AERO 4400 Aircraft Design 3 6 credit points 2002 Design Task: (Option 1) High Performance Multi-Role Unmanned Aerial Vehicle (UAV) Assessment: This task, with four (4) hand-in assignments (detailed separately) and associated presentations, final report, poster(s) and model(s) forms 100% of this course. Please note Item I of Appendix A for task requirements. Marking will be approximately based on Item II of Appendix A. Final assessment will be based on a combination of individual and team components, including peer assessments. Teams and Task Option allocations will be finalised in week 1. Design Objectives and Requirements powerplants. A recent engine development provides a REQUEST FOR PROPOSAL (RFP - Option 1): High potential opportunity to develop a HALE UAV. Performance Multi-Role UAV Opportunity thus exist to evaluate the feasibility and cost effectiveness of such UAVs. I. Opportunity Description Australia is a vast country which has: <http://www.williams-int.com/product/fjx.htm> • clear surveillance requirements for defence, Williams International is working on a cooperative coastwatch, and the monitoring and protection of effort with NASA, called the General Aviation Propulsion (GAP) Program, aimed at revolutionizing the environment and coastal natural resources; and reviving the once flourishing light aircraft • rich mineral wealth deposits which needs to be industry in the U.S. In this program, Williams exploited with due consideration to environmental International is developing the FJX-2 turbofan impact; engine for use in the next generation of four- and • a harsh climate, requiring understanding to support six-passenger general aviation airplanes. the population areas; and hence • potentially a good domestic market for Unmanned The FJX-2 is much smaller than the smallest Aerial Vehicles (UAVs). commercial turbofan of today. It is in the 700-lb The recent (2001) deployment of the Northrop Grumman thrust class and weighs less than 100 pounds. The Global Hawk High Altitude Long Endurance (HALE) engine is in development and will be flight-ready in UAV in Australia has led to much interest in acquiring the year 2000. The primary goal of the FJX-2 is such a capability. A recent market survey1 indicated affordability. It will allow jet-powered airplanes to be strong opportunities for high-altitude, long endurance priced competitive with today's general aviation (HALE) UAVs with around 100kg payload, 50-100 piston-powered planes. km/h cruising/loitering airspeed, and greater than 24 With turbofan power, this new generation of hours endurance. Although there are many UAV airplanes will fly faster, have longer range, be more systems either in operation or under development world- comfortable and quiet, and set a new standard in wide, there are few that could be considered affordable general aviation safety. to commercial operators that have attributes suitable to Based on its very low noise level, light weight, low operation for commercial purposes. High costs are emissions, low fuel consumption, and low cost in partly because most systems have been developed for quantity production, the FJX-2 engine will be a military markets and roles, and therefore subject to major factor in reviving the once flourishing light stringent military specifications. It is believed that aircraft industry. developments specifically aimed at commercial operations and therefore with attributes tailored to Engine Characteristics commercial requirements are more likely to be Thrust Class . 700 lbf acceptable to the civilian UAV market, with obvious Overall Length . 41.0 in opportunities in an increasingly cost-conscious defence Diameter . .14.5 in market. Weight . < 100 lbs One of the constraints for lowering the cost of UAV This engine is also known as the Williams EJ22. There airframes has been the availability of suitable are manned aircraft designs under development which uses two of these engines, eg. V-JET II and Eclipse 500. A contest is currently underway to design such a single 1 engine 2-seat aircraft, more information being located at Wong, et. al., “Study of the Unmanned http://www.x-plane.com/design.html. The X-Plane Aerial Vehicle (UAV) Market in Simulation Software used there may be optionally used Australia”, Aerospace Technology Forum in this task, if so desired. Report, August 1997. II. Project Objective autonomous flight controller(s), appropriate Your company wants to explore the feasibility of surveillance sensor(s), and Ground Command and building a new family of aircraft, powered by one Control station(s). The choice and relative merit of Williams International FJX-2/EJ22 turbofan engine, which is left to the designer, as long as mission to target this potentially growing UAV marketplace. The requirements are met. objective is to provide your management with a • Payload: Electro Optical (EO), Infra-Red (IR), conceptual design of a highly capable low-cost UAV and/or other surveillance sensors up to a maximum system to suit a variety of missions. The cost of at least 232 kg (510 lb). effectiveness of this new concept must be illustrated with comparisons to existing systems. Tradeoff studies • Maximum Empty Weight: 1500 lbs (682 kg). should be incorporated to show that the concept is a • Appearance: The aeroplane should be aesthetically balanced and optimum design. If the company plans to pleasing. pursue this new development program, the target date for entry into service is the year 2004. Certification: • The UAV airframe should be designed to meet the A perusal of the history of UAV development would draft CASA UAV Design requirements (see separate reveal a long list of programme failures due to mission attachment), with guideline reference to JAR-VLA. requirement growth or changes (eg. The Aquilla and Notes: Outrider UAVs), which would seemingly rule out the development of multi-role UAV systems. These high- • All performance requirements, including those cost failures have taught the UAV industry that the key presented here and those specified by the respective to successful UAV programmes is a firm definition of a regulations, should meet the regulatory values and mission and stick to it (eg. Pioneer, Predator, Aerosonde definitions. UAVs). However, because UAV application to many • Aircraft which are predicted to significantly surpass market sectors are still unexplored, the opportunity is the specified design parameters are acceptable, still clearly there for low-cost multi-role high provided this can be justified as a cost or performance UAVs to operationally trial new High marketability tradeoff. Altitude Long Endurance missions before they are firmly defined. Although recognised to be only around 15% of • Roles such as Search and Rescue (SAR), Powerline the total cost of UAV systems, the airframes remain a inspection, Coastwatch, Telecommunications Relay, critical element to meet any mission performance Bushfire Command and Control, or any other objectives (eg. Endurance, speed, range). market identified roles should be explored and detailed. III. Requirements and Constraints Structural Layout: Configuration Selection Criteria: A conceptual structural layout of the aircraft is required along with a material breakdown. Advanced materials The final configuration proposed shall be selected on the may be used in an attempt to reduce the empty weight of basis of the lowest development cost and satisfy all of the aircraft. However, any potential cost penalties from the requirements contained within the RFP. using advanced materials should be addressed. Flight Capability: Aerodynamics: • Maximum Speed: Highest possible. Consideration of advanced technologies may be included • Loiter Speed: lowest possible. in the configuration. However, the technology must prove to be affordable, reliable and easily maintainable. • Cruise: Endurance no less than 24 hours, which includes a full power and minimum time climb from Development and Acquisition Cost: sea-level to >40,000 ft cruise altitude. Cost estimates are required to develop, manufacture, and • Field Performance: The UAVmust be capable of certify the aircraft. Any advances in materials, operating from hard surfaces (bitumen, concrete) aerodynamics, or systems should be adequately and firm grass runways. Required runway length addressed in the cost estimate. should be based on operating into and out of an airport surrounded by 50' obstacles, and an outside Cost estimates should be based on a production run of a air temperature (OAT) at sea level of ISA +15 number of units selected by the designer in response to degrees Celcius. an estimate of the market niche, in Year2002 dollars. Any engineering or manufacturing features to reduce the • Powerplant: one Williams International FJX- cost should be explained. A breakdown of the total 2/EJ22 turbofan engine. development cost for the aircraft should be included as • Systems: The complete system should include at well as the resulting acquisition cost for the aircraft least aeroplane(s) fitted with off-the-shelf assuming a reasonable profit margin. A brief description of the life cycle cost model should be included. 7) Aircraft component weight statement. Show a IV. Data Requirements weight breakdown of major components and systems, and aircraft centre-of-gravity envelope. The final proposal, based on the previously stated objectives, requirements and constraints, should include 8) Aircraft drag polars and lift curves in the cruise sections and data on, but not limited to the following: configuration, and in the takeoff and landing