CN105217027A - Vertical takeoff and landing formula bimodal airflight equipment and control method thereof - Google Patents
Vertical takeoff and landing formula bimodal airflight equipment and control method thereof Download PDFInfo
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- CN105217027A CN105217027A CN201510616472.4A CN201510616472A CN105217027A CN 105217027 A CN105217027 A CN 105217027A CN 201510616472 A CN201510616472 A CN 201510616472A CN 105217027 A CN105217027 A CN 105217027A
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Abstract
The present invention relates to a kind of vertical takeoff and landing formula bimodal airflight equipment and control method thereof, this equipment includes fuselage, is characterized in: the front end of fuselage and rear end are distributed with the lifting engine unit that some lift engines form.The speed difference between inner four driving engines of lifting engine unit can be utilized, the operational torque of the driftage of flying platform under this mode, roll and pitching is provided, realizes the effective control to flying platform.The layout of front and rear part driving engine overlap, have compressed the space that flight equipment width occupies to greatest extent, and flight equipment is flown flexibly in narrow space.Effectively can win the job requirement under any two model of flights, low speed hovering, vertical takeoff and landing can either can realize again that failure-free is at a high speed flat to fly.Lifting wing is folded in fuselage interior under vertical takeoff and landing/hovering mode, makes aircraft when low-speed operations, operates dexterousr.
Description
Technical field
The present invention relates to a kind of flight equipment and control method thereof, particularly relate to a kind of vertical takeoff and landing formula bimodal airflight equipment and control method thereof.
Background technology
Vertical take-off and landing aircraft (VTOL aircraft) can make the constraint of aircraft gun off the runway, and particularly under major war condition, airport and aircraft carrier are all easy to going to wreck property and hit, thus make fixed wing aircraft lose the place of landing.In addition vertical take-off and landing aircraft (VTOL aircraft) deployment and throw in can be very hidden and timely, make the delivery of military strength have emergentness, be conducive to the task of expection.
Although traditional helicopter has vertical takeoff and landing ability, its ceiling is not high, needs comparatively big thrust loading, and flight noise is also very large.In addition, what it was huge expose, and rotor makes it be difficult under the intricately such as city and jungle condition environment, perform complicated maneuver warfare task, particularly its rotor mechanism adds the complexity of system, aerodynamics problem is brought to be coupled with Structural Dynamics the gas bullet problem of the complex produced, and comparatively large by the impact of flight environment of vehicle, therefore reliability and maintainability poor.If the advantages of both common fixed wing aircraft and helicopter can be got up, forming one can vertical takeoff and landing, has again comparatively high maneuverability, simple and reliable for structure, meet the requirement of relevant thrust-weight ratio, the aerocraft of not strict lifting restriction, so its Military value will strengthen greatly.
Prior art 201310557048.8, provide a kind of aircraft, it comprises main body, also comprises: two bonts, arranges on the body, and described two bonts interval in the working direction of described main body is arranged.Meanwhile, each described bont comprises: rotating shaft, arranges rotationally on the body; Multiple rotating blade, described multiple rotating blade is fixed on the outer peripheral face of described rotating shaft at each interval.
Further, the quantity of described multiple rotating blade is even number, and described multiple rotating blade is evenly arranged along the circumference of described rotating shaft.Each described bont also comprises: Horizontal limiting portion, is set in described rotating shaft, and described Horizontal limiting portion is arranged on the body.Each described bont also comprises: bearing, is arranged between described Horizontal limiting portion and described rotating shaft.The hand of rotation of two rotating shafts of described two bonts is contrary.Each described bont also comprises: ventilating duct, and have two relative open ends, described multiple rotating blade is arranged on the inside of described ventilating duct.Described rotating blade is two, and described two rotating blades extend in opposite direction, and described two rotating blades are fixed on contiguous block, and described contiguous block has the through hole wearing described rotating shaft, and described contiguous block is fixed in described rotating shaft.Also comprise: Double shaft-extension asynchronous motor, have the first axle drive shaft and the second axle drive shaft, two rotating shafts of described two bonts drive with described first axle drive shaft and described second axle drive shaft one_to_one corresponding and are connected.Moreover each described bont is ducted fan.
Thus, its main purpose realized is: the bont being provided with two intervals in main body, can by controlling, and the hoisting force of bont to main body reaches advance or the retrogressing of aircraft.Replace the counterweight of prior art to realize advance or the retrogressing of aircraft with two bonts, simple to operate, bont provides lift to main body, avoids the rollover phenomenon of main body.But, do not solve gas bullet problem and noise problem.
Also have a prior art 201410030256.7, which provide a kind of Multi-axis aircraft, comprise support and be installed on the drive system on described support, described drive system comprises: a motor; Multiple rotor, described motor drives described multiple rotor synchronously to rotate by synchronous drive mechanism, and described synchronous drive mechanism comprises gear.Simultaneously, described synchronous drive mechanism comprises can by the main shaft of described motor-driven rotation, described multiple rotor is symmetrically distributed in the both sides of described main shaft, is connected to the first transmission device between described main shaft and each rotor, is connected with the second transmission device between described main shaft and motor.
Its feature realized is provided with a motor, and drive all rotors synchronously to rotate by this motor, and owing to only arranging a motor, cost is low, lightweight; And relative to multiple motor, the impact of high-frequency vibration on visibility of taking photo by plane that motor produces obtains larger weakening; In addition, drive all rotors to rotate by a motor, each rotor synchronism is almost completely the same simultaneously.But it cannot realize stable high-speed flight, and belongings ability, cross-cutting application cannot be realized.
Because above-mentioned defect, the design people, actively in addition research and innovation, to founding a kind of vertical takeoff and landing formula bimodal airflight equipment and control method thereof, make it have more value in industry.
Summary of the invention
For solving the problems of the technologies described above, the object of this invention is to provide a kind of vertical takeoff and landing formula bimodal airflight equipment and control method thereof.
Vertical takeoff and landing formula bimodal airflight equipment of the present invention, include fuselage, wherein: the front end of described fuselage and rear end are distributed with the lifting engine unit that some lift engines form, the ventilation inlet cross section of each lift engine described is circular, and cross sectional shape is in the same size, the described lifting engine unit being positioned at front end includes a Duct-Burning Turbofan, No. three ducted fan driving engine compositions, the described lifting engine unit being positioned at rear end includes No. two Duct-Burning Turbofans, No. four ducted fan driving engine compositions, described No. three ducted fan driving engines, all duct is formed above the working end of No. four ducted fan driving engines, the duct place being positioned at described No. three ducted fan driving engines is provided with a Duct-Burning Turbofan, the road place being positioned at described No. four ducted fan driving engines is provided with No. two Duct-Burning Turbofans, described No. three ducted fan driving engines, Duct-Burning Turbofan is provided with overlapping region between ventilation inlet region separately, described No. four ducted fan driving engines, No. two Duct-Burning Turbofans are also provided with overlapping region between ventilation inlet region separately, described fuselage is provided with thrust fan driving engine, described fuselage is provided with energy supply device, the energy supply port of described energy supply device and a Duct-Burning Turbofan, No. three ducted fan driving engines, No. two Duct-Burning Turbofans, No. four ducted fan driving engines, the transmission of electricity port of thrust fan driving engine is connected.
Further, above-mentioned vertical takeoff and landing formula bimodal airflight equipment, wherein, described overlapping region area ratio is 5% to 70%.
Further, above-mentioned vertical takeoff and landing formula bimodal airflight equipment, wherein, described fuselage is provided with symmetrical lifting wing.
Further, above-mentioned vertical takeoff and landing formula bimodal airflight equipment, wherein, described lifting wing is folding wing, or, be inflatable wing.
Further, above-mentioned vertical takeoff and landing formula bimodal airflight equipment, wherein, below described fuselage and/or be that inside is provided with load cabin, described load cabin and fuselage adopt buckle to be connected.
Further, above-mentioned vertical takeoff and landing formula bimodal airflight equipment, wherein, load cabin comprises one or more combinations in mechanical arm, extinguishing equipment, aerial delivery provisions.
Further, above-mentioned vertical takeoff and landing formula bimodal airflight equipment, wherein, be provided with remote control in described fuselage, the host port of the control port of described remote control and a Duct-Burning Turbofan, No. three ducted fan driving engines, No. two Duct-Burning Turbofans, No. four ducted fan driving engines, thrust fan driving engine is connected.
Further, above-mentioned vertical takeoff and landing formula bimodal airflight equipment, wherein, in described fuselage, be provided with data processing equipment, described data processing equipment be connected with one or more in altitude instrument, level indicator, gyroscope, data radio station, Image transmission equipment.
Vertical takeoff and landing formula bimodal airflight apparatus control method, wherein: when being in vertical takeoff and landing/hovering mode, the blade left-hand revolution of a Duct-Burning Turbofan and No. two Duct-Burning Turbofan inside, the blade clickwise of No. three ducted fan driving engines and No. four ducted fan driving engines; Lifting wing is accommodated in fuselage interior; Be at a high speed flat when flying mode, lifting wing is opened, and thrust fan driving engine is started working, for flying platform provides propulsive force forward.
By such scheme, the present invention at least has the following advantages:
1, the lift of flight equipment under vertical takeoff and landing/hovering mode is provided by lifting engine unit, utilize the speed difference between inner four driving engines of lifting engine unit, the operational torque of the driftage of flying platform under this mode, roll and pitching is provided, realizes the effective control to flying platform.
2, the layout of front and rear part driving engine overlap, have compressed the space that flight equipment width occupies to greatest extent, flight equipment is flown flexibly in narrow space, No. three ducted fan driving engines and No. four ducted fan engine design profile of duct, makes again flight equipment obtain extra duct lift augment.
3, effectively can win the job requirement under any two model of flights, low speed hovering, vertical takeoff and landing can either can realize again that failure-free is at a high speed flat to fly.
4, lifting wing is folded in fuselage interior under vertical takeoff and landing/hovering mode, makes aircraft when low-speed operations, operates dexterousr, reduces the size dimensions of target especially in Military Application field, improve the safety in utilization of aircraft.
Above-mentioned explanation is only the general introduction of technical solution of the present invention, in order to better understand technological means of the present invention, and can be implemented according to the content of specification sheets, coordinates accompanying drawing to be described in detail as follows below with preferred embodiment of the present invention.
Accompanying drawing explanation
Fig. 1 is the structural representation of vertical takeoff and landing formula bimodal airflight equipment.
In figure, the implication of each Reference numeral is as follows.
No. 1 Duct-Burning Turbofans 2 No. three ducted fan driving engines
3 fuselage 4 load cabins
5 No. 6 four, thrust fan driving engine ducted fan driving engines
7 No. two Duct-Burning Turbofan 8 lifting wings
Detailed description of the invention
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following examples for illustration of the present invention, but are not used for limiting the scope of the invention.
Vertical takeoff and landing formula bimodal airflight equipment as shown in Figure 1, include fuselage 3, its unusual part is: in order to realize stable flight effect, there is provided necessary vertical space lifting drive, the front end of fuselage 3 and rear end are distributed with the lifting engine unit that some lift engines form.Consider current-controlled stable, the ventilation inlet cross section of each lift engine is circular, and cross sectional shape is in the same size.Specifically, in order to stable flight path can be realized, and the front and back Power output meeting fuselage 3 cooperatively interacts, the lifting engine unit being positioned at front end includes a Duct-Burning Turbofan 1, No. three ducted fan driving engines 2 and forms, and the lifting engine unit being positioned at rear end includes No. two Duct-Burning Turbofans 7, No. four ducted fan driving engines 6 and forms.
Need in conjunction with actual flight, in order to the stable driving space providing rising thrust can be had, above the working end of No. three ducted fan driving engines 2, No. four ducted fan driving engines 6, all form duct.Further, the duct place being positioned at No. three ducted fan driving engines 2 is provided with a Duct-Burning Turbofan 1, and the road place being positioned at No. four ducted fan driving engines 6 is provided with No. two Duct-Burning Turbofans 7.Meanwhile, considering from reducing intrinsic flight width to the full extent, reducing the space occupied, the present invention is provided with overlapping region between the ventilation inlet region that No. three ducted fan driving engines 2, Duct-Burning Turbofan 1 is respective.Corresponding with it, between the ventilation inlet region that No. four ducted fan driving engines 6, No. two Duct-Burning Turbofans 7 are respective, be also provided with overlapping region.Further, in order to the satisfied needs carried out flight and drive, fuselage 3 is provided with thrust fan driving engine 5.Moreover fuselage 3 is also provided with energy supply device, and energy supply port and a Duct-Burning Turbofan 1, No. three ducted fan driving engines 2, No. two Duct-Burning Turbofans 7, No. four ducted fan driving engines 6 of energy supply device, the transmission of electricity port of thrust fan driving engine 5 are connected.Thus, be used to provide the necessary operation energy, be convenient to the normal operation of each device feature.
In conjunction with the present invention one preferably embodiment, in actual manufacture debugging, overlapping region area ratio can be set between 5% to 70%.Like this, when reality is implemented, the space that occupies on flight width can be greatly reduced, can fly flexibly in narrow space more.Further, coordinate the design of ducted fan driving engine, extra duct lift augment can be obtained.
Further, consider the stable needs of follow-up high-speed flight, can not occur significantly going off course because of airflow function, fuselage 3 is provided with symmetrical lifting wing 8.Consider the space hold during actual vertical lift, reduce the impact that lifting wing 8 exists as far as possible, the lifting wing 8 of employing is folding wing.Like this, or else need can carry out actv. folding storage when using.Further, inflatable wing can also be adopted.Inflate when needs use, make lifting wing 8 launch.When needs storage, carry out Quick air-discharge, complete storage.
Meanwhile, in order to meet the lift-launch needs of each generic task equipment, improve practicality, the present invention is below fuselage 3 and/or be that inside is provided with load cabin 4.Specifically, in order to meet rapid and firm connection, the load cabin 4 of employing with fuselage 3 for buckle is connected.Further, consider that the aerial mission of actual execution is different, the load cabin 4 that the present invention adopts comprises one or more combinations in mechanical arm, extinguishing equipment, aerial delivery provisions.Like this, realize upper air installing task by mechanical arm, realize high-altitude fire extinguishing etc. by extinguishing equipment, meet different use needs.
Again further, consider the stability of energy supply, meet the needs of fast charging and discharging simultaneously, be conducive to maintenance in the future and replace fast, the energy supply device that the present invention adopts is lead-acid storage battery or is lithium-ions battery.And, in order to realize Long-distance Control needs, necessary manual intervention can be carried out during automatic cruising, improve the accuracy of flight path, the present invention is also provided with remote control in fuselage 3, and control port and a Duct-Burning Turbofan 1, No. three ducted fan driving engines 2, No. two Duct-Burning Turbofans 7, No. four ducted fan driving engines 6 of this remote control, the host port of thrust fan driving engine 5 are connected.Certainly, in order to meet intelligentized unmanned control flight needs, data processing equipment can also be provided with in fuselage, data processing equipment is connected with one or more in altitude instrument, level indicator, gyroscope, data radio station, Image transmission equipment.Thus, provide various flight call parameter, be convenient to data processing equipment to carry out the centralization process of data, promote the stability of autonomous flight.
Use control in conjunction with reality of the present invention, in order to have sound flight controlling mechanism, now coordinate hardware construction of the present invention to provide a kind of control method, its content comprises as follows:
When 1, being in vertical takeoff and landing/hovering mode, the blade left-hand revolution of a Duct-Burning Turbofan 1 and No. two Duct-Burning Turbofan 7 inside, the blade clickwise of No. three ducted fan driving engines 2 and No. four ducted fan driving engines 6.During this period, lifting wing 8 is accommodated in fuselage 3 inside.Like this, the lift utilizing lifting engine unit to produce is offset gravity and is realized flight, utilizes the speed discrepancy between four driving engines to produce the operational torque of driftage, roll, pitching.Meanwhile, because lifting wing 8 has carried out actv. storage, make flight equipment when low-speed operations, operate dexterousr, reduce the size dimensions of target especially in Military Application field, improve the safety in utilization of flight equipment.
2, be at a high speed flat when flying mode, lifting wing 8 is opened, and thrust fan driving engine 5 is started working, and provides propulsive force forward.During this period, utilize lifting wing 8 to produce most of lift, utilize lifting engine unit to produce the operational torque of flying platform driftage, roll, pitching, realize the effective control to flight equipment.Now, lift and control torque do not exist coupled relation, there is not the flat stalling incidence flown in flight equipment, therefore has very high maneuvering performance in theory.
Also can be found out by reference to the accompanying drawings by above-mentioned character express, after adopting the present invention, gather around and have the following advantages:
1, the lift of flight equipment under vertical takeoff and landing/hovering mode is provided by lifting engine unit, utilize the speed difference between inner four driving engines of lifting engine unit, the operational torque of the driftage of flying platform under this mode, roll and pitching is provided, realizes the effective control to flying platform.
2, the layout of front and rear part driving engine overlap, have compressed the space that flight equipment width occupies to greatest extent, flight equipment is flown flexibly in narrow space, No. three ducted fan driving engines and No. four ducted fan engine design profile of duct, makes again flight equipment obtain extra duct lift augment.
3, effectively can win the job requirement under any two model of flights, low speed hovering, vertical takeoff and landing can either can realize again that failure-free is at a high speed flat to fly.
4, lifting wing is folded in fuselage interior under vertical takeoff and landing/hovering mode, makes aircraft when low-speed operations, operates dexterousr, reduces the size dimensions of target especially in Military Application field, improve the safety in utilization of aircraft.
The above is only the preferred embodiment of the present invention; be not limited to the present invention; should be understood that; for those skilled in the art; under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and modification, these improve and modification also should be considered as protection scope of the present invention.
Claims (9)
1. vertical takeoff and landing formula bimodal airflight equipment, include fuselage, it is characterized in that: the front end of described fuselage (3) and rear end are distributed with the lifting engine unit that some lift engines form, the ventilation inlet cross section of each lift engine described is circular, and cross sectional shape is in the same size, the described lifting engine unit being positioned at front end includes a Duct-Burning Turbofan (1), No. three ducted fan driving engine (2) compositions, the described lifting engine unit being positioned at rear end includes No. two Duct-Burning Turbofans (7), No. four ducted fan driving engine (6) compositions, described No. three ducted fan driving engines (2), all duct is formed above the working end of No. four ducted fan driving engines (6), the duct place being positioned at described No. three ducted fan driving engines (2) is provided with a Duct-Burning Turbofan (1), the road place being positioned at described No. four ducted fan driving engines (6) is provided with No. two Duct-Burning Turbofans (7), described No. three ducted fan driving engines (2), overlapping region is provided with between the ventilation inlet region that Duct-Burning Turbofan (1) is respective, described No. four ducted fan driving engines (6), also overlapping region is provided with between the ventilation inlet region that No. two Duct-Burning Turbofans (7) are respective, described fuselage (3) is provided with thrust fan driving engine (5), (3) are provided with energy supply device to described fuselage, the energy supply port of described energy supply device and a Duct-Burning Turbofan (1), No. three ducted fan driving engines (2), No. two Duct-Burning Turbofans (7), No. four ducted fan driving engines (6), the transmission of electricity port of thrust fan driving engine (5) is connected.
2. vertical takeoff and landing formula bimodal airflight equipment according to claim 1, is characterized in that: described overlapping region area ratio is 5% to 70%.
3. vertical takeoff and landing formula bimodal airflight equipment according to claim 1, is characterized in that: described fuselage (3) is provided with symmetrical lifting wing (8).
4. vertical takeoff and landing formula bimodal airflight equipment according to claim 3, is characterized in that: described lifting wing (8) is folding wing, or, be inflatable wing.
5. vertical takeoff and landing formula bimodal airflight equipment according to claim 1, it is characterized in that: described fuselage (3) below and/or be that inside is provided with load cabin (4), described load cabin (4) adopts buckle to be connected with fuselage (3).
6. vertical takeoff and landing formula bimodal airflight equipment according to claim 5, is characterized in that: described load cabin (4) comprises one or more combinations in mechanical arm, extinguishing equipment, aerial delivery provisions.
7. vertical takeoff and landing formula bimodal airflight equipment according to claim 1, it is characterized in that: described fuselage is provided with remote control in (3), the host port of the control port of described remote control and a Duct-Burning Turbofan (1), No. three ducted fan driving engines (2), No. two Duct-Burning Turbofans (7), No. four ducted fan driving engines (6), thrust fan driving engine (5) is connected.
8. vertical takeoff and landing formula bimodal airflight equipment according to claim 1, it is characterized in that: described fuselage is provided with data processing equipment in (3), described data processing equipment is connected with one or more in altitude instrument, level indicator, gyroscope, data radio station, Image transmission equipment.
9. vertical takeoff and landing formula bimodal airflight apparatus control method, it is characterized in that: when being in vertical takeoff and landing/hovering mode, the blade left-hand revolution of a Duct-Burning Turbofan (1) and No. two Duct-Burning Turbofan (7) inside, the blade clickwise of No. three ducted fan driving engines (2) and No. four ducted fan driving engines (6); It is inner that lifting wing (8) is accommodated in fuselage (3); Be at a high speed flat when flying mode, lifting wing (8) is opened, and thrust fan driving engine (5) is started working, for flying platform provides propulsive force forward.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510616472.4A CN105217027A (en) | 2015-09-24 | 2015-09-24 | Vertical takeoff and landing formula bimodal airflight equipment and control method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510616472.4A CN105217027A (en) | 2015-09-24 | 2015-09-24 | Vertical takeoff and landing formula bimodal airflight equipment and control method thereof |
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| CN105217027A true CN105217027A (en) | 2016-01-06 |
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| CN201510616472.4A Pending CN105217027A (en) | 2015-09-24 | 2015-09-24 | Vertical takeoff and landing formula bimodal airflight equipment and control method thereof |
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| CN107676318A (en) * | 2017-10-26 | 2018-02-09 | 苏州大闹天宫机器人科技有限公司 | Seesaw toy based on true and false piston |
| CN109279005A (en) * | 2017-07-21 | 2019-01-29 | 通用电气公司 | The aircraft of vertical takeoff and landing |
| CN112607021A (en) * | 2020-12-25 | 2021-04-06 | 上海电气集团股份有限公司 | Manned unmanned aerial vehicle |
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| CN112607021A (en) * | 2020-12-25 | 2021-04-06 | 上海电气集团股份有限公司 | Manned unmanned aerial vehicle |
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