2002 Design Task: (Option 1) High Performance Multi-Role Unmanned Aerial Vehicle (UAV)

Transcription

1 AERO 4400 Aircraft Design Design Task: (Option 1) High Performance Multi-Role Unmanned Aerial Vehicle (UAV) 6 credit points 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 REQUEST FOR PROPOSAL (RFP - Option 1): High Performance Multi-Role UAV I. Opportunity Description Australia is a vast country which has: clear surveillance requirements for defence, coastwatch, and the monitoring and protection of the environment and coastal natural resources; rich mineral wealth deposits which needs to be exploited with due consideration to environmental impact; a harsh climate, requiring understanding to support the population areas; and hence potentially a good domestic market for Unmanned Aerial Vehicles (UAVs). The recent (2001) deployment of the Northrop Grumman Global Hawk High Altitude Long Endurance (HALE) UAV in Australia has led to much interest in acquiring such a capability. A recent market survey 1 indicated strong opportunities for high-altitude, long endurance (HALE) UAVs with around 100kg payload, km/h cruising/loitering airspeed, and greater than 24 hours endurance. Although there are many UAV systems either in operation or under development worldwide, there are few that could be considered affordable to commercial operators that have attributes suitable to operation for commercial purposes. High costs are partly because most systems have been developed for military markets and roles, and therefore subject to stringent military specifications. It is believed that developments specifically aimed at commercial operations and therefore with attributes tailored to commercial requirements are more likely to be acceptable to the civilian UAV market, with obvious opportunities in an increasingly cost-conscious defence market. One of the constraints for lowering the cost of UAV airframes has been the availability of suitable 1 Wong, et. al., Study of the Unmanned Aerial Vehicle (UAV) Market in Australia, Aerospace Technology Forum Report, August powerplants. A recent engine development provides a potential opportunity to develop a HALE UAV. Opportunity thus exist to evaluate the feasibility and cost effectiveness of such UAVs. < Williams International is working on a cooperative effort with NASA, called the General Aviation Propulsion (GAP) Program, aimed at revolutionizing and reviving the once flourishing light aircraft industry in the U.S. In this program, Williams International is developing the FJX-2 turbofan engine for use in the next generation of four- and six-passenger general aviation airplanes. The FJX-2 is much smaller than the smallest commercial turbofan of today. It is in the 700-lb thrust class and weighs less than 100 pounds. The engine is in development and will be flight-ready in the year The primary goal of the FJX-2 is affordability. It will allow jet-powered airplanes to be priced competitive with today's general aviation piston-powered planes. With turbofan power, this new generation of airplanes will fly faster, have longer range, be more comfortable and quiet, and set a new standard in general aviation safety. Based on its very low noise level, light weight, low emissions, low fuel consumption, and low cost in quantity production, the FJX-2 engine will be a major factor in reviving the once flourishing light aircraft industry. Engine Characteristics Thrust Class lbf Overall Length in Diameter in Weight < 100 lbs This engine is also known as the Williams EJ22. There 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 engine 2-seat aircraft, more information being located at The X-Plane Simulation Software used there may be optionally used in this task, if so desired.

2 II. Project Objective Your company wants to explore the feasibility of building a new family of aircraft, powered by one Williams International FJX-2/EJ22 turbofan engine, to target this potentially growing UAV marketplace. The objective is to provide your management with a conceptual design of a highly capable low-cost UAV system to suit a variety of missions. The cost effectiveness of this new concept must be illustrated with comparisons to existing systems. Tradeoff studies should be incorporated to show that the concept is a balanced and optimum design. If the company plans to pursue this new development program, the target date for entry into service is the year A perusal of the history of UAV development would reveal a long list of programme failures due to mission requirement growth or changes (eg. The Aquilla and Outrider UAVs), which would seemingly rule out the development of multi-role UAV systems. These highcost failures have taught the UAV industry that the key to successful UAV programmes is a firm definition of a mission and stick to it (eg. Pioneer, Predator, Aerosonde UAVs). However, because UAV application to many market sectors are still unexplored, the opportunity is still clearly there for low-cost multi-role high performance UAVs to operationally trial new High Altitude Long Endurance missions before they are firmly defined. Although recognised to be only around 15% of the total cost of UAV systems, the airframes remain a critical element to meet any mission performance objectives (eg. Endurance, speed, range). III. Requirements and Constraints Configuration Selection Criteria: The final configuration proposed shall be selected on the basis of the lowest development cost and satisfy all of the requirements contained within the RFP. Flight Capability: Maximum Speed: Highest possible. Loiter Speed: lowest possible. Cruise: Endurance no less than 24 hours, which includes a full power and minimum time climb from sea-level to >40,000 ft cruise altitude. Field Performance: The UAVmust be capable of operating from hard surfaces (bitumen, concrete) and firm grass runways. Required runway length should be based on operating into and out of an airport surrounded by 50' obstacles, and an outside air temperature (OAT) at sea level of ISA +15 degrees Celcius. Powerplant: one Williams International FJX- 2/EJ22 turbofan engine. Systems: The complete system should include at least aeroplane(s) fitted with off-the-shelf autonomous flight controller(s), appropriate surveillance sensor(s), and Ground Command and Control station(s). The choice and relative merit of which is left to the designer, as long as mission requirements are met. Payload: Electro Optical (EO), Infra-Red (IR), and/or other surveillance sensors up to a maximum of at least 232 kg (510 lb). Maximum Empty Weight: 1500 lbs (682 kg). Appearance: The aeroplane should be aesthetically pleasing. Certification: The UAV airframe should be designed to meet the draft CASA UAV Design requirements (see separate attachment), with guideline reference to JAR-VLA. Notes: All performance requirements, including those presented here and those specified by the respective regulations, should meet the regulatory values and definitions. Aircraft which are predicted to significantly surpass the specified design parameters are acceptable, provided this can be justified as a cost or marketability tradeoff. Roles such as Search and Rescue (SAR), Powerline inspection, Coastwatch, Telecommunications Relay, Bushfire Command and Control, or any other market identified roles should be explored and detailed. Structural Layout: A conceptual structural layout of the aircraft is required along with a material breakdown. Advanced materials may be used in an attempt to reduce the empty weight of the aircraft. However, any potential cost penalties from using advanced materials should be addressed. Aerodynamics: Consideration of advanced technologies may be included in the configuration. However, the technology must prove to be affordable, reliable and easily maintainable. Development and Acquisition Cost: Cost estimates are required to develop, manufacture, and certify the aircraft. Any advances in materials, aerodynamics, or systems should be adequately addressed in the cost estimate. Cost estimates should be based on a production run of a number of units selected by the designer in response to an estimate of the market niche, in Year2002 dollars. Any engineering or manufacturing features to reduce the cost should be explained. A breakdown of the total development cost for the aircraft should be included as well as the resulting acquisition cost for the aircraft assuming a reasonable profit margin. A brief description

3 of the life cycle cost model should be included. IV. Data Requirements The final proposal, based on the previously stated objectives, requirements and constraints, should include sections and data on, but not limited to the following: Configuration Sizing and Optimisation: 1) Describe the optimisation study used to minimise the development cost of the aircraft. Justify the final design and describe in detail the technologies and technical approach used to accomplish the requirements. This should include performance graphs for high lift, propulsion, conversion, or other profiles for landing and take off. Describe tradeoffs made and justify final concept selection. 2) Describe the process for sizing the aircraft. Provide carpet plots used to optimise the final selected design. Identify the most restrictive constraints in the design. 3) Describe the advantages and disadvantages of your design. Make comparisons, where relevant, to existing aircraft with similar capabilities. 4) Development and manufacturing cost analysis including sensitivity studies to verify minimum cost design. Include a discussion of how systems design, aerodynamics, propulsion, material selection, configuration layout and other factors affect cost. Report production cost with development amortised over a number of units selected by the designer in response to an estimate of the market niche. Design Data 1) Table of the aircraft external dimensions and areas 2) Aircraft 3-view dimensional drawing, including: Three view configuration drawings and tables of external dimensions; Inboard profiles, indicating the location and nature of primary structure; Description of aircraft systems with layout drawings; Layout of sensor(s), communication links, and other avionics; 3) Location and volume of fuel tanks 4) Location of the major systems on the aircraft 5) Drawings showing the conceptual structural layout of the aircraft Include an illustrated description of the primary load bearing airframe structure and state rationale for material selection. 6) Material breakdown of the aircraft 7) Aircraft component weight statement. Show a weight breakdown of major components and systems, and aircraft centre-of-gravity envelope. 8) Aircraft drag polars and lift curves in the cruise configuration, and in the takeoff and landing configurations. Show an estimated drag build up for both cruise and landing configurations. 9) A summary of the stability and control analyses is required including a description on how the empennage and control surfaces were sized. 10) Describe the major systems on the aircraft including flight controls, ice protection, electrical, hydraulic, environmental control system, and cockpit controls. 11) Provide fly-away cost for a production run of the decided number of aircraft. Performance Data 1) Performance analysis detailing field length, mission time and endurance, comparing with other similar UAVs. 2) Stability and control analysis verifying that the design conforms to applicable stability and control 3) Provide performance estimates and demonstrate aircraft stability for all flight and loading conditions. 4) Weight and balance analysis for each loading condition showing weight and centre of gravity are within limits for applicable stability and control 5) A flight envelope (altitude vs. speed) and a V-n diagram is required. 6) A detailed description of each leg of the mission showing aircraft weight, fuel used, time, distance, altitude, speed, etc. 7) Show that the cruise speed and altitude used in the design mission is optimum for the final aircraft. 8) The effects of varying payload on range should be shown. 9) The effects of altitude and aircraft weight on takeoff distance, climb gradient, and landing distance should be shown. V. Additional Supporting Data The aircraft must be powered by a Williams International FJX-2 (EJ22) Turbofan. The thermocyclic cycle of this engine is claimed to be similar to the best engines used in current bizjets, so any required information not yet publicly available can be estimated using available scaling methods.

4 Appendix A I. Proposal Requirements The technical proposal is the most important factor in the award of a contract. It should be specific and complete. While it is realised that all of the technical factors cannot be included in advance, the following should be included and keyed accordingly: 1. Demonstrate a thorough understanding of the Request for Proposal (RFP) requirements. 2. Describe the proposed technical approaches to comply with each of the requirements specified in the RFP, including phasing of tasks. Legibility, clarity, and completeness of the technical approach are primary factors in evaluation of the proposals. 3. Particular emphasis should be directed at identification of critical, technical problem areas. Descriptions, sketches, drawings, systems analysis, method of attack, and discussions of new techniques should be presented in sufficient detail to permit engineering evaluation of the proposal. Exceptions to proposed technical requirements should be identified and explained. 4. Include tradeoff studies performed to arrive at the final design. 5. Provide a description of automated design tools used to develop the design. II. Basis for Assessment 1. Technical Content (35 %) This concerns the correctness of theory, validity of reasoning used, apparent understanding and grasp of the subject, etc. Are all major factors considered and a reasonably accurate evaluation of these factors presented? 2. Organisation and Presentation (20 %) The description of the design as an instrument of communication is a strong factor on judging. Organisation of written design, clarity, and inclusion of pertinent information are major factors. 3. Originality (20 %) The design proposal should avoid standard textbook information, and should show the independence of thinking or a fresh approach to the project. Does the method and treatment of the problem show imagination? Does the method show an adaptation or creation of automated design tools. 4. Practical Application and Feasibility (25 %) The proposal should present conclusions or recommendations that are feasible and practical, and not merely lead the evaluators into further difficult or insolvable problems.

5 AERO 4400 Aircraft Design Design Task: (Option 2) Single Jet Sportplane 6 credit points 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 REQUEST FOR PROPOSAL (RFP - Option 2): Single Jet Sportplane I. Opportunity Description < Williams International is working on a cooperative effort with NASA, called the General Aviation Propulsion (GAP) Program, aimed at revolutionizing and reviving the once flourishing light aircraft industry in the U.S. In this program, Williams International is developing the FJX-2 turbofan engine for use in the next generation of four- and six-passenger general aviation airplanes. The FJX-2 is much smaller than the smallest commercial turbofan of today. It is in the 700-lb thrust class and weighs less than 100 pounds. The engine is in development and will be flight-ready in the year The primary goal of the FJX-2 is affordability. It will allow jet-powered airplanes to be priced competitive with today's general aviation piston-powered planes. With turbofan power, this new generation of airplanes will fly faster, have longer range, be more comfortable and quiet, and set a new standard in general aviation safety. Based on its very low noise level, light weight, low emissions, low fuel consumption, and low cost in quantity production, the FJX-2 engine will be a major factor in reviving the once flourishing light aircraft industry. Engine Characteristics Thrust Class lbf Overall Length in Diameter in Weight < 100 lbs This engine is also known as the Williams EJ22. Such a high-efficiency, low-cost jet engine presents an opportunity to develop an affordable personal jet transport using one of these engines, with potential costs in the 6-figure US$, rather than the current 7-figure US$ for the smallest jet transports. There are designs under development which uses two of these engines, eg. V- JET II and Eclipse 500. A contest is currently underway to design such an aircraft, more information being located at This design task is based partly on that competition, and the X-Plane Simulation Software may be optionally used if so desired. III. Requirements and Constraints Configuration Selection Criteria: The final configuration proposed shall be selected on the basis of the lowest development cost and satisfy all of the requirements contained within the RFP. Flight Capability: Cruise Speed: best possible. Loitre Speed: lowest possible Cruise Endurance: maximum possible, which includes a full power and minimum time climb from sea-level to cruise altitude. Take-Off and Landing Distance: The aeroplane must be capable of operating from hard surfaces (bitumen, concrete) and firm grass runways typical of General Aviation airports. Required runway length should be based on operating into and out of an airport surrounded by 50' obstacles, and an outside air temperature (OAT) at sea level of ISA +15 degrees Celcius. Powerplant: one Williams International FJX- 2/EJ22 turbofan engine. Payload: Two 180 lb (81.8 kg) persons and 150 lbs (68.2 kg) total cargo capacity. Maximum Empty Weight: 1500 lbs (682 kg). Fuselage Size: Minimum fuselage body radius of 2 feet (at least ½ that width for tandem seating arrangement). Appearance: The aeroplane should be aesthetically pleasing. Notes: Weight and balance shall include all equipment necessary for day or night VFR and IFR flight. Cruise speed and endurance predictions shall be done in standard atmospheric conditions. All performance requirements, including those presented here and those specified by the

6 respective regulations, should meet the regulatory values and definitions. Aircraft which are predicted to significantly surpass the specified design parameters are acceptable, provided this can be justified as a cost or marketability tradeoff. Structural Layout: A conceptual structural layout of the aircraft is required along with a material breakdown. Advanced materials may be used in an attempt to reduce the empty weight of the aircraft. However, any potential cost penalties from using advanced materials should be addressed. Aerodynamics: Consideration of advanced technologies may be included in the configuration. However, the technology must prove to be affordable, reliable and easily maintainable. Development and Acquisition Cost: Cost estimates are required to develop, manufacture, and certify the aircraft. Any advances in materials, aerodynamics, or systems should be adequately addressed in the cost estimate. Cost estimates should be based on a production run of a number of units selected by the designer in response to an estimate of the market niche in Year2002 dollars. Any engineering or manufacturing features to reduce the cost should be explained. A breakdown of the total development cost for the aircraft should be included as well as the resulting acquisition cost for the aircraft assuming a reasonable profit margin. A brief description of the life cycle cost model should be included. IV. Data Requirements The final proposal should include, but not be limited to, to the following: 1. Justify the aircraft configuration by describing the factors that led to your decisions and the factors that led you away from other configurations. 2. Dimensioned Drawings and Descriptions: a. Configuration description including three-view drawing and table of external dimensions b. Inboard profiles, indicating the location and nature of primary structure c. Description of aircraft systems with layout drawings d. Layout of the cabin area 3. Description of the process of sizing for performance. 4. Performance analysis confirming the requirements from Section III are satisfied. 5. Discussion of materials selection. 6. Discussion of engine selection, and propeller selection if appropriate. 7. Stability, Control and Handling Qualities analysis and discussion which addresses design philosophy, goals, and predictions at various loading conditions. 8. Design details that decrease the cost of the aeroplane. The final proposal, based on the previously stated objectives, requirements and constraints, should include sections and data on, but not limited to the following: Configuration Sizing and Optimisation: 1) Describe the optimisation study used to minimise the development cost of the aircraft. Justify the final design and describe in detail the technologies and technical approach used to accomplish the requirements. This should include performance graphs for high lift, propulsion, conversion, or other profiles for landing and take off. Describe tradeoffs made and justify final concept selection. 2) Describe the process for sizing the aircraft. Provide carpet plots used to optimise the final selected design. Identify the most restrictive constraints in the design. 3) Describe the advantages and disadvantages of your design. Make comparisons, where relevant, to existing aircraft with similar capabilities. 4) Development and manufacturing cost analysis including sensitivity studies to verify minimum cost design. Include a discussion of how systems design, aerodynamics, propulsion, material selection, configuration layout and other factors affect cost. Report production cost with development amortised over a number of units selected by the designer in response to an estimate of the market niche. Design Data 1) Table of the aircraft external dimensions and areas 2) Aircraft 3-view dimensional drawing, including: Three view configuration drawings and tables of external dimensions; Inboard profiles, indicating the location and nature of primary structure; Description of aircraft systems with layout drawings; Layout of cabin and cockpit area and instrument panels; 3) Interior cabin layout drawing (plan view and cross section). 4) Location and volume of fuel tanks 5) Location of the major systems on the aircraft 6) Drawings showing the conceptual structural layout

7 of the aircraft Include an illustrated description of the primary load bearing airframe structure and state rationale for material selection. 7) Material breakdown of the aircraft 8) Aircraft component weight statement. Show a weight breakdown of major components and systems, and aircraft centre-of-gravity envelope. 9) Aircraft drag polars and lift curves in the cruise configuration, and in the takeoff and landing configurations. Show an estimated drag build up for both cruise and landing configurations. 10) A summary of the stability and control analyses is required including a description on how the empennage and control surfaces were sized. 11) Describe the major systems on the aircraft including flight controls, ice protection, electrical, hydraulic, environmental control system, and cockpit controls. 12) Provide fly-away cost for a production run of the decided number of airframes, including units costs for a typical completed aeroplane. 13) Provide fly-away cost for a production run of 200 factory produced aeroplanes. Performance Data 1) Performance analysis detailing field length, mission time and endurance, comparing with other similar sportplanes. 2) Stability and control analysis verifying that the design conforms to applicable stability and control 3) Provide performance estimates and demonstrate aircraft stability for all flight and loading conditions. 4) Weight and balance analysis for each loading condition showing weight and centre of gravity are within limits for applicable stability and control 5) A flight envelope (altitude vs. speed) and a V-n diagram is required. 6) A detailed description of each leg of the mission showing aircraft weight, fuel used, time, distance, altitude, speed, etc. 7) Show that the cruise speed and altitude used in the design mission is optimum for the final aircraft. 8) The effects of varying payload on range should be shown. 9) The effects of altitude and aircraft weight on takeoff distance, climb gradient, and landing distance should be shown. V. Additional Supporting Data The aircraft must be powered by a Williams International FJX-2 (EJ22) Turbofan. The thermocyclic cycle of this engine is claimed to be similar to the best engines used in current bizjets, so any required information not yet publicly available can be estimated using available scaling methods. Appendix A I. Proposal Requirements The technical proposal is the most important factor in the award of a contract. It should be specific and complete. While it is realised that all of the technical factors cannot be included in advance, the following should be included and keyed accordingly: 1. Demonstrate a thorough understanding of the Request for Proposal (RFP) requirements. 2. Describe the proposed technical approaches to comply with each of the requirements specified in the RFP, including phasing of tasks. Legibility, clarity, and completeness of the technical approach are primary factors in evaluation of the proposals. 3. Particular emphasis should be directed at identification of critical, technical problem areas. Descriptions, sketches, drawings, systems analysis, method of attack, and discussions of new techniques should be presented in sufficient detail to permit engineering evaluation of the proposal. Exceptions to proposed technical requirements should be identified and explained. 4. Include tradeoff studies performed to arrive at the final design. 5. Provide a description of automated design tools used to develop the design. II. Basis for Assessment 1. Technical Content (35 %) This concerns the correctness of theory, validity of reasoning used, apparent understanding and grasp of the subject, etc. Are all major factors considered and a reasonably accurate evaluation of these factors presented? 2. Organisation and Presentation (20 %) The description of the design as an instrument of communication is a strong factor on judging. Organisation of written design, clarity, and inclusion of pertinent information are major factors. 3. Originality (20 %) The design proposal should avoid standard textbook information, and should show the independence of thinking or a fresh approach to the project. Does the method and treatment of the problem show imagination? Does the method show an adaptation or creation of automated design tools. 4. Practical Application and Feasibility (25 %) The proposal should present conclusions or recommendations that are feasible and practical, and not merely lead the evaluators into further difficult or insolvable problems.