CN110481756A - A kind of folding minute vehicle of the rudder wing - Google Patents

Abstract

The invention relates to a micro-aircraft with a foldable rudder wing, which belongs to the field of aircraft, and comprises a rudder drive shaft (1), a torsion spring (2), a rudder wing shaft (3), a compression spring (4), and a lock pin (5) and the rudder wing (6); the compression spring (4) and the lock pin (5) are installed in the rudder drive shaft (1) in sequence; the rudder wing (6) is connected with the rudder drive shaft (1) through the rudder wing shaft (3), And be in contact with the lock pin (5), the rudder wing (6) can rotate around the rudder wing shaft (3), and rotate with the rudder transmission shaft (1); the two ends of the torsion spring (2) are sleeved on the rudder wing shaft (3) ) and located outside the rudder transmission shaft (1), the torsion spring can rotate around the rudder wing shaft (3) under the action of an external force and store energy. A micro-aircraft with foldable rudder wings has simple folding, unfolding and locking methods for the rudder wings and firm locking, which solves the problems that the rudder wings of traditional aircraft cannot be folded, takes up a large space, and is not conducive to flexible portability.

Description

A micro-aircraft with foldable rudder wings

technical field

The invention relates to the technical field of aircraft, in particular to a micro-aircraft with foldable rudder wings.

Background technique

With the rapid development of modern weapons, aircraft used for individual combat is one of the research hotspots. In order to be convenient for individual soldiers to carry, the space requirements for aircraft are getting higher and higher. However, the rudder wings of traditional aircraft are not foldable and take up a lot of space. , is not conducive to flexible portability.

Contents of the invention

In view of the above analysis, the embodiment of the present invention aims to provide a micro-aircraft with foldable rudder blades to solve the problems that the existing rudder blades cannot be folded, occupy a large space, and are inconvenient to carry.

On the one hand, the embodiment of the present invention provides a micro-aircraft with foldable rudder wings, which includes a rudder transmission shaft, a torsion spring, a rudder wing shaft, a compression spring, a locking pin and a rudder wing; the compression spring and the locking pin are installed on the rudder in turn In the drive shaft; the rudder wing is connected with the rudder drive shaft through the rudder wing shaft and is in contact with the lock pin, the rudder wing can rotate around the rudder wing shaft and rotate with the rudder drive shaft; the two ends of the torsion spring are sleeved on both sides of the rudder wing shaft end, and located outside the rudder transmission shaft, the torsion spring can rotate around the rudder wing shaft and store energy under the action of external force.

Further, the lock pin is provided with a lock head, and the rudder wing is provided with a lock mouth, and the lock head matches the size, shape and position of the lock mouth. When the rudder wing is in the unfolded and locked state, the lock head is locked in the lock. In the mouth.

Further, the lock head is provided with an arc surface and a straight surface on the side opposite to the lock opening, so that the rudder wing can only be folded towards the rudder transmission shaft in one direction.

Further, one end of the rudder rotating shaft is equipped with two bearings, and the other end is provided with a platform, an upper plate and a lower plate, and the upper plate and the lower plate are arranged on the platform parallel to each other and perpendicular to the platform;

A notch for one end of the rudder blade to rotate around the rotation axis of the rudder blade is formed between the upper plate and the lower plate;

There are through holes respectively opened at the relative positions of the upper plate and the lower plate, and the rudder wing shaft passes through the two through holes and is installed on the rudder transmission shaft;

Go straight through the notch and provide a slotted hole for installing stage clips and locking pins at the center of the platform.

Further, the aperture of the slot hole is larger than the aperture of the slot opening, grooves are opened at corresponding positions of the upper plate and the lower plate, and the position and shape of the groove match the position and shape of the slot hole.

Further, the compression spring and the locking pin are sequentially installed in the slot, the compression spring and the locking pin have the same diameter a, the diameter of the slot is b, and b≥a.

Further, one end of the lock pin is in contact with the pressure spring, the other end is provided with a raised lock head, and a chute is provided on the side of the lock pin;

On the side of the platform, there is a first threaded hole that is perpendicular to the slot hole and communicates with the slot hole. The locking pin screw extends into the chute through the first threaded hole, and through the cooperation of the locking pin screw and the chute, Enables the locking pin to slide along the axis of the slot;

The lock head includes a straight face and an arc surface arranged oppositely. The straight face is a plane perpendicular to the end face of the lock pin, and the arc surface is a circular arc surface that transitions from the top of the lock head to the side of the lock pin in an arc shape.

Further, the rudder wing includes an airfoil and a connecting end, and a turning hole is provided on the connecting end, and the rotating shaft of the rudder wing passes through the through hole of the upper plate, the turning hole, and the through hole of the lower plate in sequence, so that the rudder wing and the rudder drive The shaft realizes the axial connection; the end surface of the connecting end is provided with a concave locking opening, and the locking opening is adapted to the shape and size of the lock head of the locking pin.

Further, the torsion spring includes two fixed rings, two rotating rings and a clamping part, and the two ends of the clamping part are sequentially connected with the rotating ring and the fixed ring;

The two rotating rings are sleeved on the two ends of the rudder wing shaft respectively, and the two fixing rings are detachably installed on opposite sides of the rudder transmission shaft, so that the clamping part can be clamped at the joint between the rudder transmission shaft and the rudder wing.

Further, the fixing ring is detachably mounted on the rudder drive shaft through locking screws.

The invention has beneficial effects: the rudder wing of the micro-aircraft is connected with the rudder drive shaft through the rudder wing shaft, so that the rudder wing can be folded toward the rudder drive shaft; A torsion spring is arranged at the joint of the wing, so that the rudder wing can be automatically locked after being unfolded under the action of a compression spring, a torsion spring, etc.; The locking method is simple and the locking is firm, which solves the problems that the traditional aircraft rudder wing cannot be folded, occupies a large space, and is not conducive to flexible carrying.

In the present invention, the above technical solutions can also be combined with each other to realize more preferred combination solutions. Additional features and advantages of the invention will be set forth in the description which follows, and some of the advantages will be apparent 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 matter particularly pointed out in the written description and appended drawings.

Description of drawings

The drawings are for the purpose of illustrating specific embodiments only and are not to be considered as limitations of the invention, and like reference numerals refer to like parts throughout the drawings.

Fig. 1 is the explosion diagram of rudder wing, rudder drive shaft and connecting parts thereof;

Figure 2 is a schematic diagram of the rudder wing unfolded state;

Figure 3 is a schematic diagram of the folded state of the rudder wing;

Fig. 4 is a schematic diagram of the folded and locked state of all the rudder wings of the MAV.

Reference signs:

1-rudder transmission shaft; 11-first bearing; 12-second bearing; 13-platform; 14-upper plate; 15-lower plate; 16-notch; 17-through hole; 18-slot hole; 1-threaded hole; 10-second threaded hole; 2-torsion spring; 21-fixed ring; 22-rotating ring; ;4-pressure spring; 5-lock pin; 51-lock head; 511-straight face; 512-curved surface; 52-chute; 53-lock pin screw; ; 621-turning hole; 622-lock mouth; 623-arc surface; 63-rudder wing action surface; 7-locking device.

Detailed ways

Preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the application and together with the embodiments of the present invention are used to explain the principle of the present invention and are not intended to limit the scope of the present invention.

A specific embodiment of the present invention, as shown in Figures 1-4, discloses a micro-aircraft with foldable rudder wings, including a rudder transmission shaft 1, a torsion spring 2, a rudder wing shaft 3, a compression spring 4, and a lock pin 5 and the rudder wing 6, wherein the compression spring 4 and the lock pin 5 are successively installed in the rudder drive shaft 1, the rudder wing 6 is connected with the rudder drive 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 shaft 3 and rotate with the rudder transmission shaft 1, so that the rudder wing can be folded and unfolded. When the rudder wing 6 rotates, it can press the lock pin 5, and the lock pin 5 can then press the compression spring 4, so that The compression spring stores energy; the two ends of the torsion spring 2 are sleeved on the two ends of the rudder wing shaft 3, and are located outside the rudder transmission shaft 1, and the torsion spring can rotate around the rudder wing shaft 3 under the action of an external force and store energy.

One end of the rudder rotating shaft 1 is equipped with two bearings, which are respectively the first bearing 11 and the second bearing 12. Through the cooperation of the first bearing 11 and the second bearing 12, the rudder transmission shaft 1 can be wound around the first bearing 11 and the second bearing. The shaft center of the second bearing 12 rotates stably.

The other end of rudder transmission shaft 1 comprises platform 13, upper plate 14 and lower plate 15, upper plate 14 and lower plate 15 are arranged on platform 13 parallel to each other, and perpendicular to platform 13, form between upper plate 14 and lower plate 15 A notch 16 for one end of the rudder wing 6 to rotate around the rudder wing shaft 3; a through hole 17 is respectively opened at the relative positions of the upper plate 14 and the lower plate 15, and the rudder wing shaft 3 passes through the two through holes 17 and is installed on the rudder transmission shaft 1; go straight through the notch 16 and open a slot 18 for installing the clip spring 4 and the lock pin 5 at the center of the platform 13. The distance between the plate 14 and the lower plate 15 is therefore provided with grooves at the corresponding positions of the upper plate 14 and the lower plate 15 , and the position and shape of the grooves are adapted to the position and shape of the slot hole 18 . In this embodiment, the rudder transmission 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 platform, and the notch 16 is perpendicular to the radial direction of the circular platform.

Stage clip 4, locking pin 5 are installed in the slotted hole 18 successively, and stage clip 4, locking pin 5 have identical diameter a, and the aperture b of slotted hole 18 is not less than diameter a, and in the present embodiment, aperture b=diameter a , so that the compression spring 4 and the lock pin 5 can be pressed vertically better, and they are not easy to be crooked, which affects the folding, compression and ejection of the rudder wing.

One end of the lock pin 5 is used to compress the compression spring, the other end is provided with a protruding lock head 51 , and a slide groove 52 is provided on the side of the lock pin 5 . On the side of the platform 13, there is a first threaded hole 19 which is perpendicular to the slotted hole 18 and communicates with the slotted hole 18. The locking pin screw 53 passes through the first threaded hole 19 and stretches into the chute 52. The cooperation of the slot 52 can make the locking pin 5 slide along the axis of the slot hole 18, so that the rudder blade can press the compression spring 4 to different degrees through the locking pin 5. In addition, the locking pin screw 53 can also prevent the locking pin 5 from popping out. The raised lock head 51 includes a straight face 511 and an arc surface 512 oppositely arranged. The straight face 511 is a plane perpendicular to the end face of the lock pin 5, and the arc face 512 is an arc transitioning from the top end of the lock head 51 to the side of the lock pin 5 in an arc shape. noodle.

Rudder wing 6 comprises airfoil 61 and connection end 62, and airfoil 61 and connection end 62 are integrally formed, and connection end 62 is provided with turning hole 621, and rudder wing 6 connection end 62 is inserted in the notch 16 of rudder transmission shaft 1, makes The rotation hole 621 is coaxial with the through hole 17, and the rudder wing shaft 3 passes through the through hole on the upper plate 14 → the rotation hole 621 → the through hole on the lower plate 15 in turn, so that the rudder wing 6 and the rudder drive shaft 1 are axially connected. . The end face of the connection end 62 is provided with a recessed locking notch 622, and the locking notch 622 is adapted to the position, shape and size of the lock head 51 of the lock pin 5 to realize locking, that is, the locking notch 622 also includes an inner straight surface and an inner arc arranged oppositely. Surface, wherein, the inner straight surface is perpendicular to the end face of the connecting end 62, the inner arc surface is arc-shaped transition from the bottom of the lock mouth 622 to the end face of the connecting end 62, and the end face of the connecting end 62 connected with the inner arc surface is an arc surface 623, the arc The surface 623 is an arcuate transition from the junction of the inner arcuate surfaces of the locking opening to the side of the connecting end 62 in an arc shape. In this embodiment, the width of the airfoil 61 is greater 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 cannot be aligned, and the side of the connecting end 62 is arc-shaped to transition to the airfoil. 61 side, this arc-shaped transition surface is called the rudder blade action surface 63.

The torsion spring 2 comprises two fixed rings 21, two rotating rings 22 and a clamping action part 23, and the two ends of the clamping action part 23 are connected with the rotating ring 22 and the fixing ring 21 successively, and the torsion spring 2 is integrally formed; The rotating rings 22 are respectively sleeved on the two ends of the rudder wing shaft 3, and the two fixed rings 21 are fixed on opposite sides of the platform 13, so that the clamping part 23 can be clamped at the joint between the rudder transmission shaft 1 and the rudder wing 6, The force receiving surface 231 of the clamping action portion 23 is in contact with the rudder wing action surface 63 , and the torsion spring 2 can rotate around the rudder wing shaft 3 under the action of an external force and store energy. In this embodiment, the fixing ring 21 is detachably mounted on the platform 13 through the locking screw 24, and the platform 13 is provided with a second threaded hole 10 for installing the locking screw 24. In practical applications, the fixing ring 21 can also be It can be detachably installed on the platform 13 through buckles, hooks, studs and other components.

A micro-aircraft with foldable rudder wings. The installation process of the folded rudder wings is as follows: insert the compression spring 4 and the lock pin 5 into the slot 18 of the rudder drive shaft 1 in sequence, and align the direction of the chute 52 of the lock pin 5 with the first The position of a threaded hole 19 is aligned; the locking pin screw 53 is inserted into the first threaded hole 19 and extends into the chute 52; the connecting end 61 of the rudder wing 6 is inserted into the notch 16 of the rudder drive shaft 1, and the The through hole 17 is coaxial with the rotation hole 621, and the lock head 51 of the lock pin 52 is inserted into the lock opening 622 for locking; the rudder wing shaft 3 passes through the through hole on the upper plate 14 → the rotation hole 621 → the through hole on the lower plate 15 , so that the rudder wing 6 and the rudder transmission shaft 1 are connected axially; the two rotating rings 22 of the torsion spring 2 are partially sleeved on the two ends of the rudder wing rotating shaft 3, and the two fixing rings 21 are locked with locking screws 24 at the second In the two threaded holes 10, the clamping action part 23 is clamped at the joint between the rudder transmission shaft 1 and the rudder wing 6, and the force surface 231 of the clamping action part 23 is in contact with the rudder wing action surface 63; the assembled rudder The wings are unfolded.

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, and the lock head 51 rotates out of the lock hole 622 under the cooperation of the arc surface 512 and the inner arc surface of the lock opening 622. The lock 622 and the lock head 51 are unlocked, the rudder wing 6 continues to rotate, the connecting end 62 constantly compresses the lock pin 5 during the rotation process, and the lock pin 5 compresses the compression spring 4. At the same time, the wing surface 63 constantly rotates The force-bearing surface of the clamping action part 23 exerts force so that the torsion spring 2 is in a twisted state to store energy. After the rudder blade 6 is turned to be perpendicular to the rudder drive shaft 1, all the rudder blades are locked together with the locking device 7 to realize In order to fold all the rudder wings of the micro air vehicle, it saves the occupied space and is easy to carry. Therefore, when the rudder wing is in the folded state, the compression spring is in the compressed state, and the torsion spring is in the torsion state. Both the compression spring and the torsion spring have stored a certain amount of energy for use when the rudder wing is automatically bounced.

The automatic unfolding process of the rudder wing: after the locking device 7 is removed, the rudder wing 6 rotates around the rudder transmission shaft 1 under the action of the torsion spring 2, and at the same time, the outward elastic force of the compression spring 4 accelerates the unfolding speed of the rudder wing 6, When turning to a certain position, the arc surface 623 is in contact with the arc surface 512 of the lock end 51, and under the cooperation of the arc surface of the lock end 51, the lock end 51 gradually turns into the lock opening 622, and the rudder wing 6 continues to rotate until The lock head 51 faces 511 and the locking opening 622 in direct contact to form a right-angle lock, and the rudder wing 6 can no longer rotate along the original direction. Under the active force of spring 2 and stage clip 4, the automatic expansion, and the locking of the lock head 51 and the lock port 622 has realized that the rudder wing 6 is locked on the rudder transmission shaft 1, and there is no large enough external force to make the lock head 51 Unlock with the locking notch 622 to realize the folding of the rudder wing 6.

It should be noted that, in this embodiment, under the action of the torsion spring, lock pin and compression spring, the rudder wing deployed can resist flight resistance during flight, that is, the rudder wing will not be affected by Folding due to the effect of flight resistance, thereby affecting the flight of the MAV, causing the aircraft to break, crash, etc. Therefore, in practical applications, appropriate torsion springs, compression springs and locking pins should be selected according to the model of the MAV. Therefore, the above-mentioned "sufficiently large external force" must be at least greater than the maximum flight resistance that the MAV will encounter during flight.

It should be noted that, in this embodiment, the lock head 51 has one curved surface and one straight surface, and the design of the lock 622 matched with it—inner straight face—inner curved surface, not only enables the rudder wing to automatically expand and lock, but also The rudder wing 6 can only be folded towards the rudder transmission shaft 1 in one direction, that is, the direction where the arc surface is located, and the rudder wing 6 and the rudder transmission shaft 1 are just locked when they are on the same straight line, so as to avoid the occurrence of the rudder wing 6 in the unfolding process. After turning over, it needs to be manually adjusted in reverse.

In addition, it should be noted that the function of the locking device 7 in this embodiment is to lock the folded rudder wings together. In practical applications, the locking device 7 with a specific structure can be used exclusively, or Simple binding devices such as ropes, bandages, and sleeves bind the folded rudder wings together.

A micro-aircraft with foldable rudder wings. The rudder wings can be folded toward the direction of the rudder transmission shaft. Under the action of compression springs, torsion springs, etc., the rudder wings can be automatically locked after being unfolded. The folding, unfolding, and locking methods It is simple and securely locked, which solves the problem that the traditional aircraft rudder wing cannot be folded, takes up a lot of space, and is not conducive to flexible portability.

The above is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed in the present invention can easily think of changes or Replacement should be covered within the protection scope of the present invention.

Claims (10)

1. a micro-aircraft with rudder wings foldable, is characterized in that, comprises rudder transmission shaft (1), torsion spring (2), rudder wing rotating shaft (3), stage clip (4), locking pin (5) and rudder wing(6); Compression spring (4) and lock pin (5) are installed in the rudder transmission shaft (1) in sequence; The rudder blade (6) is connected to the rudder transmission shaft (1) through the rudder blade rotation shaft (3), and is in contact with the lock pin (5). The rudder blade (6) can rotate around the rudder blade rotation shaft (3). (1) rotation; The two ends of the torsion spring (2) are sleeved on the two ends of the rudder wing shaft (3), and are located outside the rudder transmission shaft (1), and the torsion spring can rotate around the rudder wing shaft (3) under the action of an external force and store energy. 2. A micro-aircraft with foldable rudder wings according to claim 1, characterized in that, the lock pin (5) is provided with a lock head (51), and the rudder wings (6) are provided with locks. mouth (622), the lock head (51) is adapted to the size, shape and position of the lock port (622), when the rudder wing (6) is in the unfolded and locked state, the lock head (51) is locked in the lock port (622) . 3. A micro-aircraft with foldable rudder wings according to claim 2, characterized in that, the opposite side of the lock (51) and the lock (622) is provided with an arc surface and a straight surface, so that the rudder Wing (6) can only be folded towards the rudder drive shaft (1) in one direction. 4. a kind of micro-aircraft with foldable rudder wings according to claim 1, is characterized in that two bearings are installed on one end of said rudder turning shaft (1), and the other end is provided with platform (13), upper plate (14) and lower plate (15), upper plate (14) and lower plate (15) are arranged on the platform (13) parallel to each other, and perpendicular to platform (13); A notch (16) for one end of the rudder wing (6) to rotate around the rudder wing shaft (3) is formed between the upper plate (14) and the lower plate (15); The upper plate (14) and the lower plate (15) are respectively provided with through holes (17) at relative positions, and the rudder wing shaft (3) is installed on the rudder drive shaft (1) through the two through holes (17); A slotted hole (18) for installing stage clips (4) and locking pins (5) is provided at the center of the platform (13) directly through the notch (16). 5. a kind of micro-aircraft with foldable rudder wings according to claim 4, is characterized in that, the aperture of described slotted hole (18) is greater than notch (16) aperture, in described upper plate (14), lower Grooves are opened at corresponding positions of the plate (15), and the position and shape of the grooves are adapted to the position and shape of the slot holes (18). 6. a kind of micro-aircraft with foldable rudder wings according to claim 4, is characterized in that, described stage clip (4), lock pin (5) are installed in described slotted hole (18) successively, stage clip (4), the lock pins (5) have the same diameter a, the aperture of the slotted hole (18) is b, and b≥a. 7. A micro-aircraft with foldable rudder wings according to claim 4, characterized in that one end of the lock pin (5) is in contact with the stage clip (4), and the other end is provided with a raised lock Head (51), lock pin (5) side offers chute (52); Provide the first threaded hole (19) perpendicular to the slotted hole (18) and communicated with the slotted hole (18) on the side of the platform (13), and the lock pin screw (53) passes through the first threaded hole ( 19) Extend into the chute (52), through the cooperation of the lock pin screw (53) and the chute (52), the lock pin (5) can slide along the axis of the slot hole (18); The lock head (51) comprises a straight face (511) and an arc (512) arranged oppositely, the straight face (511) is a plane perpendicular to the end face of the lock pin (5), and the arc face (512) is formed from the top of the lock end (51). The arc transitions to the arc surface on the side of the lock pin (5). 8. A micro air vehicle with foldable rudder wings according to claim 7, characterized in that, said rudder wings (6) comprise airfoils (61) and connecting ends (62), and openings on the connecting ends (62) Rotation hole (621) is arranged, and described rudder blade rotating shaft (3) passes through the through hole (17) of upper plate (14), the through hole (17) of rotation hole (621), lower plate (15) successively, makes the rudder Wing (6) and rudder drive shaft (1) realize shaft connection; The end face of connecting end (62) is provided with concave lock mouth (622), and lock mouth (622) and the lock end of described lock pin (5) ( 51) to match the shape and size. 9. A kind of foldable rudder-blade micro-aircraft according to claim 1-8, characterized in that, said torsion spring (2) comprises two fixed rings (21), two rotating rings (22) and clips The holding action part (23), the two ends of the holding action part (23) are connected with the rotating ring (22) and the fixed ring (21) successively; The two rotating rings (22) are sleeved on the two ends of the rudder wing shaft (3) respectively, and the two fixing rings (21) are detachably mounted on opposite sides of the rudder drive shaft (1), so that the clamping part (23 ) can be clamped at the joint between the rudder transmission shaft (1) and the rudder wing (6). 10. A micro-aircraft with foldable rudder wings according to claim 9, characterized in that, the fixing ring (21) is detachably mounted on the rudder transmission shaft (1) through locking screws (24).