TWI891538B - Automatically deployable wing assembly - Google Patents

Abstract

The wing assembly of the present invention includes a first wing unit, a second wing unit, and an inertia switch. The first wing unit has a first wing and a first rotating base connected to the first wing, while the second wing unit has a second wing and a second rotating base connected to the second wing and pivotally mounted on the first rotating base. The inertia switch is configured to control whether the first rotating base and the second rotating base can rotate relative to each other. As a result, when the wing assembly accelerates in a first direction, the inertia switch actuates from a locked position in a second direction opposite to the first direction to an unlocked position, allowing the first and second rotating bases to rotate relative to each other, thereby enabling the first and second wings to automatically deploy under the action of an elastic member.

Description

Automatically deployable wing assembly

The present invention relates to a wing deployment mechanism for a drone, and in particular to a wing assembly that automatically deploys using inertial force.

The Springtrap drone is small and lightweight, allowing it to be carried by a single person and stowed in a backpack. After being launched from its cannon, it deploys its wings mid-air, making it highly maneuverable without the need for a runway. Therefore, in addition to its national defense applications, the Springtrap drone can also be used in emergency rescue, climate exploration, and terrain reconnaissance.

However, existing wing deployment mechanisms are all controlled by electronic control systems, requiring the integration of related electronic control components such as speed sensors, altitude sensors, control computers, and servers. This results in complex and costly structures, leading to potential structural improvements.

The main purpose of this invention is to provide a wing assembly that can automatically deploy through inertial force, thereby simplifying the structure and reducing costs.

To achieve the above-mentioned primary objectives, the present invention provides a wing assembly comprising a first wing unit, a second wing unit, an elastic member, and an inertia switch. The first wing unit has a first wing and a first rotating base connected to the first wing; the second wing unit has a second wing and a second rotating base connected to the second wing. The second rotating base is pivotally mounted on the first rotating base, allowing the first and second wings to move from a folded position to an extended position. The elastic member provides elastic force to move the first and second wings. The wings are movable from the folded position to the extended position. The inertia switch is movably mounted on the first and second rotating bases between a locked position and an unlocked position. When the inertia switch is in the locked position, the first and second rotating bases cannot rotate relative to each other. When the inertia switch is in the unlocked position, the first and second rotating bases can rotate relative to each other.

As can be seen from the above, when the wing assembly of the present invention accelerates in a first direction, the inertia switch is acted upon by an inertia force, actuating it from the locked position in a second direction opposite to the first direction to the unlocked position. This allows the first and second wings to automatically deploy due to the elastic force released by the elastic member. The overall structure does not require any electronic control components, thereby achieving a simplified structure and reducing costs.

Preferably, the first rotating base has a sleeve with a pinhole. The inertia switch comprises a collar, a spring, and a pin. The collar is fixed to the sleeve, the bottom end of the spring is fixed to the collar, and the pin is fixed to the top end of the spring. Thus, when the inertia switch is in the locked position, the pin is inserted into the pinhole, preventing the first and second rotating bases from rotating relative to each other. When the inertia switch is in the unlocked position due to the inertia force, the spring elastically deforms and drives the pin out of the pinhole, allowing the first and second rotating bases to rotate relative to each other.

Preferably, the second rotating base has a pivot shaft that is rotatably inserted into the sleeve of the first rotating base, and the pivot shaft has a slot formed on its outer circumference. The inertia switch further comprises a first magnetic member and a second magnetic member, the first magnetic member being positioned at the end of the pin and the second magnetic member being positioned within the slot of the pivot shaft. Thus, when the inertia switch is in the locked position, the first and second magnetic members attract each other, strengthening the connection between the pin and the pinhole, thereby preventing the pin from accidentally disengaging from the pinhole due to improper external forces.

Preferably, the first wing has a first through-slot, the first rotating base has a first arm and a first latching slot provided in the first arm, and the first arm of the first rotating base is engaged with the first through-slot of the first wing. The second wing has a second through-slot, the second rotating base has a second arm and a second latching slot provided in the second arm, and the second arm of the second rotating base is engaged with the second through-slot of the second wing. The elastic member is a torsion spring, which is sleeved on the pivot and has a first end and a second end, the first end being engaged with the first latching slot of the first rotating base, and the second end being engaged with the second latching slot of the second rotating base. In this way, when the first wing and the second wing are in the retracted position, the elastic member accumulates elastic force. Once the inertia switch is actuated to the unlocked position, the elastic force released by the elastic member automatically springs the first wing and the second wing from the retracted position to the extended position.

Preferably, the first rotating base has a pinhole. The inertia switch comprises a support, a shaft, and a return spring. The support is mounted on the first rotating base and is synchronously actuated with the first rotating base. The shaft is movably disposed in the first direction or the second direction and extends through the support. A latch is disposed at the front end of the shaft. The return spring is sleeved on the shaft and provides a spring force to retain the shaft in the pinhole. Thus, when the inertia switch is in the locked position, the latch is inserted into the pinhole. When the inertia switch is in the unlocked position, the latch is driven by the shaft to leave the pinhole and compress the return spring.

Preferably, a block is provided at the rear end of the shaft to prevent the shaft from separating from the support seat.

The detailed structure, features, assembly, and usage of the automatically deployable wing assembly provided by the present invention will be described in the detailed description of the embodiments that follow. However, those skilled in the art will understand that these detailed descriptions and the specific embodiments listed for implementing the present invention are intended solely to illustrate the present invention and are not intended to limit the scope of the patent application for the present invention.

10: Wing assembly

10’: Wing assembly

20: First wing unit

30: First Wing

32: First Slot

40: First rotating base

41: First Top Plate

42: Bushing

422: Lower groove

43: First Chassis

44: First plate

441: First shaft hole

442: Upper container

45: First arm

452: First card slot

S1: Screw

46: Top cover

462: Countersunk hole

464: Upper groove

47: Pin hole

50: Second wing unit

60: Second Wing

62: Second Slot

70: Second rotating base

71: Second top plate

72: Second plate

722: Second shaft hole

724: Lower trough

73: Second arm

732: Second card slot

74: Second Chassis

S2: Screws

75: Pivot

752: Screw hole

754: Grooving

S3: Countersunk screw

76: Spacer ring

P1: Folded position

P2: Expanded position

80: Elastic parts

81: Accumulation Department

82: First end

83: Second end

90: Inertia switch

91: Beam Ring

92: Reed

922: Top hole

S4: Screws

93: Pins

932: Threaded end

934: Insertion port

S5: Screws

N: Nut

P3: Lock position

P4: Unlock position

D1: First Direction

D2: Second Direction

94: First magnetic element

95: Second magnetic element

96: Support plate

100: Inertia switch

101: Support seat

102: Lower seat

103: Upper seat

105: Liner

106: Shaft

107: Latch

S6: Screws

108:Block

109:Return spring

Figure 1 is a perspective view of the wing assembly of the first embodiment of the present invention, mainly illustrating the first wing and the second wing in the retracted position.

Figure 2 is a partial exploded perspective view of the wing assembly of the first embodiment of the present invention.

Figure 3 is a three-dimensional exploded view of the first wing unit provided by the wing assembly of the first embodiment of the present invention.

Figure 4 is a three-dimensional exploded view of the second wing unit provided by the wing assembly of the first embodiment of the present invention.

Figure 5 is a cross-sectional view of the wing assembly of the first embodiment of the present invention, primarily illustrating the inertia switch in the locked position.

Figure 6 is similar to Figure 5, but mainly illustrates the inertia switch in the unlocked position.

Figure 7 is similar to Figure 1, primarily illustrating the movement of the first and second wings toward the deployed position.

Figure 8 is similar to Figure 7, but mainly illustrates the first and second wings in the deployed position.

Figure 9 is a partially enlarged perspective view of the wing assembly of the second embodiment of the present invention.

Figure 10 is a perspective exploded view of the inertia switch provided in the wing assembly of the second embodiment of the present invention.

Figure 11 is a side view of Figure 9, showing the inertia switch in the locked position.

Figure 12 is similar to Figure 11, but shows the inertia switch in the unlocked position.

The applicant first clarifies that throughout this specification, including the embodiments described below and the claims in the patent application, directional terms are based on the directions in the drawings. Furthermore, in the embodiments and drawings described below, identical component numbers represent identical or similar components or structural features.

Referring to FIG. 1 , the wing assembly 10 of the first embodiment of the present invention is suitable for use in a flying vehicle (such as, but not limited to, a Spring Blade drone). Further referring to FIG. 2 , the wing assembly 10 of the present invention includes a first wing unit 20 , a second wing unit 50 , an elastic member 80 , and an inertia switch 90 .

The first wing unit 20 has a first wing 30 and a first rotating base 40. As shown in FIG3 , the first wing 30 has a first through-slot 32 inside, and the first through-slot 32 extends along the length direction of the first wing 30; the first rotating base 40 has a first top plate 41, a sleeve 42, a first bottom plate 43, and a top cover 46, wherein the sleeve 42 is integrally connected to the first top plate 41 and passes through the top and bottom surfaces of the first top plate 41; the first bottom plate 43 has a first plate portion 44 and a first arm portion 45, the top surface of the first plate portion 44 abuts against the bottom surface of the first top plate 41 and is locked with a plurality of screws S1, and the first plate portion 44 has a first axial hole 441 passing through both the top and bottom surfaces and an upper receiving groove 442 surrounding the first axial hole 441. The first axial hole 441 is sleeved on the bottom end of the sleeve 42. The first arm portion 45 extends outward from the outer periphery of the first disc portion 44 along the diameter of the first disc portion 44 and is snap-fitted into the first through-groove 32 of the first wing 30. In addition, the bottom surface of the first arm portion 45 has a first snap-fitting groove 452 connected to the upper receiving groove 442. As shown in Figures 1 and 4, a top cover 46 is provided at the top end of the sleeve 42, and the top cover 46 has a countersunk hole 462. In addition, as shown in Figures 1 and 2, the outer circumference of the sleeve 42 has a lower groove 422, and the outer circumference of the top cover 46 has an upper groove 464. The upper groove 464 and the lower groove 422 correspond to each other to form a pin hole 47.

The second wing unit 50 has a second wing 60 and a second rotating base 70 . As shown in FIG4 , the second wing 60 has a second through-slot 62 extending along the length direction of the second wing 60; the second rotating base 70 has a second top plate 71, a second bottom plate 74, and a pivot 75, wherein the second top plate 71 is located below the first bottom plate 43 and a spacer ring 76 is disposed between the second top plate 71 and the first bottom plate 43. In addition, the second top plate 71 has a second plate portion 72 and a second arm portion 73. The top surface of the second plate portion 72 has a second axial hole 722 passing through the top and bottom surfaces and a lower receiving groove 724 surrounding the second axial hole 722, wherein the lower receiving groove 724 corresponds to the upper receiving groove 442 of the first bottom plate 43, and the second arm portion 73 extends from the second plate portion 72 to the second arm portion 73. The outer periphery extends outward along the diameter of the second plate 72 and is engaged with the second through slot 62 of the second wing 60. In addition, the top surface of the second arm 73 has a second engaging slot 732 connected to the lower receiving slot 724. The top surface of the second chassis 74 abuts the bottom surface of the second plate 72 and is locked with multiple screws S2. The pivot 75 is integrally connected to the second chassis 7 4 and penetrates from bottom to top into the sleeve 42 through the second axial hole 722. A screw hole 752 is provided on the top end of the pivot 75. A countersunk screw S3 is inserted through the countersunk hole 462 of the top cover 46 and locked to the screw hole 752 of the pivot 75, allowing the second rotating base 70 to rotate relative to the first rotating base 40 about the pivot 75. Thus, through the relative rotation of the first rotating base 40 and the second rotating base 70, the first wing 30 and the second wing 60 can be moved from a retracted position P1 (as shown in Figure 1) to an extended position P2 (as shown in Figure 8), driven by the first arm 45 and the second arm 73, respectively.

In this embodiment, the elastic member 80 is a torsion spring. It has a force storage portion 81, as shown in Figure 5 . The force storage portion 81 is sleeved on the sleeve 42 of the first rotating base 40 and positioned within the upper and lower receiving grooves 442 and 724 . A first end portion 82 extends outward from one end of the force storage portion 81, and a second end portion 83 extends outward from the other end. As shown in Figures 3 and 4 , the first end portion 82 engages in the first retaining groove 452 , and the second end portion 83 engages in the second retaining groove 732 . The elastic force provided by the elastic member 80, through the first and second arms 45 and 73 , maintains the first and second wings 30 and 60 in the deployed position P2 shown in Figure 8 .

The inertia switch 90 comprises a collar 91, a spring 92, and a pin 93. As shown in Figures 2 and 5, the collar 91 is mounted on the sleeve 42 of the first rotating base 40 and clamped and secured with a screw S4. It is also supported by a support plate 96 mounted on the sleeve 42. The bottom end of the spring 92 is secured to the collar 91 with a screw S5. The pin 93 has a threaded end 932 and an insertion end 934. The threaded end 932 of the pin 93 passes through a top hole 922 of the spring 92 and is secured to the top end of the spring 92 with a nut N. The insertion end 934 of the pin 93 is driven by the elastic force of the spring 92 to penetrate the pin hole 47 of the first rotating base 40.

As can be seen from the above, when the wing assembly 10 has not yet been activated, the inertia switch 90 is in a locked position P3 (as shown in FIG. 5 ). At this time, the insertion end 934 of the pin 93 is inserted into the pin hole 47 of the first rotating base 40, so that the first rotating base 40 and the second rotating base 70 cannot rotate relative to each other. In this case, the first wing 30 and the second wing 60 remain in the retracted position P1 shown in FIG. 1 , allowing the elastic member 80 to accumulate elastic force. When the wing assembly 10 accelerates in a first direction D1, as shown in Figure 7 , the spring 92 is subjected to an inertial force, causing elastic deformation. This simultaneously drives the pin 93 from the locked position P3 shown in Figure 5 in a second direction D2 opposite to the first direction D1 to an unlocked position P4 shown in Figure 6 . At this point, the elastic force released by the elastic member 80 forces the first and second rotating bases 40 and 70 to rotate relative to each other, causing the first and second wings 30 and 60 to automatically spring apart from the retracted position P1 shown in Figure 1 to the deployed position P2 shown in Figure 8 .

It should be noted that to prevent the pin 93 from accidentally disengaging from the pin hole 47 due to improper external force, the inertia switch 90 further includes a first magnetic member 94 and a second magnetic member 95. The first magnetic member 94 (e.g., a magnet or a magnetically attractable material) is positioned at the insertion end 934 of the pin 93, while the second magnetic member 95 (e.g., a magnet or a magnetically attractable metal material) is embedded in a recess 754 of the pivot 75. Consequently, when the inertia switch 90 is in the locked position P3 shown in Figure 5, the first magnetic member 94 and the second magnetic member 95 attract each other, strengthening the connection between the pin 93 and the pin hole 47. Once the inertial force acting on the inertial switch 90 exceeds the magnetic attraction of the first magnetic member 94 and the second magnetic member 95, the pin 93 is driven by the spring 92 and released from the pin hole 47.

Continuing to refer to Figures 9 and 10, the wing assembly 10' of the second embodiment of the present invention is structurally similar to that of the first embodiment described above, except for the structure of the inertia switch 100.

In this embodiment, the inertia switch 100 has a support 101, a shaft 106, and a return spring 109, wherein:

The support base 101 comprises a lower base 102 and an upper base 103. The lower base 102 is screwed to the top of the support plate 96 and is sleeved onto the first rotating base 40. The upper base 103 is also screwed to the top of the lower base 102, enabling the support base 101 to move synchronously with the first rotating base 40. Furthermore, a sleeve 105 is inserted into the upper base 103.

The shaft 106 is inserted into the sleeve 105 and can move in the first direction D1 or the second direction D2. A latch 107 is inserted into the front end of the shaft 106, and a stopper 108 is locked with a screw S6 at the rear end of the shaft 106. The stopper 108 prevents the shaft 106 from separating from the support base 101.

The return spring 109 (here a compression spring is used as an example) is mounted on the shaft 106 and presses between the latch 107 and the upper base 103 to provide a spring force to retain the latch 107 in the pin hole 47.

As can be seen from the above, when the wing assembly 10' is not yet activated, the inertia switch 100 is in the locked position P3 shown in Figure 11. At this point, the latch 107 is held in the pin hole 47 by the elastic force of the return spring 109, maintaining the first wing 30 and the second wing 60 in the retracted position P1 shown in Figure 1. When the wing assembly 10' accelerates in the first direction D1, the shaft 106 is acted upon by the inertia force, driving the latch 107 in the second direction D2 to the unlocked position P4 shown in Figure 12. This causes the latch 107 to compress the return spring 109 and disengage the pin hole 47. At this point, the first wing 30 and the second wing 60 automatically spring open to the deployed position P2 shown in Figure 8.

In summary, the wing assemblies 10, 10' of the present invention utilize the configuration of the elastic member 80 and the inertia switches 90, 100 to enable the first wing 30 and the second wing 60 to automatically deploy through inertia when the flying vehicle accelerates. The overall structure does not require any electronic control components, thereby achieving the goals of structural simplification and cost reduction.

20: First wing unit

30: First Wing

40: First rotating base

41: First Top Plate

42: Bushing

422: Lower groove

44: First plate

S1: Screw

46: Top cover

464: Upper groove

50: Second wing unit

60: Second Wing

70: Second rotating base

75: Pivot

754: Grooving

S3: Countersunk screw

76: Spacer ring

80: Elastic parts

81: Accumulation Department

82: First end

83: Second end

90: Inertia switch

91: Beam Ring

S4: Screws

92: Reed

S5: Screws

93: Pins

932: Threaded end

934: Insertion port

N: Nut

94: First magnetic element

95: Second magnetic element

96: Support plate

Claims (7)

A wing assembly comprises: a first wing unit having a first wing and a first rotating base connected to the first wing; a second wing unit having a second wing and a second rotating base connected to the second wing, the second rotating base being pivotally mounted on the first rotating base so that the first wing and the second wing can be moved from a stowed position to an extended position; an elastic member providing elastic force to move the first wing and the second wing from the stowed position to the extended position; and An inertia switch is disposed on the first and second rotating bases and is movably positioned between a locked position and an unlocked position. When the inertia switch is in the locked position, the first and second rotating bases cannot rotate relative to each other. When the inertia switch is in the unlocked position, the first and second rotating bases can rotate relative to each other. When the wing assembly accelerates in a first direction, the inertia switch actuates from the locked position in a second direction opposite to the first direction to the unlocked position. The wing assembly as described in claim 1, wherein the first rotating base has a shaft sleeve, the shaft sleeve has a pin hole; the inertia switch has a collar, a spring and a pin, the collar is fixed to the shaft sleeve, the bottom end of the spring is fixed to the collar, and the pin is fixed to the top end of the spring. When the inertia switch is in the locked position, the pin is inserted into the pin hole. When the inertia switch is in the unlocked position, the spring produces elastic deformation and drives the pin to leave the pin hole. As described in claim 2, the wing assembly, wherein the second rotating base has a pivot shaft, which is rotatably inserted into the shaft sleeve of the first rotating base, and the outer peripheral surface of the pivot shaft has an embedding groove; the inertia switch further has a first magnetic part and a second magnetic part, the first magnetic part is arranged at the end of the pin part, and the second magnetic part is arranged in the embedding groove of the pivot shaft, when the inertia switch is in the locked position, the first magnetic part and the second magnetic part are attracted to each other. The wing assembly as described in claim 1, wherein the first wing has a first through-slot, the first rotating base has a first arm and a first slot provided on the first arm, and the first arm is engaged in the first through-slot of the first wing; the second wing has a second through-slot, the second rotating base has a second arm and a second slot provided on the second arm, and the second arm is engaged in the second through-slot of the second wing; the elastic member is a torsion spring, the torsion spring having a first end and a second end, the first end being engaged in the first slot of the first rotating base, and the second end being engaged in the second slot of the second rotating base. The wing assembly as described in claim 1, wherein the first rotating base has a pin hole; the inertia switch has a support seat, a shaft, and a return spring, the support seat can be arranged on the first rotating base in synchronization with the first rotating base, the shaft can be movably passed through the support seat along the first direction or the second direction, and the return spring is sleeved on the shaft and provides elastic force to keep the shaft in the pin hole. A wing assembly as described in claim 5, wherein a latch is provided at the front end of the shaft, and when the inertia switch is in the locked position, the latch is inserted into the pin hole, and when the inertia switch is in the unlocked position, the latch is driven by the shaft to leave the pin hole and compress the return spring. As described in claim 5, a block is provided at the rear end of the shaft to prevent the shaft from separating from the support seat.