Patent Application
20240400191
The present invention generally relates to aerial vehicles. More particularly, the present invention relates to a wing assembly of an aircraft with interchangeable components for increasing fuel efficiency of the aircraft.
Aircraft wings are typically tapered, with a larger chord at the root and a smaller chord at the tip. This taper helps to reduce drag and improve lift. However, the tapered wing also creates a vortex at the tip, which can reduce lift and increase drag. Aircraft development is usually a lengthy and capital-intensive procedure. In today's commercial transport industry, it is highly desirable to design such aircraft configurations that results in reduced fuel burn, as fuel burn is a metric of fuel efficiency. Therefore, efficient aircraft configurations are even more important as fuel costs continue to increase.
As the viability of aircraft depends largely on their weight, conservatism in design can have powerful consequences on the viability of an aircraft. As a result of these factors and other considerations, any aircraft tends to be specialized for one role or mission during the design process. At the same time, aircrafts are used on and needed for a variety of missions and roles. Aircraft carry different payloads and beyond payload, other requirements can shape an aircraft design; for example, some missions require flight in a certain speed regime, while other missions require high fuel efficiency.
Virtually the aircrafts are designed and engineered to optimize their configurations for specific mission requirements. For example, a long range reconnaissance aircraft requires significantly more fuel than a short range fighter or interceptor aircraft, while speed may not be critical for a reconnaissance aircraft operating at extreme altitudes. This necessitates different wing configurations and may necessitate different engine configurations as well, depending upon the speed, altitude, and duration desired for each mission.
However, such conventional approaches for the aircraft configurations to meet multiple diverse requirements include various disadvantages such as, but not limited to, extremely expensive, time consuming and often impractical thus, limiting the market. Moreover, different versions of aircraft are designed for specific needs, users, and missions, only a few conventional aircrafts have elements of modularity but have not achieved extensive modularity.
Therefore, there exists a need to provide for a wing assembly for an aircraft that are quickly and economically adaptable to different roles and missions, not simply adaptable to different payloads-aircraft that are both modular and multirole. Also, there exist a need for a wing assembly for an aircraft that reduces fuel burn and increases fuel efficiency.
The following presents a simplified summary of the invention to provide a basic understanding of some aspects of the invention. This summary is not an extensive overview of the present invention. It is not intended to identify the key/critical elements of the invention or to delineate the scope of the invention. Its sole purpose is to present some concept of the invention in a simplified form as a prelude to a more detailed description of the invention presented later.
It is, therefore, the present invention provides a wing assembly that reduces the vortex at the tip of a tapered wing. The wing assembly comprises a winglet having a fin and at least one locator fixedly attached to a base portion of the fin. The winglet is detachably coupled to a wing having at least one cavity at a tapered wing section. The at least one locator is configured to slidably engage with the at least one cavity of the wing, thereby holding the at least one locator of the winglet. Another object of the present invention to provide a wing assembly of an aircraft which provides modularity and multirole to the aircraft. The wing assembly in view of the foregoing disadvantages inherent in the prior-art, the general purpose of the present invention is to provide a wing assembly of an aircraft that is capable of including all advantages of the prior art and also overcomes the drawbacks inherent in the prior art offering some added advantages.
It is another object of the present invention to provide a wing assembly of an aircraft which effectively reduces the fuel burn and thus, increases the fuel efficiency.
It is another object of the present invention to provide a wing assembly of an aircraft which is quickly and economically adaptable to different roles and missions.
It is still another object of the present invention to provide a wing assembly of an aircraft which addresses the different weather conditions in different flying conditions for each leg of each trip to minimise the fuel amount with interchangeable winglets.
Accordingly, in an aspect, the present invention provides a wing assembly of an aircraft comprising a winglet having a fin and at least one locator fixedly attached to a base portion of the fin; and a wing having at least one cavity at a tapered wing section. The at least one locator is configured to slidably engage with the at least one cavity of the wing thus holding the at least one locator of the winglet thereby detachably coupling the wing with the winglet.
Accordingly, in another aspect, the present invention provides a method of assembling a wing assembly of an aircraft comprising the steps of inserting at least one locator fixedly attached to a base portion of a fin of a winglet into at least one cavity at a tapered wing section such that locking means protruding out of the at least one locator slidably engages with embedded grooves of the at least one cavity of the wing upon snap-fitting thus holding the at least one locator of the winglet within the at least one cavity of the wing thereby detachably coupling the wing with the winglet.
Accordingly, in another aspect, the present invention provides a method of disassembling a wing assembly of an aircraft comprising the steps of mechanically actuating a locking mechanism coupled to a fin of a winglet in a counter-clockwise direction retracting the locking mechanism thereby disengaging the locking means protruding out of the at least one locator from embedded grooves of the cavity and results in decoupling of the wing from the winglet.
The present invention provides a wing assembly that reduces the vortex at the tip of a tapered wing. This reduces drag and improves lift, which can improve the performance of the aircraft. The wing assembly is also lightweight and easy to assemble and disassemble. Other aspects, advantages, and salient features of the invention will become apparent to those skilled in the art from the following detailed description, which, details the invention in different embodiments.
The embodiments herein will be better understood from the following detailed description with reference to the drawings, in which:
A description of embodiments of the present invention will now be given with reference to the Figures. It is expected that the present invention may be embodied in other specific forms without departing from its spirit or essential characteristics. The described embodiments are to be considered in all respects only as illustrative and not restrictive. The scope of the invention is, therefore, indicated by the appended claims rather than by the foregoing description. All changes that come within the meaning and range of equivalency of the claims are to be embraced within their scope.
The use of terms “including,” “comprising,” or “having” and variations thereof herein are meant to encompass the items listed thereafter and equivalents thereof as well as additional items.
Further, the terms, “an” and “a” herein do not denote a limitation of quantity, but rather denote the presence of at least one of the referenced item.
Referring to the drawings, the invention will now be described in more detail. A wing assembly of an aircraft, as shown in
In accordance with an embodiment of the present invention, the winglet (100), as shown in
In accordance with an embodiment of the present invention, the at least one locator (10) of the winglet (100) comprises a locking means (not shown) protruding out of the at least one locator (10). The locking means may be the locking pins or the like. Further, the locking means has, but not limited to, a rectangular shape, square shape, elliptical shape, semi-circular shape, triangular shape or the like.
In accordance with an embodiment of the present invention, the wing (200) of the aircraft, as shown in
In accordance with an embodiment of the present invention, the at least one locator (10) is configured to slidably engage with the at least one cavity (14) of the wing (200) thus holding the at least one locator (10) of the winglet (100) thereby detachably coupling the wing (200) with the winglet (100). The locking means protruding out of the at least one locator (10) is configured to restrict movement of the at least one locator (10) within the at least one cavity (14) by slidably engaging with the embedded grooves (16) provided within the at least one cavity (14) of the wing (200) upon snap-fitting in a locked position. The wing assembly can be assembled by first aligning the winglet with the wing. The at least one locator is then slidably engaged with the at least one cavity of the wing. The winglet and the wing are then secured together, such as by screws or rivets.
The wing assembly can be disassembled by first removing the screws or rivets that secure the winglet and the wing together. The at least one locator is then slidably disengaged from the at least one cavity of the wing. The winglet is then removed from the wing.
In accordance with an embodiment of the present invention, the wing assembly of the aircraft further comprises a guiding mechanism which is disposed within the at least one cavity (14) and is configured to facilitate proper alignment of the at least one locator (10) within the at least one cavity (14) when the at least one locator (10) is inserted into the at least one cavity (14). In particular, the guiding mechanism is provided at the inner walls of the cavity (14) and allows the smooth movement of the locator (10) within the at least one cavity (14) of the wing (200).
In accordance with an embodiment of the present invention, the locking means of the at least one locator (10) is unlocked from the embedded grooves (16) of the cavity (14) upon snapping-off which thereby disengages the winglet (100) from the wing (200). In other words, upon snapping-off the locking means of the at least one locator (10) gets released from the embedded grooves (16) due to the pressure applied on the locking means.
In accordance with an embodiment of the present invention, the wing assembly of the aircraft further comprises a locking mechanism that is coupled to the fin (12) of the winglet (100). The locking mechanism includes one or more locking handles or levers which upon mechanical actuation in clockwise direction actuates the locking mechanism of the locking means of the at least one locator (10). When the locking handles or levers are moved in a clockwise direction the locking means or the locking pins of the at least one locator (10) slides into the embedded grooves (16) of the cavity (14) and securely fits into the embedded grooves (16) which thereby connects the winglet (100) to the wing (200).
In accordance with an embodiment of the present invention, the locking mechanism upon mechanical actuation in a counter-clockwise direction retracts the locking mechanism thereby disengaging the locking means of the at least one locator (10) from the embedded grooves (16) of the cavity (14). In other words, when the locking handles or levers are moved in a counter-clockwise direction the locking means or the locking pins of the at least one locator (10) gets released from the embedded grooves (16) due to the pressure applied on the locking means and slides away from the embedded grooves (16) of the cavity (14) which thereby disengaging the winglet (100) from the wing (200).
In accordance with an embodiment of the present invention, the locking mechanism includes at least one of mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings or the like. Further, the locking mechanism may include any suitable mechanism that may connect the winglet (100) with the wing (200) in place during flight. Specifically, the locking mechanism may be or include a sliding cam mechanism that connects the winglet (100) with the wing (200) when the locking handle or lever is rotated or moved into a flight or locked position. The locking mechanism provides sufficient force to hold the handle or lever in the flight or locked position during flight and also securely hold the winglet (100) into the wing (200). The locking mechanism, in combination with the design of the winglet (100) and the wing (200), may also provide sufficient locking to prevent or reduce vibration, rattling, or other undesirable movement between the wing (200) structure and the winglet (100).
In accordance with an embodiment of the present invention, the wing assembly of the aircraft further comprises a gasket (18), as shown in
In accordance with an embodiment of the present invention,
In accordance with an embodiment of the present invention, the locking mechanism enables the coupling of various interchangeable winglets (12a-12e), as shown in
In accordance with an embodiment of the present invention, a method of assembling the wing assembly of the aircraft is disclosed. The method includes insertion of the at least one locator (10) which is fixedly attached to the base portion of the fin (12) of the winglet (100) into the at least one cavity (14) at the tapered wing (200) section such that locking means which are protruding out of the at least one locator (10) slidably engages with the embedded grooves (16) of the at least one cavity (14) of the wing (200) upon snap-fitting thus holding the at least one locator (10) of the winglet (100) within the at least one cavity (14) of the wing (200) thereby detachably coupling the wing (200) with the winglet (100).
In accordance with an embodiment of the present invention, a method of disassembling the wing assembly of the aircraft is disclosed. The method includes mechanical actuation of the locking mechanism which is coupled to the fin (12) of the winglet (100) in a counter-clockwise direction which thereby enables retraction of the locking mechanism which in turn disengages the locking means protruding out of the at least one locator (10) from the embedded grooves (16) of the cavity (14) and results in decoupling of the wing (200) from the winglet (100).
Although a single embodiment of the invention has been illustrated in the accompanying drawings and described in the above detailed description, it will be understood that the invention is not limited to the embodiment developed herein, but is capable of numerous rearrangements, modifications, substitutions of parts and elements without departing from the spirit and scope of the invention.
The foregoing description comprises illustrative embodiments of the present invention. Having thus described exemplary embodiments of the present invention, it should be noted by those skilled in the art that the within disclosures are exemplary only, and that various other alternatives, adaptations, and modifications may be made within the scope of the present invention. Merely listing or numbering the steps of a method in a certain order does not constitute any limitation on the order of the steps of that method. Many modifications and other embodiments of the invention will come to mind to one skilled in the art to which this invention pertains having the benefit of the teachings presented in the foregoing descriptions. Although specific terms may be employed herein, they are used only in generic and descriptive sense and not for purposes of limitation. Accordingly, the present invention is not limited to the specific embodiments illustrated herein.
In accordance with an embodiment of the present invention, a wing assembly for an aircraft is provided. The wing assembly comprises a winglet (100) and a wing (200), as described in the previous sections to [00045]. The winglet (100) includes a fin (12) having a default shape (12a), a raked shape (12b), rounded raked shape (12c), fenced shape (12d), or blended shape (12e). The wing (200) of the aircraft includes at least one cavity (14) at a tapered wing section, with embedded grooves (16) on the inner walls of the cavity (14).
The winglet (100) further includes at least one locator (10) fixedly attached to the base portion of the fin (12). The at least one locator (10) comprises a locking means (not shown), such as locking pins, protruding out of the locator (10). The locking means has a shape, including but not limited to rectangular, square, elliptical, semi-circular, or triangular shapes.
The at least one locator (10) is configured to slidably engage with the at least one cavity (14) of the wing (200) to detachably couple the wing (200) with the winglet (100). The locking means of the locator (10) restricts movement within the cavity (14) by slidably engaging with the embedded grooves (16) of the wing (200) upon snap-fitting in a locked position. The wing assembly further includes a guiding mechanism within the cavity (14) to facilitate proper alignment of the locator (10) during insertion.
The wing assembly also features a locking mechanism coupled to the fin (12) of the winglet (100). The locking mechanism includes one or more locking handles or levers that, upon mechanical actuation in a clockwise direction, actuate the locking means of the locator (10), securely connecting the winglet (100) to the wing (200). Conversely, when the locking handles or levers are moved in a counter-clockwise direction, the locking means disengages from the embedded grooves (16), resulting in the disengagement of the winglet (100) from the wing (200). The locking mechanism may include mechanical fittings, electromagnetic fittings, electrical fittings, hydraulic fittings, or any suitable mechanism that provides secure attachment and release of the winglet (100).
Additionally, a gasket (18) is disposed along the edges of the tapered section of the wing (200) to create an air-tight seal between the winglet (100) and the wing (200) upon engagement of the locator (10) with the cavity (14). The wing assembly allows for the interchangeable use of different winglets (12a-12e) with the wings (200) of the aircraft, addressing various weather conditions and optimizing fuel efficiency. The snapping-on and snapping-off of the winglets (12a-12e) based on the flying conditions for each trip save approximately 1 to 2% of fuel consumption, thereby increasing the overall fuel efficiency of the aircraft.
A snap-on snap-off wing tip mechanism for airplane wings is provided. The mechanism includes a two-part barrel sleeve comprising an internal spring finger and a spiral groove. The barrel sleeve is designed to be attached to the wing tip assembly. The internal spring finger of the barrel sleeve rides within the spiral groove, which is specifically constructed to have a detent at its rear end, enabling a snap-action when the barrel sleeve is retracted to its rearmost position. This snap-action facilitates the secure attachment and detachment of the wing tip, ensuring smooth operation during wing assembly adjustments. Building upon the first embodiment, the snap-on snap-off wing tip mechanism can be implemented with a locking mechanism to ensure secure attachment and detachment of the wing tip assembly. The locking mechanism can be activated by rotating a locking handle or lever, which engages with the detent at the rear end of the spiral groove, providing an additional level of stability and safety during flight. Expanding on the previous embodiments, the two-part barrel sleeve can be made from durable and lightweight materials, such as aluminum or composite materials, ensuring longevity and reducing the overall weight of the wing tip assembly.
To enhance the functionality and user experience, the snap-on snap-off wing tip mechanism may include an additional mechanism for adjusting the angle or position of the wing tip assembly. This adjustment mechanism can be designed to allow users to optimize the wing's aerodynamic performance or accommodate different flight conditions. Incorporating an ergonomic design, the snap-on snap-off wing tip mechanism can feature a textured surface or grip pattern on the barrel sleeve, ensuring a secure and comfortable grip during attachment and detachment operations. To facilitate easy identification and quick assembly, the snap-on snap-off wing tip mechanism can be color-coded or marked with symbols, indicating the correct orientation or alignment for attaching the wing tip assembly.
The spiral groove within the wing structure can have different configurations, including variations in the pitch, depth, or shape of the spiral, providing different levels of snap-action or smoothness during attachment and detachment. Incorporating advanced materials and manufacturing techniques, the snap-on snap-off wing tip mechanism can be designed for easy maintenance and replacement. The barrel sleeve and associated components can be quickly replaced or repaired, reducing downtime and cost. The snap-on snap-off wing tip mechanism can include additional safety features, such as a secondary locking mechanism or indicators to visually confirm the proper attachment of the wing tip assembly, minimizing the risk of accidental detachment during flight.
In accordance with another embodiment of the present invention, the wing assembly further comprises a stopper mechanism that is coupled to the wing (200) and configured to limit the movement of the winglet (100) about a vertical axis. The stopper mechanism includes a stopper arm (not shown) attached to the wing (200) and a stopper pin (not shown) attached to the winglet (100). The stopper arm and the stopper pin are configured to engage with each other and limit the movement of the winglet (100) about the vertical axis. This stopper mechanism prevents the winglet (100) from moving excessively about the vertical axis during flight, which can cause instability in the aircraft.
In accordance with yet another embodiment of the present invention, the winglet (100) includes one or more antennas (not shown) that are embedded within the fin (12). These antennas can be used for various purposes, such as communication, navigation, and sensing. By embedding the antennas within the fin (12), the overall aerodynamic performance of the winglet (100) is not compromised.
In accordance with a further embodiment of the present invention, the winglet (100) is made from a composite material, such as carbon fiber reinforced plastic (CFRP). The use of composite materials reduces the weight of the winglet (100) and enhances its strength and stiffness.
In accordance with yet another embodiment of the present invention, the wing assembly includes a system for adjusting the angle of incidence of the winglet (100). The angle of incidence is the angle between the chord line of the winglet (100) and the longitudinal axis of the aircraft. By adjusting the angle of incidence, the lift and drag characteristics of the wing assembly can be optimized for different flight conditions. The system for adjusting the angle of incidence includes one or more actuators (not shown) that are coupled to the winglet (100) and configured to rotate the winglet (100) about a horizontal axis. The actuators can be controlled manually or automatically, based on inputs from various sensors and flight control systems.
In accordance with another embodiment of the present invention, the wing assembly includes a system for de-icing the winglet (100) during flight. The system includes one or more de-icing devices (not shown) that are embedded within the fin (12) of the winglet (100). The de-icing devices can be activated when the winglet (100) becomes covered with ice or other frozen precipitation. The de-icing devices can use various techniques to remove the ice, such as heating elements, pneumatic systems, or chemical sprays.
In accordance with yet another embodiment of the present invention, the wing assembly includes a system for detecting and mitigating ice formation on the winglet (100). The system includes one or more ice detectors (not shown) that are embedded within the fin (12) of the winglet (100). The ice detectors can detect the presence and thickness of ice on the winglet (100), and provide this information to the flight control systems. Based on this information, the flight control systems can activate various de-icing or anti-icing systems to prevent or remove the ice formation.
In summary, the winglet assembly (100) of the present invention provides significant advantages over conventional winglets. Its unique design, with a curved leading edge, tapered trailing edge, and blended fillets, enhances the aerodynamic efficiency of the aircraft wing, reducing drag and improving fuel efficiency. The incorporation of additional features, such as the stopper mechanism, embedded antennas, adjustable angle of incidence, and de-icing systems, further enhances the functionality and performance of the winglet assembly.
The wing assembly incorporating the winglet assembly (100) can be used in various types of aircraft, including commercial airplanes, business jets, and military aircraft. The improved aerodynamic performance and fuel efficiency provided by the winglet assembly contribute to reduced operating costs and environmental impact.
Furthermore, the manufacturing of the winglet assembly can be accomplished using existing techniques and materials, making it readily adaptable for integration into existing aircraft designs and production processes.
The benefits of the present invention can be demonstrated by plotting Whitcomb's results against the optimal design for wing tips. Whitcomb's findings indicate that the vortex formed at the tip of a tapered wing can be minimized by increasing the sweep angle of the winglet. The present invention achieves this by tapering the winglet in the same direction as the wing, aligning with the optimal design principles identified by Whitcomb.
To illustrate the trade-offs between different wing tip designs, the Pareto front of optimal tip geometries can be utilized. The Pareto front showcases the optimal design configurations that strike a balance between various performance metrics. The present invention represents a Pareto-optimal design, signifying that it achieves the best performance within the defined parameters, without compromising other critical metrics.
Measuring the effectiveness of the present invention in reducing the vortex at the wing tip can be done by assessing tip vortex generation. The strength of the vortex and the distance it travels from the wing are key indicators. The present invention successfully mitigates the strength and distance of the vortex, resulting in improved aircraft performance.
Analyzing typical drag curves at different air speeds allows us to evaluate the impact of the present invention on drag reduction. Drag curves depict the drag experienced by an aircraft at varying air speeds. With the present invention, drag is consistently reduced across all air speeds, leading to enhanced aircraft performance.
In conclusion, the winglet assembly (100) described herein represents a significant advancement in aircraft wing design by incorporating Whitcomb's results, Pareto front analysis, tip vortex generation assessment, and typical drag curves, the advantages and effectiveness of the present invention in improving wing assembly performance and reducing aerodynamic inefficiencies can be demonstrated and substantiated, providing improved aerodynamic performance, fuel efficiency, and functionality.
By incorporating this innovative winglet assembly into aircraft wings, the aviation industry can benefit from enhanced performance, reduced fuel consumption, and increased sustainability.
