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The Peregrine

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The Peregrine The Peregrine AEROSPACE ENGINEERING 2003/2004 AIAA Undergraduate Team Aircraft Design Competition -an E/STOL, Airport Adaptive Regional Jet- Designed by Team ASCENT i The Peregrine -an E/STOL, Airport Adaptive Regional Jet- Designed by Team ASCENT 2003/2004 AIAA Undergraduate Team Aircraft Design Competition Virginia Polytechnic Institute & State University June 4, 2004 Name Signature Focus AIAA # Joe Adelmann, Team Leader _________________________ Weight, CG, Powered Lift 235569 Chris Bang _________________________ Mission, Cost 238079 Matt Eluk _________________________ Stability and Control 238089 Adam Entsminger _________________________ Configuration, CAD 239781 Jessica Hill _________________________ Aerodynamics 237236 Jason Mostaccio _________________________ Propulsion, Powered Lift 235572 Derek Reimer _________________________ Structures, Systems 235414 Faculty Advisors W.H. Mason ___________________ M.A. Cavanaugh ___________________ ii Executive Summary The Peregrine provides an innovative solution to the growing problem of airport congestion as well as serving the nation through homeland security and military support. By incorporating a hybrid, powered lift, double- slotted flap system into a 49-passenger regional jet it was possible to satisfy the 2003/2004 AIAA undergraduate RFP. Team Ascent has incorporated these advanced technologies into a unique design to be a flexible, efficient and cost effective regional jet that will revolutionize air transportation and improve national security. Multiple Missions The cost of the aircraft is split between the baseline cost of the regional jet and the additional, government- subsidized cost of converting the Peregrine to its secondary mission configuration. The Peregrine is capable of many missions including: wildfire support, air ambulance to urban and rural areas, air transport to and from combat areas and emergency evacuation. The main cabin is outfitted with quick-release seats that are easily removable to accommodate firemen, military response teams and medical personnel. To further assist with the additional missions, the auxiliary engines can be used as power sources for medical equipment and other necessary devices. The baggage area under the cabin is used to store mission support equipment such as fire suppressant canisters and an extra cargo door is installed to accommodate loading and unloading in adverse conditions. The Peregrine is designed to land on unprepared runways using landing gear with a low turnover angle and four wheels per bogey for improved weight distribution. The landing gear features long stroke shock struts and a Central Tire Inflation System for efficient use on various runways. The Peregrine is outfitted with features to address survivability in dangerous missions such as, 4 mm aluminum plating under the cockpit, self-sealing fuel tanks, fire extinguishers within the engine nacelles and separated redundant flight controls. Countermeasures are available in the form of chaff and flares. Powered Lift The Peregrine’s hybrid, powered lift system integrates two main thrusting engines, and two auxiliary, turboprop engines. The main engines produce lift through an externally blown flap arrangement. The lift generated from external blowing is dependent on exhaust plume diameter, vertical flap spacing and effective flap length. Accounting for the lift produced by the externally blown flaps and the wing, the maximum CL achieved is 3.48. This iii lift coefficient is insufficient to meet the STOL requirements of the RFP, therefore, an additional lifting source is required. Two auxiliary engines are mounted next to the fuselage, under the wing root near the primary source of application, the inboard trailing edge flaps. Each engine is connected to a high efficiency fan, which directs air through a duct that curves up into the bottom of the airfoil and fans out towards thirteen cutouts within the aft wing spar. The air then flows over the trailing edge flaps to produce the necessary lift through internal blowing. The combination of these unique lifting systems allows the aircraft to achieve a BFL of 1,016 ft. during primary mission operations and a BFL of 1,244 ft. during secondary mission operations. These remarkable performance characteristics enable the Peregrine to effectively complete multiple missions with a minimal cost increase. Landing Conditions To address the SNI approach and automated spiral descent there are several technologies integrated into the Peregrine. The Rockwell Collins FCS-4000 automatic flight control system stabilizes the spiral descent, as well as aiding the pilot with pedal-force for the rudder deflections, stabilizer deflections and bank control. During engine out conditions, the high lift system allows the Peregrine to stably continue the SNI approach and achieve a stall speed as low as 65 knots with a descent rate of 12 fps. iv RFP Data Requirements Report Location 1. Justify the final design and describe in detail the technologies and Throughout report technical approach used to meet the mission requirements. 2. Provide carpet plots used to optimize the final selected design. Figure 3.2, pg 9 3. Include a dimensioned 3-view general arrangement drawing. Foldout 3, pg 15 4. Include an inboard profile showing the general internal Foldout 2, pg 14 arrangement. 5. Include an illustrated description of the primary load bearing Foldouts 4 & 5, pgs 30 & 40 airframe structure and state rationale for material selection. 6. Include a V-n diagram. Figure 6.1, pg 33 7. Show an estimated drag build up and drag polar for the cruise Figures 4.8-4.10, pgs 22-23 configuration, the takeoff configuration and the landing configuration. 8. Show a weight breakdown of major components and systems, Table 3.1, pg 10, Figure 3.3, pg 11 and center of gravity travel. 9. Provide performance estimates and demonstrate aircraft stability Chapter 8, pgs 59-66 for all flight and loading conditions. Chapter 9, pgs 67-72 10. Describe any advanced technologies and their relative benefits Sections 5.3-5.5, pgs 26-29 as used to obtain performance improvements. 11. Provide flyaway cost and direct operating cost plus interest Section 10.4, pg 76 (DOC+I) estimates for a production runs of 150, 500, and 1500 Section 11.4, pg 80 aircraft. Increments to flyaway and direct operating costs plus Section 11.7, pg 82 interest incurred for including Homeland Security mission capability will need to be identified. vi Table of Contents Executive Summary................................................................................................................................................... iii Multiple Missions ........................................................................................................................................................... iii Powered Lift.................................................................................................................................................................... iii Landing Conditions .........................................................................................................................................................iv RFP Data Requirements...........................................................................................................................................vi List of Foldouts .............................................................................................................................................................ix List of Figures................................................................................................................................................................ix List of Tables...................................................................................................................................................................x List of Symbols..............................................................................................................................................................xi Chapter 1: Introduction, Problem Statement and RFP Analysis.........................................................1 1.1 Introduction.................................................................................................................................................................1 1.2 Opportunity Statement ...............................................................................................................................................1 1.3 RFP Analysis ..............................................................................................................................................................1 Chapter 2: Introduction of Concepts..................................................................................................................3 2.1 Peregrine .....................................................................................................................................................................3 2.2 X-03 ............................................................................................................................................................................5 2.3 Decision ......................................................................................................................................................................6 Chapter 3: Peregrine Configuration Design Description..........................................................................8 3.1 Constraint Diagrams and Sizing ................................................................................................................................8
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