CN103482057B - The telescopic wing of aircraft - Google Patents
The telescopic wing of aircraft Download PDFInfo
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- CN103482057B CN103482057B CN201310423557.1A CN201310423557A CN103482057B CN 103482057 B CN103482057 B CN 103482057B CN 201310423557 A CN201310423557 A CN 201310423557A CN 103482057 B CN103482057 B CN 103482057B
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Abstract
The present invention relates to the telescopic wing of a kind of aircraft.Specifically, being can telescopic wing on the small aircraft of the complicated region landing such as high mountain, valley.It comprises in the vertical fuselage arranged, in the middle part of body nodal point, rear side is fixed with wing covering, and all there is outlet at two ends, described wing covering left and right, and there is worm case at the center of its inner chamber, and all there is telescopic wing the left and right sides of worm case, in bearing fit between described telescopic wing and described outlet.All there is rectangular indentation the outer end of described two telescopic wings below, all has wing block in described rectangular indentation.There is worm-and-wheel gear etc. in worm case, realized the adjustment of the flexible of telescopic wing and wing block angle by worm-and-wheel gear etc.Be provided with the aircraft of this telescopic wing, oil consumption is little, and flying speed block, voyage is long.
Description
Technical field
The present invention relates to a kind of aircraft wing.Specifically, being can telescopic wing on the small aircraft of the complicated region landing such as high mountain, valley.
Background technology
The middle title of a reigning dynasty patent specification discloses a kind of can the small aircraft of the narrow and small complex-terrain landing in high mountain, valley etc.This small aircraft contains body frame, two ducts, transverse directions are put the wing, longitudinally put the wing, direction control mechanism, driving engine and support, and the axis of described two ducts parallels.There is axle bed at the center of described duct inner chamber, is evenly equipped with support between the inwall surrounding of axle bed and duct.There is oar axle in axle bed and coordinate in rotatable shape between the two.There is screw propeller oar axle upper end, is connected between the outer wall of described two ducts by link span.Described body frame is connected to the bottom of link span, and there is seat the front side of body frame.The output shaft of described driving engine is connected with two oar axles by the first transmission device.Described direction control mechanism is on body frame, direction control mechanism by left and right operating handle mechanism respectively with laterally put the wing and puts the wing with longitudinal direction and be connected.During landing, drive oar axle in two ducts and blade to rotate by engine generates power by the first transmission device, thus make aircraft produce raising force.During flight, by two cover handle operation mechanisms drive respectively laterally the pendulum wing and longitudinally the pendulum wing rotate, to meet the moving ahead of aircraft, turnon left or right-hand corner needs.Because this small aircraft can in the narrow and small complex-terrain landing of high mountain, valley and so on, can be applicable to fight flood and relieve victims and earthquake relief and other civilian and protection fields, meet other Large Scale Space Vehicle such as helicopter and fixed wing aircraft and to be beyond one's reach requirement.But because the lift relying on the High Rotation Speed of the screw propeller in two ducts to produce completely that takes off of this aircraft realizes, consumption of fuel is more, major part power consumption has all been used in and has promoted in the deadweight of aircraft, the power consumption being really used in aircraft forward flight is less, make this aircraft oil consumption large, flying speed is slow, and voyage is short.
Summary of the invention
The problem to be solved in the present invention is to provide the telescopic wing of a kind of aircraft.Be provided with the aircraft of this telescopic wing, oil consumption is little, and flying speed block, voyage is long.
The problem to be solved in the present invention is realized by following technical scheme:
The telescopic wing of aircraft of the present invention comprises in the quiescent state in the vertical fuselage arranged, wing covering is fixed with on rear side of the middle part being characterized in described body nodal point, described wing covering is approximate rectangular flat plate, and the axis being parallel of its plate face and fuselage heading, its length is greater than the transverse width of fuselage.Wherein, the cross central line of described fuselage and fuselage heading perpendicular.All there is outlet at two ends, wing covering left and right, and there is worm case at the center of its inner chamber, and all there is telescopic wing the left and right sides of worm case, in bearing fit between described telescopic wing and described outlet.All there is rectangular indentation the outer end of described two telescopic wings below, all has the wing block for carrying out fuselage balance adjustment in described rectangular indentation.
The two side of described worm case all there are the first axis hole, the second axis hole and Triaxial hole, have the first wheel shaft, the second wheel shaft and third round axle in described worm case, the two ends of described first wheel shaft, the second wheel shaft and third round axle are arranged in described first axis hole, the second axis hole and Triaxial hole in rotatable shape respectively.
Two telescopic wings relative with the first axis hole all have longitudinal screw, all has screw rod in described longitudinal screw, the screw thread of described two screw rods is respectively minus thread and right-hand screw thread, and described longitudinal screw matches with corresponding screw rod.The inner end of described two first screw rods is connected to the two ends of described first wheel shaft.Described first wheel shaft is fixed with the first worm gear, has the first worm screw in worm case, the first worm screw and the first worm gear mesh together.
To on described second axis hole and two described telescopic wings corresponding to Triaxial hole and corresponding wing block all has rod aperture, connecting rod 1101 is all had in rod aperture, described two connecting rods 1101 are extensible link, two connecting rod 1101 one end are connected with described second wheel shaft and third round axle one end respectively mutually by universal-joint, and described connecting rod 1101 other end is fixed on pass the rod aperture on a described telescopic wing respectively in slip shape after in the rod aperture on corresponding wing block.
Described second wheel shaft is fixed with the second worm gear, has the second worm screw in described worm case, described second worm screw and the second worm gear mesh together.
Be fixed with the first gear and the second gear respectively on described third round axle He on the second wheel shaft, described first gear is together with the second gears meshing.
Described first worm screw and second worm screw one end are connected with the first actuating unit and the second actuating unit respectively.
Wherein:
The turbine box tank wall that described first worm screw two ends are relative all has axis hole, and described first worm screw two ends are arranged in described corresponding axis hole by bearing respectively.
The turbine box tank wall that described second worm screw two ends are relative all has axis hole, and described second worm screw two ends are arranged in described corresponding axis hole by bearing respectively.
Described first actuating unit and the second actuating unit are electrical motors.
The outlet of described wing covering outer end all there is inner raised edge below, makes the size exported be less than the inner chamber of wing covering; Correspondingly, the inner end of described telescopic wing has and to match with wing covering inner cavity size and can prevent telescopic wing from skidding off the circumferential boss of wing covering.
Take such scheme, have the following advantages:
As can be seen from the above scheme, owing to being fixed with wing covering on rear side of the top of described body nodal point, all there is outlet at two ends, described wing covering left and right, and there is worm case at the center of its inner chamber, all there is telescopic wing the left and right sides of worm case, in bearing fit between described telescopic wing and described outlet.All there is rectangular indentation the outer end of described two telescopic wings below, all has the wing block for carrying out fuselage balance adjustment in described rectangular indentation.
The synchronization telescope of two telescopic wings can be realized by a set of worm and gear system in turbine box, when telescopic wing stretches out, steel rope is along with slowly stretching out, when wing stretches out completely, steel rope is in tension, strengthens the rigidity of wing like this, prevents the rigidity of wing from deforming not, when wing shrinks, steel rope is also slowly involved in and shrinks in reel.When aircraft takeoff, rely on the screw propeller generation lift upwards in two ducts, aircraft vertical is upwards taken off.When aircraft upwards rise fly to desired height need flight forward time, the worm screw in worm and gear system is driven to rotate by actuating unit, turbine and the first wheel shaft and screw rod is driven to rotate by worm screw again, thus make two telescopic wings protruding, by regulating rudder plate, aircraft is made to proceed to level flight condition by vertical state of flight, thus become Fixed Wing AirVehicle, larger buoyancy is brought to aircraft by wing, shrouded propeller lift upwards transfers thrust forward to, promotes aircraft fast speed flight forward.Thus reduce the oil consumption of going straight up to type aircraft, improve flying speed, extend voyage.Make the present invention possess helicopter does not need runway can the advantage of vertical takeoff and landing simultaneously, and fixed wing aircraft flying speed is fast, and voyage is far away, the advantage that effect is high, overcome helicopter flight speed slow, effect is low simultaneously, voyage is short, and fixed wing aircraft needs the shortcoming of the runway grown very much.
Accompanying drawing explanation
Fig. 1 is the telescopic wing structure schematic diagram of aircraft of the present invention;
Fig. 2 is the schematic top plan view of Fig. 1;
Fig. 3 is the A-A cross-sectional schematic of Fig. 2;
Fig. 4 is the I point enlarged diagram of Fig. 3;
Fig. 5 is the B-B cross-sectional schematic of Fig. 4;
Fig. 6 is the C-C cross-sectional schematic of Fig. 4;
Fig. 7 is that wing covering coordinates schematic diagram with telescopic wing;
Fig. 8 is the D-D cross-sectional schematic of Fig. 7.
Detailed description of the invention
As shown in Fig. 1 ~ Fig. 8, the telescopic wing of aircraft of the present invention comprises in the quiescent state in the vertical fuselage 4 arranged, wing covering 2 is fixed with on rear side of the top of described fuselage 4 center of gravity, described wing covering 2 is approximate rectangular flat plate, the axis being parallel of its plate face and fuselage 4 heading, its length is greater than the transverse width of fuselage 4.Wherein, the cross central line of described fuselage 4 and fuselage 4 heading perpendicular.Wing covering about 2 two ends are all processed with outlet, and the center of its inner chamber is provided with worm case 6, and the left and right sides of worm case 6 is provided with telescopic wing 1, in bearing fit between described telescopic wing 1 and described outlet.The outer end of described two telescopic wings 1 is all processed with rectangular indentation below, is provided with the wing block 5 for carrying out fuselage 4 balance adjustment in described rectangular indentation.
All have bearing 14 in described first axis hole, the second axis hole, Triaxial hole, the two ends of described first wheel shaft 9, second wheel shaft 10 and third round axle 11 are arranged in described first axis hole, the second axis hole, Triaxial hole by described bearing 14 respectively.The two side of described worm case 6 is all processed with the first axis hole, the second axis hole and Triaxial hole, be provided with the first wheel shaft 9, second wheel shaft 10 and third round axle 11 in described worm case 6, the two ends of described first wheel shaft 9, second wheel shaft 10 and third round axle 11 are arranged in described first axis hole, the second axis hole and Triaxial hole in rotatable shape respectively.
Two telescopic wings 1 relative with the first axis hole are all processed with longitudinal screw, are all provided with screw rod 8 in described longitudinal screw, the screw thread of described two screw rods 8 is respectively minus thread and right-hand screw thread, and described longitudinal screw matches with corresponding screw rod 8.The inner end of described two screw rods 8 is connected to the two ends of described first wheel shaft 9.Described first wheel shaft 9 is fixed with the first worm gear 13, in worm case 6, has the first worm screw 12, first worm screw 12 and the first worm gear 13 to mesh together.
To on described second axis hole and two described telescopic wings 1 corresponding to Triaxial hole and corresponding wing block 5 is all processed with rod aperture, connecting rod 1101 is all installed with in rod aperture, described two connecting rods 1101 are extensible link, one end of two connecting rods 1101 is connected with one end of described second wheel shaft 10 and third round axle 11 respectively mutually by universal-joint, described connecting rod 1101 other end is fixed on pass the rod aperture on a described telescopic wing 1 respectively in slip shape after in the rod aperture on corresponding wing block 5, and the outer end of described connecting rod 1101 adopts spline drived.
Described second wheel shaft 10 is fixed with the second worm gear 16, is provided with the second worm screw 15 in described worm case 6, described second worm screw 15 and the second worm gear 16 mesh together.
Be fixed with the first gear 17 and the second gear 18 respectively on described third round axle 11 He on the second wheel shaft 10, described first gear 17 and the second gear 18 mesh together.
Described first worm screw 12 and second worm screw 15 one end are connected with the first actuating unit 19 and the second actuating unit 1901 respectively.
Wherein:
Turbine box 6 tank wall that described first worm screw 12 two ends are relative is all processed with axis hole, and described first worm screw 12 two ends are arranged in described corresponding axis hole by bearing 14 respectively.
Turbine box 6 tank wall that described second worm screw 15 two ends are relative is all processed with axis hole, and described second worm screw 15 two ends are arranged in described corresponding axis hole by bearing 14 respectively.
Described first actuating unit 19 and the second actuating unit 1901 are all electrical motors.
For avoiding telescopic wing 1 to skid off, on following in the outlet of described wing covering 2 outer end, being all processed with inner raised edge, making the size exported be less than the inner chamber of wing covering 2.Correspondingly, the inner end of described telescopic wing 1 is processed with and matches with wing covering 2 inner cavity size and can prevent telescopic wing 1 from skidding off the upper lower bulge of wing covering 2, and meanwhile, wing covering 2 inside adopts electrical equipment inhibiting device, and duplicate protection prevents telescopic wing from skidding off wing covering 2.
Claims (7)
1. the telescopic wing of aircraft, comprise in the quiescent state in the vertical fuselage (4) arranged, wing covering (2) is fixed with on rear side of the middle part that it is characterized in that described fuselage (4) center of gravity, described wing covering (2) is approximate rectangular flat plate, the axis being parallel of its plate face and fuselage (4) heading, its length is greater than the transverse width of fuselage (4), and wherein, cross central line and fuselage (4) heading of described fuselage (4) are perpendicular; All there is outlet at wing covering (2) two ends, left and right, and there is worm case (6) at the center of its inner chamber, and all there is telescopic wing (1) left and right sides of worm case (6), in bearing fit between described telescopic wing (1) and described outlet; All there is rectangular indentation the outer end of described two telescopic wings (1) below, all has the wing block (5) for carrying out fuselage (4) balance adjustment in described rectangular indentation;
The two side of described worm case (6) all there are the first axis hole, the second axis hole and Triaxial hole, have the first wheel shaft (9), the second wheel shaft (10) and third round axle (11) in described worm case (6), the two ends of described first wheel shaft (9), the second wheel shaft (10) and third round axle (11) are arranged in described first axis hole, the second axis hole and Triaxial hole in rotatable shape respectively; Two telescopic wings relative with the first axis hole all there is longitudinal screw, screw rod (8) is all had in described longitudinal screw, the two ends screw thread of described screw rod is respectively minus thread and right-hand screw thread, described longitudinal screw matches with corresponding screw rod (8), and the inner end of described two screw rods (8) is connected to the two ends of described first wheel shaft (9); Described first wheel shaft (9) is fixed with the first worm gear (13), has the first worm screw (12) in worm case (6), the first worm screw (12) and the first worm gear (13) mesh together;
To described second axis hole with two described telescopic wings (1) corresponding to Triaxial hole are upper and corresponding wing block (5) all has rod aperture, connecting rod (1101) is all had in rod aperture, described connecting rod (1101) is extensible link, one end of two connecting rods (1101) is connected with described second wheel shaft (10) and third round axle (11) one end respectively mutually by universal-joint, and described connecting rod (1101) other end is fixed in the rod aperture on corresponding wing block (5) pass the rod aperture on a described telescopic wing (1) respectively in slip shape after;
Described second wheel shaft (10) is fixed with the second worm gear (16), has the second worm screw (15) in described worm case (6), described second worm screw (15) and the second worm gear (16) mesh together;
Described third round axle (11) above and on the second wheel shaft (10) is fixed with the first gear (17) and the second gear (18) respectively, and described first gear (17) and the second gear (18) mesh together;
Described first worm screw (12) and the second worm screw (15) one end are connected with the first actuating unit (19) and the second actuating unit (1901) respectively.
2. the telescopic wing of aircraft according to claim 1, it is characterized in that all there is bearing (14) in described first axis hole, the second axis hole, Triaxial hole, the two ends of described first wheel shaft (9), the second wheel shaft (10) and third round axle (11) are arranged in described first axis hole, the second axis hole, Triaxial hole by described bearing (14) respectively.
3. the telescopic wing of aircraft according to claim 1, it is characterized in that worm case (6) tank wall that described first worm screw (12) two ends are relative all has axis hole, described first worm screw (12) two ends are arranged in described corresponding axis hole by bearing (14) respectively.
4. the telescopic wing of aircraft according to claim 1, it is characterized in that worm case (6) tank wall that described second worm screw (15) two ends are relative all has axis hole, described second worm screw (15) two ends are arranged in described corresponding axis hole by bearing (14) respectively.
5. the telescopic wing of the aircraft according to any one of claim 1 ~ 4, is characterized in that described first actuating unit (19) and the second actuating unit (1901) are electrical motors.
6. the telescopic wing of aircraft according to claim 5, the outlet that it is characterized in that described wing covering (2) outer end all has inner raised edge below, makes the size exported be less than the inner chamber of wing covering (2); Correspondingly, the inner end of described telescopic wing (1) has and to match with wing covering (2) inner cavity size and can prevent telescopic wing (1) from skidding off the upper lower bulge of wing covering (2), and meanwhile, wing covering inside adopts electrical equipment inhibiting device, and duplicate protection prevents telescopic wing from skidding off wing covering.
7. the telescopic wing of aircraft according to claim 5, the outlet that it is characterized in that described wing covering (2) outer end all has inner raised edge below, makes the size exported be less than the inner chamber of wing covering (2); Correspondingly, the inner end of described telescopic wing (1) has and to match with wing covering (2) inner cavity size and can prevent telescopic wing (1) from skidding off the upper lower bulge of wing covering.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310423557.1A CN103482057B (en) | 2013-09-17 | 2013-09-17 | The telescopic wing of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310423557.1A CN103482057B (en) | 2013-09-17 | 2013-09-17 | The telescopic wing of aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN103482057A CN103482057A (en) | 2014-01-01 |
| CN103482057B true CN103482057B (en) | 2015-11-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310423557.1A Active CN103482057B (en) | 2013-09-17 | 2013-09-17 | The telescopic wing of aircraft |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935512A (en) * | 2014-05-12 | 2014-07-23 | 马轶 | High endurable multi-rotor craft |
| CN105711828B (en) * | 2016-02-04 | 2017-10-13 | 瀚伦贝尔通用航空器有限公司 | A kind of aircraft direction to control mechanism |
| CN108408025A (en) * | 2018-05-08 | 2018-08-17 | 成都军融项目管理有限公司 | A kind of aircraft system with stretching, extension function |
| CN113665803B (en) * | 2021-09-02 | 2022-04-08 | 涵涡智航科技(玉溪)有限公司 | Aircraft |
| CN114013629B (en) * | 2021-11-15 | 2022-11-04 | 哈尔滨工业大学 | Passive wing extending structure |
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|---|---|---|---|---|
| GB870434A (en) * | 1959-11-11 | 1961-06-14 | Dansk Stoker & Varmekedel Komp | Improvements in or relating to oil burners and methods for operating the same |
| CN2345452Y (en) * | 1998-07-16 | 1999-10-27 | 孙卫东 | Airplane with retractable wing |
| CN200995782Y (en) * | 2007-01-17 | 2007-12-26 | 赵文志 | Airplane |
| CN202054140U (en) * | 2011-03-11 | 2011-11-30 | 江西洪都航空工业集团有限责任公司 | Wing sweepback-changing worm drive mechanism for unmanned aircraft |
| CN103274048A (en) * | 2013-06-08 | 2013-09-04 | 无锡振华机械有限公司 | Aircraft capable of taking off and landing on complex terrain |
| CN203486132U (en) * | 2013-09-17 | 2014-03-19 | 无锡振华机械有限公司 | Telescopic aircraft wing |
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2013
- 2013-09-17 CN CN201310423557.1A patent/CN103482057B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB870434A (en) * | 1959-11-11 | 1961-06-14 | Dansk Stoker & Varmekedel Komp | Improvements in or relating to oil burners and methods for operating the same |
| CN2345452Y (en) * | 1998-07-16 | 1999-10-27 | 孙卫东 | Airplane with retractable wing |
| CN200995782Y (en) * | 2007-01-17 | 2007-12-26 | 赵文志 | Airplane |
| CN202054140U (en) * | 2011-03-11 | 2011-11-30 | 江西洪都航空工业集团有限责任公司 | Wing sweepback-changing worm drive mechanism for unmanned aircraft |
| CN103274048A (en) * | 2013-06-08 | 2013-09-04 | 无锡振华机械有限公司 | Aircraft capable of taking off and landing on complex terrain |
| CN203486132U (en) * | 2013-09-17 | 2014-03-19 | 无锡振华机械有限公司 | Telescopic aircraft wing |
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| CN103482057A (en) | 2014-01-01 |
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Effective date of registration: 20161212 Address after: Suzhou City, Jiangsu province 215155 Xiangcheng District Wang Ting Zhen Hua Yang Cun Hua Lu Qiang Patentee after: HELIPELLER GENERAL AIRCRAFT CO.,LTD. Address before: 214156 Jiangsu Province, Wuxi city Huishan District Yang Town Land Holly Tianshun Road No. 7 Patentee before: WUXI ZHENHUA MACHINERY CO.,LTD. |
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Effective date of registration: 20230803 Address after: Room 202, No. 11 Dexing Lane, Chong'an District, Wuxi City, Jiangsu Province, 214000 Patentee after: Yang Haiyan Address before: 215155 Qianghua Road, Huayang Village, Wangting Town, Xiangcheng District, Suzhou City, Jiangsu Province Patentee before: HELIPELLER GENERAL AIRCRAFT CO.,LTD. |