Very Light Jet Capstone Design Project

With a team of 12 members, this project was achieved within three months. The teams and roles were divided as follows: Chief Integrator, Aerodynamics, Performance, Masterlines, Stability & Control, Weight & Balance, Loads & Dynamics, Marketing & Cost, Interiors, Conceptual Design & Sizing, and Systems. My role in this project was to lead the aerodynamics and systems teams. The initial step was conceptualizing the design and determining sizing requirements as a team. This required conducting trade studies into existing VLJ aircraft in the market such as the Cirrus Vision, Honda Jet, Cessna Citation Mustang, and Embraer Phenom 100. My role in this analysis was to compare the Honda Jet's performance against other VLJs.  Upon completion of the preliminary designing of the jet, my focus shifted to designing the aerodynamics and systems of the aircraft.

The following images illustrate the work completed to design the VLJs aerodynamics. The tools used to conduct the required design work include airfoil & empennage analysis in XFLR5 and wing analysis in ANSYS Fluent. With each iteration, the design required refining the wing model as well as meshing the wing geometry based on updated geometrical and performance parameters. Due to hardware constraints, the meshes were not refined to a high degree, resulting in discrepancies in expected aerodynamic values such as the total produced lift, quarter chord moment coefficient, and pressure distribution. However the parameters were compared to existing VLJ wing data to ensure approximations were within an appropriate magnitude. Using the Lifting Line Theory method (LLT), the aerodynamic coefficients of the airfoil were computed. This method is an aerodynamics mathematical model that predicts the lift of a finite wing using the concept of circulation and the Kutta-Joukowski theorem. 

Using reference textbooks and existing data, I developed an analysis of various parameters to determine the sizing of the wing, empennage, and airfoil. For instance recognizing the implication of stall speed during landing is essential in determining the airfoil shape and required flap angles. Furthermore, determining the required data in compliance to FAR23 airworthiness standards was imperative to a successful design. A critical factor in the design of the wing required additional considerations such as structural implications. Designing a thin airfoil raises concerns regarding the structural integrity of the wing. The wing analysis required focus on crucial phases of flight such as takeoff and landing where the integrity of the aircraft is at the highest risk.

One of the priorities in our design was to ensure a short takeoff & landing as part of our marketing strategy for the VLJ. With the large size of the wing planform area, the aircraft has a landing distance of 2615 ft and takeoff field length of 2071 ft. In addition, winglets were added to reduce the drag of the aircraft and improve the fuel efficiency despite the consequences of increased weight, aircraft instability due to a spiral divergence mode, and higher acquisition cost. Other scenarios examined included rotor burst design and system redundancy to improve the safety of the aircraft.

The systems design for the aircraft was separated into the following subsystems: hydraulics system, environmental control system, electrical system, flight control system, avionics system, fuel system, and engine control system. My role as the main focal point was to design these subsystems while accounting for dimensional and weight constraints of the aircraft following FAR23 airworthiness standards. One of the design challengers included a conflict between the electrical system and structural team. The structures team had a definitive volume for the placement of electrical buses and required a volume estimate for the electrical bus. This required a thorough analysis of standard wire lengths and gauges used in VLJ aircraft to ensure compliance with industry specifications and optimize weight and performance. The evaluation considered factors such as current-carrying capacity and mechanical durability to select the appropriate wire dimensions.

The SWARM Palanquin was designed with key engineering principles to stand out in the VLJ market, meeting specific requirements for passenger capacity, weight, and performance. Through a comprehensive tradeoff analysis of existing VLJs, an over-wing engine configuration was selected, offering benefits such as reduced risk of foreign object debris (FOD) enabling takeoff on unpaved runways, improved aerodynamic performance, and flexible tail design. With a maximum takeoff weight of 10,500 lbs, it achieves a long-range cruise of 1,000 nautical miles at maximum payload. The jet excels in short takeoff and landing (STOL) performance, requiring just 2,071 ft for takeoff and 2,615 ft for landing. It offers two interior configurations, comfortably seating 1 plus 5 passengers, completed with a lavatory. The VLJ design satisfied the stakeholder requirements of the project of having a passenger capacity of 6 passengers, an MTOW of approximately 10000 lb, and achieving a range of 1000 nm in long range cruise.