CN220701344U - Steering engine driven deceleration landing ornithopter - Google Patents
Steering engine driven deceleration landing ornithopter Download PDFInfo
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- CN220701344U CN220701344U CN202322415648.2U CN202322415648U CN220701344U CN 220701344 U CN220701344 U CN 220701344U CN 202322415648 U CN202322415648 U CN 202322415648U CN 220701344 U CN220701344 U CN 220701344U
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- 238000005265 energy consumption Methods 0.000 abstract description 6
- 230000007547 defect Effects 0.000 abstract 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Abstract
The utility model discloses a steering engine driven deceleration landing ornithopter, which comprises: the device comprises a machine body, a first steering engine, a second steering engine, a third steering engine, a tail wing mechanism and a wing rod mechanism; the steering engine I is arranged at the front part of the machine body, is connected with the wing rod piece mechanism, and drives the wing rod piece mechanism to move; the mechanism for rotating the wing rod mechanism comprises: steering engine III, steering engine rocker arm I, pull rod five, pull rod III, pull rod IV, first articulated joint block, second articulated joint block, pull rod I, pull rod II, connecting rod III, connecting rod IV, square box, connecting rod I and connecting rod II; the tail wing mechanism is fixed on the rear support of the fuselage; the steering engine-driven deceleration landing ornithopter provided by the utility model has the characteristics of good wing deceleration performance, stable flight, low energy consumption and light quality, and the steering engine three rotates to drive the square box to rotate around the first connecting rod and the second connecting rod in the landing process. Solves the defects of high landing speed, high energy consumption and heavy mechanism of the existing ornithopter.
Description
Technical Field
The utility model belongs to the technical field of deceleration aircrafts, and particularly relates to a steering engine driven deceleration landing ornithopter.
Background
Along with the rapid development of flight technology, the ornithopter has become a hot spot for more and more people to study due to the characteristics of light weight, low energy consumption, convenient manufacture and easy control of flight, and various bionic ornithopters can realize different flight functions and fly in complex environments and have good flight performance.
The development of the existing ornithopter is mainly focused on the swing mechanism of the wing, so that the requirement of deceleration in the descending process of the ornithopter is omitted, and the ornithopter is required to have the function of deceleration in a specific flight environment, so that the ornithopter can more stably land and has the effect of protecting the ornithopter. In order to realize the function of decelerating the ornithopter in the landing process, a corresponding decelerating mechanism needs to be designed. Therefore, it is necessary to design a mechanism with good deceleration performance, low energy consumption and light weight, which is a problem to be solved.
Disclosure of Invention
The utility model aims to solve the problems and provides a steering engine driven deceleration landing ornithopter which has good deceleration performance, stable flight, low energy consumption and light weight.
In order to solve the technical problems, the technical scheme of the utility model is as follows: the utility model provides a steering wheel driven speed reduction falls flapping wing aircraft, includes fuselage, steering wheel one, steering wheel two, steering wheel three, fin mechanism and wing member mechanism, its characterized in that: the machine body is composed of a square box, a first connecting rod, a second connecting rod, a first machine body supporting rod, a second machine body supporting rod, a third machine body supporting rod, a fourth machine body supporting rod, a front machine body supporting rod, a rear machine body supporting rod, a third connecting rod, a fourth connecting rod, a first pull rod, a second pull rod, a first hinged joint block, a second hinged joint block, a third pull rod, a fourth pull rod, a fifth pull rod, a first steering engine rocker arm and a steering engine fixing frame, the square box is arranged at the front part of the machine body, the first steering engine and the second steering engine are fixed in the square box, the square box is connected with the first connecting rod and the second connecting rod, one end of the first machine body supporting rod penetrates through the front machine body supporting rod to be connected with the first connecting rod, the other end of the first machine body supporting rod is connected with the rear machine body supporting rod, one end of the second machine body supporting rod penetrates through the front machine body supporting rod to be connected with the rear machine body supporting rod, one end of the third machine body supporting rod is connected with the rear machine body supporting rod, the other end of the third supporting rod is connected with the rear machine body supporting rod, the other end of the fourth machine body supporting rod is connected with the front machine body supporting rod.
Preferably, the square box is connected with the third connecting rod and the fourth connecting rod, the third connecting rod is connected with the first connecting rod, the fourth connecting rod is connected with the second connecting rod, the first connecting rod is connected with the first hinging block, the second connecting rod is connected with the second hinging block, the first hinging block is connected with the third connecting rod, the second hinging block is connected with the fourth connecting rod, the third connecting rod and the fourth connecting rod are fixed on the fifth connecting rod, the fifth connecting rod is fixed on the first steering engine rocker arm, the third steering engine rocker arm is connected with the third rotating shaft of the steering engine, the third steering engine is fixed by the steering engine fixing frame, and the steering engine fixing frame is fixed on the third supporting rod of the machine body.
Preferably, the wing rod mechanism is composed of a steering engine rocker arm II, a wing fixing plate I, a wing fixing plate II, a wing main rod, a three-way valve device, a third hinge block, a fourth hinge block, a connecting rod five, a connecting rod six, a connecting rod seven, a connecting rod eight, a fifth hinge block and a connecting rod nine, wherein the steering engine rocker arm II is connected with a steering engine rotating shaft, the steering engine rocker arm II is connected with the wing fixing plate I, the wing fixing plate I is connected with the wing fixing plate II, one end of the wing main rod is fixed between the wing fixing plate I and the wing fixing plate II, the three-way valve device, the third hinge block and the fourth hinge block are fixed on the wing main rod, the three-way valve device is in 20 DEG, 40 DEG and 60 DEG, the 20 DEG port is connected with the connecting rod five, the 60 DEG port is connected with the connecting rod seven, the third hinge block is connected with the connecting rod eight, the other end of the connecting rod eight is connected with the fifth hinge block, the other end of the fifth hinge block is connected with the connecting rod nine, the other end of the connecting rod nine is connected with the fourth hinge block, and the other half wing rod mechanism is symmetrically distributed.
Preferably, the tail mechanism comprises a tail clamp, a tail fixing frame, a tail middle rod and two tail side rods, wherein the tail clamp is fixed on the rear support of the aircraft body, the tail fixing frame is fixed on the tail clamp, and the tail middle rod and the two tail side rods are fixed on the tail fixing frame.
The beneficial effects of the utility model are as follows: the steering engine driven deceleration landing ornithopter provided by the utility model has the characteristics of good deceleration performance, stable flight, low energy consumption and light weight. In the normal flight process, the steering engine I and the steering engine II control the wing rod piece mechanism to flap up and down, in the descending flight process, the steering engine driven decelerating and landing ornithopter steering engine III drives the square box, the steering engine I and the steering engine II rotate at an angle of about 65 degrees, the steering engine I and the steering engine II control the wing rod piece mechanism to flap up and down approximately, and in addition, the decelerating function of the ornithopter can also play a role in protecting the ornithopter in the landing process.
Drawings
Fig. 1 is a schematic top view of a fuselage and steering engine drive structure according to the present utility model.
FIG. 2 is a schematic side view of the fuselage and tail mechanism of the present utility model.
FIG. 3 is a schematic top view of the wing lever mechanism of the present utility model.
FIG. 4 is a schematic top view of the general structure of the flapping wing air vehicle of the utility model in normal flight.
Fig. 5 is a schematic side view of the general structure of the flapping wing air vehicle in normal flight.
FIG. 6 is a schematic side view of the general structure of the flapping wing aircraft in the utility model.
Reference numerals illustrate: 1. a body; 2. a tail wing mechanism; 3. wing rod piece mechanism; 4. a square box; 5. steering engine I; 6. steering engine II; 7. a first connecting rod; 8. a second connecting rod; 9. a first support bar of the fuselage; 10. a second support bar of the main body; 11. a third support bar of the fuselage; 12. a fourth support bar of the body; 13. a fuselage front support; 14. a fuselage rear support; 15. a connecting rod III; 16. a connecting rod IV; 17. a first pull rod; 18. a second pull rod; 19. a first hinge block; 20. a second hinge block; 21. a third pull rod; 22. a pull rod IV; 23. a fifth pull rod; 24. a steering engine rocker arm I; 25. steering engine III; 26. steering engine fixing frame; 27. a steering engine rocker arm II; 28. a wing fixing plate I; 29. a wing fixing plate II; 30. a wing main lever; 31. a three-way valve device; 32. a third hinge block; 33. a fourth articulation block; 34. a connecting rod V; 35. a connecting rod six; 36. a connecting rod seven; 37. a connecting rod eight; 38. a fifth articulation block; 39. a connecting rod nine; 40. tail clips of tail wings; 41. empennage fixing frame; 42. tail middle rod; 43. tail side bars.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
As shown in fig. 1 to 6, the utility model provides a steering engine driven deceleration landing flapping wing aircraft, which comprises a fuselage 1, a steering engine one 5, a steering engine two 6, a steering engine three 25, a tail wing mechanism 2 and a wing rod mechanism 3, and is characterized in that: the machine body 1 consists of a square box 4, a first connecting rod 7, a second connecting rod 8, a first machine body supporting rod 9, a second machine body supporting rod 10, a third machine body supporting rod 11, a fourth machine body supporting rod 12, a front machine body supporting rod 13, a rear machine body supporting rod 14, a third connecting rod 15, a fourth connecting rod 16, a first connecting rod 17, a second connecting rod 18, a first hinging block 19, a second hinging block 20, a third connecting rod 21, a fourth connecting rod 22, a fifth connecting rod 23, a first steering engine rocker arm 24 and a steering engine fixing frame 26, the square box 4 is arranged at the front part of the machine body 1, the first steering engine 5 and the second steering engine 6 are fixed in the square box 4, the square box 4 is connected with the first connecting rod 7 and the second connecting rod 8, one end of the first supporting rod 9 of the machine body penetrates through the front machine body support 13 to be connected with the first connecting rod 7, the other end of the first supporting rod is connected with the rear machine body support 14, one end of the second supporting rod 10 of the machine body penetrates through the front machine body support 13 to be connected with the second connecting rod 8, the other end of the second supporting rod is connected with the rear machine body support 14, one end of the third supporting rod 11 of the machine body is connected with the front machine body support 13, the other end of the third supporting rod is connected with the rear machine body support 14, one end of the fourth supporting rod 12 of the machine body is connected with the front machine body support 13, and the other end of the fourth supporting rod is connected with the rear machine body support 14.
As shown in fig. 1, the square box 4 is connected with a third connecting rod 15 and a fourth connecting rod 16, the third connecting rod 15 is connected with a first connecting rod 17, the fourth connecting rod 16 is connected with a second connecting rod 18, the first connecting rod 17 is connected with a first hinged block 19, the second connecting rod 18 is connected with a second hinged block 20, the first hinged block 19 is connected with a third connecting rod 21, the second hinged block 20 is connected with a fourth connecting rod 22, the third connecting rod 21 and the fourth connecting rod 22 are fixed on a fifth connecting rod 23, the fifth connecting rod 23 is fixed on a first steering engine rocker arm 24, the first steering engine rocker arm 24 is connected with a third rotating shaft 25, the third steering engine 25 is fixed by a steering engine fixing frame 26, and the steering engine fixing frame 26 is fixed on a third supporting rod 11 of the machine body.
As shown in fig. 1 and 3, the wing rod mechanism 3 is composed of a steering engine rocker arm 27, a wing fixing plate 28, a wing fixing plate 29, a wing main rod 30, a three-way valve device 31, a third hinge block 32, a fourth hinge block 33, a connecting rod five 34, a connecting rod six 35, a connecting rod seven 36, a connecting rod eight 37, a fifth hinge block 38 and a connecting rod nine 39, wherein a steering engine 5 rotating shaft is connected with the steering engine rocker arm 27, the steering engine rocker arm 27 is connected with the wing fixing plate 28, the wing fixing plate 28 is connected with the wing fixing plate 29, one end of the wing main rod 30 is fixed between the wing fixing plate 28 and the wing fixing plate 29, the three-way valve device 31, the third hinge block 32 and the fourth hinge block 33 are fixed on the wing main rod 30, the three-way valve device 31 is 20 DEG, 40 DEG and 60 DEG, the connecting rod five 34 is connected with the connecting rod six 35 at 20 DEG, the connecting rod seven 36 is connected with the opening 60 DEG, the third hinge block 32 is connected with the connecting rod eight 37, the other end of the connecting rod 37 is connected with the fifth hinge block 38, the other end of the connecting rod 37 is connected with the paired hinge block 39, the other end of the wing main rod mechanism is connected with the wing main rod 33, and the other end of the wing main rod mechanism is connected with the fourth hinge block 33.
As shown in fig. 4 and 5, in the normal flight process of the ornithopter, the steering engine three 25 does not work, and the steering engine one 5 and the steering engine two 6 drive the wing rod piece mechanism 3 to flap up and down.
As shown in fig. 6, in the process of landing of the flapping wing aircraft, the steering engine three 25 drives the steering engine rocker one 24 to rotate 15 degrees anticlockwise, the steering engine rocker one 24 drives the pull rod five 23 to rotate anticlockwise, the pull rod five 23 pulls the pull rod three 21 and the pull rod four 22 to move, the pull rod three 21 pulls the first hinging block 19 and the pull rod four 22 to move, the pull rod four 22 pulls the second hinging block 20 and the pull rod two 18 to move, the pull rod one 17 pulls the pull rod three 15 to move, the pull rod two 18 pulls the pull rod four 16 to move, the pull rod three 15 and the pull rod four 16 drive the square box 4 to rotate 65 degrees clockwise around the pull rod one 7 and the pull rod two 8, and the steering engine one 5 and the steering engine two 6 drive the wing rod piece mechanism 3 to beat back and forth approximately, so that the forward speed during landing is reduced.
As shown in fig. 2, the tail mechanism 2 is composed of a tail clip 40, a tail mount 41, a tail center bar 42, and two tail side bars 43, the tail clip 40 is fixed to the rear fuselage support 14, the tail mount 41 is fixed to the tail clip 40, and the tail center bar 42 and the two tail side bars 43 are fixed to the tail mount 41.
Working principle: in the normal flight process of the flapping-wing aircraft, the steering engine III 25 does not work, and the steering engine I5 and the steering engine II 6 drive the wing rod piece mechanism 3 to flap up and down. In the landing process of the flapping-wing aircraft, the steering engine three 25 drives the steering engine rocker one 24 to rotate 15 degrees anticlockwise, the steering engine rocker one 24 drives the pull rod five 23 to rotate anticlockwise, the pull rod five 23 pulls the pull rod three 21 and the pull rod four 22 to move, the pull rod three 21 pulls the first hinged joint block 19 and the pull rod one 17 to move, the pull rod four 22 pulls the second hinged joint block 20 and the pull rod two 18 to move, the pull rod one 17 pulls the connecting rod three 15 to move, the pull rod two 18 pulls the connecting rod four 16 to move, the connecting rod three 15 and the connecting rod four 16 drive the square box 4 to rotate 65 degrees clockwise around the connecting rod one 7 and the connecting rod two 8, meanwhile, the steering engine one 5 and the steering engine two 6 also rotate 65 degrees clockwise, and the steering engine one 5 and the steering engine two 6 drive the wing rod mechanism 3 to beat approximately forwards and backwards, so that the forward speed of the flapping-wing aircraft is reduced, and the flapping-wing aircraft can be protected.
The foregoing is only a preferred embodiment of the present utility model, but the scope of the present utility model is not limited thereto, and any person skilled in the art, who is within the scope of the present utility model, should make equivalent substitutions or modifications according to the technical solution and the inventive concept of the present utility model, and should be covered by the scope of the present utility model.
Claims (4)
1. The utility model provides a steering wheel driven speed reduction drops flapping wing aircraft, includes fuselage (1), steering wheel one (5), steering wheel two (6), steering wheel three (25), fin mechanism (2) and wing member mechanism (3), its characterized in that: the machine body (1) consists of a square box (4), a first connecting rod (7), a second connecting rod (8), a first machine body supporting rod (9), a second machine body supporting rod (10), a third machine body supporting rod (11), a fourth machine body supporting rod (12), a front machine body supporting rod (13), a rear machine body supporting rod (14), a third connecting rod (15), a fourth connecting rod (16), a first pull rod (17), a second pull rod (18), a first hinged connecting block (19), a second hinged connecting block (20), a third pull rod (21), a fourth pull rod (22), a fifth pull rod (23), a first steering engine supporting rod (24) and a steering engine fixing frame (26), the front part of the machine body (1) is provided with the square box (4), the first steering engine (5) and the second steering engine supporting rod (6) are fixed in the square box (4), the square box (4) is connected with the first connecting rod (7) and the second connecting rod (8), one end of the first machine body supporting rod (9) penetrates through the front support (13) to be connected with the first connecting rod (7), the other end of the second machine body supporting rod is connected with the rear machine body supporting rod (14), the second machine body supporting rod (10) penetrates through the first end (13) to be connected with the front machine body supporting rod (13), the other end is connected with a rear support (14) of the machine body, one end of a fourth support rod (12) of the machine body is connected with a front support (13) of the machine body, and the other end is connected with the rear support (14) of the machine body.
2. A steering engine driven deceleration landing ornithopter according to claim 1, wherein: the square box (4) is connected with a connecting rod III (15) and a connecting rod IV (16), the connecting rod III (15) is connected with a pull rod I (17), the connecting rod IV (16) is connected with a pull rod II (18), the pull rod I (17) is connected with a first hinging and linking block (19), the pull rod II (18) is connected with a second hinging and linking block (20), the first hinging and linking block (19) is connected with a pull rod III (21), the second hinging and linking block (20) is connected with a pull rod IV (22), the pull rod III (21) and the pull rod IV (22) are fixed on a pull rod V (23), the pull rod V (23) is fixed on a steering engine rocker I (24), the steering engine rocker I (24) is connected with a steering engine III (25) rotating shaft, the steering engine III (25) is fixed by a steering engine fixing frame (26), and the steering engine fixing frame (26) is fixed on a machine body third supporting rod (11).
3. A steering engine driven deceleration landing ornithopter according to claim 1, wherein: the wing rod mechanism (3) consists of a steering engine rocker arm II (27), a wing fixing plate I (28), a wing fixing plate II (29), a wing main rod (30), a three-way valve device (31), a third hinging block (32), a fourth hinging block (33), a connecting rod five (34), a connecting rod six (35), a connecting rod seven (36), a connecting rod eight (37), a fifth hinging block (38) and a connecting rod nine (39), wherein a rotating shaft of the steering engine I (5) is connected with the steering engine rocker arm II (27), the steering engine rocker arm II (27) is connected with the wing fixing plate I (28), the wing fixing plate I (28) is connected with the wing fixing plate II (29), one end of the wing main rod (30) is fixed between the wing fixing plate I (28) and the wing fixing plate II (29), the three-way valve device (31), the third hinging block (32) and the fourth hinging block (37) are fixed on the wing main rod (30), the three-way valve device (31) has angles of 20 DEG, 40 DEG and 60 DEG, 20 DEG and 60 DEG, 60 DEG and 60 DEG, 37 DEG and 37 DEG are connected with the connecting rod eight (37), the other end of the fifth hinging block (38) is connected with a connecting rod nine (39), the other end of the connecting rod nine (39) is connected with a fourth hinging block (33), and the other half wing rod mechanisms (3) are symmetrically distributed.
4. A steering engine driven deceleration landing ornithopter according to claim 1, wherein: the tail mechanism (2) comprises a tail clamp (40), a tail fixing frame (41), a tail middle rod (42) and two tail side rods (43), wherein the tail clamp (40) is fixed on a rear support (14) of the aircraft body, the tail fixing frame (41) is fixed on the tail clamp (40), and the tail middle rod (42) and the two tail side rods (43) are fixed on the tail fixing frame (41).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322415648.2U CN220701344U (en) | 2023-09-06 | 2023-09-06 | Steering engine driven deceleration landing ornithopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322415648.2U CN220701344U (en) | 2023-09-06 | 2023-09-06 | Steering engine driven deceleration landing ornithopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220701344U true CN220701344U (en) | 2024-04-02 |
Family
ID=90439452
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322415648.2U Active CN220701344U (en) | 2023-09-06 | 2023-09-06 | Steering engine driven deceleration landing ornithopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220701344U (en) |
-
2023
- 2023-09-06 CN CN202322415648.2U patent/CN220701344U/en active Active
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