CN204415729U - Culvert type vertically taking off and landing flyer - Google Patents
Culvert type vertically taking off and landing flyer Download PDFInfo
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- CN204415729U CN204415729U CN201520054376.0U CN201520054376U CN204415729U CN 204415729 U CN204415729 U CN 204415729U CN 201520054376 U CN201520054376 U CN 201520054376U CN 204415729 U CN204415729 U CN 204415729U
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- deflecting plate
- duct
- axle
- fuselage
- duct mechanism
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Abstract
Culvert type vertically taking off and landing flyer belongs to vehicle technology field, in the utility model, two structure identical duct mechanism symmetries are fixed in frame two ends, connector is fixed in the duct bucket outside face of two duct mechanisms, the affixed steering wheel in connector two ends, the tween drive shaft of output shaft deflecting plate group set by respectively on coupler and two duct buckets of two steering wheels is affixed, deflecting plate in deflecting plate group can link through gangbar, brushless motor output shaft and screw propeller affixed, brushless motor and motor base are fixed in the centre of duct bucket simultaneously, controller is fixed on the support board of frame, the utility model compatible with environment is strong, can vertical takeoff and landing, do not limit by site condition, noise be little, energy consumption is low, compact conformation, easy to operate and control.
Description
Technical field
The utility model belongs to vehicle technology field, is specifically related to a kind of culvert type vertically taking off and landing flyer.
Background technology
Duct aircraft in current aircraft is large with its thrust, noise is little, energy utilization rate is high, the advantages such as stability is strong become the many national research emphasis in the world today, duct aircraft not only has in the field such as civilian, commercial to be applied extremely widely, and the application in military is also the great attention being more and more subject to various countries.Militarily not only can carry out investigations to landform and enemy intelligence, but also Material Transportation and information transmission can be carried out for one's own side.The research of this respect is started late at home, relatively external, and knowwhy is short of, and technology is not mature enough, and relevant research data is deficient.At design aspect, lack comparatively reasonably duct layout, structure is also comparatively complicated; In flight course, the comparatively obvious shortcomings such as existence and stability is not enough, the time that is continuation of the journey is short, delelivered payload capability is low, noise is large, power utilization rate is low.Following duct aircraft be certainly towards save power, structure simple, be easy to operation, the comprehensive development in the direction such as little, the intelligent stealth capabilities of noise is strong, safety is high.
Summary of the invention
The purpose of this utility model be to provide a kind of simple and compact for structure, noise is little, save the novel culvert type vertically taking off and landing flyer of power.The power of flight, from the High Rotation Speed of screw propeller in former and later two duct mechanisms, utilizes the difference of front and back brushless motor speed, realizes the pitching of aircraft, utilizes the rotation of deflecting plate to produce moment of rotation and realizes turning to of aircraft and roll.Solve that existing Flight Vehicle Structure is complicated, operation easier large, the shortcoming of power waste, this duct aircraft cost is low, is easy to realize industrialization, is applied to reality.
The utility model is made up of duct mechanism, frame B, controller C and connector E, and the fuselage hole I 18 on the duct bucket I 1 in the fuselage bar I 15 of its mid frame B and fuselage bar II 16 left part duct mechanism I A respectively in duct mechanism, fuselage hole III 20 and fuselage hole II 19, fuselage hole IV 21 and duct mechanism I A are affixed; Fuselage hole V 22 on duct bucket II 6 in the fuselage bar I 15 of frame B and duct mechanism II D of fuselage bar II 16 right part branch not in duct mechanism, fuselage hole VII 24 and fuselage hole VI 23, fuselage hole VIII 25 are affixed with duct mechanism II D; In duct mechanism duct bucket I 1 outside face of duct mechanism I A and the left side cambered surface of connector E affixed, in duct mechanism, the motor base I 5 of duct mechanism I A is affixed with the left side central portion of fuselage bar I 15 in frame B and fuselage bar II 16; In duct mechanism duct bucket II 6 outside face of duct mechanism II D and the right side cambered surface of connector E affixed; In duct mechanism, the motor base II 10 of duct mechanism II D is affixed with the right side central of fuselage bar I 15 in frame B and fuselage bar II 16; Controller C is fixed on the support board 14 of frame B; In duct mechanism, the output shaft of the steering wheel I 26 of axle Ⅹ 63 in coupler 52 with connector E of deflecting plate III c of duct mechanism I A is affixed; In duct mechanism, the output shaft of the steering wheel II 28 of axle Ⅹ in coupler and connector E of the deflecting plate III of duct mechanism II D is affixed.
Described duct mechanism is made up of duct mechanism I A and duct mechanism II D, duct mechanism I A is identical with duct mechanism II D structure, wherein duct mechanism I A is made up of duct bucket I 1, screw propeller I 2, deflecting plate group I 3, brushless motor I 4 and motor base I 5, the output shaft of brushless motor I 4 and the centre hole interference fit of screw propeller I 2, and lock with jam nut m; Brushless motor I 4 is fixed on motor base I 5, and the output shaft of brushless motor I 4 overlaps with the center shaft of duct bucket I 1; In deflecting plate group I 3, the axle V 44 of the axle IV 45 of the axle I46 of the axle II 47 of the axle III 48 of deflecting plate I a, axle VI 49, deflecting plate II b, axle VIII 50, deflecting plate III c, axle Ⅹ 51, deflecting plate IV d, axle Ⅸ 53, deflecting plate V e, axle VII 54 are flexibly connected through the mounting hole I 31 of bearing and duct bucket I 1, mounting hole II 38, mounting hole III 30, mounting hole IV 36, mounting hole V 29, mounting hole VI 34, mounting hole VII 32, mounting hole VIII 35, mounting hole Ⅸ 33, mounting hole Ⅹ 37 respectively.
Described frame B is made up of the bar I 11 that lands, support I 12, support II 13, support board 14, fuselage bar I 15, fuselage bar II 16 and landing bar II 17, its medium-height trestle I 12 and support II 13 are all in arch, landing bar I 11 is fixed in support I 12 and support II 13 one end, landing bar II 17 is fixed in support I 12 and support II 13 other end, fuselage bar I 15 and fuselage bar II 16 are fixed in support I 12 and support II 13 top, and support board 14 is fixed in support I 12 and support II 13 top.
Described deflecting plate group I 3 is made up of deflecting plate I a, deflecting plate II b, deflecting plate III c, deflecting plate IV d, deflecting plate V e, gangbar f, bearing pin I 39, pin shaft II 40, pin shaft III 41, bearing pin IV 42 and bearing pin V 43, wherein to be fixed in deflecting plate I a line of centers on the upper side at bearing pin V 43 two ends, with axle III 48 and axle VI 49 decentraction of deflecting plate I a, be flexibly connected with gangbar f in the middle of bearing pin V 43; It is on the upper side that bearing pin IV 42 two ends are fixed in deflecting plate II b line of centers, with axle II 47 and axle VIII 50 decentraction of deflecting plate II b, is flexibly connected in the middle of bearing pin IV 42 with gangbar f; It is on the upper side that pin shaft III 41 two ends are fixed in deflecting plate III c line of centers, with axle I46 and axle Ⅹ 51 decentraction of deflecting plate III c, is flexibly connected in the middle of pin shaft III 41 with gangbar f; It is on the upper side that pin shaft II 40 two ends are fixed in deflecting plate IV d line of centers, with axle IV 45 and axle Ⅸ 53 decentraction of deflecting plate IV d, is flexibly connected in the middle of pin shaft II 40 with gangbar f; It is on the upper side that bearing pin I 39 two ends are fixed in deflecting plate V e line of centers, with axle V 44 and axle VII 54 decentraction of deflecting plate V e, is flexibly connected in the middle of bearing pin I 39 with gangbar f.
Connector E is made up of steering wheel I 26, articulamentum 27, steering wheel II 28, and wherein steering wheel I 26 is fixed on the left of articulamentum 27; Steering wheel II 28 is fixed on the right side of articulamentum 27.
In the utility model novel culvert type vertically taking off and landing flyer principle of work and control as follows:
1) vertical takeoff and landing function: the electric energy High Rotation Speed that the brushless motor II 9 in the brushless motor I 4 in duct mechanism I A and duct mechanism II D utilizes power supply to provide, then drive the screw propeller be arranged on brushless motor axle to rotate and produce lift, utilize input in controller C fly control code control former and later two duct mechanisms produce lift equal, and the resultant lift produced is greater than or less than self total force of duct aircraft, makes duct aircraft can realize pulsation-free landing.
2) pitching flying function: the rotating speed being controlled the brushless motor in duct mechanism I A and duct mechanism II D by controller C, form speed discrepancy, the lift that duct mechanism I A is produced is greater than or less than the lift that duct mechanism II D produces, and realizes the pitching flying of duct aircraft.
3) hovering function: the rotating speed being controlled the brushless motor in duct mechanism I A and duct mechanism II D by controller C, the lift that duct mechanism I A is produced equals the lift that duct mechanism II D produces, and resultant lift equals self total force of duct aircraft, realizes the hovering of aircraft.
4) turn to and roll function: the rotating speed being controlled the brushless motor in duct mechanism I A and duct mechanism II D by controller C, the lift that duct mechanism I A is produced equals the lift that duct mechanism II D produces, and resultant lift equals self total force of duct aircraft.Recycling controller C controls two deflecting plate groups and rotates, when two deflecting plate groups turn to contrary time, make duct aircraft produce moment of rotation in a horizontal direction, realize turning to of aircraft; When two deflecting plates turn to identical time, make aircraft produce in the horizontal direction one perpendicular to aircraft longitudinal direction make a concerted effort, the roll of realization.
The utility model compared with prior art has the following advantages and beneficial effect:
1. noise is little.The screw propeller of culvert type aircraft is drawn together in duct by ring, has both prevented air-flow in duct to external diffusion, to stop that propeller sound is outwards propagated, prevent again the interference in air flow around duct, reduce the turbulent noise of air-flow.
2. efficient energy-saving.When screw propeller is in duct during high speed rotating, create lift upwards, and screw propeller ring is drawn together in duct, what the duct lip radius of increasing improved duct entrance streams environment and static pressure distribution, improve the power of duct lip, air flow power is made full use of.
3. simple and compact for structure, operator only just need can realize the above function of aircraft by controlling carry-on controller, operates extremely simply, is easy to control.
4. compatible with environment is high, can vertical takeoff and landing.Utilize the vertical takeoff and landing function of duct aircraft can landing in different environment, do not limit by site condition, be convenient to extensive popularization.
Accompanying drawing explanation
Fig. 1 is the main optical axis mapping of culvert type vertically taking off and landing flyer
Fig. 2 is the main optical axis mapping of duct mechanism I
Fig. 3 is the enlarged partial sectional view of W in Fig. 2
Fig. 4 is the main optical axis mapping of duct mechanism II
Fig. 5 is the enlarged partial sectional view of R in Fig. 4
Fig. 6 is the main optical axis mapping of frame
Fig. 7 is the main shaft view 1 of duct bucket I
Fig. 8 is the main shaft view of duct bucket II
Fig. 9 is the topology view of connector E
Figure 10 is the main shaft view 2 of duct bucket I
Figure 11 is the main shaft view of deflecting plate group I
The enlarged partial sectional view of K1 in Figure 12 Figure 11
The enlarged partial sectional view of K2 in Figure 13 Figure 11
The enlarged partial sectional view of K3 in Figure 14 Figure 11
The enlarged partial sectional view of K4 in Figure 15 Figure 11
The enlarged partial sectional view of K5 in Figure 16 Figure 11
Figure 17 is the characteristic view of deflecting plate group I assembly
Wherein: A. duct mechanism I, B. frame, C. controller, D. duct mechanism II, E. connector, 1. duct bucket I, 2. screw propeller I, 3. deflecting plate group I, 4. brushless motor I, 5. motor base I, 6. duct bucket II, 7. screw propeller II, 8. deflecting plate group II, 9 brushless motors II, 10. motor base II, 11. landing bars I, 12. supports I, 13. supports II, 14. support boards, 15. fuselage bars I, 16. fuselage bars II, 17. landing bars II, 18. fuselage holes I, 19. fuselage holes II, 20. fuselage holes III, 21. fuselage holes IV, 22. fuselage holes V, 23. fuselage holes VI, 24. fuselage holes VII, 25. fuselage holes VIII, 26. steering wheels I, 27. articulamentum 28. steering wheels II, 29. mounting holes V, 30. mounting holes III, 31. mounting holes I, 32. mounting holes VII, 33. mounting holes Ⅸ, 34. mounting holes VI, 35. mounting holes VIII, 36. mounting holes IV, 37. mounting holes Ⅹ, 38. mounting holes II, 39. bearing pins I, 40. pin shaft II 41. pin shaft III, 42. bearing pins IV, 43. bearing pins V, 44. axles V, 45. axles IV, 46. axles I, 47. axles II, 48. axle III 49. axles VI, 50. axles VIII, 51. axles Ⅹ, 52. coupler, 53. axles Ⅸ, 54. axles VII, a. deflecting plate I, b. deflecting plate II c. deflecting plate III, d. deflecting plate IV, e. deflecting plate V, f. gangbar, m. jam nut
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is further described:
As shown in Figures 1 to 9: the utility model forms primarily of duct mechanism, frame B, controller C and connector E, the fuselage hole I 18 on the duct bucket I 1 in the fuselage bar I 15 of its mid frame B and duct mechanism I A of fuselage bar II 16 left part respectively in duct mechanism, fuselage hole III 20 and fuselage hole II 19, fuselage hole IV 21 are affixed with duct mechanism I A; Fuselage hole V 22 on duct bucket II 6 in the fuselage bar I 15 of frame B and duct mechanism II D of fuselage bar II 16 right part branch not in duct mechanism, fuselage hole VII 24 and fuselage hole VI 23, fuselage hole VIII 25 are affixed with duct mechanism II D; In duct mechanism duct bucket I 1 outside face of duct mechanism I A and the left side cambered surface of connector E affixed, in duct mechanism, the motor base I 5 of duct mechanism I A is affixed with the left side central portion of fuselage bar I 15 in frame B and fuselage bar II 16; In duct mechanism duct bucket II 6 outside face of duct mechanism II D and the right side cambered surface of connector E affixed, in duct mechanism, the motor base II 10 of duct mechanism II D is affixed with the right side central of fuselage bar I 15 in frame B and fuselage bar II 16; Controller C is fixed on the support board 14 of frame B; In duct mechanism, the output shaft of the steering wheel I 26 of axle Ⅹ 63 in coupler 52 with connector E of deflecting plate III c of duct mechanism I A is affixed; In duct mechanism, the output shaft of the steering wheel II 28 of axle Ⅹ in coupler and connector E of the deflecting plate III of duct mechanism II D is affixed.
As shown in Fig. 2 to Fig. 5, Figure 10, Figure 17: as described in duct mechanism be made up of duct mechanism I A and duct mechanism II D, duct mechanism I A is identical with duct mechanism II D structure, wherein duct mechanism I A is made up of duct bucket I 1, screw propeller I 2, deflecting plate group I 3, brushless motor I 4 and motor base I 5, the output shaft of brushless motor I 4 and the centre hole interference fit of screw propeller I 2, and lock with jam nut m; Brushless motor I 4 is fixed on motor base I 5, and the output shaft of brushless motor I 4 overlaps with the center shaft of duct bucket I 1; In deflecting plate group I 3, the axle V 44 of the axle IV 45 of the axle I46 of the axle II 47 of the axle III 48 of deflecting plate I a, axle VI 49, deflecting plate II b, axle VIII 50, deflecting plate III c, axle Ⅹ 51, deflecting plate IV d, axle Ⅸ 53, deflecting plate V e, axle VII 54 are flexibly connected through the mounting hole I 31 of bearing and duct bucket I 1, mounting hole II 38, mounting hole III 30, mounting hole IV 36, mounting hole V 29, mounting hole VI 34, mounting hole VII 32, mounting hole VIII 35, mounting hole Ⅸ 33, mounting hole Ⅹ 37 respectively; For the ease of I& M, duct bucket can be divided into upper and lower designing two portions from deflecting plate group junction, duct bucket I 1 is fixed together by upper and lower two halves, the latter half has bearings mounted groove, when mounted, deflecting plate group I 3 is installed complete after deflecting plate group I 3 is installed to the lower part of duct bucket I 1, then connect with bolt.
As shown in Figure 6: described frame B is made up of the bar I 11 that lands, support I 12, support II 13, support board 14, fuselage bar I 15, fuselage bar II 16 and landing bar II 17, its medium-height trestle I 12 and support II 13 are all in arch, landing bar I 11 is fixed in support I 12 and support II 13 one end, landing bar II 17 is fixed in support I 12 and support II 13 other end, fuselage bar I 15 and fuselage bar II 16 are fixed in support I 12 and support II 13 top, and support board 14 is fixed in support I 12 and support II 13 top.
As shown in Figure 11 to Figure 16: as described in deflecting plate group I 3 be made up of deflecting plate I a, deflecting plate II b, deflecting plate III c, deflecting plate IV d, deflecting plate V e, gangbar f, bearing pin I 39, pin shaft II 40, pin shaft III 41, bearing pin IV 42 and bearing pin V 43, wherein to be fixed in deflecting plate I a line of centers on the upper side at bearing pin V 43 two ends, with axle III 48 and axle VI 49 decentraction of deflecting plate I a, be flexibly connected with gangbar f in the middle of bearing pin V 43; It is on the upper side that bearing pin IV 42 two ends are fixed in deflecting plate II b line of centers, with axle II 47 and axle VIII 50 decentraction of deflecting plate II b, is flexibly connected in the middle of bearing pin IV 42 with gangbar f; It is on the upper side that pin shaft III 41 two ends are fixed in deflecting plate III c line of centers, with axle I46 and axle Ⅹ 51 decentraction of deflecting plate III c, is flexibly connected in the middle of pin shaft III 41 with gangbar f; It is on the upper side that pin shaft II 40 two ends are fixed in deflecting plate IV d line of centers, with axle IV 45 and axle Ⅸ 53 decentraction of deflecting plate IV d, is flexibly connected in the middle of pin shaft II 40 with gangbar f; It is on the upper side that bearing pin I 39 two ends are fixed in deflecting plate V e line of centers, with axle V 44 and axle VII 54 decentraction of deflecting plate V e, is flexibly connected in the middle of bearing pin I 39 with gangbar f.
As shown in Figure 9: described connector E is made up of steering wheel I 26, articulamentum 27, steering wheel II 28, wherein steering wheel I 26 is fixed on the left of articulamentum 27; Steering wheel II 28 is fixed on the right side of articulamentum 27.
Claims (5)
1. a culvert type vertically taking off and landing flyer, it is characterized in that being made up of duct mechanism, frame (B), controller (C) and connector (E), the fuselage hole I (18) on the duct bucket I (1) in the fuselage bar I (15) of its mid frame (B) and the duct mechanism I (A) of fuselage bar II (16) left part respectively in duct mechanism, fuselage hole III (20) and fuselage hole II (19), fuselage hole IV (21) are affixed with duct mechanism I (A); Fuselage hole V (22) on duct bucket II (6) in fuselage bar I (15) and fuselage bar II (16) the right part branch duct mechanism II (D) not in duct mechanism of frame (B), fuselage hole VII (24) and fuselage hole VI (23), fuselage hole VIII (25) and duct mechanism II (D) are affixed; In duct mechanism duct bucket I (1) outside face of duct mechanism I (A) and the left side cambered surface of connector (E) affixed, in duct mechanism, the motor base I (5) of duct mechanism I (A) is affixed with the left side central portion of fuselage bar I (15) in frame (B) and fuselage bar II (16); In duct mechanism duct bucket II (6) outside face of duct mechanism II (D) and the right side cambered surface of connector (E) affixed; In duct mechanism, the motor base II (10) of duct mechanism II (D) is affixed with the right side central of fuselage bar I (15) in frame (B) and fuselage bar II (16); Controller (C) is fixed on the support board (14) of frame (B); In duct mechanism, the output shaft of the steering wheel I (26) of axle Ⅹ (63) in coupler (52) with connector (E) of the deflecting plate III (c) of duct mechanism I (A) is affixed; In duct mechanism, the output shaft of the steering wheel II (28) of axle Ⅹ in coupler and connector (E) of the deflecting plate III of duct mechanism II (D) is affixed.
2. by culvert type vertically taking off and landing flyer according to claim 1, it is characterized in that described duct mechanism is made up of duct mechanism I (A) and duct mechanism II (D), duct mechanism I (A) is identical with duct mechanism II (D) structure, wherein duct mechanism I (A) is by duct bucket I (1), screw propeller I (2), deflecting plate group I (3), brushless motor I (4) and motor base I (5) form, the output shaft of brushless motor I (4) and the centre hole interference fit of screw propeller I (2), and lock with jam nut (m), brushless motor I (4) is fixed on motor base I (5), and the output shaft of brushless motor I (4) overlaps with the center shaft of duct bucket I (1), the axle III (48) of deflecting plate I (a) in deflecting plate group I (3), axle VI (49), the axle II (47) of deflecting plate II (b), axle VIII (50), the axle I (46) of deflecting plate III (c), axle Ⅹ (51), the axle IV (45) of deflecting plate IV (d), axle Ⅸ (53), the axle V (44) of deflecting plate V (e), axle VII (54) is respectively through the mounting hole I (31) of bearing and duct bucket I (1), mounting hole II (38), mounting hole III (30), mounting hole IV (36), mounting hole V (29), mounting hole VI (34), mounting hole VII (32), mounting hole VIII (35), mounting hole Ⅸ (33), mounting hole Ⅹ (37) is flexibly connected.
3. by culvert type vertically taking off and landing flyer according to claim 1, it is characterized in that described frame (B) is by landing bar I (11), support I (12), support II (13), support board (14), fuselage bar I (15), fuselage bar II (16) and landing bar II (17) form, its medium-height trestle I (12) and support II (13) are all in arch, landing bar I (11) is fixed in support I (12) and support II (13) one end, landing bar II (17) is fixed in support I (12) and support II (13) other end, fuselage bar I (15) and fuselage bar II (16) are fixed in support I (12) and support II (13) top, support board (14) is fixed in support I (12) and support II (13) top.
4. by culvert type vertically taking off and landing flyer according to claim 2, it is characterized in that described deflecting plate group I (3) is by deflecting plate I (a), deflecting plate II (b), deflecting plate III (c), deflecting plate IV (d), deflecting plate V (e), gangbar (f), bearing pin I (39), pin shaft II (40), pin shaft III (41), bearing pin IV (42) and bearing pin V (43) form, wherein to be fixed in deflecting plate I (a) line of centers on the upper side at bearing pin V (43) two ends, with axle III (48) and axle VI (49) decentraction of deflecting plate I (a), be flexibly connected with gangbar (f) in the middle of bearing pin V (43), it is on the upper side that bearing pin IV (42) two ends are fixed in deflecting plate II (b) line of centers, with axle II (47) and axle VIII (50) decentraction of deflecting plate II (b), be flexibly connected with gangbar (f) in the middle of bearing pin IV (42), it is on the upper side that pin shaft III (41) two ends are fixed in deflecting plate III (c) line of centers, with axle I (46) and axle Ⅹ (51) decentraction of deflecting plate III (c), be flexibly connected with gangbar (f) in the middle of pin shaft III (41), it is on the upper side that pin shaft II (40) two ends are fixed in deflecting plate IV (d) line of centers, with axle IV (45) and axle Ⅸ (53) decentraction of deflecting plate IV (d), be flexibly connected with gangbar (f) in the middle of pin shaft II (40), it is on the upper side that bearing pin I (39) two ends are fixed in deflecting plate V (e) line of centers, with axle V (44) and axle VII (54) decentraction of deflecting plate V (e), be flexibly connected with gangbar (f) in the middle of bearing pin I (39).
5. by culvert type vertically taking off and landing flyer according to claim 1, it is characterized in that described connector (E) is made up of steering wheel I (26), articulamentum (27), steering wheel II (28), wherein steering wheel I (26) is fixed in articulamentum (27) left side; Steering wheel II (28) is fixed in articulamentum (27) right side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520054376.0U CN204415729U (en) | 2015-01-26 | 2015-01-26 | Culvert type vertically taking off and landing flyer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520054376.0U CN204415729U (en) | 2015-01-26 | 2015-01-26 | Culvert type vertically taking off and landing flyer |
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| CN204415729U true CN204415729U (en) | 2015-06-24 |
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| CN201520054376.0U Expired - Fee Related CN204415729U (en) | 2015-01-26 | 2015-01-26 | Culvert type vertically taking off and landing flyer |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106882361A (en) * | 2017-03-27 | 2017-06-23 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of attitude coutrol mechanism of DCB Specimen unmanned plane |
| CN107042883A (en) * | 2017-03-27 | 2017-08-15 | 上海珞鹏航空科技有限公司成都研发分公司 | Double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading |
| CN108128442A (en) * | 2017-12-22 | 2018-06-08 | 北京正兴弘业科技有限公司 | For the pneumatic rudder ducted fan of vector and control method of vertical take-off and landing drone |
| CN112173069A (en) * | 2020-08-27 | 2021-01-05 | 百奥创新(天津)科技有限公司 | Unmanned aerial vehicle attitude control system with variable-angle fan blade control surface |
-
2015
- 2015-01-26 CN CN201520054376.0U patent/CN204415729U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106882361A (en) * | 2017-03-27 | 2017-06-23 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of attitude coutrol mechanism of DCB Specimen unmanned plane |
| CN107042883A (en) * | 2017-03-27 | 2017-08-15 | 上海珞鹏航空科技有限公司成都研发分公司 | Double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading |
| CN108128442A (en) * | 2017-12-22 | 2018-06-08 | 北京正兴弘业科技有限公司 | For the pneumatic rudder ducted fan of vector and control method of vertical take-off and landing drone |
| CN112173069A (en) * | 2020-08-27 | 2021-01-05 | 百奥创新(天津)科技有限公司 | Unmanned aerial vehicle attitude control system with variable-angle fan blade control surface |
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