Coaxial folding twin propeller mechanism and aircraft

Abstract

This invention discloses a coaxial folding dual-propeller mechanism and an aircraft. The coaxial folding dual-propeller mechanism includes a sleeve assembly, an inner shaft assembly, a linkage assembly, and a drive structure. The sleeve assembly includes a sleeve and a first propeller blade hinged to the sleeve. The inner shaft assembly includes an inner shaft and a second propeller blade hinged to the inner shaft. The linkage assembly includes a linkage seat, a rotating seat, a first connecting structure, and a second connecting structure. The linkage seat is slidably sleeved on the outside of the sleeve. The linkage seat and the rotating seat are rotatably connected and axially positioned so that the linkage seat and the rotating seat slide synchronously. The two ends of the first connecting structure are respectively connected to the first propeller blade and the linkage seat, so that the sliding of the linkage seat can drive the first propeller blade to unfold. The two ends of the second connecting structure are respectively connected to the rotating seat and the second propeller blade, so that the sliding of the rotating seat can drive the second propeller blade to unfold. The drive structure drives the linkage seat to slide along the axis of the sleeve. Compared with the prior art, this invention can solve the problem that the propeller blade cannot unfold at low rotational speeds.

Description

Technical Field

[0001] This invention relates to the field of loitering munition propulsion technology, and in particular to a coaxial folding dual-propeller mechanism and aircraft. Background Technology

[0002] The foldable coaxial twin-propeller structure is a common structure for aircraft, comprising an inner shaft, a sleeve, a first blade, and a second blade. The sleeve is fitted over the outer side of the inner shaft, the first blade is hinged to the sleeve, and the second blade is hinged to the inner shaft. By rotating the inner shaft and the sleeve in opposite directions, the torque exerted on the aircraft by the first blade and the torque exerted on the aircraft by the second blade can be at least partially canceled out.

[0003] For example, patent CN109624626A discloses a coaxial dual-blade mechanism that can realize synchronous folding of blades. It achieves synchronous deployment of the first blade and the second blade through a linkage structure. However, this patent has the following problem: the deployment of the blades mainly relies on the centrifugal force generated by the rotation of the blades around the inner axis. When the blade speed is low, the centrifugal force is small, and there is a problem that the blades cannot be deployed. Summary of the Invention

[0004] The purpose of this invention is to provide a coaxial folding dual-propeller mechanism and aircraft to solve the problem that the propellers cannot be deployed when the speed of rotation is low.

[0005] To achieve the above objectives, the present invention provides the following solution:

[0006] This invention discloses a coaxial folding dual-propeller mechanism, comprising:

[0007] A sleeve assembly for rotation in a first direction, the sleeve assembly including a sleeve and a first blade hinged to the sleeve;

[0008] An inner shaft assembly for rotation in a second direction opposite to the first direction; the inner shaft assembly includes an inner shaft and a second blade hinged to the inner shaft; the inner shaft passes through the sleeve and is rotatably connected to the sleeve;

[0009] A linkage assembly capable of synchronously deploying the first and second blades, the linkage assembly comprising a linkage seat, a rotating seat, a first connecting structure, and a second connecting structure; the linkage seat is slidably sleeved on the outside of the sleeve; the linkage seat and the rotating seat are rotatably connected and axially positioned so that the linkage seat and the rotating seat slide synchronously; the two ends of the first connecting structure are respectively connected to the first blade and the linkage seat so that the first blade can be driven to deploy when the linkage seat slides; the two ends of the second connecting structure are respectively connected to the rotating seat and the second blade so that the second blade can be driven to deploy when the rotating seat slides.

[0010] The drive structure installed on the sleeve drives the linkage seat to slide along the axis of the sleeve, so that the linkage seat will synchronously deploy the first blade and the second blade when sliding.

[0011] Preferably, it further includes a positioning component for axially positioning the linkage seat, the positioning component being capable of releasing the axial positioning of the linkage seat.

[0012] Preferably, the driving structure is a tension spring, with both ends of the tension spring fixed to the sleeve and the linkage seat respectively; when the first blade and the second blade are in a folded state, the tension spring is stretched; after the positioning component releases the axial positioning of the linkage seat, the tension spring causes the linkage seat to slide, so as to simultaneously unfold the first blade and the second blade.

[0013] Preferably, the first connecting structure includes a first connecting rod and a second connecting rod, the first end of the first connecting rod is fixedly connected to the hinge shaft of the first blade, the second end of the first connecting rod is hinged to the first end of the second connecting rod, and the second end of the second connecting rod is hinged to the linkage seat.

[0014] Preferably, the second connection structure includes a third link and a fourth link, the first end of the third link is fixedly connected to the hinge shaft of the second blade, the second end of the third link is hinged to the first end of the fourth link, and the second end of the fourth link is hinged to the rotating seat.

[0015] Preferably, the positioning component includes a locking tongue and a locking pin; the locking tongue is installed in one of the linkage seat and the inner shaft, and the locking pin is installed in the other; the locking tongue is provided with a locking groove, which is used to engage with the locking pin to axially position the linkage seat; the locking pin can enter and leave the locking groove.

[0016] Preferably, the locking tongue is fixed to the linkage seat, and the locking pin is slidably installed in a pin hole arranged radially on the inner shaft;

[0017] Both ends of the lock groove extend to the two sides of the lock tongue, so that the lock pin can be disengaged from the lock groove by rotating the linkage seat relative to the inner shaft.

[0018] The inner shaft has a radially arranged pin hole, into which the locking pin extends; the latch has an inclined surface, which is used to push the locking pin into the pin hole when the locking groove is close to the locking pin; a spring is provided between the bottom of the pin hole and the locking pin, which is used to apply an elastic thrust to push the locking pin out of the pin hole, so as to push the locking pin into the locking groove when the locking pin is aligned with the locking groove.

[0019] Preferably, a second hinge seat is fixed on the inner shaft for hinged connection with the second blade, and the second hinge seat is provided with a latch groove into which the latch extends, and the pin hole is located on the side wall of the latch groove.

[0020] Preferably, a first hinge seat for hinged connection with the first blade is fixed on the sleeve; along the axis of the inner shaft, the first hinge seat, the linkage seat, the rotating seat, and the second hinge seat are arranged in sequence.

[0021] The present invention also discloses an aircraft including the aforementioned coaxial folding dual-propeller mechanism.

[0022] The present invention achieves the following technical effects compared to the prior art:

[0023] This invention does not deploy the first and second blades using centrifugal force, but rather uses a drive structure to slide the linkage seat, thereby deploying the first and second blades. This avoids the problem of blades failing to deploy at low rotational speeds. In a preferred embodiment of this invention, a positioning component is used to axially position the linkage seat so that the first and second blades remain in a folded state. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the folded state of the coaxial folding dual-propeller mechanism according to an embodiment of the present invention;

[0026] Figure 2 This is a schematic diagram of the unfolded state of the coaxial folding double propeller mechanism according to an embodiment of the present invention;

[0027] Figure 3 This is a partial structural diagram of the coaxial folding dual-propeller mechanism according to an embodiment of the present invention;

[0028] Figure 4 This is a schematic diagram of the coaxial folding double propeller mechanism in a folded state along a cross section according to an embodiment of the present invention;

[0029] Figure 5 This is a schematic diagram of the coaxial folding double propeller mechanism in the folded state along another cross section according to an embodiment of the present invention;

[0030] Figure 6 This is a three-dimensional exploded view of a portion of the coaxial folding dual-propeller mechanism according to an embodiment of the present invention;

[0031] Figure 7 This is a three-dimensional exploded view of the unfolded state of a portion of the coaxial folding double propeller mechanism according to an embodiment of the present invention.

[0032] Explanation of reference numerals in the attached drawings: 1. Inner shaft; 2. Sleeve body section; 3. First blade; 4. Front blade shaft; 5. First connecting rod; 6. First hinge seat; 7. Tension spring; 8. Second connecting rod; 9. Sleeve extension section; 10. Linkage seat; 11. Rotating seat; 12. Tail blade shaft; 13. Shim; 14. Third connecting rod; 15. Fourth connecting rod; 16. Second blade; 17. Pressure plate; 18. Second hinge seat; 19. First bearing; 20. Screw; 21. Copper sleeve set screw; 22. Guide post; 23. Lubricating copper sleeve; 24. Shaft set screw; 25. Second retaining ring; 26. Fairing; 27. Second bearing; 28. First retaining ring; 29. ​​Locking pin.

[0033] A-Limiting surface; B-Lock groove; C-Lock tongue; D-Lock tongue groove. Detailed Implementation

[0034] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] The purpose of this invention is to provide a coaxial folding dual-propeller mechanism and aircraft to solve the problem that the propellers cannot be deployed when the speed of rotation is low.

[0036] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. Unless otherwise specified, the axis referred to in this embodiment refers to the axis of the inner shaft (i.e., the axis of the sleeve), the axial direction referred to in this embodiment refers to the direction of the axis of the inner shaft (i.e., the direction of the axis of the sleeve), and the hinge position referred to in this embodiment refers to the position of the hinge shaft.

[0037] Reference Figures 1 to 7 This embodiment provides a coaxial folding dual-propeller mechanism, including a sleeve assembly, an inner shaft 1 assembly, a linkage assembly, and a drive structure.

[0038] The sleeve assembly is used to rotate in a first direction (clockwise or counterclockwise), and the inner shaft 1 assembly is used to rotate in a second direction, which is opposite to the first direction. The sleeve assembly includes a sleeve and a first blade 3 hinged to the sleeve. The inner shaft 1 assembly includes an inner shaft 1 and a second blade 16 hinged to the inner shaft 1. The inner shaft 1 passes through the sleeve and is rotatably connected to the sleeve. In this embodiment, it is rotatably connected via a first bearing 19 to reduce friction. In actual use, there is no relative movement between the inner shaft 1 and the sleeve in the axial direction of the inner shaft 1.

[0039] The linkage assembly enables the first blade 3 and the second blade 16 to deploy synchronously. The linkage assembly includes a linkage seat 10, a rotating seat 11, a first connecting structure, and a second connecting structure. The linkage seat 10 is slidably fitted onto the outside of the sleeve. The linkage seat 10 and the rotating seat 11 are rotatably connected and axially positioned to allow them to slide synchronously. To reduce friction, this embodiment specifically achieves axial positioning and circumferential rotation of the linkage seat 10 and the rotating seat 11 by rotatably connecting them via a second bearing 27. The two sides of the second bearing 27 are respectively limited by a first retaining ring 28 and a pressure plate 17. The first retaining ring 28 is mounted on the linkage seat 10, and the pressure plate 17 is mounted on the rotating seat 11. The two ends of the first connecting structure are respectively connected to the first blade 3 and the linkage seat 10, so that the first blade 3 can be deployed when the linkage seat 10 slides. The two ends of the second connecting structure are respectively connected to the rotating seat 11 and the second blade 16, so that the second blade 16 can be deployed when the rotating seat 11 slides. The drive structure is mounted on the sleeve, and drives the linkage seat 10 to slide along the axis of the sleeve so that the linkage seat 10 can synchronously unfold the first blade 3 and the second blade 16 when sliding. In this embodiment, there are two first blades 3 and two second blades 16. The two first blades 3 are unfolded in a straight line, and the two second blades 16 are unfolded in a straight line.

[0040] The working principle of the coaxial folding dual-propeller mechanism in this embodiment is as follows:

[0041] Along the axial direction of the inner shaft 1, the hinge positions of the first blade 3 and the second blade 16 are located on opposite sides of the linkage seat 10. When the drive structure causes the linkage seat 10 to slide toward the hinge position of the first blade 3, the linkage seat 10 drives the first blade 3 through the first connecting structure, causing the first blade 3 to unfold. Simultaneously, the rotating seat 11 drives the second blade 16 through the second connecting structure, causing the second blade 16 to unfold. Because the linkage seat 10 and the sliding seat move synchronously along the axial direction of the inner shaft 1, the unfolding processes of the first blade 3 and the second blade 16 are synchronized, thus avoiding blade collision problems caused by asynchronous unfolding processes of the first blade 3 and the second blade 16. Furthermore, this embodiment does not use centrifugal force to unfold the first blade 3 and the second blade 16, but rather uses the drive structure to drive the linkage seat 10 to slide, thereby unfolding the first blade 3 and the second blade 16, thus avoiding the problem of blades failing to unfold at low rotational speeds.

[0042] As a possible example, in this embodiment, the coaxial folding double propeller mechanism further includes a positioning component for axially positioning the linkage seat 10, which can also release the axial positioning of the linkage seat 10. After the positioning component axially positions the linkage seat 10, the axial position of the linkage seat 10 relative to the inner shaft 1 and the sleeve remains unchanged.

[0043] As a possible example, in this embodiment, the driving structure is a tension spring 7, with its two ends fixed to the sleeve and the linkage seat 10, respectively. When the first blade 3 and the second blade 16 are in a folded state, the tension spring 7 is stretched. After the positioning component releases the axial positioning of the linkage seat 10, the tension spring 7 causes the linkage seat 10 to slide, so as to synchronously unfold the first blade 3 and the second blade 16 until the linkage seat 10 abuts against the limiting surface A on the sleeve. It is understood that the tension spring 7 can only unfold the first blade 3 and the second blade 16, but cannot fold them. When it is necessary to fold the first blade 3 and the second blade 16, it needs to be done manually or by an external structure. In order to make the linkage seat 10 rotate synchronously with the sleeve, in this embodiment, a guide post 22 is fixed on the sleeve, and a guide hole is provided on the linkage seat 10. The guide post 22 slides through the guide hole, and the guide post 22 is parallel to the inner shaft 1. The tension spring 7 is sleeved on the outside of the guide post 22. Depending on the actual needs, the tension spring 7 can also be replaced with other structures such as an electric telescopic rod to move the linkage seat 10 in both directions.

[0044] As a possible example, in this embodiment, the first connecting structure includes a first connecting rod 5 and a second connecting rod 8. The first end of the first connecting rod 5 is fixedly connected to the hinge shaft of the first blade 3 (the hinge shaft of the first blade 3 moves synchronously with the first blade 3). The second end of the first connecting rod 5 is hinged to the first end of the second connecting rod 8, and the second end of the second connecting rod 8 is hinged to the linkage seat 10. That is, in this embodiment, the first connecting structure transmits power through a connecting rod structure.

[0045] However, the actual implementation is not limited to this. For example, the first connecting structure may include a fixed rod and a roller, with the first end of the fixed rod fixed to the linkage seat 10, and the roller rotatably mounted on the second end of the fixed rod, and the roller making rolling contact with the first blade 3. When the linkage seat 10 slides close to the hinge position of the first blade 3, the roller makes rolling contact with the first blade 3, causing the first blade 3 to unfold.

[0046] As a possible example, in this embodiment, the second connecting structure includes a third link 14 and a fourth link 15. The first end of the third link 14 is fixedly connected to the hinge shaft of the second blade 16 (the hinge shaft of the second blade 16 moves synchronously with the second blade 16), the second end of the third link 14 is hinged to the first end of the fourth link 15, and the second end of the fourth link 15 is hinged to the rotating seat 11. That is, in this embodiment, the second connecting structure transmits power through a link structure.

[0047] However, the actual implementation is not limited to this. For example, the second connection structure may include a rope, with a first end fixed to the rotating seat 11 and a second end fixed to the second blade 16 (at a position other than the hinge axis).

[0048] As a possible example, in this embodiment, the positioning assembly includes a locking tongue C and a locking pin 29, preferably a ball-bearing locking pin 29. The locking tongue C is mounted on one of the linkage seat 10 and the inner shaft 1, and the locking pin 29 is mounted on the other. The locking tongue C has a locking groove B, which is used to engage with the locking pin 29 to axially position the linkage seat 10. The locking pin 29 can enter and exit the locking groove B. When the locking pin 29 enters the locking groove B, the linkage seat 10 is axially positioned. When the locking pin 29 exits the locking groove B, the linkage seat 10 is released from axial positioning.

[0049] As a possible example, in this embodiment, the latch C is fixed to the linkage seat 10, and the locking pin 29 is slidably mounted in a radially arranged pin hole on the inner shaft 1. The two ends of the locking groove B extend to the two side edges of the latch C, allowing the locking pin 29 to leave the locking groove B by rotating the linkage seat 10 relative to the inner shaft 1. A pin hole is provided radially on the inner shaft 1, into which the locking pin 29 extends. An inclined surface is provided on the latch C, located between the locking groove B and the end of the latch C. This inclined surface is used to push the locking pin 29 into the pin hole when the locking groove B approaches the locking pin 29. A spring is provided between the bottom of the pin hole and the locking pin 29. The spring is used to apply an elastic thrust to push the locking pin 29 out of the pin hole, so that the locking pin 29 is pushed into the locking groove B when aligned with the locking groove B. The structure is easy to operate. Simply rotate the linkage seat 10 relative to the inner shaft 1 to release the positioning of the linkage seat 10. Then, the linkage seat 10 moves under the action of the tension spring 7, automatically unfolding the first blade 3 and the second blade 16.

[0050] As a possible example, in this embodiment, a second hinge seat 18 for hinged connection with the second blade 16 is fixed on the inner shaft 1. The second hinge seat 18 is provided with a latch groove D for the latch C to extend into, and a pin hole is located on the side wall of the latch groove D. A first hinge seat 6 for hinged connection with the first blade 3 is fixed on the sleeve. The first hinge seat 6 is provided with a hook or hanging ring for attaching the tension spring 7. Along the axis of the inner shaft 1, the first hinge seat 6, the linkage seat 10, the rotating seat 11, and the second hinge seat 18 are arranged in sequence.

[0051] As a possible example, in this embodiment, the sleeve includes a sleeve body section 2 and a sleeve extension section 9. The sleeve body section 2 is rotatably connected to the inner shaft 1 via a first bearing 19, and the sleeve extension section 9 is fixedly connected to the sleeve body section 2 via screws 20. A lubricating copper sleeve 23 is sleeved on the outside of the sleeve extension section 9, and a linkage seat 10 is sleeved on the outside of the lubricating copper sleeve 23. The linkage seat 10 and the lubricating copper sleeve 23 are fixedly connected via a copper sleeve set screw 21. The tail end of the inner shaft 1 is threadedly connected to the fairing 26, and the fairing 26 is positioned by a second retaining ring 25 installed on the inner shaft 1. The hinge shaft of the first blade 3 (i.e., the front blade shaft 4) is fixed to the first blade 3 via a shaft set screw 24, and the hinge shaft of the second blade 16 (i.e., the tail blade shaft 12) is fixed to the second blade 16 via a shaft set screw 24. Gaskets 13 are provided between the first blade 3 and the first hinge seat 6, and between the second blade 16 and the second hinge seat 18.

[0052] This embodiment also provides an aircraft including the aforementioned coaxial folding dual-propeller mechanism. The aircraft can be a helicopter, a loitering munition, etc. Since this aircraft includes the aforementioned coaxial folding dual-propeller mechanism, it also possesses the advantages of the coaxial folding dual-propeller mechanism, which will not be elaborated further here.

[0053] This specification uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A coaxial folding double-propeller mechanism, characterized in that, include: A sleeve assembly for rotation in a first direction, the sleeve assembly including a sleeve and a first blade hinged to the sleeve; An inner shaft assembly for rotation in a second direction opposite to the first direction; the inner shaft assembly includes an inner shaft and a second blade hinged to the inner shaft; the inner shaft passes through the sleeve and is rotatably connected to the sleeve; A linkage assembly capable of synchronously deploying the first blade and the second blade, the linkage assembly including a linkage seat, a rotating seat, a first connecting structure and a second connecting structure; the linkage seat is slidably sleeved on the outside of the sleeve; the linkage seat is rotatably connected to the rotating seat and axially positioned so that the linkage seat and the rotating seat slide synchronously; the two ends of the first connecting structure are respectively connected to the first blade and the linkage seat so that the first blade can be driven to deploy when the linkage seat slides; The two ends of the second connecting structure are respectively connected to the rotating base and the second blade, so that the second blade can be driven to unfold when the rotating base slides. The drive structure installed on the sleeve drives the linkage seat to slide along the axis of the sleeve, so that the linkage seat will synchronously unfold the first blade and the second blade when sliding. It also includes a positioning component for axially positioning the linkage seat, and the positioning component is also capable of releasing the axial positioning of the linkage seat. The positioning component includes a locking tongue and a locking pin; the locking tongue is installed in one of the linkage seat and the inner shaft, and the locking pin is installed in the other; the locking tongue is provided with a locking groove, which is used to engage with the locking pin to axially position the linkage seat; the locking pin can enter and leave the locking groove. The locking tongue is fixed to the linkage seat, and the locking pin is slidably installed in the pin hole arranged radially on the inner shaft; Both ends of the lock groove extend to the two sides of the lock tongue, so that the lock pin can be disengaged from the lock groove by rotating the linkage seat relative to the inner shaft. The inner shaft has a radially arranged pin hole, into which the locking pin extends; the latch has an inclined surface, which is used to push the locking pin into the pin hole when the locking groove is close to the locking pin; a spring is provided between the bottom of the pin hole and the locking pin, which is used to apply an elastic thrust to push the locking pin out of the pin hole, so as to push the locking pin into the locking groove when the locking pin is aligned with the locking groove.

2. The coaxial folding double-propeller mechanism according to claim 1, characterized in that, The drive structure is a tension spring, with its two ends fixed to the sleeve and the linkage seat, respectively; when the first blade and the second blade are in a folded state, the tension spring is stretched. After the positioning component releases its axial positioning of the linkage seat, the tension spring causes the linkage seat to slide, so as to simultaneously unfold the first blade and the second blade.

3. The coaxial folding double propeller mechanism according to claim 2, characterized in that, The first connecting structure includes a first connecting rod and a second connecting rod. The first end of the first connecting rod is fixedly connected to the hinge shaft of the first blade. The second end of the first connecting rod is hinged to the first end of the second connecting rod. The second end of the second connecting rod is hinged to the linkage seat.

4. The coaxial folding double propeller mechanism according to claim 3, characterized in that, The second connection structure includes a third link and a fourth link. The first end of the third link is fixedly connected to the hinge shaft of the second blade, the second end of the third link is hinged to the first end of the fourth link, and the second end of the fourth link is hinged to the rotating seat.

5. The coaxial folding double-propeller mechanism according to claim 1, characterized in that, A second hinge seat is fixed on the inner shaft for hinged connection with the second blade. The second hinge seat is provided with a latch groove for the latch to extend into, and the pin hole is located on the side wall of the latch groove.

6. The coaxial folding double-propeller mechanism according to claim 5, characterized in that, The sleeve is fixed with a first hinge seat for hinged connection with the first blade; along the axis of the inner shaft, the first hinge seat, the linkage seat, the rotary seat, and the second hinge seat are arranged in sequence.

7. An aircraft, characterized in that, Includes the coaxial folding double propeller mechanism as described in any one of claims 1 to 6.

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