2003 Design Task: (Option 1) High Performance UAV for Bushfire Applications

Transcription

1 AERO 4400 Aircraft Design 3 6 credit points 2003 Design Task: (Option 1) High Performance UAV for Bushfire Applications 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 UAV for Bushfire Applications 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 increased interest in acquiring such a capability in defence. Throughout the world, millions of acres of timberland are destroyed each year by forest and bush fires. In Australia, the Rural Fire Services and regional Bushfire Brigades are tasked with the responsibility for providing protection to our national forest resources and the suppression of bushfires. When bushfires occur in remote areas the Rural Fire Services must deliver fire fighting resources to that location. The Water Bomber has been an accepted means for combatting the destruction caused by bush and forest fires for a number of years through aerial dropping of water and/or fire suppressants. The recent bushfires around the major cities in Australia further highlighted the need for early warning of impending fires moving towards populated regions, and the need to maintain close monitoring during the firefighting phase. Typically, the Fire Boss directs responding ground and air crews based on information relayed through the interpretation of observers spread out over the extent of the fire. These observers may be in the air and on the ground and have a range of experience and varying points of view. In addition, knowledge of changing weather conditions, the local topology, fire extent, and potential threat to property further compound the difficult decisions that the Fire Boss have to deal with. Similarly, instructions and commands that the response crews receive from the Fire Boss are also subject to interpretation and misinterpretation. Confusion over the intent of the command or instruction can delay effective action against the fires, often costing money and sometimes, lives. What is needed is a design solution that will significantly enhance situation awareness and provide clarity and accuracy of observation and direction. As part of this solution, a high flying UAV capable of carrying the required surveillance sensors for extended endurance and suitably high altitudes, is to be developed. II. Project Objective You have been tasked with exploring the feasibility of building a new family of unmanned aircraft to target this potentially growing UAV marketplace. The objective is to provide your management with a conceptual design of a highly capable UAV system to suit the specified bushfire surveillance and Command and Control (C&C) missions, equivalent to an unmanned version of an AWACS (Airborne Warning and Control System) aircraft. The cost effectiveness of this new concept must be illustrated with comparisons to similar 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). 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).

2 III. Requirements and Constraints Requirements - Design Mission C&C UAVs often have to travel long distances when deployed for fire fighting missions and then maintain station for extended periods over a potential danger area, or over a fire. Deployment trip time and endurance for loiter to conduct these missions are important factors of mission effectiveness. In the standby role, the UAV must have a time-on-station capability that permits the aircraft to operate in a stand-by mode and provide immediate response to calls from the ground crews at the fire site. The design will be capable of performing the following mission profile: Bushfire Command and Control Mission 1. Warm up and Takeoff - 5 minutes at idle SL plus 1 minute at maximum takeoff power. 2. Initial Climb - SL to cruise altitude at maximum climb power and all engines operating (AEO). 3. Cruise Out - Cruise 100nm less the climb distance at best cruise speed and altitude (h >10000 ft) 4. Manoeuvre - maximum sustained-g turn of 180 deg. at V rel 5. Loiter - Time on station for 24hr at best loiter speed. 6. Return Cruise - Cruise 100 NM less the climb distance at best cruise speed and altitude (h >10000 ft) 7. Descend to Base at SL. - no fuel penalty, no time or distance gained. 8. Fuel Reserves - 3% of initial fuel load. Point Performance Requirements The proposed aircraft shall satisfy the following Point Performance Requirements: 1. Maximum speed greater than 150 KTAS. 2. Maximum sustained manoeuvre load factor greater than or equal to 2.5 g at loiter altitude. 3. Maximum instantaneous manoeuvre load factor greater than or equal to 3.0g at loiter altitude. 4. Rate of Climb (ROC) at SL greater than or equal to 1000 fpm at TOGW, all engines operating. 5. Takeoff distance over 50 ft obstacle at Maximum TOGW with a runway length of less than 300m (980 ft), and an outside air temperature (OAT ) at sea level of ISA +15 degrees Celsius. 6. Landing distance over 50 ft obstacle at maximum landing weight with a runway length of less than 300m (980 ft), and an outside air temperature (OAT ) at sea level of ISA +15 degrees Celsius. 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: <50 KCAS. Cruise: Endurance no less than 24 hours, which includes a full power and minimum time climb from sea-level to cruise altitude. Field Performance: The UAV must be capable of operating from hard surfaces (bitumen, concrete) and firm grass runways. It must be capable of operating into and out of an airport surrounded by 50' obstacles, with a runway length of less than 300m (980 ft), and an outside air temperature (OAT) at sea level of ISA +15 degrees Celsius. Powerplant: any off-the-shelf commercially available engine(s). 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 220 lb (100 kg). Appearance: The aeroplane should be aesthetically pleasing. Certification: The UAV airframe should be designed to meet the draft Australian CASA UAV Design requirements (see CASA website), with guideline reference to JAR-VLA if over 150kg max. AUW. 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. Secondary Roles such as Search and Rescue (SAR), Powerline inspection, Coastwatch, Telecommunications Relay, or any other market identified roles should be explored and detailed. Weight and balance shall include all equipment necessary for day or night missions. Cruise speed and endurance predictions shall be done in standard atmospheric conditions.

3 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 Year2003 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 technical proposal from each team must convincingly demonstrate that the proposer can provide a superior solution to the need identified by this request for proposal. Therefore, it is the most important factor in the award of a contract. The proposal should satisfy the following tasks to show how the proposer would develop the design of a new aircraft. The aircraft presented in this proposal is only an example of the proposer's capability, and not the product if the proposal is selected for execution. A convincing description of process substantiated by an example aircraft that meets requirements will ultimately lead to selection. It is highly recommended that the proposer follow the Section IV outline and use it for a final quality control checklist. The proposal should contain the following minimum information:! Table of Contents keyed to the RFP! List of Illustrations! List of Tables! List of Symbols and Abbreviations! A Compliance Matrix, that identifies all requirements and where they are addressed by paragraph and page.! Executive Summary, briefly and concisely presents the important aspects of the proposal to key management personnel. The summary should present an organised progression of the work to be accomplished, without the technical details, such that the reader can grasp the core issues of the proposed program. In many cases, these two pages will be all management will use for their evaluation. The executive summary should be two pages or less including figures. Understanding the Requirements The design team must demonstrate a clear and comprehensive understanding of the aircraft and its mission role throughout its life cycle. Clearly describe the market or mission opportunity to be filled in such a way as to logically identify those aspects that generate operational requirements and constrain the design. Describe why current systems are inadequate to meet the market requirements. Surveys of up-to-date periodicals, books, and corporate literature are highly recommended and are to be referenced. Design Approach This section delineates the process by which requirements will be translated into a successful aircraft design. This process should identify the structured approach used by the design team to make the informed decisions in researching the example design; this process should identify the steps that encourage creativity and innovation. The design approach and its execution are central to the evaluation of the proposer's ability to develop an outstanding design solution. Flow charts are recommended to guide the reader through the design process. Evaluation of Relevant Technologies Investigate state of the art and future technologies that offer significant improvements in cost, performance, production, and operation. A literature survey of technical journals and publications, (such as NASA reports, AIAA papers, etc.) is recommended to support selection of technologies incorporated in the example design. Concept Exploration/Development Approach No single solution to the problem statement exists. Identify the range of potential solutions considered by the design team and explain how the path to the chosen solution was developed. The decision path from requirement to design should be fully traceable. Use of trade studies, concept generation, technology integration and optimisation techniques are encouraged. Establish a basis to determine the reasonableness of results. Example Design Demonstrate that the proposed approach will lead to a high-quality solution that meets design requirements at minimum cost. Consistent with the proposer's approach, the following activities must be described in

4 sufficient detail to identify the critical technical issues and to document design decisions. In all cases, draw conclusions from data that shows the evaluator why a calculated characteristic is good by comparison to existing systems or to design requirements or specifications. Concept Design Describe the rationale, principal features, critical technologies, performance, and analysis of all concepts considered leading to the baseline design. Present sizing charts, such as power-to-weight (P/W) or thrust-to-weight (T/W) versus wing loading (W/S) matrices including the constraints that sized the aircraft. The lowest weight aircraft is the aircraft that satisfies the most critical requirements (constraints). Aircraft that exceed all requirements will be considered to be over-designed and deemed unsatisfactory. Explain the impact of all requirements that have been exceeded. Trade Studies Describe the trade studies, sensitivity analyses, and parametric investigations used in optimising the design. Design Definition Evolve the baseline concept into a refined design. Show that all defining requirements are satisfied. Document the development of an optimised solution. As a minimum, the following should be presented: Aircraft Physical Data Descriptive drawings of key concepts, technologies, and features of the design and its operation, general arrangement (three-view) and inboard profile of the example design. Weight and Balance Weight and balance diagram. Show W E, TOGW, fuel usage, any payload deployment, etc. A Group Weight Statement shall be presented using the format shown below: Number of engines Rated thrust/hp Weight Group Wing Group Empennage Group Horizontal Tail Vertical Tail Fuselage Group Nacelle Group Landing Gear Group Nose Gear Main Gear WEIGHT STATEMENT Weight (LB) Structure Total Engines Air Induction System Fuel System Propeller Installation Propulsion Systems Power Plant Total Avionics Instruments Surface Controls Hydraulic/Pneumatic System Electrical System Air Conditioning System Pressurisation System Anti-Icing System Furnishings Paint Aircraft Systems Total Unusable Fuel/Oil Full Oil Useable Fuel Crew Payload(Design) Takeoff Gross Weight Aerodynamics Drag Polars at critical cruise and high lift conditions, design loads and operating envelope, relevant performance diagrams and constraints including payload-range performance at standard day atmospheric conditions. Stability and Control Unaugmented longitudinal and directional stability data, description of any stability augmentation systems and justification of need. Show augmented stability data, flight control type, location, and operation. Structure Structural layout including major structural components, such as, frames, ribs, and spars, landing gear structural design, sink rate capability, soft field capability, dimensions, and maintenance access to payload. Life cycle cost estimates. Sensitivity and trade study analyses. Example Aircraft Variants Identification

5 Consider corollary missions, derivatives, and variants. Because this aircraft has a narrowly focussed mission, its production size will be very small without alternate uses. A small production run is very high cost. Describe the alternate missions, the modifications to the UAV to meet these missions, and the performance of the alternate designs on those missions. Postulate additional aircraft quantities. A literature search is recommended and the source of the data should be referenced. Methods This section should provide a discussion of the methods used in making the calculations. This does not imply that sample calculations should be presented. Descriptions of existing computer tools and how they were used during the design process should be included. Design Data 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. Table of the aircraft external dimensions and areas b. Configuration description including three-view drawing and table of external dimensions c. Inboard profiles, indicating the location and nature of primary structure d. Description of aircraft systems with layout drawings 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. Material breakdown of the aircraft 7. Discussion of engine selection, and propeller selection if appropriate. 8. Stability, Control and Handling Qualities analysis and discussion which addresses design philosophy, goals, and predictions at various loading conditions. 9. Location and volume of fuel tanks 10. Location of the major systems on the aircraft 11. 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. 12. Aircraft component weight statement. Show a weight breakdown of major components and systems, and aircraft centre-of-gravity envelope. 13. 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. 14. A summary of the stability and control analyses is required including a description on how the empennage and control surfaces were sized. 15. Describe the major systems on the aircraft including flight controls, ice protection, electrical, hydraulic, environmental control system, and cockpit controls. 16. Design details that decrease the cost of the aeroplane. 17. Provide fly-away cost for a production run of the decided number of airframes, including units costs for a typical completed aeroplane. 18. Provide fly-away cost for a production run of 200 factory produced aeroplanes. 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. Performance Data 1) Performance analysis detailing field length, mission time and endurance, comparing with other similar aircraft. 2) Stability and control analysis verifying that the design conforms to applicable stability and control criteria. 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

6 criteria. 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 Will be supplied as needed. 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.

7 AERO 4400 Aircraft Design 3 6 credit points 2003 Design Task: (Option 2) High Performance Water Bomber 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): High Performance Water Bomber I. Opportunity Description Throughout the world, millions of acres of bushland and timberland are destroyed each year by fires. In Australia, the Rural Fire Services and regional Bushfire Brigades are tasked with the responsibility for providing protection to our national forest resources and the suppression of bushfires. When bushfires occur in remote areas the Rural Fire Services must deliver fire fighting resources to that location such as (1) ground crews travelling overland, (2) Smoke Jumpers that can attack the fire in its earliest stages and (3) water or fire suppressants. The Water Bomber has been an accepted means for combatting the destruction caused by bush and forest fires for a number of years. Depending largely on the speed at which the fire is progressing, water bombers are used in two fire fighting modes. The first mode is to drop water directly to the fire affected area to cool and to stop further spread of immediate destruction. The second mode is to drop fire suppressants and/or retardants ahead of the fire in an effort to deprive it from additional sources of flammable forestation. The Water Bomber has an advantage over more conventional techniques when employed in fighting fires in remote areas. Currently, the Water Bomber role has been filled by agricultural crop spraying aircraft or old surplus military aircraft (overseas) modified for the fire-fighting role or by amphibian aircraft which are range or payload limited. Many of these modified aircraft have recently been grounded after several fatal accidents due to ageing structure. A high performance aircraft with large payload capability designed specifically for water bomber operation has a potential world-wide market for replacement of present aircraft. II. Project Objective Overall Objectives The objective of this project is to design a new production aircraft with low manufacturing and operating costs that can meet the world-wide need for forest fire water bombers. This aircraft must be able to replace current aircraft types and provide enhanced mission capability not currently available. Current aircraft like the Canadair CL-215 or the larger CL-415 can deliver 1400 to 1600 gallons of payload to a fire site; the C-130 with a specialised Modular Airborne Fire Fighting System (MAFFS) can deliver 4000 gallons of payload (rather than the standard 3000 gallons); and the Erickson Helitanker (recently made famous in Australia by one named Elvis ) can deliver 2000 gallons per drop. The new aircraft design payload capability must exceed this capability. Safety is a paramount concern for both the air and ground crews and for fire fighting personnel on the ground. Flexibility in design is needed to meet the requirements Figure 1 Comparison of tankers used for firefighting (Ref: of forest fire protection over a broad range of geographic regions. III. Requirements and Constraints General Design Requirements (1) The aircraft must have the capability for stand-by mission assignments and be capable of at least two passes over target area before the need to reload. (2) The aircraft shall have a minimum crew of two. (3) The maximum landing weight equal to the maximum takeoff gross weight is desired. (4) The aircraft shall be designed for a structural limit load factor of 3.0 g's. (5) The aircraft shall be powered by a minimum of two engines. (6) The aircraft should be capable to provide multiple

8 operation cycles for firefighting at ranges up to 250 nautical miles from the operating base. (7) Cycle time on the ground during a firefighting operation should be reduced to a minimum with the limiting factor being time to load water and/or retardant. Consideration should be given to combination loadings of water and retardants in order to meet immediate needs of the situation. (8) The proposed design should be capable of carrying and delivering at least 30,000 gallons of payload per hour at a range of 80 nautical miles (nm) from the operating base. Loading times should be kept to a minimum and be at least comparable to existing systems. Requirements - Design Mission Water bombers must travel long distances when deployed for fire fighting missions and often must make several long trips between supply bases and the fire site. Deployment and round trip time are important factors of mission effectiveness. In the standby role, the water bomber must have a time-on-station capability that permits the aircraft to operate in a stand-by mode and provide immediate response to calls from the ground crews at the fire site. The design will be capable of performing the following mission profile: Typical Water Bomber Fire Patrol Mission 1. Warm up and Takeoff - 10 minutes at idle power, SLS plus 1 minute at maximum takeoff power. 2. Initial Climb - SL to cruise altitude at maximum climb power and all engines operating (AEO). 3. Cruise Out - Cruise 80nm less the climb distance at best cruise speed and altitude (h >10000 ft) 4. Descend to Target Area, 7000 ft. - no fuel penalty, no time or distance gained. 5. Jettison one half of payload on specified target 6. Manoeuvre - maximum sustained-g turn of 180 deg. at V rel 7. Loiter - Time on station for 0.5hr at best loiter speed. 8. Jettison remaining payload on specified target 9. Climb Out - Target altitude to cruise altitude at maximum climb power and all engines operating (AEO). 10. Return Cruise - Cruise 80 NM less the climb distance at best cruise speed and altitude (h >10000 ft) 11. Descend to Base at SL. - no fuel penalty, no time or distance gained. 12. Fuel Reserves - 10% of initial fuel load. Point Performance Requirements The proposed aircraft shall satisfy the following Point Performance Requirements: 1. Maximum speed greater than 200 KTAS. 2. Maximum sustained manoeuvre load factor greater than or equal to 2.5 g at best release speed at an altitude of 7000 feet. 3. Maximum instantaneous manoeuvre load factor greater than or equal to 3.0g at an altitude of 7000 feet. 4. Rate of Climb (ROC) at ft greater than or equal to 500 fpm at TOGW, all engines operating and a ROC at 7000 ft greater than or equal to 200 fpm at TOGW, one engine inoperative. 5. Takeoff distance over 50 ft obstacle at Maximum TOGW shall be less than or equal to 2600 feet (800m), and an outside air temperature (OAT) at sea level of ISA +15 degrees Celsius 6. Landing distance over 50 ft obstacle at maximum landing weight shall be less than or equal to 2600 feet (800m), and an outside air temperature (OAT) at sea level of ISA +15 degrees Celsius. Design Guidelines Additional design guidelines will be provided as required. 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 to meet mission requirements. Loitre Speed: < 100 KCAS. 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. It must be capable of operating into and out of an airport surrounded by 50' obstacles, with a runway length of 800m (2600 ft), and an outside air temperature (OAT ) at sea level of ISA +15 degrees Celcius. Powerplant: at least two engines. Payload: primarily water or retardant. Appearance: The aeroplane should be functional and aesthetically pleasing.

9 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 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 Year2003 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 technical proposal from each team must convincingly demonstrate that the proposer can provide a superior solution to the need identified by this request for proposal. Therefore, it is the most important factor in the award of a contract. The proposal should satisfy the following tasks to show how the proposer would develop the design of a new aircraft. The aircraft presented in this proposal is only an example of the proposer's capability, and not the product if the proposal is selected for execution. A convincing description of process substantiated by an example aircraft that meets requirements will ultimately lead to selection. It is highly recommended that the proposer follow the Section IV outline and use it for a final quality control checklist. The proposal should contain the following minimum information:! Table of Contents keyed to the RFP! List of Illustrations! List of Tables! List of Symbols and Abbreviations! A Compliance Matrix, that identifies all requirements and where they are addressed by paragraph and page.! Executive Summary, briefly and concisely presents the important aspects of the proposal to key management personnel. The summary should present an organised progression of the work to be accomplished, without the technical details, such that the reader can grasp the core issues of the proposed program. In many cases, these two pages will be all management will use for their evaluation. The executive summary should be two pages or less including figures. Understanding the Requirements The design team must demonstrate a clear and comprehensive understanding of the aircraft and its mission role throughout its life cycle. Clearly describe the market or mission opportunity to be filled in such a way as to logically identify those aspects that generate operational requirements and constrain the design. Describe why current systems are inadequate to meet the market requirements. Surveys of up-to-date periodicals, books, and corporate literature are highly recommended and are to be referenced. Design Approach This section delineates the process by which requirements will be translated into a successful aircraft design. This process should identify the structured approach used by the design team to make the informed decisions in researching the example design; this process should identify the steps that encourage creativity and innovation. The design approach and its execution are central to the evaluation of the proposer's ability to develop an outstanding design solution. Flow charts are recommended to guide the reader through the design process. Evaluation of Relevant Technologies Investigate state of the art and future technologies that offer significant improvements in cost, performance, production, and operation. A literature survey of technical journals and publications, (such as NASA reports, AIAA papers, etc.) is recommended to support selection of technologies incorporated in the example design. Concept Exploration/Development Approach No single solution to the problem statement exists. Identify the range of potential solutions considered by the design team and explain how the path to the chosen solution was developed. The decision path

10 from requirement to design should be fully traceable. Use of trade studies, concept generation, technology integration and optimisation techniques are encouraged. Establish a basis to determine the reasonableness of results. Example Design Demonstrate that the proposed approach will lead to a high-quality solution that meets design requirements at minimum cost. Consistent with the proposer's approach, the following activities must be described in sufficient detail to identify the critical technical issues and to document design decisions. In all cases, draw conclusions from data that shows the evaluator why a calculated characteristic is good by comparison to existing systems or to design requirements or specifications. Concept Design Describe the rationale, principal features, critical technologies, performance, and analysis of all concepts considered leading to the baseline design. Present sizing charts, such as power-to-weight (P/W) or thrust-to-weight (T/W) versus wing loading (W/S) matrices including the constraints that sized the aircraft. The lowest weight aircraft is the aircraft that satisfies the most critical requirements (constraints). Aircraft that exceed all requirements will be considered to be over-designed and deemed unsatisfactory. Explain the impact of all requirements that have been exceeded. Trade Studies Describe the trade studies, sensitivity analyses, and parametric investigations used in optimising the design. Design Definition Evolve the baseline concept into a refined design. Show that all defining requirements are satisfied. Document the development of an optimised solution. As a minimum, the following should be presented: Aircraft Physical Data Descriptive drawings of key concepts, technologies, and features of the design and its operation, general arrangement (three-view) and inboard profile of the example design. Weight and Balance Weight and balance diagram. Show W E, TOGW, water drop sequencing. A Group Weight Statement shall be presented using the format shown below: Number of engines Rated thrust/hp Weight Group Wing Group WEIGHT STATEMENT Weight (LB) Empennage Group Horizontal Tail Vertical Tail Fuselage Group Nacelle Group Landing Gear Group Nose Gear Main Gear Structure Total Engines Air Induction System Fuel System Propeller Installation Propulsion Systems Power Plant Total Avionics Instruments Surface Controls Hydraulic/Pneumatic System Electrical System Air Conditioning System Pressurisation System Anti-Icing System Furnishings Paint Aircraft Systems Total Unusable Fuel/Oil Full Oil Useable Fuel Crew Payload(Design) Takeoff Gross Weight Aerodynamics Drag Polars at critical cruise and high lift conditions, design loads and operating envelope, relevant performance diagrams and constraints including payload-range performance at standard day atmospheric conditions. Stability and Control Unaugmented longitudinal and directional stability data, description of any stability augmentation systems and justification of need. Show augmented stability data, flight control type, location, and operation.

11 Structure Structural layout including major structural components, such as, frames, ribs, and spars, landing gear structural design, sink rate capability, soft field capability, cabin seating arrangement, dimensions, ingress and egress, water tank(s) location, capacity, door operation, and sequencing. Life cycle cost estimates. Sensitivity and trade study analyses. Example Aircraft Variants Identification Consider corollary missions, derivatives, and variants. Because this aircraft has a narrowly focused mission, its production size will be very small without alternate uses. A small production run is very high cost. Describe the alternate missions, the modifications to the water bomber to meet these missions, and the performance of the alternate designs on those missions. Postulate additional aircraft quantities. A literature search is recommended and the source of the data should be referenced. Methods This section should provide a discussion of the methods used in making the calculations. This does not imply that sample calculations should be presented. Descriptions of existing computer tools and how they were used during the design process should be included. Design Data 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. Table of the aircraft external dimensions and areas b. Configuration description including three-view drawing and table of external dimensions c. Inboard profiles, indicating the location and nature of primary structure d. Description of aircraft systems with layout drawings e. Layout of cabin and cockpit area and instrument panels f. Layout of the cabin area (plan view and cross section). 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. Material breakdown of the aircraft 7. Discussion of engine selection, and propeller selection if appropriate. 8. Stability, Control and Handling Qualities analysis and discussion which addresses design philosophy, goals, and predictions at various loading conditions. 9. Location and volume of fuel tanks 10. Location of the major systems on the aircraft 11. 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. 12. Aircraft component weight statement. Show a weight breakdown of major components and systems, and aircraft centre-of-gravity envelope. 13. 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. 14. A summary of the stability and control analyses is required including a description on how the empennage and control surfaces were sized. 15. Describe the major systems on the aircraft including flight controls, ice protection, electrical, hydraulic, environmental control system, and cockpit controls. 16. Design details that decrease the cost of the aeroplane. 17. Provide fly-away cost for a production run of the decided number of airframes, including units costs for a typical completed aeroplane. 18. Provide fly-away cost for a production run of 200 factory produced aeroplanes. 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. 5)

12 Performance Data 1) Performance analysis detailing field length, mission time and endurance, comparing with other similar aircraft. 2) Stability and control analysis verifying that the design conforms to applicable stability and control criteria. 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 criteria. 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 may be powered by the turbo-prop propulsion unit supplied (AIAA Student Design Competition - Reference Library - Appendix B) for this RFP or the designers may select a propulsion unit currently in use or in an advanced state of development for which data is readily available. 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.