusion part, this clip plate and outer plate are annular and are arranged at the inner side and outer side of this utricule body respectively, and clip plate and outer plate interfix, the centre hole of this clip plate and outer plate communicates, and the position that utricule body corresponds to this centre hole has opening, this occlusion part and fixation clip are set in turn on this outer plate, this fixation clip and this outer plate interfix to be fixed between this fixation clip and this outer plate by occlusion part.
4. aerostatics as claimed in claim 1, is characterized in that, the shape of this utricule body is spherical, pumpkin-shaped or drops.
5. aerostatics as claimed in claim 1, it is characterized in that, this aerostatics also comprises buffer structure, and this buffer structure is connected to the side away from this utricule of this gondola.
6. aerostatics as claimed in claim 1, it is characterized in that, this aerostatics also comprises the truss be arranged at bottom this between hanging device and this gondola.
7. aerostatics as claimed in claim 1, it is characterized in that, the ratio of the quantity of this longitudinal force-supporting belt and the quantity of this capsule lobe is 1:2 to 1:4.
8. aerostatics as claimed in claim 1, it is characterized in that, in adjacent ring in the region that force-supporting belt and adjacent longitudinal force-supporting belt limit, this draws in the net structure and comprises the second equal power force-supporting belt and the 3rd equal power force-supporting belt further, the two ends of this second equal power force-supporting belt lay respectively at the mid point of two hoop force-supporting belts in the region of corresponding restriction, and the second equal power force-supporting belt is through the joining of two first equal power force-supporting belts; The two ends of the 3rd equal power force-supporting belt are connected to two longitudinal force-supporting belts in the region of corresponding restriction, perpendicular to this second equal power force-supporting belt and through the joining of described two first equal power force-supporting belts.
9. aerostatics as claimed in claim 1, it is characterized in that, this aerostatics comprises laser signal transmit receive unit further, and comprise at least one laser signal projector and at least one laser signal receivers, this laser signal transmit receive unit is installed on this gondola.
10. aerostatics as claimed in claim 9, it is characterized in that, the quantity of this laser signal transmit receive unit is multiple, around the surrounding being arranged on this gondola.
11. aerostatics according to claim 1, is characterized in that, described multiple optical sensor head and the tail are connected to form described polygon prism sensing device, and the sensitive surface of the plurality of optical sensor constitutes multiple sides of this polygon prism sensing device.
12. aerostatics according to claim 1, is characterized in that, described polygon prism sensing device comprises polygon prism structure-steel framing, and described multiple optical sensor is arranged at multiple sides of described polygon prism structure-steel framing respectively.
13. aerostatics according to claim 11 or 12, it is characterized in that, described polygon prism sensing device is regular prism shape.
14. aerostatics according to claim 1, is characterized in that, described polygon prism sensing device and described solar panel axially be arranged in parallel or coaxially arrange.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420635862.7U CN204606192U (en) | 2014-10-29 | 2014-10-29 | Aerostatics |
| PCT/CN2015/086771 WO2016065974A1 (en) | 2014-10-29 | 2015-08-12 | Aerostat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420635862.7U CN204606192U (en) | 2014-10-29 | 2014-10-29 | Aerostatics |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204606192U true CN204606192U (en) | 2015-09-02 |
Family
ID=53958763
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420635862.7U Expired - Fee Related CN204606192U (en) | 2014-10-29 | 2014-10-29 | Aerostatics |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN204606192U (en) |
| WO (1) | WO2016065974A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105235876A (en) * | 2015-11-10 | 2016-01-13 | 邓勤 | Wind-light complementary power generation airship carrier equipment provided with rotating shaft |
| CN105253283A (en) * | 2015-11-10 | 2016-01-20 | 陈恒兰 | Steerable solar heat collector hot-air balloon hanging system |
| CN106516070A (en) * | 2015-09-14 | 2017-03-22 | 东莞前沿技术研究院 | High-altitude balloon |
| CN110404189A (en) * | 2019-07-08 | 2019-11-05 | 中国人民解放军国防科技大学 | Portable detachable high-rise fire life-saving device |
| CN111238920A (en) * | 2020-02-26 | 2020-06-05 | 中国电子科技集团公司第三十八研究所 | Method for detecting performance of aerostat capsule material |
| CN112925044A (en) * | 2021-01-28 | 2021-06-08 | 中国科学院空天信息创新研究院 | Near space cooperative observation system and method based on multiple aerostats |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2915675Y (en) * | 2006-05-22 | 2007-06-27 | 江宁 | Solar energy hot air balloon |
| CN101339436A (en) * | 2008-09-02 | 2009-01-07 | 叶尔肯·拜山 | Solar energy board positioning system and its measuring and controlling method |
| CN101662240A (en) * | 2009-05-27 | 2010-03-03 | 北京奥腾讯达科技有限公司 | Self-orienting solar power generation device |
| CN101976084B (en) * | 2010-11-23 | 2012-02-22 | 江苏武进液压启闭机有限公司 | Spotlighting sensor suitable for solar automatic tracking system |
| US8820678B2 (en) * | 2012-01-09 | 2014-09-02 | Google Inc. | Relative positioning of balloons with altitude control and wind data |
| CN103057687B (en) * | 2013-01-18 | 2015-02-18 | 襄阳宏伟航空器有限责任公司 | Fire balloon airdrop test platform |
| CN103879540B (en) * | 2014-03-06 | 2016-04-13 | 山西铱格斯曼航空科技有限公司 | A kind of center radiation hauling type high-altitude superpressure buoyant capsule body device |
-
2014
- 2014-10-29 CN CN201420635862.7U patent/CN204606192U/en not_active Expired - Fee Related
-
2015
- 2015-08-12 WO PCT/CN2015/086771 patent/WO2016065974A1/en active Application Filing
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516070A (en) * | 2015-09-14 | 2017-03-22 | 东莞前沿技术研究院 | High-altitude balloon |
| CN105235876A (en) * | 2015-11-10 | 2016-01-13 | 邓勤 | Wind-light complementary power generation airship carrier equipment provided with rotating shaft |
| CN105253283A (en) * | 2015-11-10 | 2016-01-20 | 陈恒兰 | Steerable solar heat collector hot-air balloon hanging system |
| CN110404189A (en) * | 2019-07-08 | 2019-11-05 | 中国人民解放军国防科技大学 | Portable detachable high-rise fire life-saving device |
| CN111238920A (en) * | 2020-02-26 | 2020-06-05 | 中国电子科技集团公司第三十八研究所 | Method for detecting performance of aerostat capsule material |
| CN111238920B (en) * | 2020-02-26 | 2021-07-23 | 中国电子科技集团公司第三十八研究所 | Method for detecting performance of aerostat capsule material |
| CN112925044A (en) * | 2021-01-28 | 2021-06-08 | 中国科学院空天信息创新研究院 | Near space cooperative observation system and method based on multiple aerostats |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2016065974A1 (en) | 2016-05-06 |
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