WO2024105643A1

WO2024105643A1 - An apparatus for soft landing of an unmanned aerial vehicle

Info

Publication number: WO2024105643A1
Application number: PCT/IB2023/061685
Authority: WO
Inventors: Sandeep REDDY ENTI; Rangoju Vidyasagar; Bayela Sairaj
Original assignee: Cbai Technologies Private Limited
Priority date: 2022-11-20
Filing date: 2023-11-20
Publication date: 2024-05-23

Abstract

Present disclosure discloses an apparatus (100) for soft landing an unmanned aerial vehicle (UAV) (200) comprising a plurality of holders (120) attached to a body (106) of the UAV (200). At least one parachute (140a, 140b) configurable within each of the plurality of holders about at least one canister (132). The plurality of holders comprises at least one provision (126) extending from each holder of the plurality of holders. A connecting member (135) is defined with a sleeve portion (136) and at least one protrusion extends from the sleeve portion. The sleeve portion is configured to receive the at least one canister and the at least one protrusion is receivable within the at least one provision. The connecting member is removably attached to each of the plurality of holders about the at least one provision to accommodate the at least one parachute in a soft landing of the UAV.

Description

“AN APPARATUS FOR SOFT LANDING OF AN UNMANNED AERIAL VEHICLE”

TECHNICAL FIELD

Present disclosure in general relates to an aerial vehicle. Particularly, but not exclusively, the present disclosure relates to an unmanned aerial vehicle. Further, embodiments of the present disclosure disclose an apparatus for soft landing of the unmanned aerial vehicle.

BACKGROUND OF THE DISCLOSURE

An unmanned aerial vehicle (UAV) colloquially known as a multi-copter, is typically characterised by a centre body having four arms coming out laterally in an X-configuration. Each arm supports one helicopter-type rotor directed upward. The control for the unmanned aerial vehicle is accomplished by varying the speed of each rotor, which typically is counterrotating with respect to the rotors on either side of the rotor. For example, hovering is accomplished by having pairs of opposite corner blades operating together, in a rotational direction opposite of the other blades, and at equal speeds. Yawing is accomplished by relatively speeding up one opposing -corner pair with respect to the other, while pitch and roll is accomplished by relatively varying the speed of adjacent pairs of blades. Forward, reverse, and side-to-side motion is accomplished by tilting the craft in pitch or roll to cause a sum of the forces of the rotors to include a lateral component. Various other control protocols are known in the art.

The unmanned aerial vehicle further comprises a recovery system for safe landing of the aerial vehicle in case of any emergency or failure of any of the propellor systems. A typical soft lander or recovery system is coupled to the centre body of the unmanned aerial vehicle. The recovery system includes a canister to store a controlled decent mechanisms such as a parachute. The parachute can be of varied sizes depending upon the size of the unmanned aerial vehicle and the pay load capacity. Further, the recovery system includes an activation system and a deployment system. The activation of the parachute is performed either using a remote trigger or automatically through onboard failure detection or an emergency system. The deployment system may either use a spring-loaded or hydraulic deployment system. Further, the purpose of the recovery system is to prevent damage to the payloads and to protect the unmanned aerial vehicle from impact caused due to a crash by vertical drop from an altitude. As the unmanned aerial vehicle includes expensive payloads on it such as cameras or sensors or like. Thus, damage of these payloads results in increased manufacturing and operational cost.

Conventional, UAV recovery system includes a single parachute that deploys during an emergency. The single parachute is defined with larger diameter to provide required deceleration to the unmanned aerial vehicle. Also, the time required to inflate the parachute is directly proportional to the diameter of the parachute. Hence, a single parachute requires more time to inflate completely. If the altitude from which the unmanned aerial vehicle descends or drops is short, then the parachute with larger diameter may not completely inflate before it reaches the ground. Thus, it is challenging for the unmanned aerial vehicle with the single parachute to decelerate in a short duration of time when the drop altitude is less with respect to the ground. Further, the sudden descent may damage the unmanned aerial vehicle or payloads or any of the components. Thus, increasing the maintenance or repair costs of the unmanned aerial vehicle and/or payloads. Also, the parachute of the conventional recovery system is fixedly attached to the unmanned aerial vehicles and replacement and maintenance of the recovery system is time consuming and cumbersome task. This results in increasing assembly time and maintenance cost of the unmanned aerial vehicle.

The present disclosure is directed to overcome one or more limitations stated above or any other limitation associated with the conventional arts.

The information disclosed in this background of the disclosure section is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.

SUMMARY OF THE DISCLOSURE

One or more shortcomings of the conventional systems are overcome by the recovery system of the present disclosure.

An apparatus for soft landing an unmanned aerial vehicle is disclosed in the present disclosure having at least two parachutes. The at least two parachutes are attached to the unmanned aerial vehicle through a plurality of holders disclosed in the present disclosure.

In one non-limiting embodiment of the disclosure, an apparatus for soft landing an unmanned aerial vehicle is disclosed. The apparatus comprises a plurality of holders attached to a body of the UAV. The plurality of holders are configured to receive at least one canister. At least one parachute is configurable within each holder of the plurality of holders about the at least one canister. The plurality of holders comprises at least one provision extending away from a portion of each holder of the plurality of holders. A connecting member is defined with a sleeve portion and at least one protrusion extending from the sleeve portion. The sleeve portion is configured to receive the at least one canister and the at least one protrusion is receivable within the at least one provision. The connecting member is removably attached to each holder of the plurality of holders about the at least one provision to accommodate the at least one parachute in a soft landing of the UAV.

In an embodiment, the plurality of holders are attached to one or more side walls of the UAV defined with a first mounting provisions to accommodate the at least one parachute for recovery of the UAV.

In an embodiment, each holder of the plurality of holders is defined with a first surface and a second surface opposite to the first surface.

In an embodiment, the at least one provision extends from a portion of the first surface of each holder to accommodate the at least one canister.

In an embodiment, each holder is defined with a plurality of second mounting provisions on the second surface complementary to the first mounting provisions of the UAV to secure each holder to the one or more portions of the UAV by a fastener.

In an embodiment, the at least one provision comprises a wall structure extending from the first surface to define a slot therewithin to receive the at least one protrusion.

In an embodiment, the at least one protrusion is structured in a shape complementary to that of the slot to firmly secure the at least one canister to the UAV.

In an embodiment, the at least one parachute is deployed from the at least one canister attached to the plurality of holders during descent of the UAV.

In an embodiment, the apparatus further comprises a controller communicatively coupled to a plurality of sensors coupled and the at least one canister. The plurality of sensors are attached to a plurality of propellers and are configured to determine the actuation speed and de-actuation of the plurality of propellers. In an embodiment, the controller is configured to receive one or more signals from the plurality of sensors corresponding to the de-actuation of the plurality of propellers. The controller is also configured to deploy the at least one parachute from the at least one canister for soft landing of the UAV upon receipt of the one or more signals.

The foregoing summary is illustrative only and is not intended to be in any way limiting. In addition to the illustrative aspects, embodiments, and features described above, further aspects, embodiments, and features will become apparent by reference to the drawings and the following description.

BRIEF DESCRIPTION OF THE ACCOMPANYING DRAWINGS

The novel features and characteristic of the disclosure are set forth in the appended description. The disclosure itself, however, as well as a preferred mode of use, further objectives, and advantages thereof, will best be understood by reference to the following description of an illustrative embodiment when read in conjunction with the accompanying figures. One or more embodiments are now described, by way of example only, with reference to the accompanying figures wherein like reference numerals represent like elements and in which:

FIG. 1 illustrates an exemplary schematic view of an unmanned aerial vehicle (UAV) with the apparatus for soft landing an unmanned aerial vehicle, in accordance with an embodiment of the present disclosure.

FIGs.2a and 2b illustrates a top view and a side view of the UAV with the apparatus in accordance with an embodiment of the present disclosure.

FIG.3 a illustrates an exemplary schematic view of a UAV indicating positioning of a plurality of holders of the apparatus, in accordance with an embodiment of the present disclosure.

FIG. 3b illustrates a detailed view of each holder of the plurality of holders of the apparatus in accordance with an embodiment shown in FIG 3a.

FIGS .4a and 4b illustrates a top view and a side view of the apparatus of the UAV in accordance with another embodiment of the present disclosure.

FIG.5a illustrates a schematic view of each holder of the plurality of holders provided on the UAV, in accordance with another embodiment of the present disclosure. FIG. 5b illustrates a detailed view of each holder of the apparatus in accordance with an embodiment shown in FIG 5a.

FIG.6 illustrates an exemplary schematic view of a connecting member holding at least one least one canister of the apparatus, in accordance with an embodiment of the present disclosure; and

FIG.7 illustrates an exemplary schematic view of at least one canister coupled to each holder of the apparatus with the connecting member of FIG 5a.

FIG. 8 illustrates a schematic layout depicting a controller configured to deploy the at least one parachute from the at least one canister connected to the apparatus of Fig. 3a.

The figures depict embodiments of the disclosure for purposes of illustration only. One skilled in the art will readily recognize from the following description that alternative embodiments illustrated herein may be employed without departing from the principles of the disclosure described herein.

DETAILED DESCRIPTION

The foregoing description broadly outlines the features and technical advantages of the present disclosure in order that the description of the disclosure that follows may be better understood. Additional features and advantages of the disclosure will be described hereinafter which form the subject of the disclosure. It should be appreciated by those skilled in the art that the conception and specific embodiment disclosed may be readily utilized as a basis for modifying or designing other unmanned aerial vehicles for carrying out the same purposes of the present disclosure. It should also be realized by those skilled in the art that such equivalent constructions do not depart from the scope of the disclosure. The novel features which are believed to be characteristics of the disclosure, as to its organization, together with further objects and advantages will be better understood from the following description when considered in connection with the accompanying figures. It is to be expressly understood, however, that each of the figures is provided for the purpose of illustration and description only and is not intended as a definition of the limits of the present disclosure.

In the present document, the word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any embodiment or implementation of the present subject matter described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments.

While the disclosure is susceptible to various modifications and alternative forms, specific embodiments thereof have been shown by way of example in the drawings and will be described below. It should be understood, however, that it is not intended to limit the disclosure to the particular forms disclosed, but on the contrary, the disclosure is to cover all modifications, equivalents, and alternatives falling within the scope of the disclosure.

The terms “comprises”, “comprising”, or any other variations thereof, are intended to cover a non-exclusive inclusions, such that an assembly that comprises a list of components does not include only those components but may include other components not expressly listed or inherent to such assembly. In other words, one or more elements in the unmanned aerial vehicle or assembly proceeded by “comprises... a” does not, without more constraints, preclude the existence of other elements or additional elements in the assembly.

In the following description of the embodiments of the disclosure, reference is made to the accompanying figure that form a part hereof, and in which are shown by way of illustration specific embodiments in which the disclosure may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the disclosure, and it is to be understood that other embodiments may be utilized and that changes may be made without departing from the scope of the present disclosure. The following description is, therefore, not to be taken in a limiting sense.

The following paragraphs describe the present disclosure with reference to FIG.1. With general reference to the drawing, an unmanned aerial vehicle is illustrated and identified with reference numeral 200. The unmanned aerial vehicle (UAV) (200) may hereinafter be referred to as “the vehicle (200)” and may be alternatively used in the forthcoming paragraphs. The vehicle (200) of the present disclosure may be a quad-rotor aerial vehicle (e.g., an aerial vehicle having four rotor assemblies). It will be appreciated that the aerial vehicle may be a multi-rotor aerial vehicle having six rotor assemblies, eight rotor assemblies and the like depending on the size of the unmanned aerial vehicle (200) and pay load capacity. The vehicle (200) of the present disclosure may include a vehicle body referred to as a chassis. In the corresponding figures, the body (or) chassis is denoted by referral numeral 106. In an embodiment, the chassis (106) may be made of metal such as aluminium, or suitable plastic or polymer, or any other suitable material or combination of materials. In another embodiment, the chassis (106) may be made of composite materials but not limiting to the same. For instance, the chassis (106) may be made of carbon fibre, fiberglass, and other such suitable materials. The chassis (106) may be a truss structure, a monocoque or a semi-monocoque structure.

Referring to Figs. 2a and 2b, the chassis (106) may define a housing designed to receive and support vehicle electronics hereinafter referred to as a control module or a controller (150) (shown in Fig. 8). The controller (150) may include a printed circuit board (PCB), on-board electronics, GPS module, air telemetry and radio receiver each of them connected to the main computer board. In another embodiment, the controller (150) may include power distribution board. The chassis (106) may include a top surface plate (116a), a bottom surface plate (not shown) and a sidewall structure having one or more sidewalls (116b) a portion of which extends from the top surface plate (116a) and remaining portion of which extends from the bottom surface plate. The top surface plate (116a) and the bottom surface plate may be snapped/snap fitted to the bottom surface to form the housing defining a space therebetween to accommodate the vehicle electronics or the controller (150). In another embodiment, the top surface plate (116a) and the bottom surface plate may be connected by other means including but not limiting to screw connections. The chassis (106) may have various shapes according to distinctive designs on appearance of the unmanned aerial vehicle. For instance, the chassis (106) may be square shaped, a polygonal shape, an aerodynamic shape, a streamlined shape, or any regular or irregular shapes.

Further, the unmanned aerial vehicle (200) includes a plurality of elongated arms (104a, 104b, 104c and 104d) extending outwardly from the chassis (106). In an embodiment, the chassis (106) may be defined with one or more connecting ports [not shown]. The one or more connecting ports may be defined at a predefined location on the chassis (106). For instance, the one or more connecting ports may be defined at the outermost corners of the chassis (106). A first end of each of the elongated arms (104a, 104b, 104c and 104d) may be receivable by corresponding connecting ports of the one or more connecting ports defined on the chassis (106). In an embodiment, each of the plurality of elongated arms (104a, 104b, 104c, 104d) may be either fixedly connected or may be movably connected to the chassis (106). The chassis (106) may comprise a plurality of first mounting protrusions (124c) to receive and fasten a plurality of holders (120). In an embodiment, the first end of the elongated arms (104a, 104b, 104c) may be connected to the chassis by at least one of a binding screw mechanism or a lock pin mechanism which enables the elongated arms (104a, 104b, 104c) to displace between an extended position and a collapsed position. It should be noted that the number of elongated arms depend on the type of the vehicle (200) i.e., whether the vehicle (200) is a quad-rotor vehicle, hexa-rotor vehicle, octa-rotor vehicle, or a multi-rotor vehicle. Although, the unmanned aerial vehicle (200) depicted in the figures is a quad-rotor vehicle, the same should not be construed as a limitation of the present disclosure. In an embodiment, the plurality of elongated arms (104a, 104b, 104c, 104d) may be symmetrical with respect to substantial central portion of the chassis (106). A second end of each of the plurality of elongated arms (104a, 104b, 104c and 104d) [refer FIG.2] opposite to the first end may be defined with a receiving portion. The receiving portion defined in each of the plurality of elongated arms (104a, 104b, 104c and 104d) may be configured to receive and support thrust generators (not shown in Figs.). The thrust generators are also referred to as rotor assemblies and is denoted by referral numerals (114a, 114b, 114c and 114d) as apparent from FIG.l [114d and 114c are in the same line of 114a and 114b] . The rotor assembly includes a motor (not shown in Figs.) and a plurality of propellers (114) connected to the motor. The motor can drive the plurality of propellers (114 a-d) to rotate and hence provide a propulsion to the unmanned aerial vehicle (200). The motor of the rotor assembly (114a, 114b, 114c and 114d) may be powered by the battery module (108) connected to the chassis (106). In an embodiment, a plurality of sensors (152) may be attached to the plurality of propellers (114a-d). The plurality of sensors (152) are configured to determine the actuation and deactivation of the plurality of propellers (114a-d). The plurality of sensors (152) are communicatively coupled with the controller (150) (as shown in Fig. 8).

Referring to Figs. 3a and 3b, an apparatus (100) for soft-landing the unmanned aerial vehicle (200) is illustrated. The apparatus (100) includes a plurality of holders (120) in the form of bracket (122). The bracket (122) is removably connected to a portion of the chassis (106). The bracket (122) can be removably connected to the top surface plate (116a) of the chassis (106). The bracket (122) may be removably connected to the top surface plate (116a) and the bottom surface plate of the chassis (106). In an embodiment, the bracket (122) may be coupled to the one or more sidewalls (116b) of the chassis (106) as shown in FIG 3a and FIG 5a. In an alternate embodiment, the bracket (122) itself may be considered as a sidewall (120) structure of the chassis (106). The bracket (122) shown in FIG 3b and FIG 5b, is defined with a plurality of second mounting provisions (124a, 124b) to couple with the portion of the chassis (106). The plurality of second mounting provisions (124a, 124b) may comprise at least one of apertures like, threaded hole, slot, hinge, or the like. The plurality of second mounting provisions (124a, 124b) are provided at a first surface (128a) of the bracket (122). The plurality of second mounting provisions (124a, 124b) are complementary to the plurality of first mounting provisions (124c) of the vehicle (200) to removably couple each holder (120) of the plurality of holders (120) with the chassis (106) by fastening members or any other joining means. In an exemplary embodiment the second mounting provisions (124a, 124b) provided on the first surface (128a) of the bracket (122), is defined with an aperture of cylindrical thread hole. The bracket (122) is coupled to the unmanned aerial vehicle (200) by at least one fastening members or any other joining means by connecting the plurality of second provisions (124a, 124b) of the bracket (122) along with one or more aperture (not shown) on the chassis (106). In an exemplary embodiment shown in FIG 3 a and FIG 5a, the bracket (122) is coupled on the chassis (106) of the unmanned aerial vehicle (200).

Now referring to Figs. 4a, 4b, 5a and 5b in conjunction with Figs. 6 and 7, each holder of the plurality of holders (120) is defined with at least one provision (126, 126a, 126b) on a second surface (128b) of each holder (120) to removably accommodate a parachute canister assembly (130). The at least one provision (126) includes a wall (127) extending from the second surface (128b) of the plurality of holders (120) thereby forming a slot (129) therewithin to securely hold at least one parachute canister assembly (130) about the plurality of holders (120). The at least one parachute canister assembly (130) comprises at least one canister (132) that is configured to accommodate at least one parachute (140a, 140b) therewithin for soft landing of the vehicle (200). The at least one provision (126, 126a, 126b) is defined as a means to couple the at least one canister (132) to the plurality of holders (120). In an embodiment, the wall (127) may be defined with an opening (129) like, a slot, a groove, a cleft, or an aperture. The at least one canister (132) comprises an elongated body (132a) and defined with a hollow compartment to store the parachute (140a, 140b) inside the canister (132). Further, a connecting member (135) is configured to hold the at least one canister (132). The connecting member (135) is defined with a sleeve portion (136) configured to receive and hold the at least one canister (132) along a periphery of the elongated body (132a) of the canister (132). The at least one canister (132) may be replaceable from the connecting member (136). Further, the at least one canister (132) may be fixed to the connecting member (135) to hold the at least one canister (132). The securing member (136) further includes at least one protrusion (134) receivable within the at least one provision (126) of the plurality of holders (120). The at least one protrusion (134) extends downwardly from one end portion of the sleeve portion (136). In an embodiment, the at least one protrusion (134) may be structured complementary to be secured within the slot (129) of the at least one provision (126) to secure the at least one canister (132) with the plurality of holders (120).

In an embodiment, the at least one provision (126) defined with an “I” shape. In another embodiment, the at least one provision (126) has varying thickness of the wall structure (127) along the opening (129) of the at least one provision (126, 126a, 126b) (as shown in Fig. 5b). Furthermore, shape of the at least one provision (126) is complementary to a shape of the at least one protrusion (134) provided on the parachute canister assembly (130) as shown in FIG 6. The at least one protrusion (134) may slide into the pocket (126) for securely holding and to facilitate ease of replacement of the at least one canister (132). In an embodiment, the at least one provision (126) and the at least one protrusion (134) may have a snap fit, snug fit, clipped to each other. In an embodiment the at least one provision (126) the bracket (122) and the protrusion (134) provided on the parachute canister assembly (130) may be interchangeable.

The at least one canister (132) fitted to the plurality of holders (120), is further configured to store the at least one parachute (140a, 140b) in closed and compressed form within the canister (132). The at least one parachute (140a, 140b) in closed condition, is placed inside the hollow compartment of at least one canister (132) shown in FIG 6. The at least one parachute (140a, 140b) in an open condition has a canopy made of any fabric. The at least one parachute (140a, 140b) in the open condition will help the unmanned aerial vehicle hovering at an altitude to be landed safely. Activation of the at least one parachute (140a, 140b) may happen with a remote trigger or automatically through onboard failure detection. Automatic activation detects “unnatural” behaviour of the unmanned aerial vehicle (200) by monitoring various parameters like descent rate, pitch or roll angles. If a predefined value, or set of values, is exceeded, the parachute (140a, 140b) is deployed.

Once the plurality of parachutes (140a, 140b) are activated the parachutes are deployed through a deployment system (not shown in Figs.). The deployment system releases the canopies of the at least one parachute (140a, 140b) to open, from the at least one canister (132) connected to the plurality of holders (120). The deployment of the parachutes (140a, 140b) may be through any of the methods like, spring-release deployment, sling/catapult release deployment, pyrotechnic deployment, compressed-gas deployment, etc., Spring release deployment method uses loaded springs to eject the at least one parachute (140a, 140b). Sling/catapult release deployment method uses elastic bands to eject the least one parachute (140a, 140b). Pyrotechnic deployment system uses explosives to eject the least one parachute (140a, 140b). Compressed-gas deployment method is similar to the pyrotechnic deployment but uses compressed gas like CO2 instead of explosives.

In an embodiment the bracket (122) of the parachute recovery system is capable of holding maximum of two canisters (132), in terms of weight it is capable of withstanding 150g - 400g, as shown in FIG 2a. In another embodiment, the bracket (122) of the parachute recovery system may hold four canisters (132) as shown in FIG 4a. In an embodiment, FIG 2a and FIG 4a, discloses the unmanned aerial vehicle (200) that is provided with plurality of brackets (122) placed on the opposite sides of the fuselage (106) to maintain the centre of gravity of the unmanned aerial vehicle (200). The plurality of the brackets (122) is coupled with the plurality of the canisters (132). The embodiment of the disclosure contains at least two parachutes (140a, 140b), in plurality of the canisters (132). As the number of parachutes are more, the diameters of the parachutes will be lesser and thus the inflation time is lesser, compared to a conventional single parachute recovery system. Thus, the response of the recovery system with multiple parachutes is lesser compared to the conventional single parachute recovery systems.

An operative configuration of the soft landing of the vehicle (200) with the apparatus (100) is now explained. Initially, the apparatus (100) is fastened to the chassis (106) of the vehicle (200) about the second surface of the plurality of holders (120). The apparatus is fastened at one or more portions of the vehicle (200) sidewalls (116b) such that a plurality of parachutes (104a, 104b) are provided for soft landing of the vehicle (200). The plurality of sensors (152) sends out one or more signals to the controller (150) corresponding to a speed of the plurality of propellers (114a-d). In an undesired event or in a crash scenario or any gravity-driven fall by a drag force on the vehicle (200), the controller (150) receives the signal from the plurality of sensors (152). The signal may correspond to a deceleration in a speed of the plurality of propellers (114a-d) and de-actuation of the plurality of propellers (114a-d) due to damage during flight of the vehicle (200). The controller (150) actuates the deployment mechanism attached to the at least one canister (132) attached to the plurality of holders (120) of the apparatus (100). The deployment mechanism deploys the at least one parachute (140a, 140b) such that the vehicle (200) is landed safely.

In an embodiment, the at least one canister (132) being attached to the plurality of holders at one or more locations enables a plurality of parachutes (140a, 140b) to be deployed simultaneously by actuation of the deployment mechanism by the controller (150). Therefore, the plurality of the parachutes (140a, 140b), having lesser diameter when compared to the conventional recovery system with the single parachute of higher diameter. The inflation time or the time taken to inflate the at least one parachute (140a, 140b) is directly proportional to the nominal parachute diameter. Nominal diameter of the at least one parachute (140a, 140b) is the drag area of the fully opened at least one parachute (140a, 140b). The force exerted on the at least one parachute (140a, 140b) depends on the maximum take-off weight of the unmanned aerial vehicle (200) which decides the drag area of fully opened at least one parachute (140a, 140b). Hence the time taken for inflation is more for single parachute with large nominal diameter whereas double parachute system with comparatively lesser diameter will have less time of inflation. Advantageously, this reduction in time of inflation means the parachute recovery system with double or multiple parachutes will have quick response.

The apparatus (100) of the present disclosure provides a multi-parachute recovery solution having an additional advantage when either of individual parachute fails to deploy. Advantageously, this provides reliable recovery system for the unmanned aerial vehicle itself and for the payload on the unmanned aerial vehicle.

The apparatus (100) for the unmanned aerial vehicle makes the structure reusable, thus reducing the effective cost of manufacturing.

Equivalents:

With respect to the use of substantially any plural and/or singular terms herein, those having skill in the art can translate from the plural to the singular and/or from the singular to the plural as is appropriate to the context and/or application. The various singular/plural permutations may be expressly set forth herein for sake of clarity. While various aspects and embodiments have been disclosed herein, other aspects and embodiments will be apparent to those skilled in the art. The various aspects and embodiments disclosed herein are for purpose of illustration and are not intended to be limiting.

Table of Referral Numerals:

Claims

We Claim:

1. An apparatus (100) for soft landing an unmanned aerial vehicle (UAV) (200), the apparatus (100) comprising: a plurality of holders (120) attached to a body (106) of the UAV (200), wherein the plurality of holders (120) are configured to receive at least one canister (132); at least one parachute (140a, 140b) configurable within each holder (120) of the plurality of holders (120) about the at least one canister (132) and the plurality of holders (120) comprises: at least one provision (126) extending away from a portion of each holder (120) of the plurality of holders (120); a connecting member (135) defined with a sleeve portion (136) and at least one protrusion (134) extending from the sleeve portion (136), wherein the sleeve portion (136) is configured to receive the at least one canister (132) and the at least one protrusion (134) is receivable within the at least one provision (126); and wherein the connecting member (135) is removably attached to each holder (120) of the plurality of holders (120) about the at least one provision (126) to accommodate the at least one parachute (140a, 140b) in a soft landing of the UAV (200).

2. The apparatus (100) as claimed in claim 1, wherein the plurality of holders (120) are attached to one or more side walls (116b) of the UAV (200) defined with a plurality of first mounting provisions (124c) to accommodate the at least one parachute (140a, 140b) for recovery of the UAV (200).

3. The apparatus (100) as claimed in claim 1, wherein each holder (120) of the plurality of holders (120) is defined with a first surface (128b) and a second surface (128a) opposite to the first surface (128b).

4. The apparatus (100) as claimed in claim 3, wherein the at least one provision (126) extends from a portion of the first surface (128b) of each holder (120) to accommodate the at least one canister (132).

5. The apparatus (100) as claimed in claim 2, wherein each holder (120) is defined with a plurality of second mounting provisions (124a, 124b) on the second surface (128a) complementary to the first mounting provisions (124c) of the UAV (200) to secure each holder (120) to the one or more portions of the UAV (200) by a fastener. The apparatus (100) as claimed in claim 1, wherein the at least one provision (126) comprises a wall structure (127) extending from the first surface (128b) to define a slot (129) therewithin to receive the at least one protrusion (134). The apparatus (100) as claimed in claim 5, wherein the at least one protrusion (134) is structured in a shape complementary to that of the slot (129) to firmly secure the at least one canister (132) to the UAV (200). The apparatus (100) as claimed in claim 1, wherein the at least one parachute (140a, 140b) is deployed from the at least one canister (132) attached to the plurality of holders (120) during descent of the UAV (200). The apparatus (100) as claimed in claim 1, comprises a controller (150) communicatively coupled to a plurality of sensors coupled and the at least one canister (132), wherein the plurality of sensors are attached to a plurality of propellers (114a-114n) and are configured to determine the actuation speed and deactuation of the plurality of propellers (114a- 114n). The apparatus (100) as claimed in claim 1, wherein the controller (150) is configured to: receive one or more signals from the plurality of sensors corresponding to the de-actuation of the plurality of propellers (114a-114n); and deploy the at least one parachute (140a, 140b) from the at least one canister (132) for soft landing of the UAV (100).