Canopy-less metal parachute

Abstract

A Canopy-less metal parachute [001] The invention provides a canopy-less metal parachute (100) comprising plurality of drag generating units (10) comprising an open wind propeller unit (20) including an external metal-lattice body (21) housing multiple scimitar shaped twisted fins (22), and a central hub (23); an air compressor unit (30) including a casing (31) with inbuilt multiple fixed stators (32), a driving shaft (33), and multiple rotors; and an integrated power generation system (40) including multiple magnets (41) that are disposed on the internal surface of the central hub (23), multiple coil windings (42) coupled with a step-up converter (43) disposed on the external surface of the casing (31), and a brushless DC motor (44) coupled with an ESC (45). The process of working includes rotation of the propeller units (10), power generation and transmission, air compression and eventual descent of the metal parachute (100).

Description

FIELD OF INVENTION

[0001] The present invention relates to a metal parachute. In particular, the present invention relates to a canopy-less metal parachute that is operated by a drag generating unit without a power source.BACKGROUND

[0002] A parachute is a device designed to slow the descent of a person or object from a height by creating drag or air resistance. The key components of a conventional parachute comprises a canopy that catches the air and slows the descent, suspension lines that provides stability by distributing the load on the canopy, a harness that holds an object or a user and spreads the force of the descent, a deployment and release system that pulls the canopy out of the deployment bag to release the chute.

[0003] An improved system with descent control from the conventional system was patented (Patent No: 401611) by introducing an open canopy coupled with drag generating units comprising rotor blades, gear unit and air compressor. The planetary gear system used in the patented invention does not produce enough thrust to facilitate soft landing. Also, the structure of the rotor blades does not handle the impact during the deployment process. Thus, there exist a need to replace the planetary gear system with an alternative system that increases the thrust of the air compressor and modify the structure of the rotor blades to improve the stability of the entire system.

[0004] The patent document US9550577B1 discloses a system and method for operating an automated aerial vehicle wherein the battery life may be extended by performing one or more electricity generation procedures on the way to a destination (e.g., a delivery location for an item). In various implementations, the electricity generation procedure mayinclude utilizing an airflow to rotate one or more of the propellers of the automated aerial vehicle so that the associated propeller motors will generate electricity (e.g., which can be utilized to recharge the battery, power one or more sensors of the automated aerial vehicle, etc.). In various implementations, the airflow may consist of a wind, or may be created by the kinetic energy of the automated aerial vehicle as it moves through the air (e.g., as part of a normal flight path and / or as part of an aerial maneuver).

[0005] The patent document US12000404B1 discloses a fuel-cell-powered vehicle including an electrically-powered turbine assembly having a housing, a rotating shaft, an air compressor comprising a compressor stator fixed to the housing and a compressor rotor fixed to the rotating shaft, an electric motor including an electric motor stator fixed to the compressor stator and an electric motor rotor fixed to the rotating shaft, a turbine including a turbine stator affixed to the housing, a turbine rotor fixed to the rotating shaft, and two or more fuel cells arranged around an outside of the electrically-powered turbine assembly.

[0006] However, in the aforementioned documents, the power generation system either uses fuel cells to generate energy or stores the generated power in batteries for further energy usage.

[0007] Therefore, there exists a need for an automated power generation system integrated with the drag generating unit that doesn’t require any external source of energy thereby providing extra thrust for the descent of the canopy-less parachute.OBJECT OF THE INVENTION

[0008] The principal object of the invention is to improve the thrust transmitted to the air compressor by replacing the planetary gear of the existing system with an automated power generation system.

[0009] Another object of the invention is to employ the automated power generation system comprising multiple magnets and its associated coils, step up converters, air compressor with brushless motor and ESC to operate the rotor blades.

[0010] Another object of the invention is to improve the aerodynamic efficiency of the drag generating unit by altering the shape of the rotor blades from straight to scimitar type and minimizing the total number of rotor blades.

[0011] Another object of the invention is to generate power using an electromagnetic induction system such that the magnets are disposed on the rotor wall and its respective coil windings on the air compressor wall such that the rotation of the rotor.

[0012] Another object of the invention is to generate power without batteries or fuel cells and transmit it to the brushless motor of the rotor blades.

[0013] These and other objects and characteristics of the present invention will become apparent from the further disclosure to be made in the detailed description given below.SUMMARY OF THE INVENTION

[0014] This summary is provided to introduce a selection of concepts in a simplified form that are further described below in the Detailed Description. This summary is not intended to identify key features or essential features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter.

[0015] The invention provides an improved canopyless metal parachute comprising a drag generation unit incorporated with an automated power generation system replacing the planetary gear.

[0016] It is one aspect of the present invention to disclose the components of the power generation system comprising multiple magnets and its associated coils, and step up converters that is connected to a brushless motor of an air compressor unit equipped with an ESC.

[0017] It is another aspect of the present invention to employ the power generation system for operating the rotor blades without fuel cells and / or batteries.

[0018] It is other aspect of the present invention to improve the aerodynamic efficiency of the drag generating unit by altering the shape of the rotor blades from straight to scimitar type and minimizing the total number of rotor blades.

[0019] It is yet other aspect of the present invention to generate power using an electromagnetic induction system such that the magnets are disposed on the rotor wall and its respective coil windings on the air compressor wall such that the rotation of the rotor.

[0020] It is another aspect of the present invention to disclose the process of working of the canopy-less metal parachute using the automated power generation system comprising the steps of rotation of the propeller unit, generation and transmission of the power, and air compression resulting in the descent of the parachute.

[0021] These together with other objects of the invention, along with the various features of novelty which characterize the invention, are pointed out with particularity in the disclosure. For a better understanding of the invention, its operating advantages and the specific objects attained by its uses, reference should be had to the accompanying drawings and descriptive matter in which there are illustrated preferred embodiments of the invention.BRIEF DESCRIPTION OF DRAWINGS

[0022] The foregoing and other features of embodiments will become more apparent from the following detailed description of embodiments when read in conjunction with the accompanying drawings. In the drawings, like reference numerals refer to like elements.

[0023] In the following description, for the purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the invention. It is apparent, however, to one skilled in the art that the embodiments of the invention may be practiced without these specific details or with an equivalent arrangement. In other instances, well-known structures and devices are shown in block diagram form in order to avoid unnecessarily obscuring the embodiments of the invention.

[0024] FIG. 1 illustrates an isometric view of a canopy-less metal parachute in accordance with an embodiment of the present invention.

[0025] FIG. 2 illustrates the fin profile and magnet arrangement in the outer rotor, in accordance with an embodiment of the present invention.

[0026] FIG. 3 illustrates (a) the distribution of multiple coil windings disposed on the external surface of the compressor housing and (b) the dissected structural view of the air compressor unit, in accordance with an embodiment of the present invention.

[0027] FIG. 4 illustrates the flowchart for mechanism of working of a power generation system, in accordance with an embodiment of the present invention.DETAILED DESCRIPTION OF INVENTION

[0028] The embodiments herein and the various features and advantageous details thereof are explained more fully with reference to the non-limiting embodiments that are illustrated in the accompanying drawings and / or detailed in the following description. Descriptions of well-known components and processing techniques are omitted so as to not unnecessarily obscure the embodiments herein. The examples used herein are intended merely to facilitate an understanding of ways in which the embodiments herein may be practised and to further enable those of skill in the art to practice the embodiments herein. Accordingly, the examples should not be construed as limiting the scope of the embodiments herein.

[0029] Reference in this specification to “one embodiment” or “an embodiment” means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present disclosure. The appearance of the phrase “in an embodiment” in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Moreover, various features are described which may be exhibited by some embodiments and not by others. Similarly, various requirements are described which may be requirements for some embodiments but not for other embodiments.

[0030] Moreover, although the following description contains many specifics for the purposes of illustration, anyone skilled in the art will appreciate that many variations and / or alterations to said details are within the scope of the present disclosure. Similarly, although many of the features of the present disclosure are described in terms of each other, or in conjunction with each other, one skilled in the art will appreciate that many of these features can be provided independently of other features. Accordingly, this description of the presentdisclosure is set forth without any loss of generality to, and without imposing limitations upon the present disclosure.

[0031] The term “pitch” means angle of a blade in air referring to the angle between the propeller blade chord line and the plane of rotation of the propeller.

[0032] The term “automated power generation system” or “power generation unit”, are interchangeably used in the Specification where all these terms have same context and meaning as it describes an automated power generation system replacing a planetary gear system of the existing invention.

[0033] The term “canopy-less metal parachute” or “parachute”, are interchangeably used in the Specification where all these terms have same context and meaning as it describes the canopy-less metal parachute of the present invention.

[0034] The invention disclosed herein provides a canopy-less metal parachute incorporated with an automated power generation system wherein the said power generation system operates the brushless motor of the rotor blades without using fuel cells and / or batteries. Additionally, the aerodynamic efficiency of the canopy-less metal parachute is improved by altering the fin profile of the rotor blades.

[0035] FIG. 1 illustrates an isometric view of a canopy-less metal parachute (100) with multiple drag generating units (10) that are axially connected together by a linker shaft (50) characterized in that each drag generating unit (10) has an open wind propeller / turbine unit (20) and an air compressor unit (30) that are integrated with an automated power generation system (40). The said propeller unit (20) and the air compressor unit (30) occupies 65-75% and 25-35% space of the entire diameter in each drag generating unit (10), respectively. In an example embodiment, if the diameter of a drag generating unit (10) is 500 mm, the central 140mm is occupied by the air compressor unit (30) and the remaining portion (up to 315 mm) is occupied by the propeller unit (20) wherein the propeller unit (20) occupies at least 155 mm on either side of the drag generating unit (10). The remaining 2-5 mm indicates the air gap between the propeller unit and the air compressor unit.

[0036] In an embodiments, the specification of each propeller unit (20) is disclosed. Each open propeller unit (20) includes an external metal-lattice body (21) housing multiple fins (22), and a central hub (23) that are disposed on the extreme distal end of the linker shaft (50) as shown in FIG. 1. The average diameter of each propeller unit is 300-315 mm. The existing straight fins are replaced with a scimitar shaped twisted fins (22) wherein the fin angle changes along the length providing better air flow and reduces drag. Each fin has a winglet or a tip extension (24) to reduce drag and minimize vortex formation at the tip. It has a variable cord to improve the aerodynamic efficiency. All the fins are attached to the external surface of the central hub (23) as shown in FIG. 2 wherein the central hub (23) is disposed parallel to the head of the air compressor unit (30). The number of fins in each propeller unit (10) ranges between 6 and 10 that is decided depending on the size of the propeller unit (10). The preferable number of the propeller units (10) are either two or four wherein each propeller unit counter rotates with respect to the subsequent propeller unit to cancel out the torque.

[0037] In other embodiment, the components of the air compressor unit (30) is disclosed. The air compressor unit (30) comprises a casing (31) that has inbuilt multiple fixed stators (32) on its internal surface and multiple coil windings (42) coupled with a step-up converter (43) on its external surface, a driving shaft (33) integrated with a brushless DC motor (44) and multiple rotors (34) that are fixed co-axially with the shaft (33) wherein the brushless DC motor is coupled with an ESC (45).

[0038] In another embodiment, the components of the automated power generation system (40) is disclosed. Multiple magnets (41) are disposed on the internal surface of the central hub (23) as shown in FIG. 2 and multiple coil windings (42) are disposed on the external casing (31) of the air compressor head as shown in FIG. 3 A such that the magnets (41) face the coil windings (42) to generate the necessary power during rotation of the propeller unit (20). The coil windings (42) are connected to a step-up converter (43) that is in turn coupled to an ESC (45) integrated with a brushless motor (44) in the air compressor unit (30) as shown in FIG. 4 wherein the ESC (45) facilitates the operation of the motor (44) during deployment of the canopy-less metal parachute (100). In an example embodiment, neodymium magnets of dimension 10x15x2 mm, electromagnetic coils of dimension 10x15x10 mm and a XL6009 DC- DC Step-Up Converter Performance Ultra LM2577 Booster Circuit Board is used.

[0039] The preferable number of magnets and coil windings ranges between 35 and 40 such that the ratio between the magnet and coil windings is in between 3:4 and 9: 10. In an example embodiment, an air compressor unit (30) comprising 36 coil windings requires installation of 40 permanent magnets to produce a power in the range of 18-24 V to produce a greater torque and improve the smoothness of operation. The electrical angle / coil winding is 10°. The wiring of the 36 coil windings depends on the capacity of the motor that includes 12xlc, 6x2c, 4x3c, 3x4cand multi-voltage wiring configurations. In an example embodiment, a 6x2cwiring comprises 6 lots of 6 coils each wherein the tapping for power transmission to the ESC is performed for every 6 coil windings in each lot. This generates an AC that is further converted to DC using a rectifier and is transmitted to the step-up DC-DC converter.

[0040] In yet another embodiment, a process of working of the canopy -less parachute is disclosed comprising the steps of:(a) deployment of the canopy -less parachute (100) and capturing of wind energy by the scimitar fins of the propeller unit (20); wherein the said deployment indicates a release / drop of the parachute from the hand;(b) rotation of the propeller unit (20) providing the necessary lift and drag to the canopy -less parachute (100);(c) generation and transmission of induction waves between the magnets (41) and the coil windings (42);(d) power generation in the coil windings (42) and subsequent step-up of power by the step-up DC converter (43);(e) transmission of power generation to the BLDC motor (44) coupled with an ESC (45);(f) rotation of the driving shaft (33) in the air compressor unit (30) and eventual rotation of the rotors in the air compressor unit (30);(g) compression of air between the rotors (34) and stators (32) in the air compressor unit and its release from the head of the air compressor unit (30); and(h) generation of necessary thrust to descent the canopy -less parachute (100); wherein the rotation of the BLDC motor (44) coupled with the ESC (45) by the energy generated from the power generation unit (40) provides additional force to the produced thrust and facilitates a smooth descent and landing of the parachute (100).

[0041] In an example embodiment, a process of drag control and thrust improvement in the drag generating unit (10) using the automated power generation unit is disclosed. The total number of magnets and coil windings includes 40 and 36, respectively and the total number of wings is eight. The propeller units (n=2) capture the kinetic energy from the windafter deployment of the canopy-less metal parachute (100). The wind flows over the scimitar fins (22) of the propeller units (10) rotating the propeller units (10) wherein the rotation creates the necessary lift and drag for the metal parachute (100). When the propeller units (10) rotate, the magnets (41) in the central hub (23) induces power generation in the coil windings (42) in the head of the air compressor (30) due to the rotational energy of the propeller units (20). The generated DC power is stepped up to 24 volts using the step-up converter (43) that is serially connected with the coil windings (42). The power is transmitted to the brushless DC motor (44) equipped with an ESC (45) in the air compressor unit (30) such that it increases the rotation of the driving shaft in the air compressor unit (30). Eventually, the air travels through the compressed area between the stators (32) and rotors (34) and the compressed air is released out from the head of the air compressor unit (30) creating the necessary thrust and this additional force controls the descent of the canopy-less metal parachute. Thus, the BLDC motor (44) operated by the automated power generation unit (40) provides the necessary drag and descontrol like that of the canopy in a conventional parachute with an additional thrust resulting in a smooth descent and landing of the canopy-less metal parachute.

[0042] The canopy-less metal parachute with an integrated power generation system disclosed herein has several advantages that are listed below:1. Weather Resilience: Due to its durable construction, it performs reliably in adverse conditions like rain, snow, and hail,.2. Ideal for Planetary Landings: It is well-suited for unpredictable extra-terrestrial environments.3. Compact Size: It occupies only 30% of the space of conventional parachutes.4. Eco-Friendly: It is constructed using lightweight and recyclable materials including aluminum and Inconel making it environmentally friendly and biodegradable.5. Pre-Launch Testing: It can be tested easily before deployment.6. Precise Landing: Adjustable drag generating units allow for accurate landing direction control.7. User-Friendly: Minimal training is needed due to its simple operation.8. No Electrical Components: It operates without batteries / fuel cells, electronic chipsets, or remote controls.9. Low Maintenance: The system lacks complex mechanical parts, making it easy to maintain and overhaul.10. Easy to Replace Parts: Components are simple that can be replaced whenever needed.

[0043] Thus, the canopy-less metal parachute (100) disclosed herein is a mechanical device requiring no outside source of energy for its operation and power generation.

[0044] The foregoing description of the specific embodiments will so fully reveal the general nature of the embodiments herein that others can, by applying current knowledge, readily modify and / or adapt for various applications such specific embodiments without departing from the generic concept, and, therefore, such adaptations and modifications should and are intended to be comprehended within the meaning and range of equivalents of the disclosed embodiments. It is to be understood that the phraseology or terminology employed herein is for the purpose of description and not of limitation. Therefore, while the embodiments herein have been described in terms of preferred embodiments, those skilled in the art will recognize that the embodiments herein can be practiced with modification within the spirit and scope of the embodiments as described herein.

Claims

Claims:I claim:

1. A canopy-less metal parachute (100) comprising plurality of drag generating units (10) that are axially connected together by a linker shaft (50); characterized in that each drag generating unit (10) comprises: an open wind propeller unit (20) that are disposed on the extreme distal end of the linker shaft (50), an air compressor unit (30) that are disposed at the centre of the drag generating unit(10), and an integrated power generation system (40); wherein, each propeller unit (10) includes an external metal-lattice body (21) housing multiple scimitar shaped twisted fins(22), and a central hub (23); each air compressor unit (30) includes a casing (31) with inbuilt multiple fixed stators (32), a driving shaft (33), and multiple rotors that are fixed co-axially with the driving shaft (33); each power generation system (40) includes multiple magnets (41) that are disposed on the internal surface of the central hub (23), multiple coil windings (42) coupled with a step-up converter (43) disposed on the external surface of the casing (31), anda brushless DC motor (44) coupled with an ESC (45) disposed on the driving shaft (33) that facilitates the operation of the motor during deployment of the canopy -less metal parachute (100).

2. The canopy-less metal parachute (100) as claimed in claim 1, wherein the said propeller unit (20) and the air compressor unit (30) occupies 65-75% and 25-35% space of the entire diameter in each drag generating unit (10), respectively.

3. The canopy -less metal parachute (100) as claimed in claim 1, wherein the preferable number of magnets and coil windings ranges between 35 and 40 and the preferable ratio between magnet and coil windings is 8:9 to produce a power between 18-24 V.

4. The canopy-less metal parachute as claimed in claim 1, wherein the preferable number of the propeller units (10) are either two or four CJnumber of fins in each propeller unit (10) ranges between 6 and 10.

5. A process of working of the canopy-less parachute (100) comprises the steps of:(a) deployment of the canopy -less parachute (100) and capturing of wind energy by the scimitar fins of the propeller unit (20); wherein the said deployment indicates a release / drop of the parachute from the hand;(b) rotation of the propeller unit (20) providing the necessary lift and drag to the canopy -less parachute (100);(c) generation and transmission of induction waves between the magnets (41) and the coil windings (42);(d) power generation in the coil windings (42) and subsequent step-up of power by the step-up DC converter (43);(e) transmission of power generation to the BLDC motor (44) coupled with an ESC (45);(f) rotation of the driving shaft (33) in the air compressor unit (30) and eventual rotation of the rotors in the air compressor unit (30);(g) compression of air between the rotors (34) and stators (32) in the air compressor unit and its release from the head of the air compressor unit (30); and(h) generation of necessary thrust to descent the canopy -less parachute (100); wherein the rotation of the BLDC motor (44) coupled with the ESC (45) by the energy generated from the power generation unit (40) provides additional force to the produced thrust and facilitates a smooth descent and landing of the parachute (100).

6. The process of working of the canopy-less parachute (100) as claimed in claim 5, wherein each propeller unit counter rotates with respect to the subsequent propeller unit to cancel out the torque.Tanu SinghAgent for the applicantRegn no: IN / PA 3855Dated: 25thSeptember 2024

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