CN205022862U - Power device and fixed wing aircraft with mechanism of verting - Google Patents
Power device and fixed wing aircraft with mechanism of verting Download PDFInfo
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- CN205022862U CN205022862U CN201520680478.3U CN201520680478U CN205022862U CN 205022862 U CN205022862 U CN 205022862U CN 201520680478 U CN201520680478 U CN 201520680478U CN 205022862 U CN205022862 U CN 205022862U
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- inclining rotary
- engine installation
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Abstract
The utility model discloses a power device and fixed wing aircraft with mechanism of verting, the power device that has a mechanism of verting is including fixed pitch screw, engine, engine compartment, slipstream rudder, wing, tilting wing, steering wheel, the engine mounting in engine compartment, the output shaft of fixed pitch screw and engine, fixed connection is on engine compartment for tilting wing one end, the rotatable connection of the other end on the wing, slipstream rudder swing joint on the tilting wing, steering engine driving slipstream rudder. Fixed wing aircraft includes fuselage and the foretell power device who has the mechanism of verting. Have the mechanism of verting power device simple structure, with low costs, can show the pressure drag loss that reduces VTOL state wing and produce to the screw air current, improve output efficiency's the power device who has a mechanism of verting.
Description
Technical field
The utility model belongs to aircraft field, particularly a kind of engine installation with inclining rotary mechanism and Fixed Wing AirVehicle.
Background technology
The accurate definition of vertically taking off and landing flyer (VTOL) is: can take off with zero velocity/land, possess hover capabilities, and can with the mode horizontal flight of fixed wing aircraft.
In the aviation field of 21 century, the application of vertical takeoff and landing technology on Fixed Wing AirVehicle more and more obtains the attention of every country, this kind of Fixed Wing AirVehicle is different from traditional sliding aircraft running landing or catapult-assisted take-off, it does not need special airport and runway, complicated catapult-launching gear is not needed yet, only need very little level land just can take-off and landing, so this kind of aircraft is very low to landing environmental requirement, even if wasteland in the wild also can take-off and landing, the flight generally as autogyro, balloon etc. is not considered in the scope of vertical takeoff and landing technology.
In all previous war, people have experienced after airport is destroyed by enemy, and the sliding deficiency of running landing aircraft of tradition, therefore vertical takeoff and landing technology is born.During cold war, fears are entertained that there is the situation that general nuclear warfare damages airport, conventional airplane cannot be set out, so expedited the emergence of the vertical takeoff and landing technology of fixed wing aircraft.
Compared with conventional airplane, vertically taking off and landing flyer without dependence, and has the advantage that can hover to runway; Compared with conventional helicopters, vertically taking off and landing flyer has much higher forward flight speed, and has larger voyage; Just because of possess these advantages, vertically taking off and landing flyer is particularly useful for needs hovering or landing site is had to the occasion of particular/special requirement.
Vertical take-off and landing aircraft (VTOL aircraft) decreases the dependence to runway, can decentralized configuration in war, is convenient to launch an attack flexibly, shift and pretend hidden, not easily found by enemy, the attendance rate also significantly improves, and has very high emergentness to the strike of enemy, substantially increases the battlefield survival rate of aircraft.In addition, vertical takeoff and landing technology also eliminates expensive airport construction expense, without the need to driving bird, can also in landing under bad weather condition, and benefit is too many, reduces use cost, so the vertical takeoff and landing technology of Fixed Wing AirVehicle has become a direction of aviation development.
Now, typical vertically taking off and landing flyer is V-22 osprey formula tiltrotor, and it is a tiltrotor manufactured by American Bell Incorporated and Boeing's collaborated design, is also a medium transport aircraft.It realizes the conversion of rotor between vertical and horizontal direction by two lifting airscrews of tilting wing two ends wing tip, thus more ideally the feature of helicopter and fixed wing aircraft is combined together.Under vertical takeoff and landing state, two rotor thrust directions, perpendicular to ground, utilize auto-bank unit to keep the attitude stabilization of body longitudinal direction.V-22 osprey had both had the ability of pure helicopter vertical takeoff and landing and hovering, had again the ability of the high speed cruise flight of turboprop, was a kind of dual-use new high-tech product.At present, V-22 osprey is mainly used in military requirement, and can give battleficld command official and more select and greater flexibility.It does not need special airport and runway, easy to maintenance, and viability is strong, is specially adapted to carry out special operations, greatly can improve military personnel and deliver, deploy troops on garrison duty, hostile takedown, the speed of the action such as disaster relief.
But V-22 osprey have employed two lifting airscrews, under vertical takeoff and landing pattern, rotor needs auto-bank unit to control the stable of attitude of flight vehicle, add the difficulty of control, and blade adopts feathering device, too increases cost; And under vertical takeoff and landing pattern, the positive top blast of rotor slip-stream, on aerofoil surface, causes very large pressure drag loss, and forces wing to increase structural strength, and then cause Flight Vehicle Structure weight to increase, reduce the performance of aircraft.
Utility model content
Based on this, one of the purpose of this utility model is that providing a kind of significantly can reduce the pressure drag loss that vertical takeoff and landing state wing produces prop-blast, the engine installation with inclining rotary mechanism improving output efficiency.
The concrete technical scheme solved the problems of the technologies described above is as follows:
A kind of engine installation with inclining rotary mechanism, comprise fixedpiston screw propeller, driving engine, machinery space, slip-stream rudder, wing, tilting wing, steering wheel, driving engine is installed in machinery space, fixedpiston screw propeller is connected with the output shaft of driving engine, tilting wing one end is fixedly connected on machinery space, the other end is rotating to be connected on wing, and slip-stream rudder is movably connected on tilting wing, slip-stream rudder described in servo driving.
Wherein, described slip-stream rudderpost connects or is hingedly coupled to tilting wing end, and is positioned at the one end away from described fixedpiston screw propeller.
Wherein, also comprise rotating shaft, rotating shaft one end is rotating to be connected on wing, and the other end is fixedly connected on tilting wing.
Wherein, the length of described wing is the 35%-55% of fixedpiston diameter of propeller.
Wherein, the length of described wing is the 40%-50% of fixedpiston diameter of propeller.
Wherein, the length of described wing is the 40%-45% of fixedpiston diameter of propeller.
Wherein, described wing comprises host wing and wing flap, and wing flap is movably connected on the side of host wing, and host wing is rotationally connected with on tilting wing.
Wherein, welding, riveted joint is fixedly connected as described in.
Another object of the present utility model is to provide a kind of Fixed Wing AirVehicle, and comprise fuselage and the above-mentioned engine installation with inclining rotary mechanism, the engine installation with inclining rotary mechanism is symmetricly set in fuselage both sides, and wing is horizontally disposed with.
Wherein, the described engine installation quantity with inclining rotary mechanism is two.
A kind of engine installation with inclining rotary mechanism described in the utility model and Fixed Wing AirVehicle have the following advantages and beneficial effect:
1, the engine installation with inclining rotary mechanism described in the utility model, adopt fixedpiston screw propeller, and devise the installation site of slip-stream rudder, eliminate the complicated auto-bank unit of configuration and feathering device, structure is simple, utilize fixedpiston propeller race to control the stable of body, significantly reduce complexity and the technical risk of flight control system, decrease cost simultaneously; And under vertical takeoff and landing state, because fixedpiston screw propeller produces downward wind all in the scope of tilting wing, downward wind can not be there is again in the position of wing, thus make wing only bear fixedpiston screw propeller generation pulling force upwards, and the resistance produced under need not going to bear wind direction again, significantly reduce the resistance loss that wing produces fixedpiston prop-blast, thus the wind making fixedpiston screw propeller produce all is utilized, improve the output efficiency of fixedpiston propeller power;
2, when aircraft is in vertical takeoff and landing, when the air-flow moved downward that fixedpiston screw propeller produces arrives the position of slip-stream rudder, slip-stream rudder is front and back deflection under the effect of steering wheel, by controlling the deflection angle of slip-stream rudder, control the luffing of aircraft, and luffing is stablized; In the process that driving engine verts, change both sides screw propeller pulling force by the rotating speed of two driving engines in left and right, to control the motion of aircraft rolling, and its rolling movement is stablized.By the differential motion controlling aircraft yaw direction that two, left and right inclining rotary mechanism rotates, and its yawing rotation is stablized; When aircraft is flat fly time, slip-stream rudder can replace aileron, makes air flow deflector by differential, produces the rolling moment of aircraft, controls the rolling movement of aircraft;
3, the engine installation with inclining rotary mechanism described in the utility model, further by the ratio regulating and controlling fixedpiston diameter of propeller and wing length, and then substantially reduces the size of fixedpiston screw propeller, further reduces manufacturing cost;
4, Fixed Wing AirVehicle described in the utility model, when it is the Fixed Wing AirVehicle of vertical takeoff and landing, greatly can reduce the size of this kind of type fixedpiston screw propeller, complicated auto-bank unit and feathering device need not be configured, reduce the technical risk of tiltrotor, improve system reliability, decrease manufacturing cost, move towards commercial market for tiltrotor to lay a good foundation, vertical takeoff and landing fixed-wing unmanned plane is made to play larger effect patrolling in the operation such as pipeline and mapping, when it is short take-off and landing (STOL) Fixed Wing AirVehicle, also significantly can reduce the sliding distance of running of landing.
Accompanying drawing explanation
Fig. 1 is the structural representation of the engine installation with inclining rotary mechanism described in embodiment 1;
Fig. 2 is the structural representation of aircraft when being in vertical takeoff and landing state;
Fig. 3 is the structural representation that aircraft is in when horizontal flies state.
Description of reference numerals:
102, fixedpiston screw propeller, 104, machinery space; 106, slip-stream rudder, 108, tilting wing;
202, host wing; 204, wing flap.
Detailed description of the invention
Below with reference to specific embodiment, the utility model is described further.
Embodiment 1
A kind of engine installation with inclining rotary mechanism (as shown in Figure 1) described in the present embodiment, comprise fixedpiston screw propeller 102, driving engine (not shown in FIG.), machinery space 104, slip-stream rudder 106, host wing 202, wing flap 204, tilting wing 108, steering wheel (not shown), driving engine is installed in machinery space 104, fixedpiston screw propeller 102 is connected with the output shaft of driving engine, tilting wing 108 one end is welded on machinery space 104, what other end axle rotated is connected on host wing 202, slip-stream rudder 106 is articulated with tilting wing 108 end, and the one end be positioned at away from described fixedpiston screw propeller 102, servo driving slip-stream rudder, wing flap 204 is hingedly coupled to the side of host wing 202, host wing 202 axle is rotationally connected with on tilting wing 108.Slip-stream rudder 106, under the effect of steering wheel, can deflect front and back, flows backwards to fixedpiston screw propeller 102 air-flow, thus the control effort produced aircraft and control torque.
In a particular embodiment, the length of described wing is the 35%-55% of fixedpiston screw propeller 102 diameter.
Preferably, the length of described wing is the 40%-50% of fixedpiston screw propeller 102 diameter.
Preferred, the length of described wing is the 40%-45% of fixedpiston screw propeller 102 diameter.
The described engine installation with inclining rotary mechanism also comprises rotating shaft (rotating shaft does not draw), tilting wing 108 one end is welded on machinery space 104, the other end is connected on host wing 202 by rotating shaft, and one end of rotating shaft is rotatably connected on host wing 202.
Embodiment 2
Fixed Wing AirVehicle described in the present embodiment, comprise fuselage and two engine installations with inclining rotary mechanism, engine installation with inclining rotary mechanism is symmetricly set in fuselage both sides, and wing is horizontally disposed with (as shown in Figure 2 or Figure 3), wherein, the concrete structure of power inclining rotary mechanism is see embodiment 2.
When aircraft is in vertical takeoff and landing state (as shown in Figure 2), engine axis and horizontal plane, two screw propellers upwards provide lift, and slip-stream rudder 106 controls the luffing of aircraft by the deflection of synchronous front and back, and luffing is stablized.In the process that driving engine verts, by the pulling force of the rotating speed control break both sides screw propeller of two driving engines, to control aircraft rolling movement, and rolling movement is stablized, simultaneously by the disappointing motion controlling aircraft yaw direction that two, left and right inclining rotary mechanism rotates, and its yawing rotation is stablized.
When driving engine forwards level attitude (as shown in Figure 3) to, flat when flying forward, slip-stream rudder 106 can replace aileron, makes air flow deflector by differential, produces the rolling moment of aircraft, controls the rolling movement of aircraft.
Fixed Wing AirVehicle described in the present embodiment, have employed inclining rotary mechanism as described in Example 1, stably can keep the floating state of vertical takeoff and landing simultaneously realizing fixed wing aircraft, the driving engine of aircraft can be made please aspect to be kept to stablize in accurate process flying forward state, and make aircraft finally can enter fixed-wing to equal the state flown.
Below be only preferred implementation of the present utility model, protection domain of the present utility model be not only confined to above-described embodiment, all technical schemes belonged under the utility model thinking all belong to protection domain of the present utility model.It should be pointed out that for those skilled in the art, in the some improvement do not departed under the utility model principle prerequisite and polishing, protection domain of the present utility model should be considered as.
Claims (9)
1. the engine installation with inclining rotary mechanism, it is characterized in that, comprise fixedpiston screw propeller, driving engine, machinery space, slip-stream rudder, wing, tilting wing, steering wheel, driving engine is installed in machinery space, fixedpiston screw propeller is connected with the output shaft of driving engine, and tilting wing one end is fixedly connected on machinery space, and the other end is rotating to be connected on wing, slip-stream rudder is movably connected on tilting wing, slip-stream rudder described in servo driving.
2. the engine installation with inclining rotary mechanism according to claim 1, is characterized in that, described slip-stream rudderpost connects or is hingedly coupled to tilting wing end, and is positioned at the one end away from described fixedpiston screw propeller.
3. the engine installation with inclining rotary mechanism according to claim 2, is characterized in that, also comprise rotating shaft, and rotating shaft one end is rotating to be connected on wing, and the other end is fixedly connected on tilting wing.
4. the engine installation with inclining rotary mechanism according to any one of claim 1-3, is characterized in that, the length of described wing is the 35%-55% of fixedpiston diameter of propeller.
5. the engine installation with inclining rotary mechanism according to any one of claim 1-3, it is characterized in that, described wing comprises host wing and wing flap, wing flap is movably connected on the side of host wing, and host wing is rotationally connected with on tilting wing.
6. the engine installation with inclining rotary mechanism according to claim 5, is characterized in that, described wing flap is articulated with the side of host wing.
7. the engine installation with inclining rotary mechanism according to claim 1, is characterized in that, described in be fixedly connected as welding, riveted joint.
8. a Fixed Wing AirVehicle, is characterized in that, comprise the engine installation with inclining rotary mechanism described in fuselage and any one of claim 1-7, the engine installation with inclining rotary mechanism is symmetricly set in fuselage both sides, and wing is horizontally disposed with.
9. Fixed Wing AirVehicle according to claim 8, is characterized in that, the described engine installation quantity with inclining rotary mechanism is two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520680478.3U CN205022862U (en) | 2015-09-06 | 2015-09-06 | Power device and fixed wing aircraft with mechanism of verting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520680478.3U CN205022862U (en) | 2015-09-06 | 2015-09-06 | Power device and fixed wing aircraft with mechanism of verting |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205022862U true CN205022862U (en) | 2016-02-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520680478.3U Expired - Fee Related CN205022862U (en) | 2015-09-06 | 2015-09-06 | Power device and fixed wing aircraft with mechanism of verting |
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| CN (1) | CN205022862U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105947193A (en) * | 2016-05-10 | 2016-09-21 | 左建章 | Control system for two-axis vector balance flap tiltrotor aircraft |
| CN106828915A (en) * | 2017-03-15 | 2017-06-13 | 西北工业大学 | A kind of tilted propeller can VTOL high-speed aircraft and its flight control method |
| CN109649649A (en) * | 2019-01-21 | 2019-04-19 | 合肥工业大学 | Tiltrotor aircraft |
| WO2020134136A1 (en) * | 2018-12-29 | 2020-07-02 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN112722264A (en) * | 2021-01-12 | 2021-04-30 | 中国人民解放军国防科技大学 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings |
| CN113928068A (en) * | 2021-11-24 | 2022-01-14 | 中国船舶科学研究中心 | Underwater aerial cross-domain aircraft and cross-domain navigation method thereof |
| CN114506451A (en) * | 2022-04-21 | 2022-05-17 | 西北工业大学 | Rotor unmanned aerial vehicle verts |
-
2015
- 2015-09-06 CN CN201520680478.3U patent/CN205022862U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105947193A (en) * | 2016-05-10 | 2016-09-21 | 左建章 | Control system for two-axis vector balance flap tiltrotor aircraft |
| CN106828915A (en) * | 2017-03-15 | 2017-06-13 | 西北工业大学 | A kind of tilted propeller can VTOL high-speed aircraft and its flight control method |
| CN106828915B (en) * | 2017-03-15 | 2023-02-28 | 西北工业大学 | Control method of high-speed aircraft with tilting propeller capable of vertically taking off and landing |
| WO2020134136A1 (en) * | 2018-12-29 | 2020-07-02 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN109649649A (en) * | 2019-01-21 | 2019-04-19 | 合肥工业大学 | Tiltrotor aircraft |
| CN109649649B (en) * | 2019-01-21 | 2021-08-20 | 合肥工业大学 | Tilt rotor aircraft |
| CN112722264A (en) * | 2021-01-12 | 2021-04-30 | 中国人民解放军国防科技大学 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
| CN112722264B (en) * | 2021-01-12 | 2023-02-28 | 中国人民解放军国防科技大学 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings |
| CN113697097B (en) * | 2021-09-01 | 2024-01-02 | 中国航空研究院 | Fixed wing aircraft overall aerodynamic layout with tiltable outer wings and rotor wings |
| CN113928068A (en) * | 2021-11-24 | 2022-01-14 | 中国船舶科学研究中心 | Underwater aerial cross-domain aircraft and cross-domain navigation method thereof |
| CN114506451A (en) * | 2022-04-21 | 2022-05-17 | 西北工业大学 | Rotor unmanned aerial vehicle verts |
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Legal Events
| Date | Code | Title | Description |
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| 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: 20160210 Termination date: 20170906 |
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| CF01 | Termination of patent right due to non-payment of annual fee |