CN203681869U - Power system structure suitable for vertical take-off and landing air vehicle - Google Patents
Power system structure suitable for vertical take-off and landing air vehicle Download PDFInfo
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- CN203681869U CN203681869U CN201320859188.6U CN201320859188U CN203681869U CN 203681869 U CN203681869 U CN 203681869U CN 201320859188 U CN201320859188 U CN 201320859188U CN 203681869 U CN203681869 U CN 203681869U
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Abstract
The utility model provides a power system structure suitable for a vertical take-off and landing air vehicle. The power system structure comprises propellers for supplying power, wherein the propellers are arranged on the front sides and the rear sides of main wings on two sides of the air vehicle; the propellers positioned on the front sides of the main wings can be tilted from a vertical state into a horizontal state; the propellers positioned on the rear sides of the main wings can be tilted from a vertical state into a horizontal state. Due to the design, the power system structure realizes an arrangement and control mode similar to the conventional ripest and most stable X-type four-shaft air vehicle in a vertical take-off and landing mode, and retains the arrangement form, the effective wing area and the overall structure of the conventional reliable fixed-wing airplane under a level flight mode to the maximum extent; therefore, compared with other vertical take-off and landing air vehicles, the vertical take-off and landing air vehicle with the power system structure has the advantages of reasonable arrangement form, simple structure, ripe and reliable control mode, stable flight, far flight journey, large load and the like.
Description
Technical field
The utility model belongs to aviation aircraft design field, is specifically related to a kind of power system structure that is applicable to vertically taking off and landing flyer.
Background technology
The birth of vertical takeoff and landing technology is mainly because the deficiency, the particularly performance in all previous war of aircraft rolling start mode allow the vertical takeoff and landing of aircraft enter people's sight line.The war such as World War II and Mideast Asian war directly allows people experience to the attack on enemy airport needs the weak point of the sliding race formula aircraft of runway, and cold war is the catalyst of vertical takeoff and landing technology.Five sixties after World War II, very likely breaking out under the shade of nuclear war, fears are entertained that occurs that general nuclear warfare is to the situation that airport damages, conventional airplane cannot be set out, so expedited the emergence of the vertical takeoff and landing technology of fixed wing aircraft.Vertical take-off and landing aircraft (VTOL aircraft) reduces or has substantially broken away from the dependence to runway, only need very little level land just can rise sheer from level ground and vertical landing, so aircraft can decentralized configuration in war, be convenient to launch an attack flexibly, shift and pretend hidden, be difficult for being found by enemy, the attendance rate also significantly improves, and enemy's strike is had to very high emergentness, has greatly improved the battlefield survival rate of aircraft.
There is the fixed wing aircraft of vertical takeoff and landing ability not need special airport and runway, so just save expensive airport construction expense, need not drive bird, also can be in landing under bad weather condition, reduce use cost, but also it is far away to have voyage, the advantage that the conventional helicopters such as capacity weight height do not have.So vertical takeoff and landing Fixed Wing AirVehicle becomes a popular direction of aviation aircraft development.
Existing vertically taking off and landing flyer mostly adopts single shaft, twin shaft, or three axles etc. are controlled very difficult vertical takeoff and landing topology layout form, not only stability and reliability are all difficult to guarantee when vertical takeoff and landing pattern, and because can causing the structure of aircraft, its mode adopting is different from general conventional fixed wing aircraft, too complicated, badly influence the aerodynamic arrangement under fixed-wing pattern, thus the flight quality while having a strong impact on flat flying.Another one aspect, existing vertical take-off and landing aircraft (VTOL aircraft) major part, because its structure design is limit, is had no idea to adopt the very large span, thereby cannot be increased actv. wing area, its flight efficiency cannot be improved, and voyage is compared or differs greatly with traditional fixed wing aircraft.So, only, in the situation that adopting the most ripe cyclogyro model layout's form as far as possible and not affecting conventional fixed wing aircraft layout structure, accomplish vertical takeoff and landing function, could improve to the full extent the performance of the various aspects of vertically taking off and landing flyer.
Utility model content
The purpose of this utility model is to provide a kind of power system structure that is applicable to vertically taking off and landing flyer.
For achieving the above object, the utility model has adopted following technical scheme.
This power system structure comprises the screw propeller that power is provided, and described screw propeller is arranged in the front and back side of aircraft both sides host wing, and the screw propeller that is positioned at host wing front side can upwards vert, and the screw propeller that is positioned at host wing rear side can vert downwards.
The screw propeller of described host wing front side adopts formal dress, and the screw propeller of host wing rear side adopts anti-dress.
Described power system structure also comprises the driver train that the screw propeller for making host wing front and back side synchronously verts.
On the host wing of both sides, be respectively arranged with the some to screw propeller of equal number, every pair of screw propeller is made up of screw propeller and a screw propeller that is arranged in respective hosts wing rear side that is arranged in respective hosts wing front side, and a pair of screw propeller adopts a corresponding driving engine to drive simultaneously or adopt two driving engines to drive respectively.
On described host wing, be provided with driving engine and hang cabin, driving engine is hung the front and back end in cabin and is stretched out to host wing front and back side correspondence respectively, a set of power system is equipped with respectively in the front and back end in driving engine extension cabin, and power system comprises the driving engine of screw propeller and driving screw propeller, and driving engine is hung cabin with driving engine and is connected.
The beneficial effects of the utility model are embodied in:
The utility model adopts ripe cyclogyro model layout form and does not affect conventional fixed wing aircraft layout structure, make it more simple in structure than existing vertically taking off and landing flyer, control difficulty is low, has better vertical takeoff and landing performance and hovering performance, and has faster flying speed and farther voyage.
Adopt vertically taking off and landing flyer of the present utility model duty runway not compared with traditional fixed wing aircraft, but carry out vertical and landing takeoff, greatly reduce the requirement to runway.There is flying speed faster compared with conventional helicopters, farther voyage and the flying height of Geng Gao.The utility model is by design, not only realize under vertical takeoff and landing pattern and the existing the most mature and stable similar layout of X-type four-axle aircraft and mode, and at flat distribution form, effective wing area and the integral structure that flies to retain to the full extent under pattern traditional failure-free fixed wing aircraft.So it is reasonable to have distribution form compared with other vertically taking off and landing flyer, simple in structure, the advantage such as mode mature and reliable, flies more stable, and voyage is farther, and load-carrying is larger.Its distribution form, structure and mode not only can be used for SUAV (small unmanned aerial vehicle) also can be for small-sized manned aircraft and big-and-middle-sized transport plane, and its driving engine not only can adopt electrical motor, and piston type internal combustion engine also can adopt jet engine etc.Adopt SUAV (small unmanned aerial vehicle) of the present utility model and small-sized manned aircraft, be not only applicable to civil aviation transportation, disaster relief prospecting, aerial mapping, is also suitable for army individual-soldier and scouts use.And the utility model also has obvious advantage for big-and-middle-sized transport plane.
Adopt vertically taking off and landing flyer of the present utility model to take into account the advantage of Fixed Wing AirVehicle and helicopter, overcome the shortcoming of other vertically taking off and landing flyer, and produced prototype and take a flight test, excellent performance, reliable and stable, there is very strong comformability, have a extensive future.
Accompanying drawing explanation
Fig. 1 adopts the monnolithic case figure of vertically taking off and landing flyer of the present utility model under its level flight condition;
Fig. 2 is the monnolithic case figure of the vertically taking off and landing flyer shown in Fig. 1 under its vertical takeoff and landing and floating state;
Fig. 3 is applicable to the vertically taking off and landing flyer shown in Fig. 1 at the flat power system position view that flies state;
Fig. 4 is applicable to the power system position view of the vertically taking off and landing flyer shown in Fig. 1 under vertical takeoff and landing and floating state;
In figure: 1 is fuselage, 2 is host wing, 3 horizontal tails, and 4 is vertical fin, 5 is driving engine extension cabin, 6 is power system, and 7 is nose-gear, and 8 is main landing gear, and 51 for driving the steering wheel of servo, 52 is drive link, the 53 driven steering wheels that are driving engine, and 61 is screw propeller, 62 is driving engine.
The specific embodiment
Below in conjunction with drawings and Examples, the utility model is elaborated.
The utility model is mainly by the total arrangement to vertically taking off and landing flyer, and the appropriate design of offline mode conversion and the required mechanism of attitude control realizes.
Embodiment
The utility model provides a kind of power system structure that is applicable to vertically taking off and landing flyer, comprise the screw propeller of power 61 is provided, described screw propeller 61 is arranged in the front and back side of aircraft both sides host wing 2, the screw propeller 61 that is positioned at host wing 2 front sides can upwards be verted for horizontality by vertical state, and the screw propeller 61 that is positioned at host wing 2 rear sides can be dipped down and be transferred to horizontality by vertical state; The screw propeller 61 of described host wing front side adopts formal dress, and for aircraft provides pulling force and lift, the screw propeller 61 of host wing rear side adopts anti-dress, for aircraft provides thrust and lift; Before and after described host wing, side screw propeller 61 verting separately synchronously carried out by bar-link drive; Before and after described host wing, the screw propeller 61 of side adopts a driving engine to drive simultaneously or adopt two driving engines to drive respectively.Be specifically introduced with reference to the accompanying drawings below.
Shown in Fig. 1, Fig. 2, adopt vertically taking off and landing flyer of the present utility model to adopt conventional formula aerodynamic arrangement: to comprise fuselage 1, host wing 2, horizontal tail 3, vertical fin 4, nose-gear 7, main landing gear 8 and each rudder face etc.Wherein on both sides host wing 2, be separately installed with a driving engine and hang cabin 5, a set of power system 6 is equipped with respectively in the front and back that hang cabin at driving engine, this power system comprises screw propeller 61 and driving engine 62, and 4 cover power systems provide vertical takeoff and landing for aircraft, power when hovering and horizontal flight altogether.
As shown in Figure 3, Figure 4, in the utility model, driving engine is hung 5 inside, cabin and is provided with bar-link drive.Bar-link drive comprises the steering wheel 51 that drives servo, and the driven steering wheel 53 of drive link 52 and driving engine drives the steering wheel 51 of servo and the driven steering wheel 53 of driving engine to be connected with drive link 52.Wherein drive the diameter of the steering wheel 51 of servo and the driven steering wheel 53 of driving engine identical, and be parallel to each other, when static and driving engine extension cabin 5 axis keep 45 degree angles, thereby before and after guaranteeing in switching process, driving engine angle synchronously changes.When aircraft is flat while flying, four screw propeller 61 planes all in ground close to plumbness, for aircraft provides power forward.In the time of aircraft vertical takeoff and landing and hovering, the bar-link drive of hanging 5 inside, cabin by driving engine synchronously drives, two screw propellers of host wing front portion upwards vert, and two screw propellers at host wing rear portion vert downwards, thereby four screw propellers can provide lift upwards for aircraft; And the spin direction of four screw propellers and control method are similar to the four-axle aircraft of X-type, can in vertical takeoff and landing and hovering process, provide stable attitude control for aircraft.In offline mode when conversion,, four propeller planes can keep synchronously verting, and not only can offset the overbalance moment of torsion verting in the aircraft pitch direction producing, and the mode of four axles still can in the vertical direction be provided, and guarantee that aircraft is steady; The propeller plane process of verting is controlled in connection with the attitude on aircraft and airspeed sensor, thereby guarantees that it transforms in offline mode process steadily and not stall.The switching process of offline mode is when vertical take-off and landing aircraft (VTOL aircraft) is the most dangerous often, and the utility model is by controllability and safety that rationally design has improved this process greatly cleverly.
Claims (5)
1. one kind is applicable to the power system structure of vertically taking off and landing flyer, it is characterized in that: this power system structure comprises provides the screw propeller of power (61), described screw propeller (61) is arranged in the front and back side of aircraft both sides host wings (2), the screw propeller (61) that is positioned at host wing (2) front side can upwards vert, and the screw propeller (61) that is positioned at host wing (2) rear side can vert downwards.
2. a kind of power system structure that is applicable to vertically taking off and landing flyer according to claim 1, is characterized in that: the screw propeller (61) of described host wing (2) front side adopts formal dress, and the screw propeller (61) of host wing (2) rear side adopts anti-dress.
3. a kind of power system structure that is applicable to vertically taking off and landing flyer according to claim 1, is characterized in that: described power system structure also comprises for making the driver train that the screw propeller (61) of side synchronously verts before and after host wing (2).
4. a kind of power system structure that is applicable to vertically taking off and landing flyer according to claim 1, it is characterized in that: on both sides host wing (2), be respectively arranged with the some to screw propeller (61) of equal number, every pair of screw propeller is made up of screw propeller (61) and a screw propeller (61) that is arranged in respective hosts wing rear side that is arranged in respective hosts wing front side, and a pair of screw propeller (61) adopts a corresponding driving engine to drive simultaneously or adopt two driving engines to drive respectively.
5. a kind of power system structure that is applicable to vertically taking off and landing flyer according to claim 1, it is characterized in that: on described host wing (2), be provided with driving engine and hang cabin (5), driving engine is hung the front and back end in cabin (5) and is stretched out to host wing (2) front and back side correspondence respectively, a set of power system (6) is equipped with respectively in the front and back end in driving engine extension cabin (5), power system (6) comprises the driving engine (62) of screw propeller (61) and driving screw propeller, and driving engine is hung cabin with driving engine and is connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320859188.6U CN203681869U (en) | 2013-12-24 | 2013-12-24 | Power system structure suitable for vertical take-off and landing air vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201320859188.6U CN203681869U (en) | 2013-12-24 | 2013-12-24 | Power system structure suitable for vertical take-off and landing air vehicle |
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| CN203681869U true CN203681869U (en) | 2014-07-02 |
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| CN201320859188.6U Expired - Lifetime CN203681869U (en) | 2013-12-24 | 2013-12-24 | Power system structure suitable for vertical take-off and landing air vehicle |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738496A (en) * | 2013-12-24 | 2014-04-23 | 西安交通大学 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
| CN105083551A (en) * | 2015-08-03 | 2015-11-25 | 江苏工程职业技术学院 | Tilt rotary-wing aircraft and control method thereof |
| CN105109680A (en) * | 2015-09-29 | 2015-12-02 | 上海圣尧智能科技有限公司 | Vertical take-off and landing unmanned airplane |
| CN105480416A (en) * | 2016-01-18 | 2016-04-13 | 南京信息工程大学 | Unmanned aerial vehicle with tilted rotors |
| CN106828911A (en) * | 2016-12-09 | 2017-06-13 | 北京京东尚科信息技术有限公司 | String wing unmanned plane |
| CN107323660A (en) * | 2017-06-30 | 2017-11-07 | 马鞍山市赛迪智能科技有限公司 | A kind of VTOL method of dalta wing unmanned plane |
| CN107406141A (en) * | 2015-02-19 | 2017-11-28 | 亚马逊科技公司 | Carrier with the motor rotated between raised position and propulsion position configures |
| CN107444632A (en) * | 2017-06-30 | 2017-12-08 | 马鞍山市赛迪智能科技有限公司 | It is a kind of can VTOL dalta wing unmanned plane |
| CN109969392A (en) * | 2019-03-13 | 2019-07-05 | 庆安集团有限公司 | A kind of vertically taking off and landing flyer converted using local dynamic effect |
| CN110871892A (en) * | 2018-09-01 | 2020-03-10 | 田瑜 | Aircraft vertical stabilizer with lift propeller and using method thereof |
| CN113830301A (en) * | 2021-10-12 | 2021-12-24 | 北京航空航天大学 | Many rotor crafts of lift wing with control surface |
| US11919631B2 (en) | 2021-02-08 | 2024-03-05 | Archer Aviation, Inc. | Vertical take-off and landing aircraft with aft rotor tilting |
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2013
- 2013-12-24 CN CN201320859188.6U patent/CN203681869U/en not_active Expired - Lifetime
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738496A (en) * | 2013-12-24 | 2014-04-23 | 西安交通大学 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
| CN107406141B (en) * | 2015-02-19 | 2020-10-30 | 亚马逊科技公司 | Vehicle arrangement with a motor rotating between a lifting position and a propulsion position |
| US11319063B2 (en) | 2015-02-19 | 2022-05-03 | Amazon Technologies, Inc. | Vehicle configuration with motors that rotate between a lifting position and a thrusting position |
| CN107406141A (en) * | 2015-02-19 | 2017-11-28 | 亚马逊科技公司 | Carrier with the motor rotated between raised position and propulsion position configures |
| CN105083551A (en) * | 2015-08-03 | 2015-11-25 | 江苏工程职业技术学院 | Tilt rotary-wing aircraft and control method thereof |
| CN105109680A (en) * | 2015-09-29 | 2015-12-02 | 上海圣尧智能科技有限公司 | Vertical take-off and landing unmanned airplane |
| CN105480416A (en) * | 2016-01-18 | 2016-04-13 | 南京信息工程大学 | Unmanned aerial vehicle with tilted rotors |
| CN106828911A (en) * | 2016-12-09 | 2017-06-13 | 北京京东尚科信息技术有限公司 | String wing unmanned plane |
| WO2018103458A1 (en) * | 2016-12-09 | 2018-06-14 | 北京京东尚科信息技术有限公司 | Tandem-wing unmanned aerial vehicle |
| CN107323660B (en) * | 2017-06-30 | 2020-01-17 | 马鞍山市赛迪智能科技有限公司 | Vertical take-off and landing method of delta-wing unmanned aerial vehicle |
| CN107444632A (en) * | 2017-06-30 | 2017-12-08 | 马鞍山市赛迪智能科技有限公司 | It is a kind of can VTOL dalta wing unmanned plane |
| CN107323660A (en) * | 2017-06-30 | 2017-11-07 | 马鞍山市赛迪智能科技有限公司 | A kind of VTOL method of dalta wing unmanned plane |
| CN110871892A (en) * | 2018-09-01 | 2020-03-10 | 田瑜 | Aircraft vertical stabilizer with lift propeller and using method thereof |
| CN109969392A (en) * | 2019-03-13 | 2019-07-05 | 庆安集团有限公司 | A kind of vertically taking off and landing flyer converted using local dynamic effect |
| US11919631B2 (en) | 2021-02-08 | 2024-03-05 | Archer Aviation, Inc. | Vertical take-off and landing aircraft with aft rotor tilting |
| CN113830301A (en) * | 2021-10-12 | 2021-12-24 | 北京航空航天大学 | Many rotor crafts of lift wing with control surface |
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Granted publication date: 20140702 |