Description:DESCRIPTION OF THE INVENTION
FIELD OF THE INVENTION
The present invention relates to a detachable landing gear assembly for aerial vehicles. Particularly, the present invention relates to a detachable landing gear assembly with shock absorbing capability, thereby ensuring smooth landing of aerial vehicles.
BACKGROUND OF THE INVENTION
Aerial vehicles such as unmanned aerial vehicles (UAVs) plays vital role as are used for performing surveillance, reconnaissance, and exploration tasks for military and civilian applications. Such vehicles may carry a payload configured to perform a specific function. However, certain functions that are performed by aerial vehicles may be limited by the mobility of a vehicle that requires flight. In particular, various desired functions may be limited to conditions that are not ideal for flying the aerial vehicle.
Landing gear is one of the critical component of the aircraft as it supports the entire weight of an aircraft during landing and ground operations. Moreover, landing gear support critical structural aircraft load during taxi, takeoff, and landing operations.
Some of the traditional landing gear for aerial vehicles are non-detachable. Further, some of the traditional detachable landing gear comprises of heavy metallic components with complex design. Further, such traditional aerial vehicles are fragile, lacks user friendly nature, and are expensive.
Therefore, in view of the challenges associated with the above state of the art, there is a need for a user-friendly, lightweight, detachable landing gear assembly with minimal maintenance requirements.

OBJECT OF THE INVENTION
The primary objective of the present invention is to provide a detachable landing gear assembly for aerial vehicles.
Another objective of the present invention is to provide a detachable landing gear assembly with shock absorbing capability during landing, thereby ensuring smooth landing of aerial vehicles.
Another objective of the present invention is to provide a user-friendly, lightweight, detachable landing gear assembly with minimal maintenance requirement.
Yet another objective of the present invention is to provide landing gear leg assembly with easy installation process.
Yet another objective of the present invention is to provide cheap and easy to manufacture landing gear assembly.
Other objects and advantages of the present invention will become apparent from the following description taken in connection with the accompanying drawings, wherein, by way of illustration and example, the aspects of the present invention are disclosed.
SUMMARY OF THE INVENTION
Before the present system and method, are described, it is to be understood that this application is not limited to the particular system, and methodologies described, as there can be multiple possible embodiments that are not expressly illustrated in the present disclosures. It is also to be understood that the terminology used in the description is for the purpose of describing the particular implementations or versions or embodiments only and is not intended to limit the scope of the present application. This summary is provided to introduce aspects related to a device and a method for high voltage sub-station design. This summary is not intended to identify essential features of the claimed subject matter, nor is intended for use in determining or limiting the scope of the claimed subject matter. The following statement clearly sets forth the distinguishing features of the invention. Different aspects of the inventions are declared here.
In an aspect, the present invention provides a detachable landing gear assembly for an aerial vehicle. This assembly includes a landing gear mount with an open end and a closed end, designed to be mounted on the outer surface of the aerial vehicle. The landing gear mount features at least two pairs of full-length slots along its inner surface and two types of L-shaped slots along its circumference. These slots facilitate the secure housing and locking of various components within the landing gear assembly, ensuring stability and integrity during operation.
In another aspect, the invention incorporates a locking spring co-axially housed at the closed end of the landing gear mount. This locking spring is designed to be held in a semi-compressed state by a spring holder, which has at least two pairs of protrusions. These protrusions fit into the full-length slots and the first type of L-shaped slots, securing the spring holder in place. The vertical tube cap, also featuring protrusions, is lockable within the landing gear mount using the full-length slots and the second type of L-shaped slots. This configuration ensures that the locking spring can absorb shocks effectively, enhancing the safety and durability of the aerial vehicle during landings.
In yet another aspect, the vertical tube is coupled to the vertical tube cap at one end and to a horizontal tube at the other end. The horizontal tube forms the base of the landing gear assembly and can include horizontal tube end caps at each end for additional stability. The vertical and horizontal tubes are made of carbon fiber-reinforced plastic, contributing to the lightweight and robust nature of the assembly. The landing gear mount, spring holder, and vertical tube cap can be made of plastic material, while the locking spring is made of stainless steel, ensuring a durable and reliable construction.
In a further aspect, the detachable landing gear assembly features a straightforward locking and unlocking mechanism for the vertical tube. Locking involves inserting the vertical tube into the landing gear mount, guiding the protrusions along the full-length slots, rotating the tube by a predetermined angle while pressing along the z-axis, and then releasing the pressure. Unlocking is achieved by rotating the tube in the opposite direction, pressing along the z-axis, and guiding the protrusions out of the full-length slots. This user-friendly mechanism simplifies the installation and removal process, ensuring ease of use and minimal maintenance requirements for the aerial vehicle operators.
BRIEF DESCRIPTION OF DRAWINGS
The foregoing detailed description of embodiments is better understood when read in conjunction with the appended drawings. For the purpose of illustrating the present subject matter, an example of a construction of the present subject matter is provided as figures, however, the invention is not limited to the specific landing gear assembly for unmanned aerial vehicle.
Figure 1 illustrates top isometric view of the detachable landing gear assembly for unmanned aerial vehicle.
Figure 2 illustrates top isometric exploded view of the detachable landing gear assembly for unmanned aerial vehicle.
Figure 3A illustrates bottom isometric exploded view of the detachable landing gear assembly for unmanned aerial vehicle.
Figure 3B is an exemplary view of open end of a landing gear mount.
Figure 3C is an exemplary view of a spiring holder.
Figure 3D is an exemplary view of a vertical tube cap.
Figure 4A is a vertical sectional view of a landing gear mount.
Figure 4B is a bottom hey isometric sectional view of a landing gear mount.
Figure 5 is the vertical sectional view of the landing gear assembly in locked mode.
Figure 6 is the vertical sectional view of the landing gear assembly in unlocked mode.
The figure depicts an embodiment of the present disclosure for purposes of illustration only. One skilled in the art will readily recognize from the following discussion that alternative embodiments of the structures and methods illustrated herein may be employed without departing from the principles of the disclosure described herein.
DETAILED DESCRIPTION OF THE INVENTION
The following description describes various features and functions of the disclosed system with reference to the accompanying figures. In the figures, similar symbols identify similar components, unless context dictates otherwise. The illustrative aspects described herein are not meant to be limiting. It may be readily understood that certain aspects of the disclosed system can be arranged and combined in a wide variety of different configurations, all of which have not been contemplated herein.
Accordingly, those of ordinary skill in the art will recognize that various changes and modifications of the embodiments described herein can be made without departing from the scope of invention. In addition, descriptions of well-known functions and constructions are omitted for clarity and conciseness.
Features that are described and/or illustrated with respect to one embodiment may be used in the same way or in a similar way in one or more other embodiments and/or in combination with or instead of the features of the other embodiments.
The terms and words used in the following description are not limited to the bibliographical meanings, but, are merely used to enable a clear and consistent understanding of the invention. Accordingly, it should be apparent to those skilled in the art that the following description of exemplary embodiments of the present invention are provided for illustrative purpose only and not for the purpose of limiting the invention.
It is to be understood that the singular forms “a”, “an” and “the” include plural referents unless the context clearly dictates otherwise.
It should be emphasized that the term “comprises/comprising” when used in this specification is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps, components or groups thereof.
Accordingly, the present invention discloses a detachable landing gear assembly (100) for aerial vehicles. Particularly, the present invention relates to a detachable landing gear assembly (100) with shock absorbing capability, thereby ensuring smooth landing of the aerial vehicles.
Now referring to Fig. 1, the detachable landing gear (100) for aerial vehicles comprises of a horizontal part and a vertical part. At an outset the vertical part comprises of landing gear mount, and a vertical tube. The horizontal part comprises of horizontal tube (106) and horizontal tube (106) caps. The horizontal part and vertical part are connected to each other through a tube connector using a plurality of fasteners.
In an embodiment detachable landing gear is mounted on an aerial vehicle. The landing gear mount (101) present on the top of the vertical part is fixed on the aerial vehicle using plurality of fasteners such as landing gear mount (101) screw. The horizontal part provides a landing base to the aerial vehicle. The horizontal part and the vertical tube (105) can be detached from the landing gear mount (101).
In an embodiment the aerial vehicle maybe an aircraft, an unmanned aerial vehicle, a drone, aeroplane, or any other vehicle which requires a landing gear assembly (100) to land on ground. In an embodiment the plurality of fasteners used to connect the vertical part and horizontal part through a tube connector could be a plurality of position screw.
Now referring to figure 2, a top isometric exploded view of the detachable landing gear for aerial vehicles is shown. The figure illustrates key components involved in the mechanism of the detachable landing gear (100).
In an aspect the detachable landing gear (100) for aerial vehicles comprises of a landing gear mount (101). The landing gear mount (101) is a hollow cylindrical vertical structure having and open end (101A) and a closed end (101B). The landing gear mount (101) is open from bottom and is closed from top. The landing gear mount (101) is a fixed part of the detachable landing gear assembly (100) and the other part comprising of the horizontal tube (106) and vertical tube (105) are attachable and detachable from the landing gear mount. As shown in figure 2 the landing gear mount (101) houses small parts which forms the basis for detachable landing gear assembly (100) and the shock absorbing mechanism. In an embodiment the landing gear mount (101) may be made up of a plastic material.
The inner construction the landing gear mount (101) is illustrated in figures 4A and 4B. Figure 4A shows vertical sectional view of the landing gear mount (101) and the figure 4B show bottom isometric sectional view of the landing gear mount (101). In the aspect the inner construction of the landing gear mount (101) comprises of two types of slots: horizontal and vertical. As shown in figure 4B, the vertical slots are a full-length slot (101C) running along the length on the inner surface of the landing gear mount (101) starting from the open and to the closed end (101B). As shown in figure 4A, the horizontal slots are L-shaped slots present along the circumference on the inner side only inner surface of the landing gear mount. These are fixed length slots. There are two types of horizontal slots: first type L-shaped slots (101D) and a second type L-shaped slots (101E). The number of each type of horizontal slots is less than or equal to the number of vertical slots. Thereby, each horizontal slot corresponds to a full-length vertical slot. The L-shaped slots start horizontally from the corresponding vertical full-length slot (101C) and then turns vertically downwards to complete an L-shape. The first type of L-shaped slots (101D) are present vertically above the second type L-shaped slots (101E). In a preferred embodiment, the number of each type of horizontal slots is equal to the number of vertical slots, the number being equal to four slots.
In another aspect, the detachable landing gear mount (101) co-axially houses a locking spring (102) at the closed end (101B) as shown in figure 2. The locking spring (102) is designed to absorb shocks on impact of the landing gear assembly (100) on landing surface. In an embodiment the locking spring (102) is made up of stainless steel material. In another embodiment locking spring (102) is coaxially housed using a cylindrical groove (101F).
In another aspect, the detachable landing gear assembly (100) comprises of a spring holder (103) as shown in figure 2 and 3A. As illustrated in figure 3C, the spring holder (103) have at least two pairs of protrusions (103A) on its outer surface. The spring holder (103) is removably housed in the landing gear mount (101) using the at least two pairs of full-length slot (101C) and the at least two pairs of first L-shaped slot (101D) such that the locking spring (102) is held in a semi-compressed state. The plurality of protrusions (103A) on the outer surface of the spring holder (103) guide the spring holder (103) during insertion and removal from the landing gear mount (101). The spring holder (103) upon it’s insertion through full length slots (101C) is locked by rotating it while applying an inward axial force, thereafter releasing the force upon rotation. The plurality of protrusions (103A) on the outer surface of the spring holder (103) gets locked in the vertical part of the corresponding first L-shaped slot (101D) using a force from the locking spring. In a preferred embodiment, the spring holder (103) may be made up of material such as plastic.
In a preferred embodiment, the spring holder (103) maybe pre-locked into the landing gear mount (101) before it is made available to the user for use. The spring holder (103) can be removed from the landing gear mount (101), however it may not be considered as a detachable part for the user.
In an embodiment the spring holder (103) holds the locking spring (102) in a semi compressed state. This semi compressed locking spring (102) provides necessary outward force to lock the spring holder (103) into the landing gear mount (101). The semi compressed locking spring (102) exhibits shock absorption capability during the landing of the landing gear leg assembly (100). As the locking spring (102) is used in a semi compressed state, there is some extra space available for the locking spring (102) to further compress when force is applied on it. This force could arise due to impact of the landing gear assembly (100) with the landing surface ensuring minimal impact on the aerial vehicle and safety of other parts of the aerial vehicle. This is essential especially in cases such as harsh or fast altitude descend sequence with high de-acceleration, emergency landing, or landing on uneven surface. This shock absorbing capabilities make the aerial vehicle tolerate hard landing.
In another aspect, the detachable landing gear assembly (100) comprises of a vertical tube (105) and a vertical tube cap (104) as shown in figure 2 and 3A. The vertical tube (105) is a vertical structure is mechanically coupled to the vertical tube cap (104) at its upper end. The coupling may be a threaded connection, a press fit, a welded joint, a bolted connection, a pinned connection, a clamp or sleeve connection, or an adhesive bonding. The vertical tube (105) is attachable to and detachable from the landing gear mount. In a preferred embodiment, the vertical tube (105) is made up of carbon fibre reinforced plastic. As illustrated in figure 3D, the vertical tube cap (104) is also a cylindrical structure having at least two pairs of protrusions (104A) on its outer surface. The number of pairs of protrusions (104A) is less than or equal to the number of full-length slots (101C). In a preferred embodiment, number of pairs of protrusions (104A) is equal to the number of full-length slots (101C), the number being equal to two. The Semi-compressed locking springs (102) allows the vertical tubes (105) of the landing gear (100) to be fixed without any wobbling or loose fitting and also the vertical tube (105) can move further inside when load is applied on the vertical tube from bottom.
The vertical tube cap (104) is removably housed in the landing gear mount (101) using the at least two pairs of full-length slot (101C) and the at least two pairs of second L-shaped slot (101E) such that the locking spring (102) is held in a semi-compressed state. The plurality of protrusions (104A) on the outer surface of the vertical tube cap (104) guide the spring holder (103) during insertion and removal from the landing gear mount (101). The vertical tube cap (104) upon it’s insertion through full length slots (101C) is locked by rotating it while applying an inward axial force, thereafter releasing the force upon rotation. The plurality of protrusions (104A) on the outer surface of the vertical tube cap (104) gets locked in the vertical part of the corresponding second L-shaped slot (101E) using a force from the locking spring (102). In a preferred embodiment, the vertical tube cap (104) may be made up of material such as plastic.
In a preferred embodiment, the vertical tube cap (104) maybe locked into the landing gear mount (101) by the user as per user requirement. In another embodiment, the detachable mechanism of the vertical tube (105) and vertical tube cap (104) allows for use of different landing gear with the same mount (101). The user may use different landing gear based on different use case of the aerial vehicle.
In an embodiment the vertical tube cap (104) is locked by the semi compressed locking spring (102). This semi compressed locking spring (102) provides necessary outward force to lock the vertical tube cap (104) into the landing gear mount (101). The semi compressed locking spring (102) exhibits shock absorption capability during the landing of the landing gear assembly (100). As the locking spring (102) is used in a semi compressed state, there is some extra space available for the locking spring (102) to further compress when force is applied on it. This force could arise due to impact of the landing gear assembly (100) with the landing surface ensuring minimal impact on the aerial vehicle and safety of other parts of the aerial vehicle. This is essential especially in cases such as harsh or fast altitude descend sequence with high de-acceleration, emergency landing, or landing on uneven surface. This shock absorbing capabilities make the aerial vehicle tolerate hard landing.
In another aspect, vertical tube (105) is connected to the horizontal tube (106) at its lower end through a tube connector (108) using a plurality of fasteners (109) as shown in figure 1. The horizontal tube (106) forms the base of the landing gear assembly (100) and prevents the aerial vehicle from toppling. The plurality of fasteners (109) prevents rotational and translational motion between the horizontal tube (106) and the vertical tube. Further, the detachable landing gear assembly (100) comprises of at least one horizontal tube end cap (109) each fixed that each end of the horizontal tube (106). Horizontal tube end cap (109) prevents the aerial vehicle from slipping off the landing surface. In a preferred embodiment the horizontal tube (106) is made up of materials such as carbon fibre reinforced plastic. In an embodiment, the plurality of fasteners maybe plurality of screws.
In an aspect, locking the vertical tube (105) into the landing gear mount (101) involves inserting the vertical tube (105) into the landing gear mount (101) by guiding each of the at least two pairs of protrusions on the vertical tube cap (104) along the corresponding at least two pairs of full-length slot (101C) on the landing gear mount. Upon inserting, when an opposing force is felt by the user, the vertical tube (105) is rotated by a pre-determined angle in a pre-determined direction while pressing the vertical tube (105) along the z-axis. Upon, complete rotation by a pre-determined angle in a pre-determined direction, the pressure or force is released over the vertical tube. The assembly of all the housed parts in the landing gear mount (101) in locked mode is illustrated in figure 5. The pre-determined angle depends on the construction of the landing gear assembly (100) and is generally determined by number of full-length slot (101C) and number of second L-shaped slots. The pre-determined direction also depends on the construction of the second L-shaped slot (101E) whether clockwise or counter-clockwise along the surface. In a preferred embodiment, the pre-determined angle is 45 degrees and the pre-determined direction is clockwise towards right side. Further, the z-axis direction is the vertically upward direction along the axis of the vertical tube (105).
In another aspect, unlocking the vertical tube (105) from the landing gear mount (101) involves rotating the vertical tube (105) by a pre-determined angle in an opposite pre-determined direction while pressing the vertical tube (105) along the z-axis. Upon, complete rotation by a pre-determined angle in a pre-determined direction, the vertical tube (105) is removed from the landing gear mount (101) by guiding each of the at least two pairs of protrusions on the vertical tube cap (104) along the corresponding at least two pairs of full-length slot (101C) on the landing gear mount. The assembly of all the housed parts in the landing gear mount (101) in unlocked mode is illustrated in figure 6. The pre-determined angle depends on the construction of the landing gear assembly (100) and is generally determined by number of full-length slot (101C) and number of second L-shaped slots. The pre-determined direction also depends on the construction of the second L-shaped slot (101E) whether clockwise or counter-clockwise along the surface. In a preferred embodiment, the pre-determined angle in this aspect is 45 degrees and the pre-determined direction is counter-clockwise direction i.e. towards left side. Further, the z-axis direction is the vertically upward direction along the axis of the vertical tube (105).
Advantageously, the present invention offers a detachable landing gear assembly that significantly enhances the versatility and performance of unmanned aerial vehicles (UAVs). The innovative design allows for easy attachment and detachment, providing flexibility in operations and maintenance. This is particularly beneficial for UAVs used in various missions where different landing gear configurations may be required. The detachable mechanism, facilitated by the tube connector and the plurality of fasteners, ensures a secure yet easily removable connection between the horizontal and vertical parts. This feature not only simplifies the maintenance process but also reduces the time and effort required for gear replacement or repairs, thus minimizing downtime and enhancing operational efficiency.
Furthermore, the shock-absorbing capability of the landing gear assembly ensures smoother landings, which is critical for the safety and longevity of UAVs. The integration of a locking spring (102) within the landing gear mount (101) plays a crucial role in absorbing shocks during landing. This semi-compressed spring is designed to compress further upon impact, thereby dissipating the energy and reducing the force transmitted to the UAV's structure. This mechanism is particularly advantageous during harsh or emergency landings, where the ability to absorb shocks can prevent damage to the UAV and its components. The inclusion of L-shaped slots (101D and 101E) and vertical slots (101C) further ensures the secure locking of the spring holder (103) and the vertical tube cap (104), maintaining the stability and integrity of the landing gear during and after landing.
Additionally, the user-friendly design of the landing gear assembly emphasizes ease of installation and minimal maintenance requirements. The lightweight construction, achieved through the use of materials such as carbon fiber-reinforced plastic for the vertical tube (105) and horizontal tube (106), contributes to the overall efficiency and performance of the UAV. The precise engineering of the vertical tube cap (104) and its alignment with the full-length slots (101C) and L-shaped slots ensures a straightforward installation process. Users can easily lock and unlock the vertical tube (105) from the landing gear mount (101) by following simple rotational and axial movements, as described in the detailed assembly instructions. This not only enhances user convenience but also reduces the potential for installation errors, ensuring consistent performance and reliability of the landing gear assembly.

Reference Numeral Component Description
100 Detachable landing gear assembly
101 Landing gear mount
101A Open end of landing gear mount
101B Closed end of landing gear mount
101C Full-length slot in landing gear mount
101D First type L-shaped slot in landing gear mount
101E Second type L-shaped slot in landing gear mount
101F Cylindrical groove for housing locking spring
102 Locking spring
103 Spring holder
103A Protrusions on the outer surface of spring holder
104 Vertical tube cap
104A Protrusions on the outer surface of vertical tube cap
105 Vertical tube
106 Horizontal tube
107 Horizontal tube end cap
108 Tube connector
109 Tube connector Fasteners

, Claims:CLAIMS
We claim,
1. A detachable landing gear assembly (100) for aerial vehicles, comprising:
a landing gear mount (101), having an open end (101A) and a closed end (101B), mounted on outer surface of an unmanned aerial vehicle comprising:
at least two pairs of a full-length slot (101C) along the length, on the inner surface of the landing gear mount (101),
at least two pairs of a first L-shaped slot (101D) along the circumference, on the inner surface of the landing gear mount (101),
at least two pairs of a second L-shaped slot (101E) along the circumference, on the inner surface of the landing gear mount (101),
a locking spring (102) co-axially housed at the closed end (101B) of the landing gear mount (101);
a spring holder (103) having at least two pairs of protrusions (103A), removably housed in the landing gear mount (101) using the at least two pairs of full-length slots (101C) and the at least two pairs of first L-shaped slots (101D) to hold the locking spring (102) in a semi-compressed state;
a vertical tube cap (104) having at least two pairs of protrusions (104A) lockable in the landing gear mount (101) using the at least two pairs of full-length slots (101C) and the at least two pairs of second L-shaped slots (101E);
a vertical tube (105) coupled to the vertical tube cap (104) at one end and to a horizontal tube (106) at other end.
2. The detachable landing gear assembly (100) for aerial vehicles as claimed in claim 1 wherein the detachable landing gear assembly (100) comprises of at least one horizontal tube end cap (107) each fixed at each end of the horizontal tube (106).
3. The detachable landing gear assembly (100) for aerial vehicles as claimed in claim 1 wherein the landing gear mount (101), the spring holder (103), and the vertical tube cap (104) is made up of plastic material.
4. The detachable landing gear assembly (100) for aerial vehicles as claimed in claim 1 wherein the locking spring (102) is made up of stainless steel material.
5. The detachable landing gear assembly (100) for aerial vehicles as claimed in claim 1 wherein the vertical tube (105) and the horizontal tube (106) is made up of carbon fiber reinforced plastic.
6. The detachable landing gear assembly (100) for aerial vehicles as claimed in claim 1 wherein locking the vertical tube (105) into the landing gear mount (101) comprises steps of:
inserting the vertical tube (105) into the landing gear mount by guiding each of the at least two pairs of protrusions (104A) on the vertical tube cap (104) along the corresponding at least two pairs of full-length slots (101C) on the landing gear mount (101);
rotating the vertical tube (105) by a pre-determined angle in a pre-determined direction while pressing the vertical tube (105) along the z-axis;
releasing the pressure over the vertical tube (105).
7. The detachable landing gear assembly (100) for aerial vehicles as claimed in claim 1 wherein unlocking the vertical tube (105) from the landing gear mount (101) comprises steps of:
rotating the vertical tube (105) by a pre-determined angle in an opposite pre-determined direction while pressing the vertical tube (105) along the z-axis;
removing the vertical tube (105) from the landing gear mount (101) by guiding each of the at least two pairs of protrusions (104A) on the vertical tube cap (104) along the corresponding at least two pairs of full-length slots (101C) on the landing gear mount (101).
8. The detachable landing gear assembly (100) for aerial vehicles as claimed in claim 1 wherein the vertical tube (105) is coupled to the horizontal tube (106) through a tube connector (108) using a plurality of fasteners (109).
9. The detachable landing gear assembly (100) for aerial vehicles as claimed in claim 1 wherein the locking spring (102) is designed to absorb shocks on impact of the landing gear assembly (100) with a landing surface.

Dated: 2nd July 2024