CN110481756B - Miniature aircraft with foldable rudder wings - Google Patents
Miniature aircraft with foldable rudder wings Download PDFInfo
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- CN110481756B CN110481756B CN201910795522.8A CN201910795522A CN110481756B CN 110481756 B CN110481756 B CN 110481756B CN 201910795522 A CN201910795522 A CN 201910795522A CN 110481756 B CN110481756 B CN 110481756B
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- rudder
- lock pin
- wing
- transmission shaft
- lock
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
Abstract
The invention relates to a micro aircraft with foldable rudder wings, which belongs to the field of aircraft and comprises a rudder transmission shaft (1), a torsion spring (2), a rudder wing rotating shaft (3), a pressure spring (4), a lock pin (5) and a rudder wing (6); the pressure spring (4) and the lock pin (5) are sequentially arranged in the rudder transmission shaft (1); the rudder wing (6) is connected with the rudder transmission shaft (1) through the rudder wing rotating shaft (3) and is in contact with the lock pin (5), and the rudder wing (6) can rotate around the rudder wing rotating shaft (3) and rotate along with the rudder transmission shaft (1); the two ends of the torsion spring (2) are sleeved at the two ends of the rudder wing rotating shaft (3) and are located on the outer side of the rudder transmission shaft (1), and the torsion spring can rotate around the rudder wing rotating shaft (3) under the action of external force and store energy. The miniature aircraft with the foldable rudder wings has the advantages that the folding, unfolding and locking modes of the rudder wings are simple, the locking is firm, and the problems that the traditional aircraft rudder wings cannot be folded, occupy large space and are not beneficial to flexible carrying are solved.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a miniature aircraft with foldable rudder wings.
Background
With the rapid development of modern weapons, an aircraft for individual combat is one of research hotspots, so that the requirement on the space of the aircraft is higher and higher for the convenience of individual carrying, and the rudder wing of the traditional aircraft is not foldable, occupies a larger space and is not beneficial to flexible carrying.
Disclosure of Invention
In view of the foregoing analysis, an embodiment of the present invention is directed to provide a micro aircraft with foldable rudder wings, so as to solve the problems that the existing rudder wings cannot be folded, occupy a large space, and are inconvenient to carry.
On one hand, the embodiment of the invention provides a micro aircraft with foldable rudder wings, which comprises a rudder transmission shaft, a torsion spring, a rudder wing rotating shaft, a pressure spring, a lock pin and a rudder wing; the pressure spring and the lock pin are sequentially arranged in the rudder transmission shaft; the rudder wing is connected with the rudder transmission shaft through the rudder wing rotating shaft and is in contact with the lock pin, and the rudder wing can rotate around the rudder wing rotating shaft and rotate along with the rudder transmission shaft; the two ends of the torsion spring are sleeved at the two ends of the rudder wing rotating shaft and are positioned outside the rudder transmission shaft, and the torsion spring can rotate around the rudder wing rotating shaft and store energy under the action of external force.
Furthermore, a lock head is arranged on the lock pin, a lock opening is formed in the rudder wing, the lock head is matched with the size, shape and position of the lock opening, and when the rudder wing is in an unfolding and locking state, the lock head is locked in the lock opening.
Furthermore, the opposite side of the lock head and the lock opening is provided with an arc plane and a flat plane, so that the rudder wing can be folded towards the rudder transmission shaft towards one direction only.
Further, two bearings are mounted at one end of the rudder rotating shaft, a platform, an upper plate and a lower plate are arranged at the other end of the rudder rotating shaft, and the upper plate and the lower plate are arranged on the platform in parallel and are perpendicular to the platform;
a notch for enabling one end of the rudder wing to rotate around the rudder wing rotating shaft is formed between the upper plate and the lower plate;
through holes are respectively formed in the positions, corresponding to the upper plate and the lower plate, of the upper plate, and the rudder wing rotating shaft penetrates through the two through holes and is installed on the rudder transmission shaft;
the slot hole for installing the pressure spring and the lock pin is arranged at the center of the platform and passes through the notch in a straight way.
Furthermore, the aperture of the slotted hole is larger than the aperture of the slotted hole, grooves are formed in the corresponding positions of the upper plate and the lower plate, and the position shape of each groove is matched with the position shape of the slotted hole.
Furthermore, the pressure spring and the lock pin are sequentially arranged in the slotted hole, the pressure spring and the lock pin have the same diameter a, the aperture of the slotted hole is b, and b is larger than or equal to a.
Furthermore, one end of the lock pin is in contact with the pressure spring, the other end of the lock pin is provided with a protruding lock head, and the side surface of the lock pin is provided with a sliding groove;
a first threaded hole which is perpendicular to the slotted hole and communicated with the slotted hole is formed in the side face of the platform, the lock pin screw penetrates through the first threaded hole and extends into the sliding groove, and the lock pin can slide along the axis of the slotted hole through the matching of the lock pin screw and the sliding groove;
the lock head comprises a straight surface and an arc surface which are oppositely arranged, the straight surface is a plane which is vertical to the end surface of the lock pin, and the arc surface is an arc surface which is transited from the arc shape of the top end of the lock head to the side surface of the lock pin.
Furthermore, the rudder wing comprises a wing surface and a connecting end, a rotating hole is formed in the connecting end, and the rotating shaft of the rudder wing sequentially penetrates through the through hole of the upper plate, the rotating hole and the through hole of the lower plate, so that the rudder wing is in shaft connection with the rudder transmission shaft; the end face of the connecting end is provided with an inwards concave locking notch, and the locking notch is matched with the shape and the size of the lock head of the lock pin.
Furthermore, the torsion spring comprises two fixed rings, two rotating rings and a clamping action part, and two ends of the clamping action part are sequentially connected with the rotating rings and the fixed rings;
two rotating rings are respectively sleeved at two ends of the rudder wing rotating shaft, and two fixing rings are detachably mounted at two opposite sides of the rudder transmission shaft, so that the clamping action part can be clamped at the joint of the rudder transmission shaft and the rudder wing.
Further, the fixed ring is detachably mounted on the rudder transmission shaft through a locking screw.
The invention has the beneficial effects that: the rudder wing of the micro aircraft is connected with the rudder transmission shaft through the rudder wing rotating shaft, so that the rudder wing can be folded towards the direction of the rudder transmission shaft; the rudder wing can be automatically locked after being unfolded under the action of the pressure spring, the torsion spring and the like by arranging the pressure spring and the lock pin in the rudder transmission shaft and arranging the torsion spring at the joint of the rudder transmission shaft and the rudder wing; the miniature aircraft with the foldable rudder wings disclosed by the embodiment of the invention has the advantages that the folding, unfolding and locking modes of the rudder wings are simple, the locking is firm, and the problems that the rudder wings of the traditional aircraft cannot be folded, the occupied space is large, and the traditional aircraft is not convenient to flexibly carry are solved.
In the invention, the technical schemes can be combined with each other to realize more preferable combination schemes. Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, wherein like reference numerals are used to designate like parts throughout.
FIG. 1 is an exploded view of a rudder wing, a rudder propeller shaft and their connecting parts;
FIG. 2 is a schematic view of the unfolded state of the rudder wings;
FIG. 3 is a schematic view of a folded state of a rudder wing;
fig. 4 is a schematic view of the folding and locking state of all the rudder wings of the micro aircraft.
Reference numerals:
1-rudder transmission shaft; 11-a first bearing; 12-a second bearing; 13-a platform; 14-upper plate; 15-lower plate; 16-notches; 17-a through hole; 18-slotted holes; 19-a first threaded hole; 10-a second threaded hole; 2-torsion spring; 21-a fixed ring; 22-a rotating ring; 23-a clamping action portion; 231-a force-bearing surface; 24-locking screws; 3-rudder wing rotating shaft; 4-pressure spring; 5-a lock pin; 51-a lock head; 511-straight side; 512-cambered surface; 52-a chute; 53-lockpin screws; 6-rudder wing; 61-control surface; 62-a connection end; 621-rotation hole; 622-locking notch; 623-arc surface; 63-rudder wing acting surface; 7-locking device.
Detailed Description
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate preferred embodiments of the invention and together with the description, serve to explain the principles of the invention and not to limit the scope of the invention.
The invention discloses a micro aircraft with foldable rudder wings, which comprises a rudder transmission shaft 1, a torsion spring 2, a rudder wing rotating shaft 3, a pressure spring 4, a lock pin 5 and a rudder wing 6, wherein the pressure spring 4 and the lock pin 5 are sequentially arranged in the rudder transmission shaft 1, the rudder wing 6 is connected with the rudder transmission shaft 1 through the rudder wing rotating shaft 3 and is in contact with the lock pin 5, so that the rudder wing 6 can rotate around the rudder wing rotating shaft 3 and rotate along with the rudder transmission shaft 1, the folding and unfolding actions of the rudder wing are realized, the lock pin 5 can be pressed when the rudder wing 6 rotates, and the lock pin 5 further presses the pressure spring 4, so that the pressure spring stores energy; the two ends of the torsion spring 2 are sleeved at the two ends of the rudder wing rotating shaft 3 and are positioned outside the rudder transmission shaft 1, and the torsion spring can rotate around the rudder wing rotating shaft 3 and store energy under the action of external force.
Two bearings are installed to the one end of rudder axis of rotation 1, are first bearing 11 and second bearing 12 respectively, and through the cooperation of first bearing 11, second bearing 12, the realization rudder transmission shaft 1 can be around the axle center stable rotation of first bearing 11, second bearing 12.
The other end of the rudder transmission shaft 1 comprises a platform 13, an upper plate 14 and a lower plate 15, the upper plate 14 and the lower plate 15 are arranged on the platform 13 in parallel and are perpendicular to the platform 13, and a notch 16 for allowing one end of the rudder wing 6 to rotate around the rudder wing rotating shaft 3 is formed between the upper plate 14 and the lower plate 15; through holes 17 are respectively formed in the positions, opposite to the upper plate 14 and the lower plate 15, of the rudder wing rotating shaft 3, and the rudder wing rotating shaft 3 penetrates through the two through holes 17 and is installed on the rudder transmission shaft 1; a slotted hole 18 for installing the pressure spring 4 and the lock pin 5 is formed in the center of the platform 13 and penetrates through the slotted hole 16 in a straight mode, in the embodiment, the aperture of the slotted hole 18 is larger than the aperture of the slotted hole 16, namely, the aperture is larger than the distance between the upper plate 14 and the lower plate 15, therefore, grooves are formed in corresponding positions of the upper plate 14 and the lower plate 15, and the position shape of each groove is matched with the position shape of the slotted hole 18. In this embodiment, the rudder propeller shaft 1 is integrally formed, that is, the platform 13, the upper plate 14 and the lower plate 15 are integrally formed, the platform 13 is a circular truncated cone, and the notch 16 is perpendicular to the radial direction of the circular truncated cone.
The pressure spring 4 and the lock pin 5 are sequentially installed in the slot hole 18, the pressure spring 4 and the lock pin 5 have the same diameter a, the aperture b of the slot hole 18 is not smaller than the diameter a, in the embodiment, the aperture b is equal to the diameter a, so that the pressure spring 4 and the lock pin 5 can be better and vertically compressed, and are not easy to be pressed askew, and the folding, compressing and popping of the rudder wing are affected.
One end of the lock pin 5 is used for compressing the pressure spring, the other end of the lock pin is provided with a convex lock head 51, and the side surface of the lock pin 5 is provided with a sliding groove 52. A first threaded hole 19 which is perpendicular to the slotted hole 18 and communicated with the slotted hole 18 is formed in the side face of the platform 13, a lock pin screw 53 penetrates through the first threaded hole 19 and extends into the sliding groove 52, the lock pin 5 can slide along the axis of the slotted hole 18 through the matching of the lock pin screw 53 and the sliding groove 52, the rudder wing can compress the pressure spring 4 to different degrees through the lock pin 5, and in addition, the lock pin screw 53 can also prevent the lock pin 5 from popping out. The convex lock head 51 comprises a straight surface 511 and an arc surface 512 which are oppositely arranged, wherein the straight surface 511 is a plane perpendicular to the end surface of the lock pin 5, and the arc surface 512 is an arc surface which is in arc transition from the top end of the lock head 51 to the side surface of the lock pin 5.
The rudder wing 6 comprises a wing surface 61 and a connecting end 62, the wing surface 61 and the connecting end 62 are integrally formed, a rotating hole 621 is formed in the connecting end 62, the connecting end 62 of the rudder wing 6 is inserted into the notch 16 of the rudder transmission shaft 1, so that the rotating hole 621 and the through hole 17 are coaxial, and the rudder wing rotating shaft 3 sequentially passes through the through hole → the rotating hole 621 → the through hole in the upper plate 14 and the through hole in the lower plate 15, so that the rudder wing 6 and the rudder transmission shaft 1 are in shaft connection. The terminal surface of link 62 has seted up indent fore shaft 622, the position shape size looks adaptation of fore shaft 622 and the tapered end 51 of lockpin 5 realizes the closure, and the fore shaft 622 also includes relative interior straight surface and the intrados that sets up, and wherein, interior straight surface is perpendicular with link 62 terminal surface, and the intrados passes through to link 62 terminal surface from fore shaft 622 mouth bottom arc, and the link 62 terminal surface that meets with the intrados is arc surface 623, and arc surface 623 is the cambered surface that passes through to link 62 side from fore shaft intrados department arc that meets. In the present embodiment, the width of the airfoil 61 is larger than the width of the connecting end 62, and one side is aligned to form the long side of the rudder wing 6, and the other side is not aligned, and the side of the connecting end 62 is arc-shaped to transition to the side of the airfoil 61, and the arc-shaped transition surface is called as a rudder wing action surface 63.
The torsion spring 2 comprises two fixed rings 21, two rotating rings 22 and a clamping action part 23, two ends of the clamping action part 23 are sequentially connected with the rotating rings 22 and the fixed rings 21, and the torsion spring 2 is integrally formed; the two rotating rings 22 are respectively sleeved at two ends of the rudder wing rotating shaft 3, the two fixing rings 21 are fixed at two opposite sides of the platform 13, so that the clamping action part 23 can be clamped at the joint of the rudder transmission shaft 1 and the rudder wing 6, the stress surface 231 of the clamping action part 23 is contacted with the rudder wing action surface 63, and the torsion spring 2 can rotate around the rudder wing rotating shaft 3 and store energy under the action of external force. In this embodiment, the fixing ring 21 is detachably mounted on the platform 13 through the locking screw 24, the platform 13 is provided with the second threaded hole 10 for mounting the locking screw 24, and in practical application, the fixing ring 21 can also be detachably mounted on the platform 13 through a buckle, a hook, a stud and other components.
A miniature aircraft with foldable rudder wings is disclosed, wherein the mounting process of the foldable rudder wings comprises the following steps: sequentially plugging a pressure spring 4 and a lock pin 5 into a slotted hole 18 of a rudder transmission shaft 1, and aligning the direction of a sliding groove 52 of the lock pin 5 with the position of a first threaded hole 19; inserting the locking pin screw 53 into the first threaded hole 19 and into the slide groove 52; the connecting end 61 of the rudder wing 6 is inserted into the notch 16 of the rudder transmission shaft 1, the through hole 17 is coaxial with the rotating hole 621, and the lock head 51 of the lock pin 52 is inserted into the lock notch 622 for locking; the rudder wing rotating shaft 3 passes through the through hole → the rotating hole 621 → the through hole on the lower plate 15 on the upper plate 14, so that the rudder wing 6 and the rudder transmission shaft 1 are in shaft connection; the two rotating rings 22 of the torsion spring 2 are respectively sleeved at two ends of the rudder wing rotating shaft 3, the two fixing rings 21 are locked in the second threaded holes 10 by using locking screws 24, the clamping action part 23 is clamped at the joint of the rudder transmission shaft 1 and the rudder wing 6, and the stress surface 231 of the clamping action part 23 is contacted with the rudder wing action surface 63; the assembled rudder wing is in a unfolded state.
The folding process of the rudder wing: under the action of a large enough external force, the rudder wing 6 rotates around the rudder transmission shaft 1, the lock head 51 rotates out of the lock opening 622 under the matching of the cambered surface 512 and the inner cambered surface of the lock opening 622, the lock opening 622 is unlocked from the lock head 51, the rudder wing 6 continues to rotate, the lock pin 5 is continuously pressed in the rotation process of the connecting end 62, the lock pin 5 presses the pressure spring 4, meanwhile, the wing surface acting surface 63 continuously applies force to the stressed surface of the clamping acting part 23 in the rotation process, the torsion spring 2 is in a torsion state, energy is stored, and after the rudder wing 6 rotates to be vertical to the rudder transmission shaft 1, all the rudder wings are locked together by the locking device 7, so that all the rudder wings of the micro aircraft are folded, the occupied space is saved, and the carrying is convenient. Therefore, when the rudder wing is in a folded state, the pressure spring is in a compressed state, the torsion spring is in a twisted state, and the pressure spring and the torsion spring store certain energy for use when the rudder wing automatically pops open.
The automatic unfolding process of the rudder wing: after the locking device 7 is taken away, the rudder wing 6 rotates around the rudder transmission shaft 1 under the action of the torsion spring 2, meanwhile, the outward elasticity of the compression spring 4 accelerates the unfolding speed of the rudder wing 6, when the rudder wing rotates to a certain position, the arc surface 623 contacts with the arc surface 512 of the lock head 51, the lock head 51 gradually rotates into the lock opening 622 under the matching of the arc surface of the lock head 51, the rudder wing 6 continues to rotate until the straight surface 511 of the lock head 51 contacts with the straight surface in the lock opening 622 to form a right-angle lock, the rudder wing 6 cannot rotate along the original direction, at the moment, the rudder wing 6 and the rudder transmission shaft 1 are on the same straight line, the automatic unfolding of the rudder wing 6 under the action force of the torsion spring 2 and the compression spring 4 is realized, the locking of the lock head 51 and the lock opening 622 realizes the locking of the rudder wing 6 on the rudder transmission shaft 1, and no large external force exists, the lock head 51 and the lock opening 622.
It should be noted that, in this embodiment, the unfolded rudder wing can resist the flight resistance in the flight process under the action of the torsion spring, the lock pin and the pressure spring, that is, in the flight process, the rudder wing is not folded under the action of the flight resistance, so that the flight of the micro aircraft is affected, and the aircraft is broken, crashed and the like. The "sufficiently large external force" is at least greater than the maximum flight resistance that the micro-aircraft will encounter during flight.
It should be noted that, in this embodiment, the lock 51 is designed to have an arc surface and a straight surface, and a lock 622 adapted to the lock, an inner straight surface and an inner arc surface, so that the rudder wing can be automatically unfolded and locked, and the rudder wing 6 can be folded toward the rudder transmission shaft 1 only in one direction, that is, the direction of the arc surface is located, and the rudder wing 6 and the rudder transmission shaft 1 are exactly locked when being on the same straight line, thereby avoiding the situation that the rudder wing 6 needs to be manually adjusted in a reverse direction after passing through in the unfolding process.
It should be noted that the locking device 7 in this embodiment is used to lock the folded rudder wings together, and in practical applications, the locking device 7 with a specific structure may be specially used, or a simple binding device such as a rope, a bandage, a sleeve, etc. may be used to bind the folded rudder wings together.
The utility model provides a miniature aircraft that rudder wing is folding, its rudder wing can be folded to rudder transmission shaft direction, under the effect of pressure spring, torsional spring etc. the rudder wing can expand the back and can lock automatically, and it is folding, expand, the locking mode is simple, and locking is firm, has solved traditional aircraft rudder wing can not fold, occupation space is great, be unfavorable for the problem of nimble carrying.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Claims (8)
1. A micro aircraft with foldable rudder wings is characterized by comprising a rudder transmission shaft (1), a torsion spring (2), a rudder wing rotating shaft (3), a compression spring (4), a lock pin (5) and a rudder wing (6);
the pressure spring (4) and the lock pin (5) are sequentially arranged in the rudder transmission shaft (1);
the rudder wing (6) is connected with the rudder transmission shaft (1) through the rudder wing rotating shaft (3) and is in contact with the lock pin (5), and the rudder wing (6) can rotate around the rudder wing rotating shaft (3) and rotate along with the rudder transmission shaft (1);
the two ends of the torsion spring (2) are sleeved at the two ends of the rudder wing rotating shaft (3) and are positioned outside the rudder transmission shaft (1), and the torsion spring can rotate around the rudder wing rotating shaft (3) under the action of external force and store energy;
the lock pin (5) is provided with a lock head (51), the rudder wing (6) is provided with a lock opening (622), the lock head (51) is matched with the size, shape and position of the lock opening (622), and when the rudder wing (6) is in an unfolding and locking state, the lock head (51) is locked in the lock opening (622);
the opposite side of the lock head (51) and the lock opening (622) is provided with an arc plane and a flat plane, so that the rudder wing (6) can be folded towards the rudder transmission shaft (1) only in one direction;
the lock head (51) comprises a straight surface (511) and an arc surface (512) which are oppositely arranged, the straight surface (511) is a plane perpendicular to the end surface of the lock pin (5), and the arc surface (512) is an arc surface which is in arc transition from the top end of the lock head (51) to the side surface of the lock pin (5).
2. Micro aircraft with foldable rudder wings according to claim 1, characterized in that the rudder propeller shaft (1) has two bearings mounted at one end and a platform (13), an upper plate (14) and a lower plate (15) at the other end, the upper plate (14) and the lower plate (15) are arranged parallel to each other on the platform (13) and perpendicular to the platform (13);
a notch (16) for enabling one end of the rudder wing (6) to rotate around the rudder wing rotating shaft (3) is formed between the upper plate (14) and the lower plate (15);
through holes (17) are respectively formed in the opposite positions of the upper plate (14) and the lower plate (15), and the rudder wing rotating shaft (3) penetrates through the two through holes (17) to be installed on the rudder transmission shaft (1);
a slotted hole (18) for installing the pressure spring (4) and the lock pin (5) is arranged at the center of the platform (13) and directly penetrates through the notch (16).
3. The miniature aircraft with foldable rudder wings as claimed in claim 2, wherein the aperture of the slot (18) is larger than the aperture of the notch (16), and grooves are formed in the corresponding positions of the upper plate (14) and the lower plate (15), and the positions and the shapes of the grooves are matched with those of the slot (18).
4. The micro aircraft with foldable rudder wings as claimed in claim 2, wherein the compression spring (4) and the lock pin (5) are sequentially installed in the slot (18), the compression spring (4) and the lock pin (5) have the same diameter a, the aperture of the slot (18) is b, and b is greater than or equal to a.
5. The micro aircraft with foldable rudder wings as claimed in claim 2, wherein one end of the lock pin (5) is in contact with the pressure spring (4), the other end of the lock pin is provided with a convex lock head (51), and the side surface of the lock pin (5) is provided with a sliding groove (52);
a first threaded hole (19) which is perpendicular to the slotted hole (18) and communicated with the slotted hole (18) is formed in the side face of the platform (13), a lock pin screw (53) penetrates through the first threaded hole (19) to extend into the sliding groove (52), and the lock pin (5) can slide along the axis of the slotted hole (18) through the matching of the lock pin screw (53) and the sliding groove (52).
6. The micro aircraft with foldable rudder wings according to claim 5, wherein the rudder wing (6) comprises an airfoil surface (61) and a connecting end (62), a rotating hole (621) is formed in the connecting end (62), and the rudder wing rotating shaft (3) sequentially passes through a through hole (17) of the upper plate (14), the rotating hole (621) and a through hole (17) of the lower plate (15) so that the rudder wing (6) is in shaft connection with the rudder transmission shaft (1); the end face of the connecting end (62) is provided with a concave locking notch (622), and the locking notch (622) is matched with the shape and the size of the lock head (51) of the lock pin (5).
7. The miniature aircraft with foldable rudder wings as claimed in any one of claims 1 to 6, wherein the torsion spring (2) comprises two fixed rings (21), two rotating rings (22) and a clamping action part (23), and two ends of the clamping action part (23) are connected with the rotating rings (22) and the fixed rings (21) in sequence;
two rotating rings (22) are respectively sleeved at two ends of the rudder wing rotating shaft (3), and two fixing rings (21) are detachably mounted on two opposite sides of the rudder transmission shaft (1), so that a clamping action part (23) can be clamped at the joint of the rudder transmission shaft (1) and the rudder wing (6).
8. Micro-aircraft with foldable rudder wings according to claim 7, characterised in that the fixing ring (21) is detachably mounted on the rudder propeller shaft (1) by means of locking screws (24).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910795522.8A CN110481756B (en) | 2019-08-26 | 2019-08-26 | Miniature aircraft with foldable rudder wings |
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| CN201910795522.8A CN110481756B (en) | 2019-08-26 | 2019-08-26 | Miniature aircraft with foldable rudder wings |
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| CN110481756A CN110481756A (en) | 2019-11-22 |
| CN110481756B true CN110481756B (en) | 2021-04-20 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111114754B (en) * | 2019-12-31 | 2021-06-22 | 北京机电工程研究所 | Locking mechanism and folding airfoil with same |
| CN111306996B (en) * | 2020-01-23 | 2022-07-05 | 西安现代控制技术研究所 | Ammunition flight resistance device |
| CN114216647A (en) * | 2021-12-16 | 2022-03-22 | 中国航天空气动力技术研究院 | Rudder wing transient unfolding and folding device for wind tunnel test |
| CN114485287B (en) * | 2021-12-30 | 2023-11-07 | 北京动力机械研究所 | Self-locking bearing structure of folding rudder |
| CN114812294A (en) * | 2022-03-02 | 2022-07-29 | 武汉高德红外股份有限公司 | High-overload-resistant electric steering engine with telescopic wings |
| CN114562918A (en) * | 2022-03-25 | 2022-05-31 | 西安雷神防务技术有限公司 | Miniature electric folding steering engine |
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| CN103707090A (en) * | 2013-12-26 | 2014-04-09 | 无锡市贝斯特精密机械有限公司 | Elastic locating mechanism |
| CN109000521A (en) * | 2018-07-24 | 2018-12-14 | 湖北泰和电气有限公司 | Rudder wingfold device, micro missile and rudder wingfold method |
| CN109649637A (en) * | 2018-12-05 | 2019-04-19 | 兰州飞行控制有限责任公司 | A kind of self-locking steering engine |
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| CN110481756A (en) | 2019-11-22 |
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