CN104176235A - Rotatable wing of rotor craft - Google Patents
Rotatable wing of rotor craft Download PDFInfo
- Publication number
- CN104176235A CN104176235A CN201310193936.6A CN201310193936A CN104176235A CN 104176235 A CN104176235 A CN 104176235A CN 201310193936 A CN201310193936 A CN 201310193936A CN 104176235 A CN104176235 A CN 104176235A
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Abstract
The invention relates to a rotatable wing of a rotor craft, relates to the technical field of the wing of the rotor craft, and particularly relates to the technical field of a rotatable wing of the rotor craft. Two ends of the wing are connected to engine compartments with rotors through tilting drive devices; the middle of the wing is fixed on one end of a rotating shaft; the other end of the rotating shaft is connected together with a fuselage top of the craft through a positioning brake device, and is vertical to an axis of the fuselage, so that the wing and components installed thereon can rotate around the rotating shaft; the length of the wing is controlled at 1.5-3.5 times of a diameter of the rotor; and linear speed of the wing end portion is controlled at 17 m/s-56m/s when the rotor craft takes off and lands, thereby reducing engine power required by vertically taking off and landing of the rotor craft by 30%-40%, realizing the objects of reducing oil consumption, reducing weight of the craft and reducing production cost and use cost of the craft, and further increasing bearing capability of the craft.
Description
Technical field
The present invention relates to the wing technical field of rotor craft, particularly relate to the rotatable wing technical field of rotor craft.
Background technology
At present, flying speed rotor craft the fastest and volume production is the osprey V-22 tiltrotor of the U.S. in the world.It is on the basis of fixed wing aircraft, realizes and taking off vertically and high-speed flight by the rotor that can vert is set in wing end, and while taking off, the axis of rotor is vertical with fuselage axis, puts down axis and the fuselage axis line parallel of rotor while flying.But the wing that rotor is installed due to two ends is fixed, while taking off vertically, still needs larger engine power ability lift fuselage to complete and take off.
Summary of the invention
The technical matters that the present invention solves is: required engine power while reducing rotor craft vertical takeoff and landing.
Technical scheme of the present invention is: required engine power when reducing rotor craft vertical takeoff and landing, the special rotatable wing that proposes a kind of rotor craft, its structure as shown in Figure 1, comprise wing 1, the two ends of described wing 1 are connected with the piggyback pod 4 with rotor 3 by tilting drive 2, the middle part of described wing 1 is fixed on one end of S. A. 5, the other end of S. A. 5 is connected as a single entity with the back of aircraft by positioning and braking device 6 and is vertical with fuselage axis, and the related parts mounted thereto of wing 1 can be rotated around S. A. 5.
As shown in Figure 2, described piggyback pod 4 and rotor 3, leaning forward of implementing by tilting drive 2 be rotor 3 above wing 1 and the axis of piggyback pod 4 and rotor 3 with respect to the axis of S. A. 5 leading-edge droop to wing 1, scope is 0 °～90 °; The hypsokinesis of implementing by tilting drive 2 be rotor 3 above wing 1 and the axis of piggyback pod 4 and rotor 3 tilt to the trailing edge of wing 1 with respect to the axis of S. A. 5, scope is decided to be 0 °～10 °.
As shown in Figure 1, described rotatable wing, in the time taking off vertically, closes positioning and braking device 6 wing 1 can be rotated around the axis of S. A. 5; And make by tilting drive 2 adjustment that 3, one groups of the related rotors of two piggyback pods 4 that wing 1 two ends are connected lean forward, another group hypsokinesis the identical angle that tilts; Engine installation in piggyback pod 4 drives rotor 3 to rotate, and the pulling force of two rotors produces the vertical fuselage resultant moment of making a concerted effort and rotating around S. A. 5 axis upwards; Make a concerted effort to pass through S. A. 5 by aircraft pull-up, resultant moment drives wing 1 and middle part to be fixedly installed S. A. 5 around its axis rotation; In take-off process, adjust the inclination angle of rotor 3 by tilting drive 2, control the linear velocity of wing 1 end within the specific limits.
Described rotatable wing, after completing and taking off, periodically changes respectively pitch and the feathering of two rotors 3, makes it produce one at S. A. 5 places and makes the downward moment of aircraft head, and the plane of rotation of wing 1 is leaned forward, and before entering, flies acceleration phase; The inclination angle that synchronously reduces the piggyback pod 4 at wing 1 two ends in accelerator by tilting drive 2, while making aircraft forward flight speed reach a certain speed range, the inclination angle of piggyback pod 4 is decreased to 0 °, causes wing 1 to lose gradually rotational power; Under the effect of inertia, when the leading edge of wing 1 turns to when consistent with aircraft flight direction and vertical with fuselage axis, start positioning and braking device 6 wing 1 is fixed on to the position vertical with fuselage axis; Meanwhile, drive two piggyback pods 4 to lean forward 90 ° by tilting drive 2 is synchronous, make its axis and fuselage axis line parallel enter state of flight; As shown in Figure 2, now the rotor 3 in bispin wing mechanism serves as before screw propeller effect pulls aircraft at a high speed and flies, and the lift that wing 1 produces holds up aircraft.
Described rotatable wing, in the time of landing, is tilted to the position vertical with fuselage axis by tilting drive 2 by piggyback pod 4; In the time that aircraft decelerates to a certain speed range, close positioning and braking device 6 wing 1 can be rotated around the axis of S. A. 5; And by tilting drive 2 by 3, one groups of related piggyback pod 4 rotors lean forward, another group hypsokinesis the identical angle that tilts; Along with aircraft flight speed declines and adjusts its tilt angle, in the time that aircraft forward flight speed is decreased to 0, the linear velocity that wing 1 two ends piggyback pod rotates around S. A. 5 within the specific limits time, can be implemented vertical landing.
It is suitable that the span length of described wing 1 will be chosen, and length is crossed conference increases too much structure cost, because the weight of whole fuselage is all born by wing 1 while taking off; Wing 1 is too short, ensure that the linear velocity at wing 1 two ends can make the centrifugal acceleration at rotor 3 and piggyback pod 4 places excessive, causes the incoming flow of rotor 3 more asymmetric, can make the hypotelorism between tail that rotor hauls out increase the interference between rotor; Therefore it is proper that wing 1 length is chosen for 1.5～3.5 times of rotor 3 diameters.
The rotative speed of described wing 1, when wing 1 rotates, the linear velocity at its two ends should not be greater than 56m/s, makes the centnifugal force at rotor 3 and piggyback pod 4 places excessive because linear velocity is crossed conference, and the resistance of rotor 3 and machinery space 4 increases, the distance that rotor is hauled out between tail reduces, and disturbs and increases; While taking off vertically, the linear velocity at wing 1 its two ends of rotation should not be less than 17m/s yet, can not reduce well the needed power of rotor 3 while taking off because linear velocity is too small; So, should control aircraft takeoff or landing time, make by tilting drive 2 adjustment that 3, one groups of the related rotors of two piggyback pods 4 that wing 1 two ends are connected lean forward, another group hypsokinesis the identical angle that tilts, when wing 1 is rotated, the linear velocity of its end is at 17m/s～56m/s.
The invention has the beneficial effects as follows: because wing two ends are connected with the piggyback pod with rotor by tilting drive, the middle part of described wing is fixed on one end of S. A., the other end of S. A. is connected as a single entity with the back of aircraft by positioning and braking device and is vertical with fuselage axis, and the related parts mounted thereto of wing can be rotated around S. A.; Described wing length is controlled at 1.5～3.5 times of rotor diameter, the linear velocity of landing tip extension on opportunity is controlled at 17m/s～56m/s, required 30%～40% engine power while having reduced rotor craft vertical takeoff and landing, realize and reduced oil consumption and reduce aircraft weight and reduce the productive costs of aircraft, the object of use cost, further improved the load-carrying capacity of aircraft.
Brief description of the drawings
Fig. 1 is the schematic diagram of rotatable wing of the present invention in the time taking off vertically;
Fig. 2 is the schematic diagram of rotatable wing of the present invention in the time of flight.
Detailed description of the invention
Below in conjunction with accompanying drawing and detailed description of the invention, the present invention is described in further detail:
A kind of rotatable wing of rotor craft, its structure as shown in Figure 1, comprise wing 1, the two ends of described wing 1 are connected with the piggyback pod 4 with rotor 3 by tilting drive 2, the middle part of described wing 1 is fixed on one end of S. A. 5, the other end of S. A. 5 is connected as a single entity with the back of aircraft by positioning and braking device 6 and is vertical with fuselage axis, and the related parts mounted thereto of wing 1 can be rotated around S. A. 5.
The span length of getting wing 1 is three times of rotor 3 diameters, and the maximum disk loading of getting rotor is 75kg/m
2.This rotatable wing is in the time that aircraft takes off vertically, and the linear velocity that rotate around S. A. 5 at wing 1 two ends is not more than 50m/s.
This rotatable wing is arranged on to the top of aircraft, and while ensureing that rotatable wing rotates around S. A. 5 and fuselage do not interfere; While taking off vertically, close positioning and braking device 6, make by tilting drive 2 adjustment that 3, one groups of the related rotors of two piggyback pods 4 that wing 1 two ends are connected lean forward, another group hypsokinesis the 3 ° of identical angles that tilt; Piggyback pod 4 internally-powered devices drive rotor 3 to rotate, and the pulling force of two rotors produces the vertical fuselage resultant moment of making a concerted effort and rotating around S. A. 5 upwards.Resultant moment is by S. A. 5 by fuselage pull-up, and the S. A. 5 that resultant moment drives wing 1 and middle part to be fixedly installed rotates; In take-off process, adjust the inclination angle of rotor 3 by tilting drive 2, control the linear velocity of wing 1 end between 30～50m/s.
After taking off, periodically change respectively pitch and the feathering of two rotors 3, make it produce one at S. A. 5 places and make the downward moment of aircraft head, and then the plane of rotation of wing 1 is leaned forward, before entering, fly acceleration phase; The inclination angle of synchronously reducing the piggyback pod 4 at the two ends of wing 1 in accelerator by tilting drive 2, while making its forward flight speed reach 150km/h left and right, the inclination angle of piggyback pod 4 is reduced to 0 °, causes wing 1 to lose gradually rotational power; Under the effect of inertia, when the leading edge of wing 1 turns to when consistent with aircraft flight direction and vertical with fuselage axis, start positioning and braking device 6 wing 1 is fixed on to the position vertical with fuselage axis; Meanwhile, drive two piggyback pods 4 to lean forward 90 ° by tilting drive 2 is synchronous, make its axis and fuselage axis line parallel enter state of flight; As shown in Figure 2, now the rotor 3 in bispin wing mechanism serves as before screw propeller effect pulls aircraft at a high speed and flies, and the lift that wing 1 produces holds up aircraft.
When landing, by tilting drive 2, piggyback pod 4 is tilted to vertically with fuselage axis, aircraft decelerates to about 150km/h, closes positioning and braking device 6 wing 1 can be rotated around the axis of S. A. 5; And by tilting drive 2 by 3, one groups of related piggyback pod 4 rotors lean forward, another group hypsokinesis the identical angle that tilts; Along with aircraft flight speed declines and adjusts its tilt angle, in the time that aircraft forward flight speed is decreased to 0, the linear velocity that wing 1 two ends piggyback pod rotates around S. A. 5 between 30～50m/s time, can be implemented vertical landing.
Theoretical calculation analysis: when the tiltrotor disk loading that takes off vertically is 75kg/m
2time, in the time that rotor takes off vertically, rotor induced power accounts under the condition of rotor power 80%, and calculating the density of air adopting is 0.125kg/m
3, the induction velocity that calculates rotor according to momentum theorem is 17.32m/s.
Adopt rotatable wing of the present invention, the span length that makes wing 1 is 3 times of rotor 3 diameters, wing 1 two ends are 40m/s around the linear velocity of S. A. 5, when getting wing 1 and rotating, a rotor is 0.2 to the interference factor of another rotor, the related rotor 3 of two piggyback pods 4 that wing 1 two ends are connected, one group lean forward, another group hypsokinesis while tilting 3 ° of angles identical, now the inflow velocity of rotor is 9.3m/s as calculated, the profile drag power when profile drag power of rotor equals to hover while supposing this speed, the rotor induced power of this rotatable wing is tilting rotor 53%.The rotor gross horsepower of this rotatable wing is 63% of tilting rotor gross horsepower, considers other factors, and the take-off power of this bispin wing mechanism should be between 60%～70% of tilting rotor; So, required 30%～40% engine power when the rotatable wing of a kind of rotor craft of the present invention can reduce rotor craft vertical takeoff and landing, realize and reduce oil consumption and reduce aircraft weight and reduce the productive costs of aircraft, the object of use cost, can further improve the load-carrying capacity of aircraft.
Claims (7)
1. the rotatable wing of a rotor craft, comprise wing (1), the two ends of described wing (1) are connected with the piggyback pod (4) with rotor (3) by tilting drive (2), it is characterized in that: the middle part of described wing (1) is fixed on one end of S. A. (5), the other end of S. A. (5) is connected as a single entity with the back of aircraft by positioning and braking device (6) and is vertical with fuselage axis, and the related parts mounted thereto of wing (1) can be rotated around S. A. (5).
2. the rotatable wing of rotor craft according to claim 1, it is characterized in that: described piggyback pod (4) and rotor (3), leaning forward of implementing by tilting drive (2) be rotor (3) above wing 1 and the axis of piggyback pod (4) and rotor (3) with respect to the axis of S. A. (5) leading-edge droop to wing (1), scope is 0 °～90 °; The hypsokinesis of implementing by tilting drive (2) is that rotor (3) tilts to the trailing edge of wing (1) with respect to the axis of S. A. (5) at the axis of wing (1) top and piggyback pod (4) and rotor (3), and scope is decided to be 0 °～10 °.
3. the rotatable wing of rotor craft according to claim 1, it is characterized in that: described rotatable wing, in the time taking off vertically, close positioning and braking device (6) wing (1) can be rotated around the axis of S. A. (5); And the related rotors of two piggyback pods (4) (3) that wing (1) two ends are connected by tilting drive (2) adjustment, one group lean forward, another group hypsokinesis the identical angle that tilts; In take-off process, adjust the inclination angle of rotor (3) by tilting drive (2), control the linear velocity of wing (1) end within the specific limits.
4. the rotatable wing of rotor craft according to claim 1, it is characterized in that: described rotatable wing, after completing and taking off, periodically change respectively pitch and the feathering of two rotors (3), make it locate to produce one at S. A. (5) and make the downward moment of aircraft head, the plane of rotation of wing (1) is leaned forward, before entering, fly acceleration phase; In accelerator, synchronously reduce the inclination angle of the piggyback pod (4) at wing (1) two ends by tilting drive (2), while making aircraft forward flight speed reach a certain speed range, the inclination angle of piggyback pod (4) is decreased to 0 °, causes wing (1) to lose gradually rotational power; Under the effect of inertia, when the leading edge of wing (1) turns to when consistent with aircraft flight direction and vertical with fuselage axis, start positioning and braking device (6) wing (1) is fixed on to the position vertical with fuselage axis; Meanwhile, synchronously drive two piggyback pods (4) to lean forward 90 ° by tilting drive (2), make its axis and fuselage axis line parallel enter state of flight.
5. the rotatable wing of rotor craft according to claim 1, is characterized in that: described rotatable wing, in the time of landing, is tilted to the position vertical with fuselage axis by tilting drive (2) by piggyback pod (4); In the time that aircraft decelerates to a certain speed range, close positioning and braking device (6) wing (1) can be rotated around the axis of S. A. (5); And by tilting drive (2) by the related rotor of piggyback pod (4) (3), one group lean forward, another group hypsokinesis the identical angle that tilts; Along with aircraft flight speed declines and adjusts its tilt angle, in the time that aircraft forward flight speed is decreased to 0, the linear velocity that wing (1) two ends piggyback pod rotates around S. A. (5) within the specific limits time, can be implemented vertical landing.
6. the rotatable wing of rotor craft according to claim 1, is characterized in that: the length of described wing (1) is chosen for 1.5～3.5 times of rotor (3) diameter.
7. according to the rotatable wing of the arbitrary rotor craft described in claim 1,3 or 5, it is characterized in that: the rotative speed of described wing (1), should control aircraft takeoff or landing time, the related rotors of two piggyback pods (4) (3) that wing (1) two ends are connected by tilting drive (2) adjustment, one group lean forward, another group hypsokinesis the identical angle that tilts, while making wing (1) rotation, the linear velocity of its end is at 17m/s～56m/s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310193936.6A CN104176235A (en) | 2013-05-23 | 2013-05-23 | Rotatable wing of rotor craft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310193936.6A CN104176235A (en) | 2013-05-23 | 2013-05-23 | Rotatable wing of rotor craft |
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| Publication Number | Publication Date |
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| CN104176235A true CN104176235A (en) | 2014-12-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310193936.6A Pending CN104176235A (en) | 2013-05-23 | 2013-05-23 | Rotatable wing of rotor craft |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217030A (en) * | 2015-10-30 | 2016-01-06 | 佛山市神风航空科技有限公司 | A kind of composite rotating wing lift unit |
| CN105292454A (en) * | 2015-11-06 | 2016-02-03 | 极翼机器人(上海)有限公司 | Multi-rotor-wing unmanned plane |
| CN107053983A (en) * | 2017-05-11 | 2017-08-18 | 湖南顶立科技有限公司 | A kind of hovercar |
| CN107116981A (en) * | 2017-05-11 | 2017-09-01 | 湖南顶立科技有限公司 | A kind of four wing hovercars |
| CN107139665A (en) * | 2017-05-11 | 2017-09-08 | 湖南顶立科技有限公司 | A kind of folded paddle hovercar |
| CN110127046A (en) * | 2019-05-10 | 2019-08-16 | 广州中国科学院工业技术研究院 | A kind of new vertical landing aircraft and its control method |
| CN110901890A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | High-speed rotor craft with rotor capable of being designed in classification mode |
| CN112896485A (en) * | 2021-02-24 | 2021-06-04 | 河南大学 | Two-shaft inclined wing aircraft with streamlined fuselage and control method |
| CN113086194A (en) * | 2021-04-17 | 2021-07-09 | 合肥市方升信息科技有限公司 | Smart city data set system and method based on echo airborne laser scanning data |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217030A (en) * | 2015-10-30 | 2016-01-06 | 佛山市神风航空科技有限公司 | A kind of composite rotating wing lift unit |
| CN105292454A (en) * | 2015-11-06 | 2016-02-03 | 极翼机器人(上海)有限公司 | Multi-rotor-wing unmanned plane |
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| CN107139665A (en) * | 2017-05-11 | 2017-09-08 | 湖南顶立科技有限公司 | A kind of folded paddle hovercar |
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| CN112896485A (en) * | 2021-02-24 | 2021-06-04 | 河南大学 | Two-shaft inclined wing aircraft with streamlined fuselage and control method |
| CN113086194A (en) * | 2021-04-17 | 2021-07-09 | 合肥市方升信息科技有限公司 | Smart city data set system and method based on echo airborne laser scanning data |
| CN113086194B (en) * | 2021-04-17 | 2024-02-20 | 合肥市方升信息科技有限公司 | Echo-based airborne laser scanning data smart city data collection system and method |
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Application publication date: 20141203 |