Description:AERODYNAMIC LANDING GEAR SYSTEM WITH DRAG REDUCTION FEATURES
Field of the Invention
The current invention relates to aerodynamic optimization of airplane landing gear systems. More precisely, it is the design and modification of landing gear structures to incorporate drag-reducing devices or geometry, such as vortex generators (VGs), in order to reduce aerodynamic drag during flight and increase overall aircraft performance.
Background of the Invention

Landing gear structures contribute a large amount of aerodynamic drag in aircraft, particularly during takeoff, landing, and gear deployment. This drag not only influence flight efficiency, but it also increases fuel consumption and noise. Various attempts have been made over the years to minimize landing gear-induced drag, including the use of aerodynamic fairings, wheel covers, and retractable systems. However, these methods frequently increase weight, complexity, and cost.

The aerodynamic drag induced by exposed landing gear components is primarily due to flow separation and vortex shedding around the gear strut, wheels, and linkages. Earlier studies in this field have involved attempts to reduce drag by applying fairings or flattening the surface features of gear parts. For example, U.S. Patent No. US20110278497A1 describes a fairing for landing gear that improves airflow, whereas US20130112804A1 describes a noise and drag reduction system based Theon porous fairing. In addition, patent US20150115045A1 describes an aerodynamic wheel covering system for exposed undercarriage components. Despite these advancements, many conventional solutions continue to struggle with balancing aerodynamic performance, weight, durability, and manufacturability. There is still a need for a passive, structurally simple, and efficient drag reduction approach.

The proposed invention conquers these issues by altering the shape of the landing gear itself. This includes the use of passive flow control components like as vortex generators (VGs) on the gear struts and fairings, as well as structural reshaping to streamline the overall system. The goal is to create an aerodynamically improved landing gear design that decreases parasitic drag while needing no significant changes to the aircraft's retraction systems or load-bearing qualities.
This innovation contributes to the current industry desire for lighter, more economical aircraft by enhancing aerodynamic efficiency during gear-deployed flight operations while retaining a visually appealing and functionally effective gear assembly.
Conventional landing gear designs often include exposed struts, bogies, and wheel assemblies, which obstruct airflow and produce extensive wake zones with turbulent vortices. While partial solutions like fairings and covers have been investigated, they frequently add structural complexity and may not provide adequate drag reduction under changing flight conditions. This research, inspired by aerodynamic control techniques utilized in other technical areas, such as vortex generators and flow manipulators, looks at a modified landing gear layout. The design makes tiny geometric changes, such as strategically positioned fins or slots, to impact boundary layer behavior and reduce wake size behind the gear.
The original and updated landing gear designs were analyzed using computational fluid dynamics (CFD) to examine improvements in pressure distribution and drag coefficients. The results show considerable drag reduction in the improved model, demonstrating the viability of passive flow control devices as an efficient solution for landing gear aerodynamics.

Summary of the Invention
The current invention refers to the development of an aerodynamically optimized aircraft landing gear assembly. It describes a unique landing gear structure with incorporated geometric components, such as vortex generator-like fins or surface contours, that reduce drag by changing the shape and flow interaction characteristics of the gear. The creative design has a streamlined appearance with practical surface characteristics that set it apart from traditional landing gear shapes, contributing to both visual uniqueness and aerodynamic enhancement.
Brief Description of Drawings
The design will be described with reference to illustrative views provided:
Figure 1 – Front isometric view of the modified landing gear design incorporating aerodynamic surface features.
Detailed Description of the Invention
The current invention pertains to an aircraft landing gear system that has been aerodynamically optimized and incorporates sophisticated flow control features to lower drag and improve in-flight efficiency. By incorporating passive aerodynamic features into the landing gear geometry itself, the design tackles important problems related to parasitic drag brought on by exposed landing gear structures, especially during approach and landing phases.

The main innovation is the strategic placement of vortex generators (VGs), which are tiny, fin-like protrusions, across the landing gear strut and fairing components' structural surfaces. These devices are well-known for their efficiency in controlling flow and energizing the boundary layer. When positioned properly, VGs reduce turbulent wake formation behind the gear by encouraging streamwise vortices that prolong the airflow's attachment to the surface and delay flow separation. As a result, pressure drag is greatly reduced.
The main load-bearing component of the landing gear structure is a cylindrical, vertically oriented shock absorber strut. In contrast to earlier claims of reshaping, the strut maintains its conventional circular cross-section while adding aerodynamic functionality by strategically placing tiny vortex generators throughout specific areas. In order to create controlled streamwise vortices, these VGs are arranged in a linear array and have swept leading edges and pointed trailing edges. Better airflow management around the gear surface is the end result, supporting less flow separation and better pressure recovery.
Furthermore, the wheel assembly incorporates geometric cutouts and aerodynamically contoured hubs to minimize interference drag. The symmetrical arrangement of these cutouts reduces wake turbulence caused by rotating components. The lower strut provides structural support for the wheels, which are mounted to a central transverse axle. This axle is made to transfer loads efficiently while obstructing as little as possible the incoming airflow. The wheels' outer rims are concentrically rounded and grooved to facilitate a smoother flow transition around the tire surface.
The drag brace, which joins the lower strut to the fuselage attachment, is an essential component of the overall design. This part is designed with aerodynamics in mind, in addition to improving mechanical rigidity against landing loads. Its smooth curvature and slim profile prevent abrupt changes that might result in pressure imbalances or vortical shedding. The landing gear's upper and lower linkages are similarly made to balance flow and structural integrity. These components are shaped to follow the gear's natural streamlines and have blended transitions, which lessen abrupt geometry changes. By connecting the strut's internal piston mechanism to the airframe through a pivoting eyelet joint, the compact and streamlined design is maintained while functional compliance under dynamic loads is guaranteed.
This invention suggests integrated aerodynamic refinements into the structural surfaces as opposed to conventional external fairings or large enclosures that are added to the gear. This reduces extra weight and eliminates the need for complicated retractable coverings, improving the system's manufacturing and efficiency. The fundamental mechanical needs of the landing gear, such as load absorption during landing and taxi operations, are maintained despite the aerodynamic optimization. Without sacrificing ground-handling stability or retraction mechanics, this landing gear model is easily incorporated into traditional retractable systems. Because of its modular design, the invention can be applied to a wide range of platforms, including light aircraft, commercial airliners, regional transports, and unmanned aerial vehicles (UAVs).
Surface-curved transitions, integrated vortex generator arrays, and structurally efficient linkages combine to produce a distinctive, recognizable visual and functional profile from the standpoint of design innovation. In contrast to standard tubular or rectangular-section struts, the design incorporates aesthetic improvements that also serve as aerodynamic aids. These aesthetic adjustments, which include symmetric VG placement, progressive tapering, and curvature continuity, provide improved performance as well as a more contemporary look consistent with next-generation aerospace design concepts.
Additionally, the invention permits material flexibility based on mission requirements. The use of high-strength steels where cost-effectiveness and durability are crucial, or titanium alloys for weight-sensitive applications, is supported by the structural form. Standard shock-absorbing mechanisms can be incorporated into the internal framework without affecting the flow-optimized outer shell. In conclusion, this invention offers a cutting-edge yet workable way to improve aerodynamic efficiency and lower aircraft drag without sacrificing structural integrity or operational dependability. It offers a unique advantage in landing gear technology by combining structural engineering, functional aerodynamics, and design aesthetics in an integrated way.
Equivalents
The present invention provides a modified landing gear design with aerodynamic surface characteristics, such as vortex generators or fin-like protrusions integrated into the gear's external construction. Although the primary goal of this configuration is to reduce aerodynamic drag in aircraft, other exposed external structures in transportation systems, such as struts, bogies, or chassis elements in trains, drones, UAVs, or cars, may benefit from similar design concepts and geometric changes. As a result, this invention's applications are not limited to aircraft landing gear. , Claims:1. A drag-reducing aircraft landing gear system consists of:
a) a shock strut (1), which serves as the main structural member and is designed to absorb and soften landing forces, with an outer cylinder and an inner sliding piston.
b) A torque arm assembly (2) is pivotally coupled to the upper cylinder of the shock strut (1) and the lower piston section, preventing relative rotation between the upper and lower components of the strut during wheel travel.
c) A wheel axle assembly (3) attached to the lower end of the shock strut (1) and designed to support a dual-wheel arrangement (4) on either side, enhancing load-carrying capacity.
d) A pair of aircraft wheels (4) positioned on either side of the wheel axle (3), each with a rim and tire assembly with internal vents and ribbed characteristics for increased structural strength and braking effectiveness.
e) A drag-reducing fairing or vortex generator (5), positioned externally to the shock strut (1) or incorporated into its profile, is intended to streamline airflow around the landing gear and reduce aerodynamic drag during flight.
2. According to claim 1, the shock strut (1) is designed to retract into the aircraft fuselage or wing bay and includes an internal oleo-pneumatic damper for energy absorption during landing. The torque arm assembly (2) includes an upper arm pivotally attached to the strut cylinder and a lower arm connected to the piston, both joined by a hinge pin to provide synchronization during compression and extension.
3. According to claim 1, the wheel axle assembly (3) is rigidly fixed to the base of the piston section of the strut and made of a high-strength alloy that can bear high-impact loads and each aircraft wheel (4) has several radial supports and an inner hub that can accept disc brakes, resulting in high-efficiency braking and heat dissipation during aircraft deceleration.
4. According to claim 1, the drag-reducing fairing or vortex generator (5) is either integrally molded into the shock strut housing or mounted externally to minimize pressure drag and delay flow separation by electrifying the boundary layer.
5. According to claim 1,the shock strut (1), torque arm assembly (2), wheel axle assembly (3), dual wheels (4), and vortex generator (5) form a structurally strong and aerodynamically optimized landing gear system that improves aircraft performance and fuel efficiency during takeoff, flight, and landing.