CN204587293U - Low energy consumption aircraft - Google Patents
Low energy consumption aircraft Download PDFInfo
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- CN204587293U CN204587293U CN201420633993.1U CN201420633993U CN204587293U CN 204587293 U CN204587293 U CN 204587293U CN 201420633993 U CN201420633993 U CN 201420633993U CN 204587293 U CN204587293 U CN 204587293U
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Abstract
The utility model relates to field of fluid mechanics, is specifically related to buoyancy flight equipment field.Low energy consumption aircraft, comprises an air bag main body, also comprises the radio signal reception system, the microprocessor system that are directly or indirectly fixed on air bag main body, and one provides the lifting power plant of power for rising or declining; The signal output part microprocessor system of radio signal reception system, microprocessor system connects the signal input part of lifting power plant; Air bag main body is the closed cavity of a flexibility; The gas that density is less than air is filled with in air bag main body.To realize comprising the remote control of upgrading and controlling to low energy consumption aircraft, and because natural buoyancy effect during flight, only need the lift that lifting power plant provides very little, can take off, or raise.Greatly reduce energy consumption.
Description
Technical field
The utility model relates to field of fluid mechanics, is specifically related to flight equipment field.
Background technology
Huge advance that aircraft is the life of the mankind, science and technology, economy, industrial belt are known clearly.Aircraft needs to overcome self gravitation, just can take off.When overcoming self gravitation and taking off, need at substantial energy.
Utility model content
The purpose of this utility model is, provides a kind of low energy consumption aircraft, to solve the problem.
The technical matters that the utility model solves can realize by the following technical solutions:
Low energy consumption aircraft, comprises an air bag main body, it is characterized in that, also comprises the radio signal reception system, the microprocessor system that are directly or indirectly fixed on air bag main body, and one provides the lifting power plant of power for rising or declining;
Microprocessor system described in the signal output part of described radio signal reception system, described microprocessor system connects the signal input part of lifting power plant;
Described air bag main body is the closed cavity of a flexibility;
The gas that density is less than air is filled with in described air bag main body;
Be filled with the buoyancy that density is less than the air bag main body of the gas of air and be greater than gravity, but the difference of buoyancy and gravity, be less than the gravity sum of described radio signal reception system and described lifting power plant.
To realize comprising the remote control of upgrading and controlling to low energy consumption aircraft, and because natural buoyancy effect during flight, only need the lift that lifting power plant provides very little, can take off, or raise.Greatly reduce energy consumption.
In addition, because the overall gravity of low energy consumption aircraft is greater than buoyancy again, can ground be dropped to after forfeiture power, instead of out of control missing.
Also comprise a suspension position fixing system; Described suspension position fixing system is connected on described air bag main body;
Described suspension position fixing system, comprises the height measuring device of a detection height;
Described height measuring device connects described microprocessor system, lifting power plant described in described microprocessor system control linkage one.
Radio signal reception system, microprocessor system, lifting power plant and suspension position fixing system are encapsulated in a shell, fix together.
The chamber wall of described air bag main body is elastic material.The chamber wall thickness of described air bag main body, is less than 2mm, is greater than 0.05mm.
Described height measuring device detects flying height.And elevation information is passed to described microprocessor system, microprocessor system, according to elevation information, controls lifting power plant.And then control the flying height of air bag main body.
When height detecting device detects flying height lower than setting height, described microprocessor system controls described lifting power plant and performs vertical motion, makes air bag main body increase.When flying height being detected higher than setting height, described microprocessor system controls described lifting power plant and performs down maneuver, and air bag main body is declined.
The aerial buoyancy of described low energy consumption aircraft is less than self gravitation, and described lifting power plant is for only providing the lifting power plant of lifting power.To simplify system.
Or described lifting power plant, for both providing lifting power, can provide again the lifting power plant of decline power.To realize flexible response.
Described lifting power plant can adopt a propeller arrangement, a fin arrangement, or a heat energy regulator control system.
When described lifting power plant adopts propeller arrangement, described propeller arrangement comprises an electrical motor and a screw propeller fin, the blowing direction of described screw propeller fin upward or down, described electrical motor connects described screw propeller fin by transmission device, drive described screw propeller fin to rotate, and then produce thrust.
Described upgrading engine installation is provided with at least two screw propellers, and two screw propeller symmetry arrangement are in the center of gravity both sides of air bag main body.Thus allow after omission is similar to the structure of empennage of helicopter, still can held stationary flight.
When described lifting power plant adopts fin arrangement, described fin arrangement comprises an electrical motor and and swings fin, the swaying direction of described swing fin is for swinging up and down, described electrical motor connects described swing fin by described transmission device, drive described swing fin to swing, and then produce upwards or downward thrust.
When described lifting power plant adopts a heat energy regulator control system, described heat energy regulator control system comprises an electric heater unit, described electric heater unit is on a balloon, for described balloon provides heat, expand after material in balloon is heated, and then impel balloon volume to increase, and then buoyancy is increased, thus produce buoyancy upwards.
Described electric heater unit can be positioned at described balloon or be attached to outside the balloon wall of described balloon.
Described balloon can be described air bag main body, and namely described electric heater unit is positioned at described air bag main body.
Described balloon also independent of described air bag main body, can be connected with described air bag main body.Can be positioned at outside described air bag main body or described air bag main body.
Also be provided with a container below described balloon, the heater element of described electric heater unit is positioned at described container.
Described container content has liquid substance, and described liquid substance, under the heating of described heater element, produces steam, and then increases the volume of described balloon.Thus increase buoyancy.Described liquid can adopt the boiling points such as water, propylene dichloride, parabolic hydrocarbon, alkene, alcohol, aldehyde, amine, ester, ether, ketone, aromatic hydrocarbon, hydrogenate hydrocarbon, terpene hydrocarbon, halogenated hydrocarbons lower, be easy to the liquid evaporated, concrete composition can also be water, alcohol, formaldehyde, gasoline, ether.
Described container is positioned at below described balloon, and the edge of opening of described container and the balloon wall of described balloon are fitted.So that become liquid or solid-state material after cooling, again fall back in described container, use in order to heating next time.
Described height measuring device can adopt reflective height measuring device, comprises a sender unit and a signal receiving device;
The signal downrange of described sender unit towards, with the Signal reception direction of described signal receiving device towards consistent so that receive the signal fired back.
The signal downrange of described sender unit towards, with the Signal reception direction of described signal receiving device towards, all downward or top.
Downward time, by measuring terrain clearance, elevation information can be known.Upward time, can by the distance of measuring distance top ceiling when indoor, side reflects the elevation information of flight.
Described signal receiving device is after receiving the signal that described sender unit sends, produce a high level, described high level output gives described microprocessor system, and described microprocessor system is that described lifting power plant is powered, and makes described lifting power plant work.
Described microprocessor system can be a signal amplification circuit.Amplify the electric current that described signal receiving device exports, and then drive described lifting power plant work.
Described microprocessor system can comprise a time delay circuit.Time delay is carried out to the current impulse that described signal receiving device exports, and then drives described lifting power plant to work gently, avoid pulse current to cause rush of current to described lifting power plant.
Described suspension position fixing system also comprises a battery system, and described battery system is provided with charging inlet.And power for described suspension position fixing system.
Signal reception direction towards down, during the useful signal launched by described sender unit reflected below described signal receiving device receives, described microprocessor system is considered as flying height lower than setting height, controls the lift that described lifting power plant provides rising.
Signal reception direction towards down, during the useful signal launched by described sender unit reflected below described signal receiving device does not receive, described microprocessor system is considered as flying height higher than setting height, controls the power that described lifting power plant provides decline.
Signal reception direction towards upward, during the useful signal launched by described sender unit reflected above described signal receiving device receives, described microprocessor system is considered as flying height higher than setting height, controls the power that described lifting power plant provides decline.
Reflective height measuring device, can adopt an active infra-red distance measuring equipment (DME), described sender unit adopts an infrared launcher, and described signal receiving device adopts an infrared receiving device.
Reflective height measuring device, can adopt a supersonic range finder, and described sender unit adopts a ultrasonic transmission device, and described signal receiving device adopts a ultrasonic probe, ultrasonic receiver.
Reflective height measuring device, can adopt a laser ranging system, and described sender unit adopts a laser emitting device, and described signal receiving device adopts a laser signal receiving device.
Being filled with the gas that density is less than air in described air bag main body, can be hydrogen, helium or other gas.
Described air bag main body sealing.Avoid gas leakage.
The difference of the aerial buoyancy of described low energy consumption aircraft and self gravitation, is less than 1/10th of self gravitation value.Further preferably, the difference of the aerial buoyancy of low energy consumption aircraft and self gravitation, one of two percentages being greater than self gravitation value.
Described air bag main body can for being at least one in superman, angel, angle, fairy maiden, dragon, bird, winged insect, aircraft, the sun or moon moulding.
Described suspension position fixing system detouchable is fixed on described air bag main body.Can be by being adhesively fixed on described air bag main body.So that described suspension position fixing system and common air bag main body are arranged in pairs or groups flexibly.
Can be that described suspension position fixing system is bonded in above described air bag main body or below.
Described suspension position fixing system is provided with a bonding coat.Described bonding coat can be provided with a parting paper.In use parting paper is peeled off, be then bonded on described air bag main body.
Can be that flying power system do not installed by described low energy consumption aircraft so that simplification system, reduce gravity, reduce costs, save energy extend the flight time.
Also can be also comprise a flying power system, and a signal handling equipment, described signal handling equipment also connects the control interface of described flying power system.Described flying power system provides action power for low energy consumption aircraft.
Described flying power system comprises electrical motor and blower impeller, and blower impeller described in described direct motor drive rotates and provides power.
Can also be that described flying power system comprises electrical motor and fin, fin described in described direct motor drive swings and provides power.
Described signal handling equipment is also connected with a wireless interaction system, and described wireless interaction system support has a wireless interaction terminal.Low energy consumption aircraft realizes information interaction by described wireless interaction system and wireless interaction terminal.
Described information interaction comprises low energy consumption aircraft state data and is handed down to described unlimited interactive terminal.Also comprise, control command is uploaded to described wireless interaction system by described wireless interaction terminal, and then is uploaded to described signal handling equipment.
Also comprise, described wireless interaction terminal sends remote signal to described wireless interaction system in real time, and then is uploaded to described signal handling equipment, carries out real time remote control control.
Described low energy consumption aircraft is also equipped with picture pick-up device, and GPS fixing aid or Big Dipper fixing aid, described picture pick-up device and described GPS fixing aid or Big Dipper fixing aid are connected to a microprocessor system, and the information association that the image data that described picture pick-up device absorbs by described microprocessor system and described GPS fixing aid or Big Dipper fixing aid are located is preserved.So that stored images, and the geographic position of image is indicated.
Can also wireless signal transmission system be set, in good time by picture pick-up device data and GPS fixing aid or Big Dipper fixing aid data transmission to wayside equipment.
Accompanying drawing explanation
Fig. 1 is a kind of integral structure schematic diagram of low energy consumption aircraft;
Fig. 2 is lifting power plant structural principle schematic diagram.
Detailed description of the invention
The technological means realized to make the utility model, creation characteristic, reaching object and effect is easy to understand, setting forth the utility model further below in conjunction with concrete diagram.
With reference to Fig. 1, Fig. 2, low energy consumption aircraft, comprises an air bag main body 1, also comprises the radio signal reception system, the microprocessor system that are directly or indirectly fixed on air bag main body, and one provides the lifting power plant of power for rising or declining.
The signal output part microprocessor system of radio signal reception system, microprocessor system connects the signal input part of lifting power plant; Air bag main body 1 is the closed cavity of a flexibility; The gas that density is less than air is filled with in air bag main body 1; Be filled with the buoyancy that density is less than the air bag main body 1 of the gas of air and be greater than gravity, but the difference of buoyancy and gravity, be less than the gravity sum of radio signal reception system and lifting power plant.
To realize comprising the remote control of upgrading and controlling to low energy consumption aircraft, and because natural buoyancy effect during flight, only need the lift that lifting power plant provides very little, can take off, or raise.Greatly reduce energy consumption.In addition, because the overall gravity of low energy consumption aircraft is greater than buoyancy again, can ground be dropped to after forfeiture power, instead of out of control missing.
Low energy consumption aircraft, also comprises a suspension position fixing system 2; Suspension position fixing system 2 is fixed on air bag main body 1.Suspension position fixing system 2, comprises the height measuring device 23 of a detection height.Height measuring device 23 connects microprocessor system 22, microprocessor system 22 control linkage one lifting power plant 21.A microprocessor system can be provided with in microprocessor system 22.In order to processing data.Air bag main body 1 is the closed cavity of a flexibility.The chamber wall of air bag main body 1 is elastic material.The chamber wall thickness of air bag main body 1, is less than 2mm, is greater than 0.05mm.
Height measuring device 23 detects flying height.And elevation information is passed to microprocessor system 22, microprocessor system 22, according to elevation information, controls lifting power plant 21.And then control the flying height of air bag main body 1.
When height detecting device detects flying height lower than setting height, microprocessor system 22 controls lifting power plant 21 and performs vertical motion, makes air bag main body 1 increase.When flying height being detected higher than setting height, microprocessor system 22 controls lifting power plant 21 and performs down maneuver, and air bag main body 1 is declined.Radio signal reception system, microprocessor system, lifting power plant and suspension position fixing system are encapsulated in a shell, fix together.
Being filled with the gas that density is less than air in air bag main body 1, can be hydrogen, helium or other gas.Air bag main body 1 seals.Avoid gas leakage.The difference of the aerial buoyancy of low energy consumption aircraft and self gravitation, is less than 1/10th of self gravitation value.Further preferably, the difference of the aerial buoyancy of low energy consumption aircraft and self gravitation, one of two percentages being greater than self gravitation value.
Air bag main body 1 can for being at least one in superman, angel, angle, fairy maiden, dragon, bird, winged insect, aircraft, the sun or moon moulding.
Suspension position fixing system 2 detouchable is fixed on air bag main body 1.Can be by being adhesively fixed on air bag main body 1.So that suspension position fixing system 2 and common air bag main body 1 are arranged in pairs or groups flexibly.Can be that suspension position fixing system 2 is bonded in above air bag main body 1 or below.Suspension position fixing system 2 is provided with a bonding coat.Bonding coat is provided with a parting paper.In use parting paper is peeled off, be then bonded on air bag main body 1.Can be that flying power system do not installed by low energy consumption aircraft so that simplification system, reduce gravity, reduce costs, save energy extend the flight time.
In concrete enforcement, a kind of form can be set to: the aerial buoyancy of low energy consumption aircraft is less than self gravitation, lifting power plant 21 for only providing the lifting power plant 21 of lifting power, to simplify system.To simplify system; Or can be set to: lifting power plant 21, for both providing lifting power, can provide again the lifting power plant 21 of decline power, to realize flexible response.
In concrete enforcement, lifting power plant 21 can adopt following form:
(1) lifting power plant 21 adopts propeller arrangement, propeller arrangement comprises an electrical motor and a screw propeller fin, and the blowing direction of screw propeller fin upward or down, electrical motor connects screw propeller fin by transmission device, drive screw propeller fin to rotate, and then produce thrust.
Upgrading engine installation 21 is provided with at least two screw propellers, and two screw propeller symmetry arrangement are in the center of gravity both sides of air bag main body.Thus allow after omission is similar to the structure of empennage of helicopter, still can held stationary flight.
(2) lifting power plant 21 adopts fin arrangement, fin arrangement comprises an electrical motor and and swings fin, swings the swaying direction of fin for swinging up and down, and electrical motor connects swing fin by transmission device, drive and swing fin and swing, and then produce upwards or downward thrust.
(3) lifting power plant 21 adopts a heat energy regulator control system, heat energy regulator control system comprises an electric heater unit, electric heater unit is on a balloon, for balloon provides heat, expand after material in balloon is heated, and then impel balloon volume to increase, and then buoyancy is increased, thus produce buoyancy upwards.Electric heater unit can be positioned at balloon or be attached to outside the balloon wall of balloon.Balloon can be air bag main body 1, and namely electric heater unit is positioned at air bag main body 1.Balloon also independent of air bag main body 1, can be connected with air bag main body 1.Can be positioned at outside air bag main body 1 or air bag main body 1.
When adopting heat energy regulator control system, be also provided with a container below balloon, the heater element of electric heater unit is positioned at container.Container content has liquid substance, and liquid substance, under the heating of heater element, produces steam, and then increases the volume of balloon.Thus increase buoyancy.Liquid can adopt the boiling points such as water, propylene dichloride, parabolic hydrocarbon, alkene, alcohol, aldehyde, amine, ester, ether, ketone, aromatic hydrocarbon, hydrogenate hydrocarbon, terpene hydrocarbon, halogenated hydrocarbons lower, be easy to the liquid evaporated, concrete composition can also be water, alcohol, formaldehyde, gasoline, ether.Container is positioned at below balloon, and the edge of opening of container and the balloon wall of balloon are fitted.So that become liquid or solid-state material after cooling, again fall back in container, use in order to heating next time.
In specific embodiment, height measuring device 23 can adopt following form:
Height measuring device 23 can adopt reflective height measuring device 23, comprises a sender unit and a signal receiving device.The signal downrange of sender unit towards, with the Signal reception direction of signal receiving device towards consistent so that receive the signal fired back.The signal downrange of sender unit towards, with the Signal reception direction of signal receiving device towards, all downward or top.
Downward time, by measuring terrain clearance, elevation information can be known.Upward time, can by the distance of measuring distance top ceiling when indoor, side reflects the elevation information of flight.
Signal receiving device is after receiving the signal that sender unit sends, produce a high level, high level output is to microprocessor system 22, and microprocessor system 22 is powered for lifting power plant 21, lifting power plant 21 is worked, carries out rising or declining.
Microprocessor system 22 can be a signal amplification circuit.The electric current that amplifying signal receiving device exports, and then drive lifting power plant 21 to work.Microprocessor system 22 can comprise a time delay circuit.Time delay is carried out to the current impulse that signal receiving device exports, and then drives lifting power plant 21 to work gently, avoid pulse current to cause rush of current to lifting power plant 21.Suspension position fixing system 2 also comprises a battery system, and battery system is provided with charging inlet.And power for suspension position fixing system 2.
Signal reception direction towards down, during the useful signal launched by sender unit reflected below signal receiving device receives, microprocessor system 22 is considered as flying height lower than setting height, controls the lift that lifting power plant 21 provides rising.
Signal reception direction towards down, during the useful signal launched by sender unit reflected below signal receiving device does not receive, microprocessor system 22 is considered as flying height higher than setting height, controls the power that lifting power plant 21 provides decline.
Signal reception direction towards upward, during the useful signal launched by sender unit reflected above signal receiving device receives, microprocessor system 22 is considered as flying height higher than setting height, controls the power that lifting power plant 21 provides decline.
Reflective height measuring device 23, can adopt an active infra-red distance measuring equipment (DME), sender unit adopts an infrared launcher, and signal receiving device adopts an infrared receiving device.
Reflective height measuring device 23, can adopt a supersonic range finder, and sender unit adopts a ultrasonic transmission device, and signal receiving device adopts a ultrasonic probe, ultrasonic receiver.
Reflective height measuring device 23, can adopt a laser ranging system, and sender unit adopts a laser emitting device, and signal receiving device adopts a laser signal receiving device.
Low energy consumption aircraft is also passable, also comprises a flying power system, and a signal handling equipment, and signal handling equipment also connects the control interface of flying power system.Flying power system provides action power for low energy consumption aircraft.
Flying power system comprises electrical motor and blower impeller, and motor driven fan wheel rotation provides power.Can also be that flying power system comprises electrical motor and fin, direct motor drive fin swings and provides power.
Signal handling equipment is also connected with a wireless interaction system, and wireless interaction system support has a wireless interaction terminal.Low energy consumption aircraft realizes information interaction by wireless interaction system and wireless interaction terminal.
Information interaction comprises low energy consumption aircraft state data and is handed down to unlimited interactive terminal.Also comprise, control command is uploaded to wireless interaction system by wireless interaction terminal, and then is uploaded to signal handling equipment.Also comprise, wireless interaction terminal sends remote signal to wireless interaction system in real time, and then is uploaded to signal handling equipment, carries out real time remote control control.
Low energy consumption aircraft is also equipped with picture pick-up device, and GPS fixing aid or Big Dipper fixing aid, picture pick-up device and GPS fixing aid or Big Dipper fixing aid are connected to a microprocessor system, and the information association that the image data that picture pick-up device absorbs by microprocessor system and GPS fixing aid or Big Dipper fixing aid are located is preserved.So that stored images, and the geographic position of image is indicated.
Can also wireless signal transmission system be set, in good time by picture pick-up device data and GPS fixing aid or Big Dipper fixing aid data transmission to wayside equipment.
More than show and describe groundwork of the present utility model and principal character and advantage of the present utility model.The technical personnel of the industry should be understood; the utility model is not restricted to the described embodiments; what describe in above-described embodiment and specification sheets just illustrates principle of the present utility model; under the prerequisite not departing from the utility model spirit and scope; the utility model also has various changes and modifications, and these changes and improvements all fall within the scope of claimed the utility model.The claimed scope of the utility model is defined by appending claims and equivalent thereof.
Claims (63)
1. low energy consumption aircraft, comprises an air bag main body, it is characterized in that, also comprises the radio signal reception system, the microprocessor system that are directly or indirectly fixed on air bag main body, and one provides the lifting power plant of power for rising or declining;
The signal output part of described radio signal reception system connects described microprocessor system, and described microprocessor system connects the signal input part of lifting power plant;
Described air bag main body is the closed cavity of a flexibility;
The gas that density is less than air is filled with in described air bag main body;
Be filled with the buoyancy that density is less than the air bag main body of the gas of air and be greater than gravity, but the difference of buoyancy and gravity, be less than the gravity sum of described radio signal reception system and described lifting power plant.
2. low energy consumption aircraft according to claim 1, is characterized in that: also comprise a suspension position fixing system; Described suspension position fixing system is connected on described air bag main body.
3. low energy consumption aircraft according to claim 2, is characterized in that: described suspension position fixing system, comprises the height measuring device of a detection height;
Described height measuring device connects described microprocessor system, lifting power plant described in described microprocessor system control linkage one.
4. low energy consumption aircraft according to claim 2, is characterized in that: radio signal reception system, microprocessor system, lifting power plant and suspension position fixing system are encapsulated in a shell, fix together.
5. low energy consumption aircraft according to claim 1, is characterized in that: the chamber wall of described air bag main body, is elastic material.
6. low energy consumption aircraft according to claim 1, is characterized in that: the chamber wall thickness of described air bag main body, is less than 2mm, is greater than 0.05mm.
7. low energy consumption aircraft according to claim 3, it is characterized in that: described height measuring device detects flying height and elevation information is passed to described microprocessor system, microprocessor system, according to elevation information, controls lifting power plant.
8. low energy consumption aircraft according to claim 7, is characterized in that: when height detecting device detects flying height lower than setting height, and described microprocessor system controls described lifting power plant and performs vertical motion, makes air bag main body increase;
When flying height being detected higher than setting height, described microprocessor system controls described lifting power plant and performs down maneuver, and air bag main body is declined.
9. low energy consumption aircraft according to claim 1, is characterized in that: the aerial buoyancy of described low energy consumption aircraft is less than self gravitation, and described lifting power plant is for only providing the lifting power plant of lifting power.
10. low energy consumption aircraft according to claim 1, is characterized in that: described lifting power plant, for both providing lifting power, can provide again the lifting power plant of decline power.
11. low energy consumption aircraft according to claim 1, is characterized in that: described lifting power plant adopts a propeller arrangement, a fin arrangement, or a heat energy regulator control system.
12. low energy consumption aircraft according to claim 11, is characterized in that: described lifting power plant adopts propeller arrangement;
Described propeller arrangement comprises an electrical motor and a screw propeller fin, and the blowing direction of described screw propeller fin upward or down, described electrical motor connects described screw propeller fin by transmission device, drives described screw propeller fin to rotate.
13. low energy consumption aircraft according to claim 12, is characterized in that: described lifting power plant is provided with at least two screw propellers, and two screw propeller symmetry arrangement are in the center of gravity both sides of air bag main body.
14. low energy consumption aircraft according to claim 11, it is characterized in that: when described lifting power plant adopts fin arrangement, described fin arrangement comprises an electrical motor and and swings fin, the swaying direction of described swing fin is for swinging up and down, described electrical motor connects described swing fin by transmission device, drives described swing fin to swing.
15. low energy consumption aircraft according to claim 11, is characterized in that: when described lifting power plant adopts a heat energy regulator control system, described heat energy regulator control system comprises an electric heater unit, and described electric heater unit is on a balloon.
16. low energy consumption aircraft according to claim 15, it is characterized in that: described electric heater unit provides heat for described balloon, expands, and then impel balloon volume to increase after the material in balloon is heated, and then buoyancy is increased, thus produce buoyancy upwards.
17. low energy consumption aircraft according to claim 15, is characterized in that: described electric heater unit is positioned at described balloon or is attached to outside the balloon wall of described balloon.
18. low energy consumption aircraft according to claim 15, is characterized in that: described balloon is described air bag main body, and namely described electric heater unit is positioned at described air bag main body.
19. low energy consumption aircraft according to claim 15, is characterized in that: described balloon, independent of described air bag main body, is connected with described air bag main body.
20. low energy consumption aircraft according to claim 19, is characterized in that: described balloon is positioned at outside described air bag main body or described air bag main body.
21. low energy consumption aircraft according to claim 11, it is characterized in that: when described lifting power plant adopts a heat energy regulator control system, described heat energy regulator control system comprises an electric heater unit, also be provided with a container below one balloon, the heater element of described electric heater unit is positioned at described container.
22. low energy consumption aircraft according to claim 21, is characterized in that: described container content has liquid substance.
23. low energy consumption aircraft according to claim 22, is characterized in that: described liquid substance, under the heating of described heater element, produces steam, and then increases the volume of described balloon, thus increases buoyancy.
24. low energy consumption aircraft according to claim 22, is characterized in that: described liquid substance adopts boiling point lower, is easy to the liquid evaporated.
25. low energy consumption aircraft according to claim 22, is characterized in that: described liquid substance adopt in water, propylene dichloride, parabolic hydrocarbon, alkene, alcohol, aldehyde, amine, ester, ether, ketone, aromatic hydrocarbon, hydrogenate hydrocarbon, terpene hydrocarbon, halogenated hydrocarbons any one.
26. low energy consumption aircraft according to claim 22, is characterized in that: described liquid substance adopt in alcohol, formaldehyde, gasoline, ether any one.
27. low energy consumption aircraft according to claim 21, is characterized in that: described container is positioned at below described balloon, and the edge of opening of described container and the balloon wall of described balloon are fitted.
28. low energy consumption aircraft according to claim 3, is characterized in that: described height measuring device adopts reflective height measuring device, comprise a sender unit and a signal receiving device;
The signal downrange of described sender unit towards, with the Signal reception direction of described signal receiving device towards consistent.
29. low energy consumption aircraft according to claim 28, it is characterized in that: described signal receiving device is after receiving the signal that described sender unit sends, produce a high level, described high level output gives described microprocessor system, described microprocessor system is that described lifting power plant is powered, and makes described lifting power plant work.
30. low energy consumption aircraft according to claim 1, is characterized in that: described microprocessor system is a signal amplification circuit.
31. low energy consumption aircraft according to claim 30, is characterized in that: signal amplification circuit amplifies the electric current that described signal receiving device exports, and then drives described lifting power plant work.
32. low energy consumption aircraft according to claim 1, is characterized in that: described microprocessor system comprises a time delay circuit.
33. low energy consumption aircraft according to claim 32, it is characterized in that: time delay circuit carries out time delay to the current impulse that described signal receiving device exports, and then drive described lifting power plant to work gently, avoid pulse current to cause rush of current to described lifting power plant.
34. low energy consumption aircraft according to claim 2, is characterized in that: described suspension position fixing system also comprises a battery system, and described battery system is provided with charging inlet.
35. low energy consumption aircraft according to claim 34, is characterized in that: described battery system is that described suspension position fixing system is powered.
36. low energy consumption aircraft according to claim 28, it is characterized in that: Signal reception direction towards down, during the useful signal launched by described sender unit reflected below described signal receiving device receives, described microprocessor system is considered as flying height lower than setting height, controls the lift that described lifting power plant provides rising.
37. low energy consumption aircraft according to claim 36, it is characterized in that: Signal reception direction towards down, during the useful signal launched by described sender unit reflected below described signal receiving device does not receive, described microprocessor system is considered as flying height higher than setting height, controls the power that described lifting power plant provides decline.
38. low energy consumption aircraft according to claim 28, it is characterized in that: Signal reception direction towards upward, during the useful signal launched by described sender unit reflected above described signal receiving device receives, described microprocessor system is considered as flying height higher than setting height, controls the power that described lifting power plant provides decline.
39. low energy consumption aircraft according to claim 28, it is characterized in that: reflective height measuring device, adopt an active infra-red distance measuring equipment (DME), described sender unit adopts an infrared launcher, and described signal receiving device adopts an infrared receiving device.
40. low energy consumption aircraft according to claim 28, it is characterized in that: reflective height measuring device, adopt a supersonic range finder, described sender unit adopts a ultrasonic transmission device, and described signal receiving device adopts a ultrasonic probe, ultrasonic receiver.
41. low energy consumption aircraft according to claim 28, it is characterized in that: reflective height measuring device, adopt a laser ranging system, described sender unit adopts a laser emitting device, and described signal receiving device adopts a laser signal receiving device.
42., according to the low energy consumption aircraft in claim 1-41 described in any one, is characterized in that: be filled with hydrogen or helium that density is less than air in described air bag main body.
43., according to the low energy consumption aircraft in claim 1-41 described in any one, is characterized in that: described air bag main body sealing.
44., according to the low energy consumption aircraft in claim 1-41 described in any one, is characterized in that: the difference of the aerial buoyancy of described low energy consumption aircraft and self gravitation, is less than 1/10th of self gravitation value.
45. low energy consumption aircraft according to claim 44, is characterized in that: the difference of the aerial buoyancy of low energy consumption aircraft and self gravitation, one of two percentages being greater than self gravitation value.
46., according to the low energy consumption aircraft in claim 2-4,34-35 described in any one, is characterized in that: described suspension position fixing system detouchable is fixed on described air bag main body.
47. low energy consumption aircraft according to claim 46, is characterized in that: described suspension position fixing system is by being adhesively fixed on described air bag main body.
48. low energy consumption aircraft according to claim 47, is characterized in that: described suspension position fixing system is bonded in above described air bag main body or below.
49., according to the low energy consumption aircraft in claim 2-4,34-35 described in any one, is characterized in that: described suspension position fixing system is provided with a bonding coat.
50. low energy consumption aircraft according to claim 49, is characterized in that: described bonding coat is provided with a parting paper.
51., according to the low energy consumption aircraft in claim 1-41 described in any one, is characterized in that: flying power system do not installed by described low energy consumption aircraft.
52., according to the low energy consumption aircraft in claim 1-41 described in any one, is characterized in that: also comprise a flying power system, and a signal handling equipment, and described signal handling equipment also connects the control interface of described flying power system.
53. low energy consumption aircraft according to claim 52, is characterized in that: described flying power system provides action power for low energy consumption aircraft.
54. low energy consumption aircraft according to claim 52, is characterized in that: described flying power system comprises electrical motor and blower impeller, and blower impeller described in described direct motor drive rotates and provides power.
55. low energy consumption aircraft according to claim 52, is characterized in that: described flying power system comprises electrical motor and fin, and fin described in described direct motor drive swings and provides power.
56., according to the low energy consumption aircraft in claim 1-41 described in any one, is characterized in that: described signal handling equipment is also connected with a wireless interaction system, and described wireless interaction system support has a wireless interaction terminal.
57. low energy consumption aircraft according to claim 56, is characterized in that: low energy consumption aircraft realizes information interaction by described wireless interaction system and wireless interaction terminal.
58. low energy consumption aircraft according to claim 57, is characterized in that: described information interaction comprises low energy consumption aircraft state data and is handed down to described wireless interaction terminal.
59. low energy consumption aircraft according to claim 58, is characterized in that: described information interaction also comprises, control command is uploaded to described wireless interaction system by described wireless interaction terminal, and then is uploaded to described signal handling equipment.
60. low energy consumption aircraft according to claim 59, it is characterized in that: described information interaction also comprises, described wireless interaction terminal sends remote signal to described wireless interaction system in real time, and then is uploaded to described signal handling equipment, carries out real time remote control control.
61. according to the low energy consumption aircraft in claim 1-41 described in any one, it is characterized in that: described low energy consumption aircraft is also equipped with picture pick-up device, and GPS fixing aid or Big Dipper fixing aid, described picture pick-up device and described GPS fixing aid or Big Dipper fixing aid are connected to a microprocessor system.
62. low energy consumption aircraft according to claim 61, is characterized in that: the information association that the image data that described picture pick-up device absorbs by described microprocessor system and described GPS fixing aid or Big Dipper fixing aid are located is preserved.
63. low energy consumption aircraft according to claim 61, is characterized in that: be also provided with in good time by picture pick-up device data and GPS fixing aid or the Big Dipper fixing aid data transmission wireless signal transmission system to wayside equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420633993.1U CN204587293U (en) | 2014-10-29 | 2014-10-29 | Low energy consumption aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420633993.1U CN204587293U (en) | 2014-10-29 | 2014-10-29 | Low energy consumption aircraft |
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| Publication Number | Publication Date |
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| CN204587293U true CN204587293U (en) | 2015-08-26 |
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| CN201420633993.1U Expired - Fee Related CN204587293U (en) | 2014-10-29 | 2014-10-29 | Low energy consumption aircraft |
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| CN (1) | CN204587293U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105644763A (en) * | 2016-03-24 | 2016-06-08 | 成都衔石科技有限公司 | Hot gas balloon capable of facilitating energy consumption reduction |
| CN105799906A (en) * | 2016-03-24 | 2016-07-27 | 成都衔石科技有限公司 | Energy-saving type hot light balloon |
| CN106291757A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of using method of the sounding balloon of adjustable point monitoring |
| CN106291759A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of using method of pinpoint sounding balloon |
| CN106291758A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of pinpoint sounding balloon |
-
2014
- 2014-10-29 CN CN201420633993.1U patent/CN204587293U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105644763A (en) * | 2016-03-24 | 2016-06-08 | 成都衔石科技有限公司 | Hot gas balloon capable of facilitating energy consumption reduction |
| CN105799906A (en) * | 2016-03-24 | 2016-07-27 | 成都衔石科技有限公司 | Energy-saving type hot light balloon |
| CN105644763B (en) * | 2016-03-24 | 2018-07-27 | 成都衔石科技有限公司 | Convenient for reducing the fire balloon of energy consumption |
| CN106291757A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of using method of the sounding balloon of adjustable point monitoring |
| CN106291759A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of using method of pinpoint sounding balloon |
| CN106291758A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of pinpoint sounding balloon |
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