EARLIEST PRIORITY DATE:

This Application claims priority from a Complete patent application filed in India having Patent Application No. 202141052020, filed on November 12, 2021 and titled “A SYSTEM FOR ENABLING DESCENT CONTROLOF A PAYLOAD”.

FIELD OF INVENTION

Embodiments of the present disclosure relate to the field of parachutes and more particularly to a system for enabling descent control of a payload.

BACKGROUND

A parachute is a device used to slow down a motion of an object which is free falling through an atmosphere by providing drag or lift. The parachutes are composed of light as well as strong fabric such as silk, nylon and the like. A variety of pay loads may be attached to the parachute, including people, food, equipment, space capsules, and military equipments. Based on shape, the parachute may be classified into round parachutes, cruciform parachutes, rogallo wings, ram air parachutes and the like. The round parachutes and the cruciform parachutes lacks maneuverability since the round parachutes and the cruciform parachutes may not be able to glide or provide lift. Also, application of the rogallo wings is limited with trikes and space crafts.

Currently, there exists many problems associated with the parachute. The parachute may fail to operate in whether conditions such as windy, rainy, hailstorm and the like. During rainy conditions, rainwater droplets may get accumulated on parachute fabric which may cause the parachute fabric to stretch causing the parachute inoperable. Also, pre-flight testing of the parachute may not be possible due to operational constraints. Further, the parachutes are very bulky, and may require significant surface area for deployment. Lack of maneuverability, inability to achieve pinpoint landing of the parachutes are another points of concern. Hamess and the associated suspension lines may cause entanglement of the parachute during deployment and may cause accidents. Hence, there is a need for an improved system for enabling descent control of a payload to address the aforementioned issue(s).

BRIEF DESCRIPTION

In accordance with an embodiment of the present disclosure, a system for enabling descent control of a payload is provided. The system includes one or more drag generating units coupled to corresponding one or more open canopies located at a proximal end of the one or more drag generating units. The one or more open canopies are coupled together by a connector to support a payload. The one or more drag generating units are adapted to generate drag from air resistance. The one or more drag generating units includes one or more rotary blades coupled to an outer gear of an epicyclic gear assembly. The one or more rotary blades are adapted to rotate the outer gear of the epicyclic gear assembly when incoming air falls on the one or more rotary blades. The one or more drag generating units also includes a compressor coupled to an inner gear of the epicyclic gear assembly. The compressor includes one or more compressor blades adapted to draw air from an outside environment by rotation of the one or more compressor blades corresponding to the rotation of the inner gear of the epicyclic gear assembly. The one or more compressor blades also adapted to compress the air drawn from the outside environment by the rotation of the one or more compressor blades to obtain compressed air. The one or more compressor blades further adapted to expel the compressed air to the outside environment via an outlet provided in the compressor, thereby enabling descent control of the payload.

To further clarify the advantages and features of the present disclosure, a more particular description of the disclosure will follow by reference to specific embodiments thereof, which are illustrated in the appended figures. It is to be appreciated that these figures depict only typical embodiments of the disclosure and are therefore not to be considered limiting in scope. The disclosure will be described and explained with additional specificity and detail with the appended figures.

BRIEF DESCRIPTION OF THE DRAWINGS

The disclosure will be described and explained with additional specificity and detail with the accompanying figures in which: FIG. 1 is a schematic representation of a system for enabling descent control of a payload in accordance with an embodiment of the present disclosure;

FIG. 2 is a schematic representation of one embodiment of the system of FIG. 1, depicting a top view of one or more open canopies and a connector in accordance with an embodiment of the present disclosure;

FIG. 3 is a schematic representation of another embodiment of the system of FIG. 1 , depicting an angle between two distal edges of one or more rotary blades in accordance with an embodiment of the present disclosure; and

FIG. 4 is a schematic representation of yet another embodiment of the system of FIG. 1, depicting a planetary gear assembly in accordance with an embodiment of the present disclosure.

Further, those skilled in the art will appreciate that elements in the figures are illustrated for simplicity and may not have necessarily been drawn to scale. Furthermore, in terms of the construction of the device, one or more components of the device may have been represented in the figures by conventional symbols, and the figures may show only those specific details that are pertinent to understanding the embodiments of the present disclosure so as not to obscure the figures with details that will be readily apparent to those skilled in the art having the benefit of the description herein.

DETAILED DESCRIPTION

For the purpose of promoting an understanding of the principles of the disclosure, reference will now be made to the embodiment illustrated in the figures and specific language will be used to describe them. It will nevertheless be understood that no limitation of the scope of the disclosure is thereby intended. Such alterations and further modifications in the illustrated system, and such further applications of the principles of the disclosure as would normally occur to those skilled in the art are to be construed as being within the scope of the present disclosure.

The terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process or method that comprises a list of steps does not include only those steps but may include other steps not expressly listed or inherent to such a process or method. Similarly, one or more devices or sub-systems or elements or structures or components preceded by "comprises... a" does not, without more constraints, preclude the existence of other devices, sub-systems, elements, structures, components, additional devices, additional sub-systems, additional elements, additional structures, or additional components. Appearances of the phrase "in an embodiment", "in another embodiment" and similar language throughout this specification may, but not necessarily do, all refer to the same embodiment.

Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which this disclosure belongs. The system, methods, and examples provided herein are only illustrative and not intended to be limiting.

In the following specification and the claims, reference will be made to a number of terms, which shall be defined to have the following meanings. The singular forms “a”, “an”, and “the” include plural references unless the context clearly dictates otherwise.

Embodiments of the present disclosure relate to a system for enabling descent control of a payload. In accordance with an embodiment of the present disclosure, a system for enabling descent control of a payload is provided. The system includes one or more drag generating units coupled to corresponding one or more open canopies located at a proximal end of the one or more drag generating units. The one or more open canopies are coupled together by a connector to support a payload. The one or more drag generating units are adapted to generate drag from air resistance. The one or more drag generating units includes one or more rotary blades coupled to an outer gear of an epicyclic gear assembly. The one or more rotary blades are adapted to rotate the outer gear of the epicyclic gear assembly when incoming air falls on the one or more rotary blades. The one or more drag generating units also includes a compressor coupled to an inner gear of the epicyclic gear assembly. The compressor includes one or more compressor blades adapted to draw air from an outside environment by rotation of the one or more compressor blades corresponding to the rotation of the inner gear of the epicyclic gear assembly. The one or more compressor blades also adapted to compress the air drawn from the outside environment by the rotation of the one or more compressor blades to obtain compressed air. The one or more compressor blades further adapted to expel the compressed air to the outside environment via an outlet provided in the compressor, thereby enabling descent control of the payload.

FIG. 1 is a schematic representation of a system (10) for enabling descent control of a payload (50) in accordance with an embodiment of the present disclosure. The system (10) includes one or more drag generating units (20) coupled to corresponding one or more open canopies (30) located at a proximal end of the one or more drag generating units (20). As used herein, canopies may be defined as a predefined shape formed above a parachute by a suitable material for trapping incoming air by forming an envelope. The canopy may create a region of high pressure which retards a movement of the parachute in a direction opposite to the incoming air flow. In an exemplary embodiment, the one or more open canopies (30) may include a circular opening at top. The one or more drag generating units (20) are adapted to generate drag from air resistance. In one embodiment, the one or more drag generating units (20) may be foldable to provide maneuverability during flight. The one or more open canopies (30) are coupled together by a connector (40) to support a pay load (50). As used herein, the payload (50) may be defined as an object or an entity which is being carried by an aircraft, the parachute, or a launch vehicle. In a specific embodiment, shroud lines may be attached to the connector (40) for securing the payload (50). As used herein, the shroud lines may be defined as one or more lines which may be used to secure the payload (50) to the parachute. Top view of the one or more open canopies (30) and the connector (40) may be seen in FIG. 2. In one embodiment, the one or more open canopies (30) and the connector (40) may be composed of materials includes at least one of metal, fiber, plastic, polymers, carbon fiber or a combination thereof.

Further, the one or more drag generating units (20) includes one or more rotary blades (60) coupled to an outer gear (FIG. 4, 70) of an epicyclic gear assembly (80). As used herein, the epicyclic gear assembly (80) may be defined as a gear assembly in which at least two gears mounted in such a way that centre of one gear revolves around the centre of the other. In one embodiment, the one or more rotary blades (60) may be enclosed by the corresponding one or more open canopies (30). In some embodiments, the corresponding one or more open canopies (30) may be adapted to protect the one or more rotary blades (60) from the outside environment. In one embodiment, the one or more rotary blades (60) may include an angle of at least 45° between two distal edges of corresponding one or more rotary blades (60) (as shown in FIG. 3). In one embodiment, the epicyclic gear assembly (80) may include a planetary gear. The one or more rotary blades (60) are adapted to rotate the outer gear (FIG. 4, 70) of the epicyclic gear assembly (80) when incoming air falls on the one or more rotary blades (60). In some embodiments, the one or more rotary blades (60) corresponding to the one or more drag generating units (20) may be adapted to rotate in opposite direction to provide operational stability. In one embodiment, the one or more rotary blades (60) and the one or more compressor blades (100) may be adapted to rotate in opposite direction.

Furthermore, the one or more drag generating units (20) also includes a compressor (90) coupled to an inner gear (FIG. 4, 110) of the epicyclic gear assembly (80). In one embodiment, the compressor (90) may include, but not limited to, axial compressor, centrifugal compressor, and mixed flow compressor. In one embodiment, cross sectional area of the compressor (90) may be gradually decreasing from the proximal end of the compressor (90) to the distal end of the compressor (90). In some embodiments, the compressor (90) may include stabilizing blades to stabilize an air flow. In one embodiment, the outer gear (FIG. 4, 70) and the inner gear (FIG. 4, 110) may be a sun gear and a ring gear of the planetary gear. In some embodiments, the outer gear (FIG. 4, 70) and the inner gear (FIG. 4, 110) may be coupled together by a gear ratio of at least 1: 3. In one embodiment, the one or more open canopies (30) may be adapted to generate a differential air pressure zone above the one or more rotary blades (60) to provide continuous air supply to the compressor (90). The compressor (90) includes one or more compressor blades (100) adapted to draw air from the outside environment by rotation of the one or more compressor blades (100) corresponding to the rotation of the inner gear (110) of the epicyclic gear assembly (80). In a specific embodiment, length of the one or more compressor blades (100) may be gradually decreasing from the proximal end of the compressor (90) to the distal end of the compressor (90).

Also, in one embodiment, the one or more compressor blades (100) may be twisted to enable uniform distribution of thrust generated on the one or more compressor blades (100). In some embodiments, the one or more compressor blades (100) may be bent towards the distal end of the compressor (90). The one or more compressor blades (100) also adapted to compress the air drawn from the outside environment by the rotation of the one or more compressor blades (100) to obtain compressed air. The one or more compressor blades (100) further adapted to expel the compressed air to the outside environment via an outlet (120) provided in the compressor (90), thereby enabling descent control of the payload (50). In one embodiment, the outlet (120) provided in the compressor (90) may include a nozzle adapted to increase pressure of the compressed air. In some embodiments, the system (10) may include an actuator unit (not shown in FIG. 1) adapted to increase speed of the one or more compressor blades (100) prior to landing. In such an embodiment, the actuator unit may include tensed wires to increase speed of rotation of the one or more compressor blades (100).

Various embodiments of the system for enabling descent control of a pay load described above enable various advantages. The system is capable of operating in various weather conditions such as rain, snow fall, hailstorm, heavy winds and the like. The system consumes less space during deployment and preflight testing of the system is possible due to compactness of the system. Also, provision of the drag generating units which are foldable provides maneuverability during operation. The system is cost effective as well as light weight. Additionally, the system may not require additional electronic components or fuel to operate which enables standalone functionality and reliability of the system. Absence of any complex mechanism enables easy operability of the system.

It will be understood by those skilled in the art that the foregoing general description and the following detailed description are exemplary and explanatory of the disclosure and are not intended to be restrictive thereof. While specific language has been used to describe the disclosure, any limitations arising on account of the same are not intended.

The figures and the foregoing description give examples of embodiments. Those skilled in the art will appreciate that one or more of the described elements may well be combined into a single functional element. Alternatively, certain elements may be split into multiple functional elements. Elements from one embodiment may be added to another embodiment. For example, the order of processes described herein may be changed and are not limited to the manner described herein. Moreover, the actions of any flow diagram need not be implemented in the order shown; nor do all the acts need to be necessarily performed. Also, those acts that are not dependent on other acts may be performed in parallel with the other acts. The scope of embodiments is by no means limited by these specific examples.