Description: A PROPELLER ASSEMBLY COMPRISING AN ADAPTER HAVING A DAMPENING MEMBER FOR CONNECTING A BLADE AND REDUCING VIBRATION DURING FLIGHT

FIELD OF INVENTION
[001] The present invention generally relates to an adapter for propeller blades. More specifically, the present invention relates to a propeller assembly comprising an adapter having a dampening member, the dampening member connecting and locking a blade having notches in a flight state and folded state, and reducing vibration during the flight state.

BACKGROUND OF INVENTION
[002] An aircraft such as a drone or an unmanned aerial vehicle (UAV), helicopter, quadcopters utilises a propeller comprising blades to provide required thrust or lift to achieve flight. Modern aircraft allow folding the blades. The blades are folded to reduce the space footprint the blades take when compared to their extended configuration during a flight state. In order to achieve the folding of the blades, adapters or central hubs are used.
[003] Several adapters facilitating folding of the blades have been disclosed in the past. Once such an example is disclosed in a United States granted patent no. 10,543,915, entitled, “Self-folding propeller” (“the ‘915 Patent”). The ‘915 Patent discloses a propeller assembly including propeller blades that self-fold when not in use, which reduces the overall footprint of the propeller assembly and enables efficient storage. During flying conditions, the propeller blades unfold and extend to a flight configuration that enables the generation of lift on the propeller blades and consequently to an attached aerial vehicle. In various embodiments, the transitioning of the propeller blades between a flight and folded configuration may be enabled by torsion springs coupled to each propeller blade. For example, the torsion springs cause each propeller blade to rotate and self-fold when no external forces are applied. Alternatively, during flying conditions, centrifugal forces that arise as the propeller assembly rotates counteract the torsion springs, enabling each propeller blade to achieve an extended flight configuration.
[004] Another example is disclosed in a United States granted patent no. 10,689,103, entitled, “Quick release folding propeller blades for a model aircraft” (“the ‘103 Patent”). The ‘103 Patent discloses a quick release propeller for model airplanes including two or more blades mounted to a hub. For each blade, the hub includes a slot and a shoulder. Each blade includes a base portion having pins which slide into the slot in the hub. The slots are curved which prevents the blades from being removed unless they are rotated at predefined threshold angle with respect to the hub.
[005] The above disclosures are useful in providing a foldable feature while also ensuring that the blades remain secured and operational during the flight. However, they have few problems. For example, when the aircraft is put to work, a sudden jerk is formed due to improper positioning of the blades. Further, during the flight, the propellers often experience minor vibrations due to aerodynamic imbalance. The vibrations get transferred to the entire aircraft resulting in instability. In order to overcome the above problems, a solution i.e., including a rubber bush or rubber ring in the adapter was proposed. However, the rubber bush helps only as a positioning device to lock at the end in order to prevent damage to the blade when it is folded. Other solutions include providing a rubber bush screwed on to the adapter to dampen the vibration of a motor connecting the adapter. However, the rubber bush cannot be used in a foldable propeller.
[006] None of the above solutions were able to solve the problem of reducing vibrations caused by blades during the flight and also locking the blade both in a flight state and a folded state when not in use.
[007] Therefore, there is a need for improvements in the design of the adapters and/or blades to address the problems discussed above.

SUMMARY OF THE INVENTION
[008] It is an object of the present invention to provide an improved propeller assembly that avoids the drawback of known adapters and blades.
[009] It is another object of the present invention to provide a propeller assembly comprising an adapter having a dampening member.
[010] It is another object of the present invention to provide a propeller assembly comprising an adapter having a dampening member, the dampening member connecting and locking a blade and reducing vibration in a flight state.
[011] It is yet another object of the present invention to provide a blade having one or more notches at its root to lock the blade to the adapter.
[012] In order to achieve one or more objects, the present invention provides a propeller assembly for connecting a blade and reducing vibration. The propeller assembly includes an adapter having a first plate and a second plate. The first plate indicates a bottom plate and the second plate indicates a top plate. The propeller assembly includes blades, each blade comprising a body portion having a root at one end and a tip at another end.
[013] In one aspect of the present invention, the first plate includes raised sections. The raised sections extend from the first plate facing the second plate. Each raised section includes a groove that configures to receive a dampening member.
[014] In another aspect of the present invention, the root of the blade comprises notches, one notch aligning with a central axis of the blade and two notches positioned opposite to each other and perpendicular to the notch aligning with the central axis of the blade.
[015] The first plate and the second plate receive the root such that the notch aligning with the central axis of the blade connects the dampening member and locks the position of the blade. The dampening member dampens the vibrations caused during the flight state and ensures the vibration does not get transferred to the raised sections, the first plate and the second plate and the propeller assembly and an aircraft incorporating the propeller assembly are stable. The blade rotates to engage another notch with the dampening member to lock the blade in a folded state.
[016] In one technical advantageous feature of the present invention, the adapter provides a dampening member at the groove provided at the raised section. The dampening member locks the position of the blade to the adapter before starting a motor for flight. The dampening member quickly absorbs and greatly reduces the initial jerk caused in the propeller assemblies as known in the art.
[017] In another technical advantageous feature of the present invention, the adapter provides a dampening member that absorbs and mitigates minor vibrations caused during the flight and gives better stability to the propeller assembly and the aircraft such as a drone incorporating the propeller assembly. The dampening member dampens the vibrations caused due to aerodynamic imbalance.
[018] In yet another technical advantageous feature of the present invention, the notches at the root of the blade help to lock on to the dampening member placed inside the adapter both in the flight state and folded state.
[019] Features and advantages of the subject matter hereof will become more apparent in light of the following detailed description of selected embodiments, as illustrated in the accompanying FIGURES. As will be realised, the subject matter disclosed is capable of modifications in various respects, all without departing from the scope of the subject matter. Accordingly, the drawings and the description are to be regarded as illustrative in nature.

BRIEF DESCRIPTION OF THE DRAWINGS
[020] Further features and advantages of the present subject matter will become apparent from the following detailed description, taken in combination with the appended drawings, in which:
[021] FIGS. 1A and 1B illustrate a top perspective view and a bottom perspective view, respectively of a propeller assembly, in accordance with one embodiment of the present invention;
[022] FIGS. 2A and 2B illustrate a top perspective view and a front view, respectively of an adapter, in accordance with one embodiment of the present invention;
[023] FIGS. 3A and 3B illustrate a top perspective view and a front view, respectively of a first plate or bottom plate of the adapter, in accordance with one embodiment of the present invention;
[024] FIGS. 4A and 4B illustrate a side perspective view and a top view, respectively of a dampening member, in accordance with one embodiment of the present invention;
[025] FIGS. 5 illustrates a top perspective view of a second plate i.e., top plate of the adapter, in accordance with one embodiment of the present invention;
[026] FIGS. 6 and 7 illustrate a perspective view and a top view, respectively of a blade, in accordance with one embodiment of the present invention;
[027] FIGS. 8 and 9 illustrate the blade connecting the adapter, in accordance with one embodiment of the present invention;
[028] FIG. 10 illustrates an exploded view of adapter receiving the blade, in accordance with one embodiment of the present invention;
[029] FIG. 11 illustrates a side perspective view of the propeller assembly in the folded state, in accordance with one embodiment of the present invention;
[030] FIG. 12 illustrates an exploded view of an adapter, in accordance with another embodiment of the present invention; and
[031] FIG. 13 illustrates a side-exploded view of the adapter receiving blades, in accordance with one embodiment of the present invention.
[032] It will be noted that throughout the appended drawings, like features are identified by like-reference numerals.

DETAILED DESCRIPTION OF THE EMBODIMENTS
[033] The detailed description set forth below in connection with the appended drawings is intended as a description of exemplary embodiments in which the presently disclosed subject matter may be practiced. The term “exemplary” used throughout this description means “serving as an example, instance, or illustration,” and should not necessarily be construed as preferred or advantageous over other embodiments. The detailed description includes specific details for providing a thorough understanding of the presently disclosed propeller assembly. However, it will be apparent to those skilled in the art that the presently disclosed subject matter may be practiced without these specific details. In some instances, well-known structures and devices are shown in functional or conceptual diagram form in order to avoid obscuring the concepts of the presently disclosed propeller assembly.
[034] In the present specification, an embodiment showing a singular component should not be considered limiting. Rather, the subject matter preferably encompasses other embodiments including a plurality of the same component, and vice-versa, unless explicitly stated otherwise herein. Moreover, the applicant does not intend for any term in the specification to be ascribed an uncommon or special meaning unless explicitly set forth as such. Further, the present subject matter encompasses present and future known equivalents to the known components referred to herein by way of illustration.
[035] Although the present subject matter describes a propeller assembly, it is to be further understood that numerous changes may arise in the details of the embodiments of the propeller assembly. It is contemplated that all such changes and additional embodiments are within the true scope of this subject matter.
[036] The following detailed description is merely exemplary in nature and is not intended to limit the described embodiments or the application and uses of the described embodiments. As used herein, the word “exemplary” or “illustrative” means “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” or “illustrative” is not necessarily to be construed as preferred or advantageous over other implementations. All of the implementations described below are exemplary implementations provided to enable persons skilled in the art to make or use the embodiments of the subject matter and are not intended to limit the scope of the subject matter.
[037] It should be understood that the present invention describes a propeller assembly for connecting a blade and reducing vibration. The propeller assembly includes an adapter having a first plate and a second plate. The first plate indicates a bottom plate and the second plate indicates a top plate. The propeller assembly includes blades, each blade comprising a body portion having a root at one end and a tip at another end. The first plate includes raised sections. The raised sections extend from the first plate facing the second plate. Each raised section includes a groove that configures to receive a dampening member. The dampening member connects and locks the position of the blade. Further, the dampening member absorbs and mitigates minor vibrations caused during the flight and gives better stability to the propeller assembly and the aircraft such as a drone incorporating the propeller assembly.
[038] Various features and embodiments of a propeller assembly for connecting a blade and reducing vibration are explained in conjunction with the description of FIGURES (FIGs) 1A-13.
[039] The present invention discloses a propeller assembly for connecting a blade and reducing vibration. FIGs. 1A and 1B show a top perspective view and a bottom perspective view, respectively of a propeller assembly 10, in accordance with one embodiment of the present invention. Propeller assembly 10 includes an adapter or hub or adapter hub or central hub 12. Propeller assembly 10 includes blades or rotor blades or propeller blades 14 removably affixed to adapter 12. In the present embodiment, two blades 14 affix to adapter 12, as shown in FIGs. 1A and 1B. However, a person skilled in the art understands that more than two blades 14 can be affixed in further embodiments of the present invention (including 3, 4 or more blades), or a single blade with a counterweight on the opposite side of adapter 12. As such, adapter 12 in the present invention is configured to receive a pair of blades 14 but can be altered to receive one or more blades 14.
[040] FIGs. 2A and 2B show a top perspective view and a front view, respectively of adapter 12, in accordance with one embodiment of the present invention. Adapter 12 includes a first plate 16 and a second plate 18. First plate 16 indicates a bottom or lower plate and second plate 18 indicates a top or upper plate. First plate 16 and second plate 18 form two separate halves which are connected to each other using a known mechanism. In one example, adapter 12 comes as assembled or unitary construction. Each of first plate 16 and second plate 18 is made of metal, hard plastic or any other suitable material such as a composite material, for example.
[041] FIGs. 3A and 3B show a top perspective view and a front view, respectively of first plate 16, in accordance with one embodiment of the present invention. First plate 16 encompasses a flat portion 20. Flat portion 20 presents shoulder portion 22 extending from both sides of flat portion 20. Shoulder portion 22 includes a first centre hole 23 and first holes 24. First centre hole 23 positions at the centre region of flat portion 20 and first holes 24 position adjacent to and surround first centre hole 23. First centre hole 23 and first holes 24 align with second centre hole 46 and second holes 58 of second plate 18 to receive a motor drive shaft (not shown). The motor drive shaft is threaded to adapter 12 to rotate with the motor drive shaft. The motor drive shaft attaches to adapter 12 in any form as known in the art for corresponding rotation of adapter 12 and attached blades 14. Further, flat portion 20 presents first side holes 26. First side holes 26 position at proximal or distal ends of flat portion 20.
[042] In accordance with the present embodiment, flat portion 20 encompasses raised sections 28. Raised sections 28 extend adjacent to shoulder portion 22 facing second plate 18. Each raised section 28 encompasses a groove 30 for receiving a dampening member 38. Groove 30 extends the entire length i.e., height of raised section 28, as can be seen from at least FIG. 3A. Groove 30 includes flat section 32, a semi-circular section 34 and an opening 36. In the present embodiment, groove 30 configures to receive dampening member 38. Dampening member 38 indicates an insert member that fits in groove 30 and connects to blade 14. Dampening member 38 is made of silicone, rubber, plastic or any other suitable material. Dampening member 38 is rigid and can withstand wear and tear for a long period of time. FIGs. 4A and 4B show a side perspective view and a top view, respectively of dampening member 38, in accordance with one embodiment of the present invention. Dampening member 38 includes a flat portion 40 and an extending portion 42. Extending portion 42 extends from flat portion 40 and includes a curved section 44. Extending portion 42 presents a smooth configuration to engage with blade 14. In the present invention, dampening member 38 inserts in groove 30 of raised section 28. Here, dampening member 38 aligns with groove 30 such that flat portion 40 aligns with flat section 32 and extending portion 42 aligns with opening 36. Subsequently, groove 30 receives dampening member 38, as shown in FIG. 3A. As can be seen, curved section 44 allows dampening member 38 to fit at distal end of semi-circular section 34 leaving a portion of extending portion 42 to protrude out from raised section 28. The portion of extending portion 42 protruding out from raised section 28 engages or locks with blade 14 and helps to reduce the vibrations caused during the flight.
[043] Now referring to FIGs. 2A, 2B and 5, constructional features of second plate 18 are explained. Second plate 18 encompasses a flat portion 45. Flat portion 45 encompasses second centre hole 46 and second holes 48. Second centre hole 46 positions at the centre region of flat portion 45 and second holes 48 position adjacent to and surrounding second centre hole 46. Second centre hole 46 and second holes 48 align with first centre hole 23 and first holes 24 of first plate 16 to receive the motor drive shaft, as explained above. The motor drive shaft is threaded to adapter 12 to rotate with the motor drive shaft. The motor drive shaft attaches to adapter 12 in any form as known in the art for corresponding rotation of adapter 12 and attached blades 14. Further, flat portion 45 presents second side holes 50. Second side holes 50 position at proximal or distal ends of flat portion 45, as shown in at least FIG. 5. Second side holes 50 align with first side holes 26 when first plate 16 and second plate 18 are staked or connected together.
[044] Adapter 12 includes connecting members 52. Connecting members 52 indicate fasteners or screws used for connecting first plate 16 and second plate 18. Each fastener 52 encompasses a shaft or elongated body 54 having head 56 at one end and threaded portion 58 at another end. In use, shaft 54 inserts through second side holes 50 (as shown in FIG. 5) and first side holes 26 such that threaded portion 58 protrudes below first plate 16. Subsequently, threaded portion 58 receives a locking unit or nut 60 to lock the position of connecting member 52 and to connect first plate 16 and second plate 18, as shown in at least FIG. 2B.
[045] FIGs. 6 and 7 show a perspective view and a top view, respectively of blade 14, in accordance with the present invention. Blade 14 includes a body portion 62. Blade 14 is made of metal, plastic, composite material or any other suitable material. Blade 14 is configured to provide a forward thrust to an aircraft (not shown) when propeller assembly 10 is connected and rotated with the motor (not shown) within the aircraft. Here, the aircraft includes, but not limited to, a drone or unmanned aerial vehicle (UAV), helicopter or multicopter, wind turbine, etc. A person skilled in the art understands blade 14 comes in different sizes and configurations for providing forward thrust depending on the size of the aircraft or the environment in which the aircraft is used.
[046] Body portion 62 encompasses a root or connecting end 64 at one end and a tip 66 at another end. Root 64 encompasses a blade hole or connecting hole 68. Connecting hole 68 configures to receive connecting member 52 and helps to connect blade 14 to adapter 12. In accordance with the present invention, root 64 includes a first notch or forward notch 70 and second notches or side notches 72. First notch 70 positions parallel to the central axis of body portion 62. Second notches 72 position perpendicularly to first notch 70 opposite to each other. In the present embodiment, two second notches 72 are provided at the opposite side of root 64 to allow folding of blade 14 in both directions. However, it is possible to provide a single second notch 72 at only one side of root 64 to fold blade 14 in one side. Such an implementation falls within the scope of the present invention. Each of first notch 70 and second notches 72 comes in a curved (semi-circle) configuration and configures to align and fits over the extending portion 42 of dampening member 38 protruding out from raised section 28. In other words, each of first notch 70 and second notches 72 has a smooth concave configuration and receives the convex shape of extending portion 42 of dampening member 38. In one implementation, adapter 12 includes spacer plates 74 positioned in between root 64, and first plate 16 and second plate 18. Spacer plates 74 are made of synthetic material such as Polytetrafluoroethylene (PTFE) or any other suitable material. Spacer plates 74 help to avoid direct contact between root 64 and first plate 16 and second plate 18.
[047] In order to connect blade 14 to adapter 12, at first, first notch 70 of root 64 is made to face raised section 28. Subsequently, first notch 70 is positioned adjacent to connecting extending portion 42. Further, connecting hole 68 is aligned with first side hole 26 and second side hole 50 of first plate 16 and second plate 18, respectively. Further, connecting member 52 inserts through first side hole 26 and second side hole 50 and receives locking unit 60 at its threaded portion 58. FIG. 8 shows the feature of blade 14 connecting adapter 12. FIG. 9 shows the feature of blades 14 connecting adapter 12 from both sides.
[048] FIGs. 1A and 1B show propeller assembly 100 in a flight state or during flight, in accordance with one exemplary embodiment. The flight state refers to a condition (flying condition) in which propeller assembly 100 attaches to the motor of the aircraft. In the flight state (e.g., as the propeller blades rotate), blades 14 extend to a flight configuration to enable the generation of lift due to centrifugal forces imparted on blades 14. In other words, in the flight state, blades 14 of propeller assembly 100 rotate and lift is generated on blades 14 (and consequently the aircraft that propeller assembly 100 is attached to). In the flight state, propeller assembly 100 is attached to an arm or wing of the aircraft. During the operation, blades 14 rotate in a clockwise direction such that tip 66 of each blade 14 meets the air and provides forward thrust. As presented above, the presently disclosed adapter 12 encompasses dampening member 38 and root 64 of blade 14 encompasses first notch 70 that connects or engages dampening member 38. In other words, during the flight, first notch 70 of blade 14 locks onto dampening member 38 placed inside adapter 12. As the profile of first notch 70 receives the protruding portion of dampening member 38, the vibration caused by fast rotating blade 14 gets absorbed by dampening member 38. Dampening member 38 absorbs or dampens the vibration and ensures the vibration does not get transferred to any other part of adapter 12 and ensures aerodynamic balance for the entire propeller assembly 100 and the aircraft. In other words, dampening member 38 dampens the vibrations caused due to aerodynamic imbalance caused by blades 14 while also locking blades 14 in position with adapter 12.
[049] Propeller assembly 100 transitions from the flight state to a folded state as shown in FIGs. 10 and 11. FIG. 10 shows an exploded view of the components aligned in the folded state. FIG. 11 shows propeller assembly 100 in the folded state. The folded state is achieved when blades 14 (propeller assembly 100 and the aircraft) are not in use or when propeller assembly 100 is at rest i.e., when no external forces are applied on propeller assembly 100. Blades 14 fold to minimize the overall footprint of propeller assembly 100 compared to the overall footprint of propeller assembly 100 when in the flight state (e.g., propeller assembly 100 shown in FIGs. 1A and 1B). In order to fold blades 14, each blade 14 rotates in the opposite direction. For example, right side blade 14 rotates in a clockwise direction and left side blade 14 rotates in an anticlockwise direction. During the transition from the flight state to the folded state, root 64 of each blade 14 rotates corresponding to rotation of blade 14. Due to the force exerted on blade 14 to rotate, first notch 70 disengages with dampening member 38. As blade 14 rotates about 90 degrees, one of second notches 72 aligns and engages with dampening member 38. Once engaged, second notch 72 at each blade 14 gets locked with dampening member 38, as shown in at least FIG. 10. As a result, blades 14 remain in position in the folded state. In case a user (not shown) wishes to operate propeller assembly 100 in the flight state, then the user rotates blades 14 manually or using an automated mechanism to connect first notch 70 to dampening member 38, as shown in FIGs. 1A, 1B and 9, for example.
[050] In one implementation, each blade 14 is designed to have a different tip 68 to allow one blade 14 to position underneath another blade 14 in the folded state. In one example, the entire structure of body portion 62 and tip 66 of each blade 14 is provided with a different configuration to position one blade 14 underneath another blade 14 in the folded state. In another example, one blade 14 is designed with an angle of attack at the tip 66, which is different from the angle of attack at the tip 66 of another blade 14. In yet another example, both blades 14 are designed to have the same angle of attack at their respective tips 66. In yet another example, both blades 14 are designed to have different angle of attack along the length of body portion 62 to enable a portion of one blade 14 to nest underneath another blade 14.
[051] FIG. 12 shows an adapter 100 having three arms for connecting three blades, in accordance with another embodiment of the present invention. Adapter 100 encompasses a first plate 102. First plate 102 indicates a bottom plate. First plate 102 is made of metal, plastic or any other suitable material. First plate 102 comes in a flat configuration having a centre portion 104 and three first arms 106. Each of the first arm 106 extends at about 120 degrees from centre portion 104. Centre portion 104 presents raised section 107 having holes 108 for receiving a motor drive shaft for rotation of adapter 100. Further, each of first arms 106 includes a side slot 110. Side slots 110 receive connecting members or fasteners 126 for connecting first plate 102 and second plate 118. In accordance with the present embodiment, raised section 107 provides groove 112 (similar to groove 30 in FIG. 3A). Groove 112 configures to receive dampening member or insert 114 (similar to dampening member 38 in FIG. 3A). In one implementation, adapter 100 includes spacer plates 116 positioned in between blades 140 and first plate 102 and second plate 118. Spacer plates 116 are made of synthetic material such as Polytetrafluoroethylene (PTFE) or any other suitable material. Spacer plates 116 help to avoid direct contact between blades 140 and first plate 102 and second plate 118. Spacer plates 116 encompass spacer hole 117 for drawings through connecting member 126.
[052] Adapter 100 further includes second plate 118. Second plate 118 indicates a top plate. Second plate 118 includes centre slot 120 and adjacent holes 121 for receiving the motor drive shaft. Second plate 118 includes second arms 122 extending at about 120 degrees. Each second arm 122 includes arm slot 124 for receiving connecting member 126. Connecting member 126 includes a shaft 128 having a head 130 at one end and threaded portion 132 at the other end. In order to connect first plate 102 and second plate 118 (and drawing blade 140 in between), connecting member 126 draws through arm slots 124, spacer holes 117, and side slots 110. Subsequently, threaded portion 132 receives a locking unit or nut 134 to lock the position of connecting member 126.
[053] The presently disclosed adapter 100 receives three blades 140 between first arms 106 and second arms 122. Each blade 140 includes a body portion 142 having a root 144 at one end and a tip (not shown) at another end. Similar to blade 14, root 144 of each blade 140 encompasses blade hole or connecting hole 146 for receiving connecting member 126 for connecting blade 140 between first plate 102 and second plate 118. Root 144 includes a first notch or forward notch 148 and second notches or side notches 150. First notch 148 positions parallel to the central axis of body portion 142. Second notches 150 position perpendicularly to first notch 148. In the present embodiment, two second notches 150 are provided at the opposite side of root 144 to allow folding of blades 140 in both sides/direction. However, it is possible to provide a single second notch 150 at only one side of root 144 to fold blade 140 in one side. Such an implementation falls within the scope of the present invention. Each of first notch 148 and second notches 150 come in a curved configuration and configures to align and fit over dampening member 114 protruding out from raised section 107.
[054] Blades 140 connect to adapter 100 and operate similarly to blades 14 during the flight state, explained above. Blades 140 also fold in the folded state such that one of second notches 150 aligns and engages with dampening member 114. Once engaged, second notch 150 at each blade 140 gets locked with dampening member 114.
[055] Based on the above, it is evident that the present invention discloses a unique propeller assembly having an adapter with dampening members to lock the position of the blades to the adapter and reduce the vibrations caused during the flight.
[056] A person skilled in the art appreciates that the propeller assembly may come in a variety of sizes depending on the need and comfort of the user. Further, different materials in addition to or instead of materials described herein may also be used and such implementations may be construed to be within the scope of the present subject matter. Further, many changes in the design and placement of components may take place without deviating from the scope of the presently disclosed propeller assembly.
[057] In the above description, numerous specific details are set forth such as examples of some embodiments, specific components, devices, methods, in order to provide a thorough understanding of embodiments of the present subject matter. It will be apparent to a person of ordinary skill in the art that these specific details need not be employed, and should not be construed to limit the scope of the subject matter.
[058] In the development of any actual implementation, numerous implementation-specific decisions must be made to achieve the developer's specific goals, such as compliance with system-related and business-related constraints. Such a development effort might be complex and time-consuming, but may nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill. Hence as various changes could be made in the above constructions without departing from the scope of the subject matter, it is intended that all matter contained in the above description or shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense.
[059] The foregoing description of embodiments is provided to enable any person skilled in the art to make and use the subject matter. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the novel principles and subject matter disclosed herein may be applied to other embodiments without the use of the innovative faculty. It is contemplated that additional embodiments are within the scope of the disclosed subject matter. , Claims: WE CLAIM:

1. A propeller assembly (10) for connecting a blade (14) and reducing vibration, the propeller assembly (10) comprising:
an adapter (12) having a first plate (16) and a second plate (18), wherein the first plate (16) indicates a bottom plate and the second plate (18) indicates a top plate; and
blades (14), each blade (14) comprising a body portion (62) having a root (64) at one end and a tip (66) at another end;
characterized in that:
wherein the first plate (16) comprises raised sections (28), wherein the raised sections (28) extend from the first plate (16) facing the second plate (18), wherein each raised section (28) comprises a groove (30), wherein the groove (30) receives a dampening member (38),
wherein the root (64) comprises notches (70, 72), wherein the first plate (16) and the second plate (18) receive the root (64), wherein the dampening member (38) connects to a notch (70) of the notches (70, 72) to lock the position of blade (14) and to reduce the vibrations caused during the flight of an aircraft incorporating the propeller assembly (10), and wherein the dampening member (38) connects to another notch (72) upon rotating the blade (14) to lock the position of blade (14) in a folded state.

2. The propeller assembly (10) as claimed in claim 1, wherein the notch (70) aligns with a central axis of the blade (14), wherein the notches (72) position perpendicularly to the notch (70), wherein the blade (14) rotates in a clockwise direction and allows to connect one of notches (72) to the dampening member (38) to lock the blade (14) in the folded state, and wherein the rotates in an anti-clockwise direction and allows to connect another notch (72) to the dampening member (38) to lock the blade (14) in the folded state.

3. The propeller assembly (10) as claimed in claim 1, wherein the groove (30) comprises a flat section (32), a semi-circular section (34) and an opening (36).

4. The propeller assembly (10) as claimed in claim 3, wherein the dampening member (38) comprises a flat portion (40) and an extending portion (42), wherein the extending portion (42) extends from the flat portion (40) and comprises a curved section (44), and wherein the flat section (32) aligns with the flat portion (40) and receives the dampening member (38) in the groove (30).

5. The propeller assembly (10) as claimed in claim 4, wherein a portion of the extending portion (42) protrudes from the raised section (28) and engages one of the notches (70, 72) to lock the position of blade (14).

6. The propeller assembly (10) as claimed in claim 1, wherein the aircraft comprises one of a drone or unmanned aerial vehicle (UAV), a helicopter, and a multicopter.

7. The propeller assembly (10) as claimed in claim 1, wherein each of the first plate (16) and the second plate (18) comprises side slots (26, 50), and wherein the side slots (26, 50) receive connecting members (52) for connecting the first plate (16) and the second plate (18).

8. An adapter (12, 100) for use with blades (14, 140), the adapter (12, 100) comprising:
a first plate (16, 102), wherein the first plate (16, 102) indicates a bottom plate; and
a second plate (18, 118), wherein the second plate (18, 118) indicates a top plate; and
characterized in that:
wherein the first plate (16, 102) comprises raised sections (28, 107), wherein the raised sections (28, 107) extend from the first plate (16, 102) facing the second plate (18, 118), wherein each raised section (28, 107) comprises a groove (30, 108), wherein the groove (30, 108) receives a dampening member (38, 114), wherein the dampening member (38, 114) engages notches (70, 72, 148, 150) provided at a root (64, 144) of a blade (14, 140), wherein the dampening member (38, 114) engages a notch (70, 148) of the notches (70, 72, 148, 150) for locking the position of the blade (14, 140) and for absorbing the vibrations caused during the rotation of the blade (14, 140), and wherein the dampening member (38, 114) engages with another notch (72, 150) of the notches (70, 72, 148, 150) for locking the position of the blade (14, 140) in a folded state.

9. The adapter (12) as claimed in claim 8, wherein each of the first plate (16, 102) and the second plate (18, 118) comprises two or more arms (122), each comprising side slots (26, 50, 110, 124), and wherein the side slots (26, 50, 110, 124) receive connecting members (52, 126) for connecting the first plate (16, 102) and the second plate (18, 118).

10. The adapter (12) as claimed in claim 8, wherein the dampening member (38, 114) dampens the vibration caused during the rotation of the blade (14, 140) and ensures the vibration does not get transferred to the raised sections (28, 107), the first plate (16, 102) and the second plate (18, 118).