Vertical take-off and landing aircraft with enhanced ergonomics

Abstract

A vertical take-off and landing (VTOL) aircraft is disclosed, including a fuselage having an elevated front section configured to accommodate antennas for obstruction- free communication and a rear section configured to hold an engine, fuel storage, battery, and payload with easy and ergonomic access for loading, unloading, and maintenance A pair of wings extends laterally from fuselage to generate lift during flight, while a pair of canards are positioned forward of the wings to improve stability. The fuselage, the wings and canards are shaped to provide a significant nose-up pitching moment, enabling longitudinal stability at positive angles of attack. A pair of booms interconnect fuselage, wings, and canards to form an interconnected box-like structure that uniformly distributes loads across the aircraft. The aircraft includes VTOL rotors for vertical thrust, concealed landing gears for reduced air drag, and a cowling system with air inlets and outlets that provide efficient engine cooling.

Description

[0001] VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH ENHANCED ERGONOMICS

[0002] TECHNICAL FIELD

[0003] The present disclosure relates to generally to the field of unmanned air vehicles (UAVs) and more specifically to a multi-role high endurance UAV with enhanced ergonomics.

[0004] BACKGROUND

[0005] Unmanned aerial vehicles (UAVs) have emerged as a vital technology for applications, such as aerial surveillance, logistics, communication support, environmental monitoring, and defence operations. With the capability to be remotely piloted or autonomously operated, UAVs provide flexibility, reduce human risk in hazardous environments, and extend operational reach in areas where, traditional aircrafts face limitations. Vertical take-off and landing (VTOL) configurations in particular have expanded the operational scope of UAVs by eliminating the need for dedicated runways, thereby enabling deployment in urban areas, confined zones, and unprepared terrains.

[0006] Despite these advantages, conventional UAV designs face several technical challenges that limit their efficiency and operational reliability. The stability and control during transition between vertical and horizontal flight modes often require complex mechanisms, which increase structural weight and compromise aerodynamic performance. Twin-boom VTOL aircraft, in particular, are prone to substantial stress at the wing root structure due to the additional loads and vibrations generated by VTOL rotors on the cantilever structure. The concentration of stress reduces the operational lifespan of the aircraft, increases maintenance demands, and imposes limitations on payload capacity. Conventional UAVs are further constrained by shorter battery life, difficulties in achieving stable transitions between vertical and horizontal flight modes, and limited aerodynamic efficiency. In addition, restricted internal space often leads to inadequate cooling of propulsion units and onboard electronics, which adversely affects long-duration missions. Attempts to address the above structural issues have led to the exploration of alternative configurations, such as tandem wing or canard-wing configuration. While the tandem wing or canard-wing configuration of the UAVs can reduce the stress on the UAV, such configuration also presents certain challenges. The tandem wing or canard-wing configuration makes the payload of the VTOL aircraft inaccessible for loading and unloading. Additionally, the tandem wing or canard- wing configuration decreases the aerodynamic efficiency of the aircraft. Moreover, canard configurations are typically not used in conventional VTOL UAVs because the placement of the canards often coincides with the location of the VTOL rotors, which makes the canard configuration less effective. As a result, there exists a technical problem of how to develop a UAV configuration that minimizes structural stress at the wing root while simultaneously ensuring aerodynamic efficiency, unobstructed payload accessibility, effective canard placement for longitudinal stability, and reliable thermal management of propulsion systems.

[0007] Therefore, in light of the foregoing discussion, there exists a need to overcome the aforementioned drawbacks associated with the conventional designs of the VTOL aircraft.

[0008] SUMMARY

[0009] The present disclosure provides an improved UAV configuration that provides enhanced aerodynamic efficiency, structural robustness, effective cooling of propulsion units, and reliable integration of communication systems, while ensuring stable and efficient operation across multiple flight modes. The present disclosure provides a solution to the existing problem of how to develop a UAV configuration that minimizes structural stress at the wing root while simultaneously ensuring aerodynamic efficiency, unobstructed payload accessibility, effective canard placement for longitudinal stability, and reliable thermal management of propulsion systems. An aim of the present disclosure is to provide a solution that overcomes at least partially the problems encountered in the prior art, and provide an improved UAV configuration that provides enhanced aerodynamic efficiency, structural robustness, effective cooling of propulsion units, and reliable integration of communication systems, while ensuring stable and efficient operation across multiple flight modes. The object of the present disclosure is achieved by the solutions provided in the enclosed independent claims. Advantageous implementations of the present disclosure are further defined in the dependent claims.

[0010] In one aspect, the present disclosure provides a vertical take-off and landing (VTOL) aircraft, comprising a fuselage extending along a longitudinal axis of the VTOL aircraft and housing an engine. The fuselage comprises an elevated front section configured to hold one or more antennas for obstruction free communication and a rear section comprising the engine, associated propulsion components and payload. The VTOL aircraft further comprises a pair of wings extending laterally from opposite sides of the fuselage and configured to generate lift during cruise flight and a pair of canards coupled to the elevated front section of the fuselage. The VTOL aircraft further comprises a pair of booms interconnecting the pair of wings with the pair of canards. The fuselage along with the pair of wings and the pair of canards has a shape configured to generate a nose-up pitching moment to achieve longitudinal stability and equilibrium at a positive angle of attack. The VTOL aircraft further comprises a plurality of VTOL rotors mounted on the aircraft and configured to generate vertical thrust for take-off and landing operations. The VTOL aircraft further comprises a pair of vertical stabilizers positioned at the pair of wings and configured to provide directional stability, where a pair of main landing gears is concealed within the pair of vertical stabilizers to enhance aerodynamic efficiency during flight. The VTOL aircraft further comprises a retractable nose landing gear assembly housed within the fuselage. The VTOL aircraft further comprises a cowling system integrated with the fuselage and comprising strategically positioned one or more air inlets configured to capture airflow and one or more air outlets configured to discharge airflow. The one or more air inlets and the one or more air outlets are connected by internal air passages that direct controlled airflow specifically to cool an engine cylinder head during aircraft operation. The fuselage, the pair of wings, the pair of canards and the pair of booms are arranged to form an interconnected box-like structural configuration configured to uniformly distribute and transfer loads across the VTOL aircraft structure.

[0011] The disclosed VTOL aircraft provides a combination of structural, aerodynamic, and operational advantages that address limitations of conventional unmanned aerial vehicles. The fuselage incorporates the elevated front section that ensures obstruction- free communication by accommodating one or more antennas and the rear section that houses the engine, fuel storage, battery, and payload with easy and ergonomic access for loading, unloading, and maintenance. The pair of wings, in cooperation with the forward-positioned pair of canards, generate lift and induce a nose-up pitching moment for longitudinal stability at positive angles of attack, thereby reducing control input requirements and improving stall resistance. The pair of booms interconnects the pair of wings and the pair of canards to form an interconnected box-like structural configuration that uniformly distributes loads, reduces localized stresses, and increases structural rigidity. The pair of vertical stabilizers enhances directional stability while concealing the pair of main landing gears to reduce aerodynamic drag, complemented by the retractable nose landing gear assembly housed within the fuselage for streamlined performance. Additionally, the cowling system with strategically positioned air inlets and outlets directs airflow through internal passages to cool the engine cylinder head, ensuring efficient thermal management during extended missions. Collectively, these features enable the VTOL aircraft to deliver high endurance, superior stability, efficient cooling, and improved aerodynamic efficiency, making the VTOL aircraft suitable for versatile and demanding mission profiles.

[0012] It is to be appreciated that all the aforementioned implementation forms can be combined. All steps which are performed by the various entities described in the present application as well as the functionalities described to be performed by the various entities are intended to mean that the respective entity is adapted to or configured to perform the respective steps and functionalities. It will be appreciated that features of the present disclosure are susceptible to being combined in various combinations without departing from the scope of the present disclosure as defined by the appended claims.

[0013] Additional aspects, advantages, features, and objects of the present disclosure would be made apparent from the drawings and the detailed description of the illustrative implementations construed in conjunction with the appended claims that follow.

[0014] BRIEF DESCRIPTION OF THE DRAWINGS Embodiments of the present disclosure will now be described, by way of example only, with reference to the following diagrams wherein:

[0015] FIG. 1A is a diagram depicting a top view of a vertical take-off and landing (VTOL) aircraft, in accordance with an embodiment of the present disclosure;

[0016] FIG. IB is a diagram depicting an isometric view of a VTOE aircraft, in accordance with an embodiment of the present disclosure;

[0017] FIG. 1C is a diagram depicting an enlarged view of a rear section of a VTOL aircraft, in accordance with an embodiment of the present disclosure; and

[0018] FIG. ID is a diagram depicting a side view of a VTOL aircraft, in accordance with another embodiment of the present disclosure.

[0019] A non-underlined number relates to an item identified by a line linking the nonunderlined number to the item. When a number is non-underlined and accompanied by an associated arrow, the non-underlined number is used to identify a general item at which the arrow is pointing.

[0020] DETAILED DESCRIPTION OF EMBODIMENTS

[0021] The following detailed description illustrates embodiments of the present disclosure and ways in which they can be implemented. Although some modes of carrying out the present disclosure have been disclosed, those skilled in the art would recognize that other embodiments for carrying out or practicing the present disclosure are also possible.

[0022] FIG. 1A is a diagram depicting a top view of a vertical take-off and landing (VTOL) aircraft, in accordance with an embodiment of the present disclosure. With reference to FIG. 1A, there is shown a top view 100A of a vertical take-off and landing (VTOL) aircraft 102 that includes a fuselage 104 comprising an elevated front section 106A and a rear section 106B, a pair of wings 108, and a pair of canards 110. There is further shown that the VTOL aircraft 102 comprises a pair of booms comprising a first boom 126A and a second boom 126B. The VTOL aircraft 102 is an unmanned aerial vehicle (UAV) designed to operate without the requirement of conventional runways, as the aircraft can ascend, hover, and descend vertically. By integrating lift-generating rotors or propellers with fixed-wing aerodynamic surfaces, the VTOL aircraft 102 combines the advantages of rotary-wing and fixed-wing flight. The vertical lift capability of the VTOL aircraft 102 enables operation in confined or unprepared environments, while the pair of wings 108 provide efficient forward flight with extended range and endurance. The VTOL aircraft 102 is referred to as a multi-role high-endurance UAV as the aircraft is configured to perform diverse operational missions including surveillance, reconnaissance, logistics, and communication support, while the hybrid design combining vertical lift and fixed-wing flight enables extended range and prolonged mission duration.

[0023] The fuselage 104 may be referred to as a primary structural body that houses various components including but not limited to propulsion system of the aircraft (i.e., the VTOL aircraft 102), fuel storage, battery modules, avionics, payload and communication systems. The fuselage 104 is aerodynamically contoured to minimize drag while providing structural integrity to withstand aerodynamic loads, inertial loads, rotor-induced vibrations, and payload stresses. The fuselage design also accommodates cooling pathways for thermal management of propulsion units and electronic subsystems. In addition to supporting the attachment of the pair of wings 108, the pair of booms (i.e., the first boom 126A and the second boom 126B), the pair of canards 110, and a plurality of vertical stabilizers (shown in FIG. IB), the fuselage 104 ensures balanced weight distribution, accessibility for payload loading, unloading and management and integration of one or more antennas for reliable communication and navigation.

[0024] The elevated front section 106A of the fuselage 104 is configured to house navigation and communication modules, such as Global Positioning System (GPS) and Satellite Communication (SATCOM) antennas, ensuring unobstructed satellite connectivity and enhanced situational awareness during flight. More specifically, the elevated front section 106A is configured to hold one or more antennas for obstruction free communication. Examples of the one or more antennas my include, but are not limited to a GPS antenna, an infrared antenna, a SATCOM antenna, a telemetry antenna, a video transmission antenna, a payload antenna, and the like. The elevation also contributes to improved aerodynamic flow over the fuselage 104, reducing interference with forward-mounted control surfaces. The rear section 106B of the fuselage 104 accommodates the engine, the propulsion system, energy storage units, and payload bay, with its layout designed to balance the center of gravity while minimizing structural stress from rotor-induced loads. More specifically, the rear section 106B is configured to hold various vital components of the VTOL aircraft 102, such as the engine, fuel storage, battery and payload, and the like for easy and ergonomic access during loading, unloading and maintenance. By distributing functional components between the elevated front section 106A and the rear section 106B (may also be referred to as reinforced rear section), the fuselage 104 achieves improved stability, accessibility for operations and integration of payload and mission-critical systems.

[0025] The pair of wings 108 is configured to extend laterally from the fuselage 104 to provide lift and aerodynamic stability during forward flight. The pair of wings 108 is structurally reinforced to withstand aerodynamic loads and rotor-induced vibrations while maintaining a lightweight profile for efficient performance. The geometry of the pair of wings 108 is designed to enhance lift-to-drag ratio, thereby improving endurance and range during cruise operations. In addition to supporting control surfaces for manoeuvrability, the pair of wings 108 also serve as mounting points for vertical stabilizers and booms, forming an integrated structure that distributes stresses evenly across the VTOL aircraft 102. The configuration of the pair of wings 108 ensures smooth transition between vertical and horizontal flight modes, contributing to the overall stability and efficiency of the VTOL aircraft 102.

[0026] The VTOL aircraft 102 includes the pair of canards 110 positioned forward of the pair of wings 108 to enhance longitudinal stability and control. The pair of canards 110 is aerodynamic ally shaped and sized to generate a controlled nose-up pitching moment, thereby contributing to equilibrium during various flight modes. The pair of canards 110 is positioned at a considerable large distance from the pair of wings 108 therefore, the pair of canards 110 minimize aerodynamic interference while improving stall resistance and manoeuvrability. Furthermore, the pair of canards 110 is integrated with the fuselage 104 and boom assembly to form part of a rigid structure that uniformly distributes aerodynamic and rotor-induced loads, thereby reducing stress on the wing root. This configuration allows the pair of canards 110 to function not only as stabilizing surfaces and active control elements that improve the overall aerodynamic efficiency and flight performance but also as structural member that helps in uniform distribution of load and reduces stress on the wing root of the VTOL aircraft 102.

[0027] Each of the first boom 126A and the second boom 126B refers to a straight, elongated structure connecting the pair of wings 108 and the pair of canards 110. The pair of booms (i.e., the first boom 126A and the second boom 126B) interconnecting the pair of wings 108 and the pair of canards 110 is configured to provide the VTOL aircraft 102 an interconnected box-like structure. In an implementation, the pair of booms is configured to provide a mounting point for the plurality of VTOL rotors and various equipment or sensors, taking advantage of its strategic position between the pair of wings 108 and the pair of canards 110.

[0028] FIG. IB is a diagram depicting an isometric view of a VTOL aircraft, in accordance with an embodiment of the present disclosure. FIG. IB is to be understood in conjunction with the elements illustrated in FIG. 1A. With reference to FIG. IB, there is shown an isometric view 100B of the VTOL aircraft 102. The VTOL aircraft 102 includes a plurality of VTOL rotors including a first rotor 112A, a second rotor 112B, a third rotor 112C, and a fourth rotor 112D, a pair of vertical stabilizers 114, and a cowling system 116.

[0029] Each of the plurality of VTOL rotors (i.e., the first rotor 112A, the second rotor 112B, the third rotor 112C, and the fourth rotor 112D) refers to a rotating component mounted on the VTOL aircraft 102. Each rotor is configured to provide a vertical lift required for the VTOL aircraft 102 to take off, hover, and perform vertical manoeuvres. Each rotor is electrically or mechanically driven and designed with enhanced blade geometry to ensure efficient thrust generation while minimizing vibration and noise. The placement of each rotor is aligned with the aerodynamic surfaces (i.e., the pair of wings 108 and the pair of canards 110) of the VTOL aircraft 102 to reduce rotor wing interference, thereby enabling smooth transition between vertical and horizontal flight modes. Furthermore, each rotor is configured to operate in coordination with other rotors to stabilize and control the VTOL aircraft 102 during flight. In an implementation, the first rotor 112A and the second rotor 112B are positioned between the pair of canards 110 and the pair of wings 108 while the third rotor 112C and the fourth rotor 112D are positioned behind the pair of wings 108. In an exemplary scenario, the plurality of VTOL rotors (i.e., the first rotor 112A, the second rotor 112B, the third rotor 112C, and the fourth rotor 112D) can be co-axial rotors. The coaxial rotors may be mounted on the same axis but rotate in opposite directions, thereby allowing for the cancellation of torque. The distributed rotor configuration also enhances redundancy and fault tolerance, ensuring continued flight stability in the event of partial rotor failure. By balancing lift forces across the aircraft, the plurality of VTOL rotors contributes to reduced structural stress, improved manoeuvrability, and reliable VTOL capability under diverse operating conditions.

[0030] The pair of vertical stabilizers 114 is configured to provide directional stability and yaw control during forward flight modes. The pair of vertical stabilizers 114 is aerodynamic ally profiled and positioned in alignment with the plurality of VTOL rotors to minimize airflow disturbances and improve control effectiveness. In addition to the stabilizing function, the pair of vertical stabilizers 114 may accommodate integrated components, such as rudders or housing for main landing gear assembly, thereby contributing to aerodynamic efficiency and structural compactness. The placement of the pair of vertical stabilizers 114 on the pair of wings 108 and the pair of booms forms part of a rigid structural configuration that distributes aerodynamic and rotor-induced forces evenly across the aircraft structure. By enhancing yaw authority and maintaining flight balance, the pair of vertical stabilizers 114 play a vital role in ensuring manoeuvrability, stability, and safety of the VTOL aircraft 102 across diverse operating conditions.

[0031] The VTOL aircraft 102 further includes the cowling system 116, which refers to a removable covering or enclosure positioned at the rear section 106B of the fuselage 104. The cowling system 116 includes one or more air inlets and one or more air outlets to provide cooling to the engine while minimizing the increase in air drag. The one or more air inlets allows external air to enter the cowling system 116, which flows over the engine, absorbs heat generated by the engine, thereby preventing overheating, and ensuring that the engine operates within a suitable temperature range. Moreover, the air exits through the one or more air outlets, carrying away the absorbed heat and maintaining a stable operating environment for the engine.

[0032] FIG. 1C is a diagram depicting an enlarged view of a rear section of a VTOL aircraft, in accordance with an embodiment of the present disclosure. FIG. 1C is to be understood in conjunction with the elements illustrated in FIGs. 1A and IB. With reference to FIG. 1C, there is shown an enlarged view 100C of the rear section 106B of the VTOL aircraft 102. The enlarged view 100C represents that the rear section 106B includes a payload compartment 118 having a payload 120.

[0033] In an example, the payload 120 can be general freight. In another example, the payload 120 can be ammunition or artillery. In yet another example, the payload 120 can be food supplies, cargo, tools, instruments, and the like. The payload compartment 118 is configured to remain stable and secure during all phases of flight of the VTOL aircraft 102. The pay load compartment 118 is typically designed with reinforced walls and mounting points to prevent the pay load 120 from shifting or becoming dislodged during flight, which is required for maintaining the balance and aerodynamic integrity of the VTOL aircraft 102. Further, the pay load compartment 118 may also include shockabsorbing materials or mechanisms to protect sensitive payloads, such as delicate instruments or ammunition, from the stresses of take-off, landing, and in-flight turbulence of the VTOL aircraft 102. In another implementation, the payload compartment 118 is configured to allow easy loading and unloading of the payload 120 and provide an easy maintenance.

[0034] Moreover, the payload compartment 118 is accessible through hatches or doors, which are designed to be easily opened and closed for loading and unloading of the payload 120. The hatches or doors are shaped aerodynamically to minimize air drag when closed, ensuring that the performance of the VTOL aircraft 102 is not compromised. The payload compartment 118 may also be equipped with temperature control systems, particularly for payloads like medical supplies, food supplies or sensitive electronic equipment, ensuring that the contents are kept in suitable conditions throughout the flight. In some implementations, the rear section 106B of the fuselage 104 is also designed with dedicated compartments for the battery, the fuel storage and the engine similar to the payload compartment 118 for easy and ergonomic access during loading, unloading and maintenance. Advantageously, by providing the dedicated compartments for the payload 120, the battery, the engine and the fuel storage, the VTOL aircraft 102 ensures an appropriate space utilization within the fuselage 104. Additionally, by isolating the components, such as the payload 120, the battery, the engine and the fuel storage, the VTOL aircraft 102 reduces the risk of interference or damage between the safety- critical components.

[0035] FIG. ID is a diagram depicting a side view of a VTOL aircraft, in accordance with another embodiment of the present disclosure. FIG. ID is to be understood in conjunction with the elements illustrated in the FIGs. 1A, IB, and 1C. With reference to FIG. ID, there is shown a side view 100D of the VTOL aircraft 102. The side view 100D represents a pair of main landing gears 122 concealed within the pair of vertical stabilizers 114 and a retractable nose landing gear assembly 124.

[0036] The VTOL aircraft 102 comprises the pair of main landing gears 122 positioned symmetrically on opposite sides of the fuselage 104 to provide stable ground support during taxiing, take off, and landing operations. Each main landing gear includes a robust strut assembly, shock-absorbing elements, and a set of wheels designed to withstand high impact loads and distribute the aircraft’s weight evenly on the runway surface. The positioning of the pair of main landing gears 122 relative to the aircraft’ s center of gravity ensures balanced load distribution and enhances ground manoeuvrability. Furthermore, the pair of main landing gears 122 located inside designated compartments within the pair of vertical stabilizers 114, thereby remaining concealed during flight to reduce aerodynamic drag and maintain the streamlined profile of the VTOL aircraft 102.

[0037] In addition to the pair of main landing gears 122, the VTOL aircraft 102 is equipped with the retractable nose landing gear assembly 124. The design of the retractable nose landing gear assembly 124 involves a robust mechanical system that allows the retractable nose landing gear assembly 124 to extend and retract smoothly. The retractable nose landing gear assembly 124 is housed within the fuselage 104, such that the retractable nose landing gear assembly 124 remains securely stored during flight.

[0038] In an implementation, the retractable nose landing gear assembly 124 functions by extending outward when the VTOL aircraft 102 is prepared for landing, or the VTOL aircraft 102 is grounded. The outward extension of the retractable nose landing gear assembly 124 is typically controlled by an onboard mechanism that responds to the altitude, speed, and other flight parameters of the VTOL aircraft 102, ensuring that the retractable nose landing gear assembly 124 is deployed at the appropriate time. Moreover, once the VTOL aircraft 102 takes off, the retractable nose landing gear assembly 124 is configured to retract into the fuselage 104 via the controlled mechanism, thereby reducing the air drag and enhancing the aerodynamic profile of the VTOL aircraft 102.

[0039] There is provided the VTOL aircraft 102 comprising the fuselage 104 extending along a longitudinal axis of the VTOL aircraft 102 and housing an engine. The fuselage 104 comprises the elevated front section 106A configured to hold one or more antennas for obstruction free communication and the rear section 106B comprising the engine, associated propulsion components and the payload 120. The elevated front section 106A provides a raised profile that positions the one or more antennas above surrounding structural elements, ensuring uninterrupted communication and navigation links during operation. The fuselage 104 includes the rear section 106B in which the engine the associated propulsion components including the fuel storage and the battery, and the payload 120 are positioned for easy and ergonomic loading, unloading and maintenance. Locating the propulsion system in the rear section 106B enables compact integration and balanced weight distribution along the longitudinal axis of the VTOL aircraft 102. This configuration allows the central and forward portions of the fuselage 104 to be effectively utilized for avionics, communication modules, power distribution and other accommodation, thereby improving internal space utilization. The arrangement further contributes to improved aerodynamic performance by maintaining a streamlined fuselage profile, while also facilitating efficient cooling pathways and ease of maintenance for the engine, the other associated propulsion subsystems and the payload 120. The VTOL aircraft 102 further comprises the pair of wings 108 extending laterally from opposite sides of the fuselage 104 and configured to generate lift during cruise flight. The pair of wings 108 is aerodynamically contoured to provide an efficient lift-to-drag ratio, thereby enhancing endurance and range of the aircraft. In addition to generating lift, the pair of wings 108 contribute to the overall stability of the VTOL aircraft 102. The structural design of the pair of wings 108 also enables integration of control surfaces to facilitate manoeuvrability, while serving as attachment points for the pair of vertical stabilizers 114 and pair of booms. By combining vertical lift capability with efficient wing-based lift in cruise, the VTOL aircraft 102 achieves improved operational flexibility and energy efficiency.

[0040] The VTOL aircraft 102 further comprises the pair of canards 110 coupled to the elevated front section 106A of the fuselage 104. By being coupled to the elevated front section 106A of the fuselage 104, the pair of canards 110 operate in unobstructed airflow, thereby improving aerodynamic efficiency and contributing to the overall manoeuvrability of the VTOL aircraft 102.

[0041] The VTOL aircraft 102 further comprises the pair of booms interconnecting the pair of wings 108 and the pair of canards 110, where the fuselage 104 along with the pair of wings 108 and the pair of canards 110 has a shape configured to generate a nose-up pitching moment to achieve longitudinal stability and equilibrium at a positive angle of attack. The VTOL aircraft 102 further comprises the pair of booms (i.e., the first boom 126A and the second boom 126B) interconnecting the pair of wings 108 and the pair of canards 110 to provide structural continuity between forward air lifting surfaces (i.e., the pair of canards 110) and backward aft lifting surfaces (i.e., the pair of wings 108). In this configuration, the fuselage 104 along with the pair of wings 108 and the pair of canards 110 defines an aerodynamic shape that generates the nose-up pitching moment, thereby promoting longitudinal stability and maintaining equilibrium at positive angles of attack. The nose-up pitching moment helps the VTOL aircraft 102 to maintain the positive angle of attack, which is the angle between the oncoming air and the pair of wings 108. The positive angle is required for generating the necessary lift to keep the VTOL aircraft 102 airborne, especially during take-off and landing operations. The arrangement of the pair of canards 110 at the elevated front section 106A, the pair of wings 108 at the rare-fuselage, and the interconnecting booms ensures effective load sharing and aerodynamic balance, reducing the requirement of large control surface deflections and improving overall flight efficiency.

[0042] The VTOL aircraft 102 further comprises the plurality of VTOL rotors mounted on the aircraft and configured to generate vertical thrust for take-off and landing operations. The plurality of VTOL rotors (e.g., the first rotor 112A, the second rotor 112B, the third rotor 112C and the fourth rotor 112D) are positioned to provide balanced lift distribution about the longitudinal and lateral axes of the VTOL aircraft 102, thereby ensuring stable vertical flight. The distributed rotor arrangement also enhances redundancy, allowing the VTOL aircraft 102 to maintain controlled flight in the event of partial rotor malfunction. By enabling reliable vertical thrust, the plurality of VTOL rotors eliminates the requirement for conventional runway infrastructure and enhances the operational versatility of the aircraft in diverse environments.

[0043] The VTOL aircraft 102 further comprises the pair of vertical stabilizers 114 positioned at the pair of wings 108 and configured to provide directional stability, where the pair of main landing gears 122 is concealed within the pair of vertical stabilizers 114 to enhance aerodynamic efficiency during flight. The VTOL aircraft 102 further comprises the pair of vertical stabilizers 114 positioned at the pair of wings 108 and configured to provide directional stability by counteracting yawing moments during forward flight modes. The pair of vertical stabilizers 114 are aerodynamically profiled and structurally reinforced to withstand rotor-induced airflow and aerodynamic loads. Uniquely, the pair of main landing gears 122 is concealed within the pair of vertical stabilizers 114, thereby reducing air drag and improving aerodynamic efficiency during cruise flight. This integrated arrangement not only minimizes external protrusions that can disturb airflow but also enhances structural utilization of the pair of vertical stabilizers 114 by accommodating the landing gear mechanism within them. The concealment of the pair of main landing gears 122 further contributes to a streamlined configuration, enhancing endurance and performance while maintaining functional ground handling capability of the VTOL aircraft 102. The pair of vertical stabilizers 114 are hollow and the pair of main landing gears 122 is part of internal structure of the vertical stabilizers. The VTOL aircraft 102 further comprises the retractable nose landing gear assembly 124 housed within the fuselage 104. The retractable nose landing gear assembly 124 incorporates a mechanical retraction mechanism driven by an electric actuator, the retraction mechanism being mechanically linked to the doors of landing gear bay. The system is configured such that the retraction and deployment of the retractable nose landing gear assembly 124 and the opening and closing of the bay doors are mechanically synchronized, allowing all motions to be controlled by a single actuator. Such an arrangement of the retractable nose landing gear assembly 124 within the fuselage 104 ensures a streamlined aerodynamic profile during flight by eliminating protrusions that may otherwise increase drag or disrupt airflow around the fuselage 104. The integration of the retractable nose landing gear assembly 124 within the fuselage 104 also provides protection to the gear assembly from environmental exposure and impact during flight, thereby enhancing durability and reducing maintenance requirements.

[0044] The VTOL aircraft 102 further comprises the cowling system 116 integrated with the fuselage 104 and comprising strategically positioned one or more air inlets configured to capture airflow and one or more air outlets configured to discharge airflow, where the one or more air inlets and the one or more air outlets are connected by internal air passages that direct controlled airflow specifically to cool engine cylinder heads during aircraft operation. The arrangement of the one or more air inlets and the one or more air outlets within the cowling system 116 ensures effective thermal management by dissipating heat generated by the propulsion system, thereby preventing overheating and maintaining improved engine performance. The positioning of the one or more air inlets and the one or more air outlets is selected to maximize airflow capture with minimal aerodynamic disturbance, while the enclosed passages provide efficient routing of the cooling air within the fuselage 104. By integrating the cowling system 116 into the aircraft structure, engine reliability and overall endurance of the VTOL aircraft 102 are significantly enhanced without compromising aerodynamic efficiency.

[0045] The fuselage 104, the pair of wings 108, the pair of canards 110 and the pair of booms are arranged to form an interconnected box-like structural configuration configured to uniformly distribute and transfer loads across the VTOL aircraft structure. The interconnected box-like structural configuration enables aerodynamic, inertial, and rotor-induced loads to be uniformly distributed and transferred across multiple members of the VTOL aircraft 102, rather than being concentrated at localized junctions, such as the wing roots (i.e., the pair of wings 108). The configuration minimizes structural stress, reduces fatigue, and prolongs the service life of the VTOL aircraft 102 while maintaining a lightweight construction. In addition, the interconnected box-like arrangement provides a stable platform for integrating lifting and control surfaces, thereby contributing to improved flight stability and overall structural efficiency of the VTOL aircraft 102.

[0046] In accordance with an embodiment, the pair of canards 110 has a span extraordinarily smaller than that of the pair of wings 108 and is positioned forward of the pair of wings 108 at a considerably large distance sufficient to minimize aerodynamic interference between the pair of canards 110 and the pair of wings 108. Such configuration enables the pair of canards 110 to generate a controlled nose-up pitching moment for enhancing longitudinal stability without adversely affecting the aerodynamic efficiency of the pair of wings 108. The extraordinary smaller size of the pair of canards 110 in comparison to the pair of wings 108 ensures that their lift contribution remains limited to stability augmentation, while their forward placement maximizes control authority and stall resistance. The forward positioning of the pair of canards 110 relative to the pair of wings 108 provides additional lifting surfaces that enhance longitudinal stability and controllability of the VTOL aircraft 102. By minimizing aerodynamic overlap between the pair of canards 110 and the pair of wings 108, such arrangement reduces air drag, improves overall lift distribution, and enhances manoeuvrability of the VTOL aircraft 102 during transition between vertical and horizontal flight modes.

[0047] In accordance with an embodiment, the shape of the fuselage 104 is a non-uniform shape with an elevated nose profile comprising a flat bottom surface and a rounded top surface, configured to generate a pressure difference which further generates an upward force near the elevated front section 106A of the fuselage 104 and contributes to the nose-up pitching moment. Compared to the rear section 106B of the fuselage 104, the nose (or the front section i.e., the elevated front section 106A) of the fuselage 104 is elevated at a positive incidence angle and incorporates the flat bottom surface with the rounded top profile. This contour generates a pressure differential that produces an upward force near the elevated front section 106A of the fuselage 104, thereby inducing the nose -up pitching moment. The cooperative aerodynamic effect of the non-uniform shape of the fuselage 104 along with the pair of the wings 108, the pair of canards 110 and the pair of booms enables the VTOL aircraft 102 to maintain natural trim and equilibrium at positive angles of attack without requiring significant control surface deflection. The arrangement not only improves stall resistance and transition stability between vertical and horizontal flight modes but also reduces pilot or system control input, enhances aerodynamic efficiency, and contributes to extended endurance and reliable UAV operation under varied aerodynamic conditions.

[0048] In accordance with an embodiment, wherein each boom of the pair of booms is configured to extend longitudinally between the pair of wings 108 and the pair of canards 110, and where the pair of booms is configured to provide structural reinforcement and rigidity to the interconnected box-like structural configuration. The arrangement of the pair of booms (i.e., the first boom 126A and the second boom 126B) interconnecting the pair of wings 108 and the pair of canards 110 creates a closed structural loop that distributes aerodynamic and rotor-induced loads across multiple members, thereby reducing localized stress concentrations at the pair of wings 108 (or the wing root) and other junctions. By channelling forces through the interconnected box-like structural configuration, the pair of booms enhances the rigidity of the aircraft structure while minimizing material fatigue and deformation during prolonged operations. The interconnected box-like structural configuration of the VTOL aircraft 102 also provides a stable structural platform for mounting rotors and control surfaces, which contributes to improved load-bearing capacity, reduced vibrations, and extended service life of the VTOL aircraft 102.

[0049] In accordance with an embodiment, the plurality of VTOL rotors is positioned in alignment with the pair of vertical stabilizers 114 to minimize aerodynamic interference during operation. The positioning of the plurality of VTOL rotors (i.e., the first rotor 112A, the second rotor 112B, the third rotor 112C and the fourth rotor 112D) along the same vertical plane as the pair of vertical stabilizers 114, reduces airflow disturbances and vortex shedding that may occur between the lifting surfaces and the stabilizing structures. This alignment ensures smoother airflow around the airframe, thereby enhancing yaw stability, reducing drag, and improving overall aerodynamic efficiency. By minimizing interference effects, the configuration also decreases vibration loads transmitted to the fuselage 104 and structural members, which contributes to improved flight stability, reduced structural fatigue, and extended operational lifespan of the VTOL aircraft 102.

[0050] In accordance with an embodiment, the retractable nose landing gear assembly 124, when retracted, is fully housed within the fuselage 104 such that no portion of the retractable nose landing gear assembly 124 extends beyond an external surface profile of the fuselage 104. The arrangement of the retractable nose landing gear assembly 124 within the fuselage 104 ensures a streamlined aerodynamic contour during flight, reduces air drag, and protects the landing gear components from external exposure while maintaining reliable deployment and retraction functionality.

[0051] In accordance with an embodiment, the cowling system 116 further comprises a heat exchanger positioned within the internal air passages to enhance cooling efficiency of the engine cylinder head. The heat exchanger facilitates transfer of thermal energy from the engine to the controlled airflow channelled through the passages, thereby maintaining the cylinder head within a suitable temperature range during operation. The placement of the heat exchanger within the air passages ensures direct and continuous exposure to cooling airflow, maximizing heat dissipation without requiring additional external structures. In certain implementations, the heat exchanger may or may not be present depending upon the type of engine employed, and its type, design, orientation, and position may also vary according to engine configuration and cooling requirements. The flexible integration of the heat exchanger allows the cowling system 116 to be tailored for different propulsion architectures while ensuring effective thermal management, improved reliability, and extended service life of the propulsion system.

[0052] In accordance with an embodiment, the elevated front section 106A of the fuselage 104 has a raised profile specifically configured to position one or more antennas above surrounding structural elements of the VTOL aircraft 102 to ensure unobstructed communication. The raised profile of the elevated front section 106A ensures that the one or more antennas, including but not limited to GPS and SATCOM antennas (described in detail, for example, in FIG. 1A), are positioned above potential sources of structural or aerodynamic obstruction, thereby maintaining clear signal paths during flight. By integrating the one or more antennas into the elevated front section 106A, the design prevents interference from the pair of wings 108, the pair of canards 110, or rotor assemblies, ensuring reliable navigation, control, and data transmission. This configuration not only enhances communication efficiency but also contributes to the aerodynamic shaping of the fuselage 104 by streamlining the antenna integration within the airframe, thereby improving performance and reducing external mounting requirements.

[0053] In accordance with an embodiment, the associated propulsion components comprise, engine accessories, fuel storage, battery, engine control unit, starter-alternator, power management unit, and fuel delivery system, and where each of the engine, the associated propulsion components, and the payload 120 is arranged in the rear section 106B in a manner to provide weight balance along the longitudinal axis of the VTOL aircraft 102 and to allow access for loading, unloading and maintenance. Positioning the engine, the associated propulsion components comprising the engine accessories, fuel storage, battery, engine control unit, starter-alternator, power management unit, and fuel delivery system, and the payload 120 within the rear section 106B provides balanced distribution of mass along the longitudinal axis of the aircraft, thereby enhancing stability during both vertical and horizontal flight modes. The arrangement of propulsion and energy storage elements in the rear section 106B also simplifies structural reinforcement and thermal management by confining heat-generating and load-bearing systems to designated compartments. Additionally, housing the payload 120 in the rear section 106B allows for modular installation and secure retention while maintaining accessibility for mission-specific configurations. This arrangement enhances internal space utilization within the fuselage 104, contributes to improved aerodynamic shaping and weight balance, and advantageously frees the forward fuselage for accommodating communication modules, navigation systems, power distribution system and sensor equipment without structural or spatial constraints. Furthermore, the rear section layout provides easy and ergonomic access for loading, unloading, operations and maintenance, thereby improving operational efficiency and reducing turnaround time between missions.

[0054] In accordance with an embodiment, the one or more air inlets of the cowling system 116 are positioned on upper surface of the fuselage 104 to capture undisturbed airflow during forward flight modes. The one or more air inlets are located just behind the bulge of the fuel tank on the upper fuselage surface and extend across the entire width of the fuselage 104 between the pair of wings 108. The aerodynamic shaping of both the fuel tank bulge and the one or more air inlets is configured to accelerate the airflow passing over the fuselage 104, thereby directing a higher velocity stream of air into the inlets. Such an accelerated and undisturbed airflow enhances the efficiency of engine cooling by increasing both the volume and pressure of air supplied to the internal passages and, where present, heat exchangers. The upper-surface positioning also minimizes interference from rotor downwash and prevents ingestion of dust or debris during take-off and landing. As a result, the configuration ensures reliable thermal management while maintaining aerodynamic smoothness and operational efficiency of the VTOL aircraft 102.

[0055] Thus, the VTOL aircraft 102 provides significant operational and structural advantages over conventional UAV designs. The aircraft configuration includes the fuselage 104 having the non-uniform shape, the pair of wings 108 and the pair of canards 110, which together generate the nose-up pitching moment to achieve longitudinal stability and equilibrium at positive angles of attack. The pair of canards 110 is intentionally sized extraordinary smaller than the pair of wings 108 and positioned at the considerable large distance forward to minimize aerodynamic interference while contributing to stall resistance and manoeuvrability. Further, the pair of booms (i.e., the first boom 126A and the second boom 126B) interconnects the pair of wings 108 and the pair of canards 110 to form an interconnected box-like structural configuration that reduces stress concentrations on the pair of wings 108 and other structural members, thereby enhancing rigidity and extending service life of the aircraft structure. The VTOL aircraft 102 further comprises the plurality of VTOL rotors aligned with the pair of vertical stabilizers 114 (positioned at the pair of wings 108) to minimize aerodynamic interference, ensuring smooth airflow, improved yaw stability, and reduced vibration. The aerodynamic efficiency is further enhanced by concealing the pair of main landing gears 122 within the pair of vertical stabilizers 114 and housing the retractable nose landing gear assembly 124 within the fuselage 104, maintaining a streamlined external profile during flight. Additionally, the cowling system 116 integrated into the fuselage 104 includes strategically positioned air inlets and outlets, with optional incorporation of the heat exchanger, to deliver controlled cooling airflow to the engine cylinder head for reliable propulsion performance. The elevated front fuselage section (i.e., the elevated front section 106A) provides unobstructed accommodation for GPS, SATCOM and other antennas, ensuring reliable navigation and communication links. Further, the arrangement of the engine, the associated propulsion components and the payload 120 in the rear section 106B of the fuselage 104 allows easy and ergonomic loading, unloading and maintenance. Collectively, these features enable the VTOL aircraft 102 to operate as a multi-role, high-endurance platform offering enhanced payload capacity, superior stability, efficient thermal management, aerodynamic refinement, and versatile mission adaptability.

[0056] Modifications to embodiments of the present disclosure described in the foregoing are possible without departing from the scope of the present disclosure as defined by the accompanying claims. Expressions such as "including", "comprising", "incorporating", "have", "is" used to describe, and claim the present disclosure are intended to be construed in a non-exclusive manner, namely allowing for items, components or elements not explicitly described also to be present. Reference to the singular is also to be construed to relate to the plural. The word "exemplary" is used herein to mean "serving as an example, instance or illustration". Any embodiment described as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments and / or to exclude the incorporation of features from other embodiments. The word "optionally" is used herein to mean "is provided in some embodiments and not provided in other embodiments". It is appreciated that certain features of the present disclosure, which are, for clarity, described in the context of separate embodiments, may also be provided in combination in a single embodiment. Conversely, various features of the present disclosure, which are, for brevity, described in the context of a single embodiment, may also be provided separately or in any suitable combination or as suitable in any other described embodiment of the disclosure.

Claims

CLAIMSWe claim:

1. A vertical take-off and landing, VTOL aircraft (102), comprising: a fuselage (104) extending along a longitudinal axis of the VTOL aircraft (102) and housing an engine, wherein the fuselage (104) comprises an elevated front section (106A) configured to hold one or more antennas for obstruction free communication and a rear section (106B) comprising the engine, associated propulsion components, and payload; a pair of wings (108) extending laterally from opposite sides of the fuselage (104) and configured to generate lift during cruise flight; a pair of canards (110) coupled to the elevated front section (106A) of the fuselage (104); a pair of booms interconnecting the pair of wings (108) with the pair of canards (110), wherein the fuselage (104) along with the pair of wings (108) and the pair of canards (110) has a shape configured to generate a nose-up pitching moment to achieve longitudinal stability and equilibrium at a positive angle of attack; a plurality of VTOL rotors mounted on the aircraft and configured to generate vertical thrust for take-off and landing operations; a pair of vertical stabilizers (114) positioned at the pair of wings (108) and configured to provide directional stability, wherein a pair of main landing gears (122) is concealed within the pair of vertical stabilizers (114) to enhance aerodynamic efficiency during flight; a retractable nose landing gear assembly (124) housed within the fuselage (104); and a cowling system (116) integrated with the fuselage (104) and comprising strategically positioned one or more air inlets configured to capture airflow and one or more air outlets configured to discharge airflow, wherein the one or more air inlets and the one or more air outlets are connected by internal air passages that direct controlled airflow specifically to cool an engine cylinder head during aircraft operation, wherein the fuselage (104), the pair of wings (108), the pair of canards (110) and the pair of booms are arranged to form an interconnected box-like structural configurationconfigured to uniformly distribute and transfer loads across the VTOL aircraft structure.

2. The VTOL aircraft (102) as claimed in claim 1, wherein the pair of canards (110) has a span extraordinary smaller than that of the pair of wings (108) and is positioned forward of the pair of wings (108) at a considerably large distance sufficient to minimize aerodynamic interference between the pair of canards (110) and the pair of wings (108).

3. The VTOL aircraft (102) as claimed in claim 2, wherein the shape of the fuselage (104) is a non-uniform shape with an elevated nose profile comprising a flat bottom surface and a rounded top surface, configured to generate a pressure difference which further generates an upward force near the elevated front section (106A) of the fuselage (104) and contributes to the nose-up pitching moment.

4. The VTOL aircraft (102) as claimed in claim 1, wherein each boom of the pair of booms is configured to extend longitudinally between the pair of wings (108) and the pair of canards (110), and wherein the pair of booms is configured to provide structural reinforcement and rigidity to the interconnected box-like structural configuration.

5. The VTOL aircraft (102) as claimed in claim 1, wherein the plurality of VTOL rotors is positioned in alignment with the pair of vertical stabilizers (114) to minimize aerodynamic interference during operation.

6. The VTOL aircraft (102) as claimed in claim 1, wherein the retractable nose landing gear assembly (124), when retracted, is fully housed within the fuselage (104) such that no portion of the retractable nose landing gear assembly (124) extends beyond an external surface profile of the fuselage (104).

7. The VTOL aircraft (102) as claimed in claim 1, wherein the cowling system (116) comprises a heat exchanger positioned within the internal air passages to enhance cooling efficiency of the engine cylinder head.

8. The VTOL aircraft (102) as claimed in claim 1, wherein the elevated front section (106A) of the fuselage (104) has a raised profile specifically configured to position the one or more antennas above surrounding structural elements of the VTOL aircraft (102) to ensure unobstructed communication.

9. The VTOL aircraft (102) as claimed in claim 1, wherein the associated propulsion components comprise engine accessories, fuel storage, battery, engine control unit, starter-alternator, power management unit, and fuel delivery system, and wherein each of the engine, the associated propulsion components, and the payload is arranged in the rear section (106B) in a manner to provide weight balance along the longitudinal axis of the VTOL aircraft (102) and to allow easy and ergonomic access for loading, unloading and maintenance.

10. The VTOL aircraft (102) as claimed in claim 1, wherein the one or more air inlets of the cowling system (116) are positioned on an upper surface of the fuselage (104) to capture undisturbed airflow during forward flight modes.

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