CN205034339U - Bimodal air travel equipment - Google Patents
Bimodal air travel equipment Download PDFInfo
- Publication number
- CN205034339U CN205034339U CN201520747804.8U CN201520747804U CN205034339U CN 205034339 U CN205034339 U CN 205034339U CN 201520747804 U CN201520747804 U CN 201520747804U CN 205034339 U CN205034339 U CN 205034339U
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- China
- Prior art keywords
- duct
- fan driving
- ducted fan
- fuselage
- bimodal
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Abstract
The utility model relates to a bimodal air travel equipment, this equipment including fuselage, its characteristics is: the lift engine group that cloth is compriseed is divided equally a plurality of lift engine to the front end and the rear end of fuselage. Rotational speed difference between four engines in the usable lift engine inter block portion provides the operating torque of driftage, roll and the every single move of flying platform under this mode, realizes the effective control to the flying platform. The overall arrangement that preceding rear engine adopt to be overlapped, furthest's compression the space that occupies on the flight equipment width, make the flight equipment can nimble flight in constrictive space. Can be competent at two kinds of flight job requirements under the mode effectively, can reach that low -speed hovers, the VTOL can realize again that reliable high speed tie flies. The lift wing makes flight equipment when low -speed flies in VTOL / hover and fold inside the fuselage under the mode, operate dexterouslyr.
Description
Technical field
The utility model relates to a kind of flight equipment, particularly relates to a kind of bimodal airflight equipment.
Background technology
Vertical take-off and landing aircraft (VTOL aircraft) can make the constraint of flight equipment 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 flight equipment, 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 flight equipment.Replace the counterweight of prior art to realize advance or the retrogressing of flight equipment 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 multiaxis flight equipment, 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 bimodal airflight equipment, make it have more value in industry.
Utility model content
For solving the problems of the technologies described above, the purpose of this utility model is to provide a kind of bimodal airflight equipment.
Bimodal airflight equipment of the present utility model, 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 duct 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 bimodal airflight equipment, wherein, described overlapping region area ratio is 5% to 70%.
Further, above-mentioned bimodal airflight equipment, wherein, described fuselage is provided with symmetrical lifting wing.
Further, above-mentioned bimodal airflight equipment, wherein, described lifting wing is folding wing, or, be inflatable wing.
Further, above-mentioned bimodal airflight equipment, wherein, the below of 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 bimodal airflight equipment, wherein, load cabin is one or more combinations in mechanical arm, extinguishing equipment, aerial delivery provisions.
Further, above-mentioned 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 bimodal airflight equipment, wherein, is provided with data processing equipment in described fuselage, described data processing equipment is connected with one or more in altitude instrument, level indicator, gyroscope, data radio station, Image transmission equipment.
By such scheme, the utility model at least has the following advantages:
1, by lifting engine unit, the lift of flight equipment under vertical takeoff and landing/hovering mode is provided, 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, front and rear part driving engine adopts overlapping layout, 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 flight equipment when low-speed operations, operates dexterousr, reduces the size dimensions of target especially in Military Application field, improve the safety in utilization of flight equipment.
Above-mentioned explanation is only the general introduction of technical solutions of the utility model, in order to better understand technological means of the present utility model, 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 utility model.
Accompanying drawing explanation
Fig. 1 is the structural representation of 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, detailed description of the invention of the present utility model is described in further detail.Following examples for illustration of the utility model, but are not used for limiting scope of the present utility model.
Bimodal airflight equipment as shown in Figure 1, include fuselage 3, its unusual part is: in order to realize stable flight effect, and provide 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 duct 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 utility model 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 utility model 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 utility model is in the below of 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 utility model adopts is 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 utility model 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 utility model 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 utility model, 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 utility model, gather around and have the following advantages:
1, by lifting engine unit, the lift of flight equipment under vertical takeoff and landing/hovering mode is provided, 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, front and rear part driving engine adopts overlapping layout, 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 flight equipment when low-speed operations, operates dexterousr, reduces the size dimensions of target especially in Military Application field, improve the safety in utilization of flight equipment.
The above is only preferred implementation of the present utility model; be not limited to the utility model; should be understood that; for those skilled in the art; under the prerequisite not departing from the utility model know-why; can also make some improvement and modification, these improve and modification also should be considered as protection domain of the present utility model.
Claims (8)
1. 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 duct 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. bimodal airflight equipment according to claim 1, is characterized in that: described overlapping region area ratio is 5% to 70%.
3. bimodal airflight equipment according to claim 1, is characterized in that: described fuselage (3) is provided with symmetrical lifting wing (8).
4. bimodal airflight equipment according to claim 3, is characterized in that: described lifting wing (8) is folding wing, or, be inflatable wing.
5. bimodal airflight equipment according to claim 1, it is characterized in that: the below of described fuselage (3) and/or be that inside is provided with load cabin (4), described load cabin (4) adopts buckle to be connected with fuselage (3).
6. bimodal airflight equipment according to claim 5, is characterized in that: described load cabin (4) is mechanical arm, one or more in extinguishing equipment, aerial delivery provisions combine.
7. 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. 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520747804.8U CN205034339U (en) | 2015-09-24 | 2015-09-24 | Bimodal air travel equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520747804.8U CN205034339U (en) | 2015-09-24 | 2015-09-24 | Bimodal air travel equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205034339U true CN205034339U (en) | 2016-02-17 |
Family
ID=55293258
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520747804.8U Expired - Fee Related CN205034339U (en) | 2015-09-24 | 2015-09-24 | Bimodal air travel equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205034339U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217027A (en) * | 2015-09-24 | 2016-01-06 | 苏州大闹天宫机器人科技有限公司 | Vertical takeoff and landing formula bimodal airflight equipment and control method thereof |
| CN106741979A (en) * | 2017-03-09 | 2017-05-31 | 杭州米为科技有限公司 | A kind of drive mechanism for aircraft |
| WO2018163159A1 (en) * | 2017-03-07 | 2018-09-13 | Colugo Systems Ltd | Folded wing multi rotor |
-
2015
- 2015-09-24 CN CN201520747804.8U patent/CN205034339U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217027A (en) * | 2015-09-24 | 2016-01-06 | 苏州大闹天宫机器人科技有限公司 | Vertical takeoff and landing formula bimodal airflight equipment and control method thereof |
| WO2018163159A1 (en) * | 2017-03-07 | 2018-09-13 | Colugo Systems Ltd | Folded wing multi rotor |
| EP3592645A4 (en) * | 2017-03-07 | 2020-12-16 | Colugo Systems Ltd | Folded wing multi rotor |
| CN106741979A (en) * | 2017-03-09 | 2017-05-31 | 杭州米为科技有限公司 | A kind of drive mechanism for aircraft |
| CN106741979B (en) * | 2017-03-09 | 2023-08-15 | 杭州米为科技有限公司 | Transmission structure for aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160217 Termination date: 20160924 |
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| CF01 | Termination of patent right due to non-payment of annual fee |