Proteus Payload User's Guide - Scaled Composites

Proteus Payload User’s Guide

SCR 03-014 September 29, 2004

Scaled Composites, LLC 1624 Flight Line Mojave, CA 93501-1663 Telephone: (805) 824-4541 FAX: (805) 824-4174

Release Version: Initial (9/29/03) – Made available to NASA following successful checkout of Dryden Double Q-bay pod

Points of Contact New Business/Contracts: Bob Williams, Scaled Composites, 661-824-4541 Engineering: Mike Alsbury, Scaled Composites, 661-824-4541 NASA Contracts: Bob Curry, NASA Dryden, 661-276-3715

Table of Contents Proteus Summary ................................................................................................................ 7 Basic Dimensions: .............................................................................................................. 7 Weights: .............................................................................................................................. 7 Flight envelope: .................................................................................................................. 7 Performance: ....................................................................................................................... 8 Estimation of Maximum Cruise Range........................................................................... 9 Estimation of Loiter Endurance .................................................................................... 12 Estimation of Aircraft Service Ceiling ......................................................................... 14 Overview of Integration Process, Checkout, Deployment................................................ 16 Previous Campaigns.......................................................................................................... 16 Demonstrated External Pod Shapes .................................................................................. 19 Platform Availability ........................................................................................................ 21 Contracting........................................................................................................................ 21 Flight Ops.......................................................................................................................... 22 Flight Safety.................................................................................................................. 22 Configuration Control................................................................................................... 22 Scheduling..................................................................................................................... 22 Briefings........................................................................................................................ 22 Technical Interchange Meeting................................................................................. 22 Preflight..................................................................................................................... 23 Post flight .................................................................................................................. 23 Test Conduct ............................................................................................................. 23 Ground Support Equipment for Deployments .................................................................. 25 Deployment Location Requirements ................................................................................ 25 Proteus Instrumentation .................................................................................................... 26 Payload Volumes .............................................................................................................. 27 Generic Payload Interface................................................................................................. 30 Mechanical:................................................................................................................... 30 Electrical ....................................................................................................................... 30 Payload Environment........................................................................................................ 32 Double Q-bay Pod Payload Interface ............................................................................... 33 Mechanical.................................................................................................................... 33 Electrical ....................................................................................................................... 34 Customer Data Requirements ........................................................................................... 36

List of Figures Figure 1: Proteus 3-view..................................................................................................... 8 Figure 2: Flight Envelope ................................................................................................... 9 Figure 3 – Max Cruise Range vs. Payload Weight for 12,500 lb. GTOW ....................... 10 Figure 4 – Max Cruise Range vs. Payload Weight for 15,000 lb. GTOW ....................... 11 Figure 5 – Max Loiter Endurance vs. Payload Weight for 12,500 lb. GTOW................. 12 Figure 6 – Max Loiter Endurance vs. Payload Weight for 15,000 lb. GTOW................. 13 Figure 7 – Initial Service Ceiling vs. Gross Take-Off Weight ......................................... 14 Figure 8– Service Ceiling vs. Aircraft Weight ................................................................. 15 Figure 9: NASA Langley Pod........................................................................................... 19 Figure 10: Angel Technologies & Raytheon Telecommunications Dish ......................... 19 Figure 11: Airborne Laser Target Body............................................................................ 19 Figure 12: Resistor Load Bank Attached to Proteus Center Pylon................................... 20 Figure 13: Sandia National Labs: Fuselage Belly Pod, Upper Fuselage Platform, Left Vertical Tail Boom Extension, Canard Cuffs ........................................................... 20 Figure 14: NASA Dryden Double Q-bay Pod .................................................................. 20 Figure 15: Angel Technologies and Raytheon Telecommunications Pod 3-view............ 27 Figure 16: NASA Langley Pod 3-view............................................................................. 28 Figure 17: Internal Payload Locations.............................................................................. 29 Figure 18: Fuselage Payload Volumes ............................................................................. 29 Figure 19: Layout of Proteus Q-bay Pod .......................................................................... 33 Figure 20: NASA ER2 Q-bay Layout............................................................................... 34 Figure 21: ER2 Q-bay EIP................................................................................................ 35

Proteus Summary The Proteus aircraft is a multipurpose manned platform for long duration high altitude operations. In its current role, the Proteus is used for sensor development and flight test. The configuration is designed to carry payloads in various areas on the aircraft. The all composite airframe is powered by two FJ44-2E turbofan engines that have been specially modified by Williams International for high altitude operation. The two pilots operate in a shirt sleeve environment in the 7 PSID pressurized cabin. The second crewmember adds flexibility and can be dedicated to running various developmental payload systems. The airplane is controlled through a reversible, mechanical, unboosted control system. The retractable tricycle landing gear with nose wheel steering is powered by electrohydraulic. 28 VDC electrical power on the airplane is provided by two 400 amp starter generators. Additional information on the Proteus can be found at www.scaled.com.

Basic Dimensions: Wing Span Wing Area Wing Aspect Ratio Canard Span Canard Area Canard Aspect Ratio Length Height Tail down angle (max) Tail down angle (min)

77.6 ft. 300.5 ft2 20 54.7 ft 178.7 ft2 16.7 56 ft. 4 in. 17 ft. 7 in. (approx.) 12° (nose & main gear fully extended) 7.3° (nose & main gear fully compressed)

Weights: Gross weight Empty weight Fuel weight Minimum landing weight Maximum landing weight

12,500 lb. (operated to 15,000 lbs with reduced g limits) 6800 lb. 6176 lb. (max. possible without bladder) 5800 (no payload) 12,500 lb.

Flight envelope: Proteus was designed to the FAR Part 23 normal category with limit loads of +3.2 and -1.8 g’s. At light weights (