CN103523199A - Novel tubular-structure electric unmanned helicopter - Google Patents
Novel tubular-structure electric unmanned helicopter Download PDFInfo
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- CN103523199A CN103523199A CN201310454463.0A CN201310454463A CN103523199A CN 103523199 A CN103523199 A CN 103523199A CN 201310454463 A CN201310454463 A CN 201310454463A CN 103523199 A CN103523199 A CN 103523199A
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Abstract
The invention relates to a novel tubular-structure electric unmanned helicopter which has the prominent advantages of large load, high stability and long duration of voyage. When the novel tubular-structure electric unmanned helicopter is applied in different industries, the workflow is optimized, the working efficiency is improved, and the operation strength and the safety risk of labor personnel are reduced. The novel tubular-structure electric unmanned helicopter is implemented through the following technical scheme: the electric unmanned helicopter uses a novel material, is designed in a four-tube structure, is low in cost and high in safety and can load different equipment to work; due to the high transmission ratio and duty ratio as well as a lithium polymer battery, the running time of a novel power battery is prolonged, and a piece of much heavier operation equipment can be loaded; a tail tube detachable device, a tail vane shock mitigation system and a flybarless structure guarantee the stability and the safety of the unmanned helicopter; a cloud deck stabilizing technique guarantees the shooting angle, so that the picture flutter can be reduced to the greatest extent in the shooting from high altitude; and the industrial-grade application of the unmanned helicopter is achieved in the true sense.
Description
Technical field
The present invention relates to a kind of novel pipe structure electric depopulated helicopter, there is the outstanding advantages such as load is large, stability is high, duration of voyage is long, be applied in without in industry, can optimized work flow, increase work efficiency, reduce work personnel's operation intensity and security risk.
The present invention adopts four tubular type airframe structures (1), tail pipe detachable apparatus (2), tail actuator shock mitigation system (3) and without aileron structure (5), be the design of a kind of high transmission ratio and duty ratio (4), load the electric depopulated helicopter of lithium polymer battery.Relate to a kind of new forms of energy power that utilizes, can carry the unmanned helicopter system that distinct device carries out operation, combining wireless electricity, satellite navigation, gyroscope technology, can realize depopulated helicopter automatic Pilot, remote safe operation, the unmanned helicopter system of Long-range Data Transmission, storage.Increase The Cloud Terrace and increased the angle that steady technology (8) has been guaranteed shooting, when high-altitude is taken, can farthest reduce the shake of picture simultaneously.
The present invention has guaranteed stability and the safety of electric unmanned helicopter aircraft, has extended the duration of voyage of new forms of energy batteries; For relevant industries have improved work efficiency, saved labour cost again.
Background technology
Along with the applied research of depopulated helicopter in every profession and trade, people all the more now depopulated helicopter are day by day remarkable in the effect of social production and life various aspects.Use modern new and high technology mechanical equipment, not only can increase work efficiency with quality, reduce operating cost, can also reduce the risk of personnel's operation, the protection security of the lives and property.Along with science and technology is constantly progressive, the enhancing of economic capability, the lifting of the level of consumption, the work that the alternative traditional manpower of modern conveniences is engaged in excessive risk, highly difficult, high operation intensity has become inexorable trend.The whole world for the third time industrial revolution prelude is pulled open, and develops the depopulated helicopter of low cost, high stability, applied range, has become a kind of exigence.
At present domestic depopulated helicopter is also in elementary development phase, because the Structure Designing Problem of fuselage, cause high cost, stability not, fuselage and the bottleneck such as load equipment matching degree is low, restricting depopulated helicopter always and carrying out other widespread use of industrial grade.Along with the active demand of every profession and trade to industrial grade depopulated helicopter, a kind of low cost, the unmanned helicopter system that stability is high, fuselage can be realized electrodeless adjusting seem particularly important.The present invention adopts the airframe structure of four tubular types, has strengthened again the intensity of airframe structure when saving manufacturing cost, can realize electrodeless adjusting, can carry neatly different industry equipment.Tail pipe detachable apparatus (2) design, not only can reduce the wearing and tearing of Timing Belt, alleviates Timing Belt resonance, guarantee the safety and stability of unmanned helicopter flight, can also make depopulated helicopter transportation convenient, operating efficiency is higher, reduces traffic cost.Tail actuator shock mitigation system (3), can alleviate the load of steering wheel, improves precision and speed of response that tail vane is controlled, guarantees flight safety, increases the service life.High transmission ratio and duty ratio (4) can provide larger lift, strengthen the load-carrying capacity of depopulated helicopter, realize duty ratio and reach 1:1.83.Without aileron structure (5), not only alleviated the weight of depopulated helicopter, can also keep the stability of aircraft flight, controlled helicopter and fly flexibly.Adopt new material and new type power power supply, strengthened the fuselage intensity of depopulated helicopter, improved the aeroplane performance of depopulated helicopter, extended the cruise duration of depopulated helicopter.The Cloud Terrace increases steady technology (8) and has guaranteed the angle of taking, and when high-altitude is taken, can farthest reduce the shake of picture simultaneously.
The present invention can make unmanned helicopter system combine with sector application, realizes the depopulated helicopter industry level applications of real meaning.
Summary of the invention
The problem that the present invention mainly solves is, has overcome the technical bottleneck of existing depopulated helicopter, and a kind of new material that used is provided, and low cost, the high security of four tubular structures designs, can carry the electric unmanned helicopter that distinct device carries out operation; Design by high transmission ratio and duty ratio (4), adds lithium polymer battery, has extended the duration of voyage of new forms of energy batteries, and can carry the implement that weight is larger; Tail pipe detachable apparatus (2), tail actuator shock mitigation system (3), and without aileron structure (5), all guaranteed stability and the safety of unmanned helicopter flight; The Cloud Terrace increases steady technology (8) and has guaranteed shooting angle, while taking in high-altitude, can farthest reduce float; Realize the depopulated helicopter industrial scale applications of real meaning.
1, four tubular type airframe structures (1)
The present invention adopts the airframe structure of four tubular types, compares with traditional design (board-like framed structure), can save 60% production material, reduces by 40% manufacturing cost, improves 20% production efficiency.First, circular pipe can be more easy in the course of processing, saved complicated technique in conventional processes and loaded down with trivial details link.Make the agent structure simplification that becomes, process simplyr, it is also more convenient to assemble; Reduced material cost, can enhance productivity again.Secondly, four tubular type airframe structures (1) are compared with traditional depopulated helicopter airframe structure, and because its intensity has obtained reinforcement, so wind loading rating, anti-external interference ability gets a promotion.Make depopulated helicopter more stable in flight course, properties of product have more standby stability, reliability and safety, reach domestically leading level.Again, four tubular type airframe structures (1) have greatly alleviated the weight of depopulated helicopter self, strengthen load-carrying capacity, extend flying time limit.Four tubular type main body mechanisms (1) feature of paramount importance, is embodied in and can realizes electrodeless adjusting, fuselage can freedom and flexibility the different industry equipment of ground collocation, carry out engineer operation.Tubular type Design of Main Structure, simple in structure.Make the layout of inner driving system more reasonable, increased inner space, facilitated the installation of corollary equipment.Increased the space of flying platform fuselage, the comfort feature connecting between equipped system is increased, counterweight is more easy to operate.At present, because fuselage design does not mate with carrying equipment, restricting depopulated helicopter in application and the safety of every profession and trade.The present invention can flexible airframe structure, adapts to different industry equipment, after carrying equipment of the present invention, can adjust depopulated helicopter center of gravity, makes that flight is more stable, safety.
Adopt four tubular type airframe structures (1), main body frame is comprised of four circular pipes, and recycling is buckle fixedly, is connected with running part, empennage part, The Cloud Terrace and the foot rest of depopulated helicopter; Four tubular type airframe structures (1) are by 3 fuselage ring links and 2 transmission shaft permanent seat parts, by 4 sections of circular pipes, are fastenedly connected side by side; It is characterized in that: four tubular type airframe structures (1) can carry out electrodeless adjusting, fuselage ring link and transmission shaft permanent seat parts can be adjusted to freedom and flexibility length and size on circular pipe; The limitation of having avoided traditional design mode to install, has increased inner space, and the restricted of the mechanical parts such as motor, battery reduced, and can conveniently connect and fix.
The design's advantage: can conveniently install, debug and change parts, improve the matching degree of whole parts; Again more point of adjustment can be set on main body frame, arbitrarily install, accelerate the speed of installing.The limitation of having avoided traditional design mode to install, particularly, to flight debugging and maintenance, has played vital effect.
2, tail pipe detachable apparatus (2)
The present invention adopts tail pipe detachable apparatus (2) design, by adding synchronizing wheel, reduce the length of tail Timing Belt, such benefit is to reduce the wearing and tearing of Timing Belt, extend the service life of Timing Belt, reduce because the air crash hidden danger that Timing Belt fracture causes.Because the shortening of Timing Belt girth, has reduced the resonance that Timing Belt produces in operation process, make unmanned helicopter flight more stable, guarantee the safety of flight.Meanwhile, because the reduction of vibrations also can reduce the impact that vibrations produce the precision instrument and equipment carrying.
The design of tail pipe detachable apparatus (2) makes to transport convenient, and when carrying out engineer operation task, owing to often wanting converting field, the transportation convenience of depopulated helicopter, directly has influence on the efficiency of operation.The design of tail pipe detachable apparatus (2), the tail pipe (6) that convenient working personnel can fast assembling-disassembling depopulated helicopter, saves time, and realizes quick transition, improves operating efficiency.During simultaneously because of transportation depopulated helicopter, reduce in shared space, and traffic cost also significantly reduces.
The present invention solves its technical matters and realizes by the following technical solutions:
A kind of electric unmanned helicopter tail pipe detachable apparatus (2), comprises tail pipe connecting device and synchronous transmission device, and described tail pipe connecting device includes adaptor union and is connected with screw, for being connected of depopulated helicopter tail pipe (6) and fuselage; Synchronous transmission device includes synchronizing wheel and axle and bearing, bearing is inlayed and is connected with adaptor union, pass through belt-driving, power transmission for tail rotor, reducing strap length reduces belt wearing and tearing and reduces belt resonance, one of them gear of synchronizing wheel is connected with depopulated helicopter power system by belt, and another gear is connected with the transmission gear of the tail rotor of depopulated helicopter by belt, by such connection mode, power transmission, gives tail rotor.
3, tail actuator shock mitigation system (3)
The present invention adopts tail actuator shock mitigation system (3), is to use unstressed principle, controls the key component of tail rotor; By tail actuator, control system and shock mitigation system three parts, formed, by tail actuator control system, drive the rotation of tail rotor, in rotary course, be arranged on 8 damping springs of tail actuator control system, the torsion of meeting self-equalizing tail rotor rotation, thus make tail rotor reach damping; Tail actuator shock mitigation system (3), can balance from the torsion of four direction up and down; Tail actuator shock mitigation system (3) is positioned at the empennage part of depopulated helicopter, and for controlling tail rotor, the balance depopulated helicopter reactive torque that main rotor produces when flight, adjusts the heading of depopulated helicopter and the posture in flight course.In routine, because the long-time higher load condition of tail actuator carries out work, shortened in the life-span of tail actuator, and easy et out of order, once fault generation result will be the crash that causes whole depopulated helicopter, the harm people's the security of the lives and property.
The present invention has added tail actuator shock mitigation system (3), the physical design that it is special, can significantly reduce tail actuator at suffered load of when work, improves the precision that tail actuator is controlled, extend the service life of tail actuator, guarantee the safety of unmanned helicopter flight.
4, high transmission ratio and duty ratio (4)
The present invention, through long-term experimental verification, sums up a series of gear ratio coefficient.High transmission ratio and duty ratio (4), adopt double reduction driving gear set, by motor driving first order transmission gear, to the reducing gear of the first order, then by the reducing gear coaxial linkage of the first order, drive second stage transmission gear, transmission gear by the second stage, to the reducing gear (being main gear) of the second stage,, reach the object of deceleration.Thereby by double reduction, can significantly reduce the diameter of main gear, guaranteed that airframe structure is compacter, increase the transmitting ratio of depopulated helicopter, under high load condition, guarantee depopulated helicopter stable output of motor power when work, the hoisting force of depopulated helicopter is strengthened, airworthiness promotes, and guarantees the safety of flight, and reaching duty ratio is 1:1.83; This has very positive meaning for extending depopulated helicopter duration of voyage.
5, without aileron structure (5)
It is connection and the opposed installation in two ends of 2 main oar folders in 1 that the present invention has used without aileron structure (5), by transverse axis, connects; 2 main oars are arranged on respectively two main oar folders above, use screw and nut to carry out fastening.The middle main shaft top that is arranged on, is used screw and nut to penetrate fastening, below middle, adopts fastening design, use 2 screws locked with being connected of main shaft, by 2 connecting rod the controlled pitch of screws; Reduce the complexity of rotor head, alleviate the weight of aircraft, make the more close main rotor plane of center of gravity, retain original speed of response and alerting ability, guarantee again the stability of flight; The present invention has used the mode combining with three-axis gyroscope without aileron structure (5) to control, in conjunction with gyroscope effect, the reaction Billy of electronic system wants fast a lot of with the aileron speed of response that physical principle is carried out balance, the amount of revising also puts in place very much, utilize the mixing of steering wheel to control, the stability that can keep aircraft flight, controls helicopter and flies flexibly.
6, the application of new material
The application of new material, comprises that tail pipe (6) adopts special carbon fibre material, and this carbon fibre material goods are by impregnated carbon fiber resin by the continuous pultrusion of pressurization of heating to grinding tool, and specification shape is as bar, sheet material and other profile shapes; Possess the characteristics such as high strength, lightweight, withstanding corrosion, high temperature resistant, rub resistance, pliable and tough good, easy processing; What foot rest (7) part adopted is hydronalium; This material is a kind of cold treatment forging and stamping alloy, and intensity is high, outclass mild steel; Depopulated helicopter is used this material as fuselage grillage, has strengthened resistance to abrasion, the fuselage intensity of depopulated helicopter, has also alleviated the weight of depopulated helicopter simultaneously.
7, The Cloud Terrace increases steady technology (8)
It is The Cloud Terrace damping and the effective combination that increases steady technology that the The Cloud Terrace that the present invention uses increases steady technology (8) essence, by 4 installation components, four groups, amounts to 12 rubber sphere and 1 The Cloud Terrace adapter plate forms; Four drift angles of The Cloud Terrace adapter plate are laid one group of 3 rubber sphere, amount to four groups; The Cloud Terrace adapter plate is connected with 4 fixing bodies by rubber sphere; By shock-absorbing ball, alleviate the shake of The Cloud Terrace; , the The Cloud Terrace of design is three axle The Cloud Terraces, except can realizing level rolling, upper and lower pitching, can also carry out 360 and horizontally rotate; Compared to traditional The Cloud Terrace, add The Cloud Terrace to increase steady technology (8) and there is more wide visual angle, higher stability, can guarantee the device security that The Cloud Terrace carries, when carrying out high-altitude shooting, can farthest reduce the shake of picture.
8, the application of new forms of energy
The present invention uses the lithium polymer battery more environmental and durable than lithium ion battery, compared to traditional battery, and the lithium polymer battery Reusability that can repeatedly circulate, durable, can not produce any pollution to environment; Secondly, lithium polymer battery has higher discharge rate, can meet the requirement of the high power consumption of depopulated helicopter; Again, lithium polymer battery is easily designed to different shapes, and volume is relatively little, can meet well the structural requirement of depopulated helicopter; Finally, lithium polymer battery, under equal volume, is compared other battery qualities lighter, can effectively reduce the load pressure of depopulated helicopter.
The present invention adopts driven by power, has than the moving lower noise of depopulated helicopter of oil, disguised better.Cruise duration of the present invention is longer, discharges and recharges number of times more, longer service life.
Accompanying drawing explanation
Fig. 1 is the present embodiment structural representation;
Fig. 2 is the present embodiment state of flight schematic diagram;
Fig. 3 is the present embodiment plan sketch;
Fig. 4 is the present embodiment four tubular type airframe structure (1) global facility figure;
Fig. 5 is the present embodiment four tubular type airframe structure (1) main element figure;
Fig. 6 is that the present embodiment four tubular type airframe structures (1) split component diagram;
Fig. 7 is the present embodiment tail pipe detachable apparatus (2) main element figure;
Fig. 8 is the present embodiment tail pipe detachable apparatus (2) intraware figure;
Fig. 9 is that the present embodiment tail pipe detachable apparatus (2) splits component diagram;
Figure 10 is the present embodiment tail actuator shock mitigation system (3) global facility figure;
Figure 11 is the present embodiment high transmission ratio and duty ratio (4) global facility figure;
Figure 12 is that the present embodiment is without aileron structure (5) global facility figure;
Figure 13 is the present embodiment tail pipe (6) global facility figure;
Figure 14 is the present embodiment foot rest (7) global facility figure;
Figure 15 is that the present embodiment The Cloud Terrace increases steady technology (8) global facility figure;
Figure 16 is that the present embodiment The Cloud Terrace increases steady technology (8) main element figure;
Figure 17 is that the present embodiment The Cloud Terrace increases steady technology (8) fractionation component diagram;
Figure 18 is the present embodiment battery mounting (9) global facility figure.
In figure, (1) four tubular type airframe structure, (2) tail pipe detachable apparatus, (3) tail actuator shock mitigation system, (4) high transmission ratio and duty ratio, (5) are without aileron structure, (6) tail pipe, (7) foot rest, (8) The Cloud Terrace increases steady technology, (9) battery mounting.
The specific embodiment
Below in conjunction with accompanying drawing and preferred embodiment, to according to the specific embodiment provided by the invention, structure, feature and effect thereof, be described in detail as follows.
Embodiment: as Figure 1-3, a kind of new material that used, low cost, the high security of four tubular structures designs, can carry the electric unmanned helicopter that distinct device carries out operation; Design by high transmission ratio and duty ratio (4), adds lithium polymer battery, has extended the duration of voyage of new forms of energy batteries, and can carry the implement that weight is larger; Tail pipe detachable apparatus (2), tail actuator shock mitigation system (3), and without aileron structure (5), all guaranteed stability and the safety of unmanned helicopter flight; The Cloud Terrace increases steady technology (8) and has guaranteed shooting angle, while taking in high-altitude, can farthest reduce float; Realize the depopulated helicopter industrial scale applications of real meaning.
The electric unmanned helicopter of the present embodiment, comprises following summary of the invention:
1) as Figure 4-Figure 6, adopt four tubular type airframe structures (1), main body frame is comprised of four circular pipes, and recycling is buckle fixedly, is connected with running part, empennage part, The Cloud Terrace and the foot rest of depopulated helicopter; Four tubular type airframe structures (1) are by 3 fuselage ring links and 2 transmission shaft permanent seat parts, by 4 sections of circular pipes, are fastenedly connected side by side; It is characterized in that: four tubular type airframe structures (1) can carry out electrodeless adjusting, fuselage ring link and transmission shaft permanent seat parts can be adjusted to freedom and flexibility length and size on circular pipe.
2) as Figure 7-9, electric unmanned helicopter tail pipe detachable apparatus (2), tail pipe connecting device and synchronous transmission device, consist of, described tail pipe connecting device includes adaptor union and is connected with screw, for being connected of depopulated helicopter tail pipe and fuselage; Synchronous transmission device includes synchronizing wheel and axle and bearing, bearing is inlayed and is connected with adaptor union, pass through belt-driving, power transmission for tail rotor, one of them gear of synchronizing wheel is connected with depopulated helicopter power system by belt, another gear is connected with the transmission gear of the tail rotor of depopulated helicopter by belt, by such connection mode, power transmission, gives tail rotor.
3) as shown in figure 10, tail actuator shock mitigation system (3), is to use unstressed principle, controls the key component of tail rotor; By tail actuator, control system and shock mitigation system three parts, formed, by tail actuator control system, drive the rotation of tail rotor, in rotary course, be arranged on 8 damping springs of tail actuator control system, the torsion of meeting self-equalizing tail rotor rotation, thus make tail rotor reach damping; Tail actuator shock mitigation system (3), can balance from the torsion of four direction up and down; Tail actuator shock mitigation system (3) is positioned at the empennage part of depopulated helicopter, and for controlling tail rotor, the balance depopulated helicopter reactive torque that main rotor produces when flight, adjusts the heading of depopulated helicopter and the posture in flight course.
4) as shown in figure 11, high transmission ratio and duty ratio (4), adopt double reduction driving gear set, by motor driving first order transmission gear, to the reducing gear of the first order, then by the reducing gear coaxial linkage of the first order, drive second stage transmission gear, by the transmission gear of the second stage, to the reducing gear (being main gear) of the second stage,, reach the object of deceleration.Thereby by double reduction, can significantly reduce the diameter of main gear, guaranteed that airframe structure is compacter, increase the transmitting ratio of depopulated helicopter, under high load condition, guarantee depopulated helicopter stable output of motor power when work, the hoisting force of depopulated helicopter is strengthened, airworthiness promotes, and guarantees the safety of flight, and reaching duty ratio is 1:1.83.
5) as shown in figure 12, without aileron structure (5), be connection and the opposed installation in two ends of 2 main oar folders in 1, by transverse axis, connect; 2 main oars are arranged on respectively two main oar folders above, use screw and nut to carry out fastening.The middle main shaft top that is arranged on, is used screw and nut to penetrate fastening, below middle, adopts fastening design, use 2 screws locked with being connected of main shaft, by 2 connecting rod the controlled pitch of screws; Reduce the complexity of rotor head, alleviate the weight of aircraft, make the more close main rotor plane of center of gravity, retain original speed of response and alerting ability, guarantee again the stability of flight; The present invention has used the mode combining with three-axis gyroscope without aileron structure (5) to control, in conjunction with gyroscope effect, the reaction Billy of electronic system wants fast a lot of with the aileron speed of response that physical principle is carried out balance, the amount of revising also puts in place very much, utilize the mixing of steering wheel to control, the stability that can keep aircraft flight, controls helicopter and flies flexibly.
6) as shown in Figure 13-14, the application of new material, comprise that tail pipe (6) adopts special carbon fibre material, this carbon fibre material goods are by impregnated carbon fiber resin by the continuous pultrusion of pressurization of heating to grinding tool, and specification shape is as bar, sheet material and other profile shapes; Possess the characteristics such as high strength, lightweight, withstanding corrosion, high temperature resistant, rub resistance, pliable and tough good, easy processing; What foot rest (7) part adopted is hydronalium; This material is a kind of cold treatment forging and stamping alloy, and intensity is high, outclass mild steel; Depopulated helicopter is used this material as fuselage grillage, has strengthened resistance to abrasion, the fuselage intensity of depopulated helicopter, has also alleviated the weight of depopulated helicopter simultaneously.
7) as shown in Figure 15-17, it is The Cloud Terrace damping and the effective combination that increases steady technology that The Cloud Terrace increases steady technology (8) essence, by 4 installation components, four groups, amounts to 12 rubber sphere and 1 The Cloud Terrace adapter plate forms; Four drift angles of The Cloud Terrace adapter plate are laid one group of 3 rubber sphere, amount to four groups; The Cloud Terrace adapter plate is connected with 4 fixing bodies by rubber sphere; By shock-absorbing ball, alleviate the shake of The Cloud Terrace; , the The Cloud Terrace of design is three axle The Cloud Terraces, except can realizing level rolling, upper and lower pitching, can also carry out 360 and horizontally rotate; Compared to traditional The Cloud Terrace, add The Cloud Terrace to increase steady technology (8) and there is more wide visual angle, higher stability, can guarantee the device security that The Cloud Terrace carries, when carrying out high-altitude shooting, can farthest reduce the shake of picture.
8) as shown in figure 18, the application of new forms of energy refers to that depopulated helicopter has been used the lithium polymer battery more environmental and durable than lithium ion battery; Lithium polymer battery is to adopt file alloy to do positive pole, adopts macromolecule conducting material, polyacetylene, polyaniline or poly-Pyrogentisinic Acid etc. to do negative pole, and organic solvent is as electrolyte.Compared to traditional battery, the lithium polymer battery Reusability that can repeatedly circulate, durable, has higher discharge rate, can meet the requirement of the high power consumption of depopulated helicopter; Small volume, can be designed to different shapes, can meet well the structural requirement of depopulated helicopter; The depopulated helicopter that adopts lithium polymer battery to drive, has lower noise, and disguised better, cruise duration is longer, discharges and recharges number of times more, longer service life.
Claims (8)
1. a novel pipe structure electric depopulated helicopter, adopts four tubular type airframe structures (1), and main body frame is comprised of four circular pipes, and recycling is buckle fixedly, is connected with running part, empennage part, The Cloud Terrace and the foot rest of depopulated helicopter; Four tubular type airframe structures (1) are by 3 fuselage ring links and 2 transmission shaft permanent seat parts, by 4 sections of circular pipes, are fastenedly connected side by side; It is characterized in that: four tubular type airframe structures (1) can carry out electrodeless adjusting, fuselage ring link and transmission shaft permanent seat parts can be adjusted to freedom and flexibility length and size on circular pipe.
2. electric unmanned helicopter tail pipe detachable apparatus (2), is comprised of tail pipe connecting device and synchronous transmission device, and described tail pipe connecting device includes adaptor union and is connected with screw, for being connected of depopulated helicopter tail pipe and fuselage; Synchronous transmission device includes synchronizing wheel and axle and bearing, bearing is inlayed and is connected with adaptor union, pass through belt-driving, power transmission for tail rotor, one of them gear of synchronizing wheel is connected with depopulated helicopter power system by belt, another gear is connected with the transmission gear of the tail rotor of depopulated helicopter by belt, by such connection mode, power transmission, gives tail rotor.
3. tail actuator shock mitigation system (3), is to use unstressed principle, controls the key component of tail rotor; By tail actuator, control system and shock mitigation system three parts, formed, by tail actuator control system, drive the rotation of tail rotor, in rotary course, be arranged on 8 damping springs of tail actuator control system, the torsion of meeting self-equalizing tail rotor rotation, thus make tail rotor reach damping; Tail actuator shock mitigation system (3), can balance from the torsion of four direction up and down; Tail actuator shock mitigation system (3) is positioned at the empennage part of depopulated helicopter, and for controlling tail rotor, the balance depopulated helicopter reactive torque that main rotor produces when flight, adjusts the heading of depopulated helicopter and the posture in flight course.
4. high transmission ratio and duty ratio (4), adopt double reduction driving gear set, by motor driving first order transmission gear, to the reducing gear of the first order, then by the reducing gear coaxial linkage of the first order, drive second stage transmission gear, transmission gear by the second stage, to the reducing gear (being main gear) of the second stage,, reach the object of deceleration.Thereby by double reduction, can significantly reduce the diameter of main gear, guaranteed that airframe structure is compacter, increase the transmitting ratio of depopulated helicopter, under high load condition, guarantee depopulated helicopter stable output of motor power when work, the hoisting force of depopulated helicopter is strengthened, airworthiness promotes, and guarantees the safety of flight, and reaching duty ratio is 1:1.83.
5. without aileron structure (5), be connection and the opposed installation in two ends of 2 main oar folders in 1, by transverse axis, connect; 2 main oars are arranged on respectively two main oar folders above, use screw and nut to carry out fastening.The middle main shaft top that is arranged on, is used screw and nut to penetrate fastening, below middle, adopts fastening design, use 2 screws locked with being connected of main shaft, by 2 connecting rod the controlled pitch of screws; Reduce the complexity of rotor head, alleviate the weight of aircraft, make the more close main rotor plane of center of gravity, retain original speed of response and alerting ability, guarantee again the stability of flight; The present invention has used the mode combining with three-axis gyroscope without aileron structure (5) to control, in conjunction with gyroscope effect, the reaction Billy of electronic system wants fast a lot of with the aileron speed of response that physical principle is carried out balance, the amount of revising also puts in place very much, utilize the mixing of steering wheel to control, the stability that can keep aircraft flight, controls helicopter and flies flexibly.
6. a kind of novel pipe structure electric depopulated helicopter according to claim 1, is characterized in that, described tail pipe (6) employing novel carbon fiber material is made, foot rest (7) adopts novel aluminum-magnesium alloy material to make.
7. to increase steady technology (8) essence be The Cloud Terrace damping and the effective combination that increases steady technology to The Cloud Terrace, by 4 installation components, four groups, amounts to 12 rubber sphere and 1 The Cloud Terrace adapter plate forms; Four drift angles of The Cloud Terrace adapter plate are laid one group of 3 rubber sphere, amount to four groups; The Cloud Terrace adapter plate is connected with 4 fixing bodies by rubber sphere; By shock-absorbing ball, alleviate the shake of The Cloud Terrace; , the The Cloud Terrace of design is three axle The Cloud Terraces, except can realizing level rolling, upper and lower pitching, can also carry out 360 and horizontally rotate; Compared to traditional The Cloud Terrace, add The Cloud Terrace to increase steady technology (8) and there is more wide visual angle, higher stability, can guarantee the device security that The Cloud Terrace carries, when carrying out high-altitude shooting, can farthest reduce the shake of picture.
8. a kind of novel pipe structure electric depopulated helicopter according to claim 1, is characterized in that, described battery mounting (9) will carry a kind of new forms of energy battery of lighium polymer.
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803070A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN103803072A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN103803081A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN103818551A (en) * | 2014-01-24 | 2014-05-28 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN104554700A (en) * | 2015-01-28 | 2015-04-29 | 张伟 | Upper beam, helicopter airframe adopting same and helicopter |
| CN104691767A (en) * | 2014-06-19 | 2015-06-10 | 安阳全丰航空植保科技有限公司 | Shock absorbing system and shock absorbing method of unmanned helicopter with water-cooled engine |
| CN104773297A (en) * | 2015-04-27 | 2015-07-15 | 中国直升机设计研究所 | Electric-driven unmanned helicopter |
| CN104973256A (en) * | 2015-07-08 | 2015-10-14 | 芜湖万户航空航天科技有限公司 | Hybrid decelerator and unmanned helicopter |
| CN105059538A (en) * | 2015-07-31 | 2015-11-18 | 山西微风无人系统科技有限公司 | Modularized tail transmission system of unmanned helicopter |
| WO2016000485A1 (en) * | 2014-07-03 | 2016-01-07 | 青岛宏百川金属精密制品有限公司 | I-beam fuselage structure of unmanned helicopter |
| CN105329435A (en) * | 2014-12-19 | 2016-02-17 | 四川精石航空科技开发有限公司 | Tubular ultra-light helicopter frame |
| CN106275446A (en) * | 2015-06-01 | 2017-01-04 | 深圳市大疆创新科技有限公司 | Fixed structure and apply the flight equipment of this fixed structure |
| CN106770299A (en) * | 2017-03-14 | 2017-05-31 | 中国科学院遗传与发育生物学研究所农业资源研究中心 | The method and unmanned plane equipment that crop nitrogen analysis and soil application are instructed are carried out using unmanned plane crop canopies picture |
| CN108327897A (en) * | 2018-03-09 | 2018-07-27 | 深圳市轻准科技有限公司 | Equip with arms unmanned helicopter |
| CN108945515A (en) * | 2018-07-18 | 2018-12-07 | 中国人民解放军总参谋部第六十研究所 | A kind of helicopter fuselage frame and its application method with monitoring device |
| CN110634252A (en) * | 2019-10-26 | 2019-12-31 | 张争奇 | Visual hospital bed calling system |
| CN111216869A (en) * | 2020-04-22 | 2020-06-02 | 北京清航紫荆装备科技有限公司 | Cross double-rotor unmanned helicopter and rack assembly thereof |
| CN112896497A (en) * | 2021-03-23 | 2021-06-04 | 珠海紫燕无人飞行器有限公司 | Unmanned helicopter |
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Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803070A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN103803072A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN103803081A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN103818551A (en) * | 2014-01-24 | 2014-05-28 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN103818551B (en) * | 2014-01-24 | 2016-04-13 | 兰州神龙航空科技有限公司 | Vertical takeoff and landing rotary wind type unmanned vehicle |
| CN103803072B (en) * | 2014-01-24 | 2016-04-06 | 兰州神龙航空科技有限公司 | Engineering-type rotary wind type unmanned vehicle |
| CN103803070B (en) * | 2014-01-24 | 2016-04-06 | 兰州神龙航空科技有限公司 | Engineering-type rotary wind type unmanned vehicle |
| CN103803081B (en) * | 2014-01-24 | 2016-03-30 | 兰州神龙航空科技有限公司 | Vertical takeoff and landing rotary wind type unmanned vehicle |
| CN104691767A (en) * | 2014-06-19 | 2015-06-10 | 安阳全丰航空植保科技有限公司 | Shock absorbing system and shock absorbing method of unmanned helicopter with water-cooled engine |
| WO2016000485A1 (en) * | 2014-07-03 | 2016-01-07 | 青岛宏百川金属精密制品有限公司 | I-beam fuselage structure of unmanned helicopter |
| CN105329435A (en) * | 2014-12-19 | 2016-02-17 | 四川精石航空科技开发有限公司 | Tubular ultra-light helicopter frame |
| CN104554700A (en) * | 2015-01-28 | 2015-04-29 | 张伟 | Upper beam, helicopter airframe adopting same and helicopter |
| CN104773297A (en) * | 2015-04-27 | 2015-07-15 | 中国直升机设计研究所 | Electric-driven unmanned helicopter |
| CN106275446A (en) * | 2015-06-01 | 2017-01-04 | 深圳市大疆创新科技有限公司 | Fixed structure and apply the flight equipment of this fixed structure |
| CN106275446B (en) * | 2015-06-01 | 2020-05-05 | 深圳市大疆创新科技有限公司 | Fixed knot constructs and uses this fixed knot to construct flight equipment |
| CN104973256A (en) * | 2015-07-08 | 2015-10-14 | 芜湖万户航空航天科技有限公司 | Hybrid decelerator and unmanned helicopter |
| CN105059538A (en) * | 2015-07-31 | 2015-11-18 | 山西微风无人系统科技有限公司 | Modularized tail transmission system of unmanned helicopter |
| CN106770299A (en) * | 2017-03-14 | 2017-05-31 | 中国科学院遗传与发育生物学研究所农业资源研究中心 | The method and unmanned plane equipment that crop nitrogen analysis and soil application are instructed are carried out using unmanned plane crop canopies picture |
| CN108327897A (en) * | 2018-03-09 | 2018-07-27 | 深圳市轻准科技有限公司 | Equip with arms unmanned helicopter |
| CN108945515A (en) * | 2018-07-18 | 2018-12-07 | 中国人民解放军总参谋部第六十研究所 | A kind of helicopter fuselage frame and its application method with monitoring device |
| CN110634252A (en) * | 2019-10-26 | 2019-12-31 | 张争奇 | Visual hospital bed calling system |
| CN111216869A (en) * | 2020-04-22 | 2020-06-02 | 北京清航紫荆装备科技有限公司 | Cross double-rotor unmanned helicopter and rack assembly thereof |
| CN112896497A (en) * | 2021-03-23 | 2021-06-04 | 珠海紫燕无人飞行器有限公司 | Unmanned helicopter |
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