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Preliminary Design, Flight Simulation, and Task Evaluation of a Mars Airplane University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Masters Theses Graduate School 12-2008 Preliminary Design, Flight Simulation, and Task Evaluation of a Mars Airplane Dodi DeAnne Walker University of Tennessee - Knoxville Follow this and additional works at: https://trace.tennessee.edu/utk_gradthes Part of the Aerospace Engineering Commons Recommended Citation Walker, Dodi DeAnne, "Preliminary Design, Flight Simulation, and Task Evaluation of a Mars Airplane. " Master's Thesis, University of Tennessee, 2008. https://trace.tennessee.edu/utk_gradthes/496 This Thesis is brought to you for free and open access by the Graduate School at TRACE: Tennessee Research and Creative Exchange. It has been accepted for inclusion in Masters Theses by an authorized administrator of TRACE: Tennessee Research and Creative Exchange. For more information, please contact [email protected]. To the Graduate Council: I am submitting herewith a thesis written by Dodi DeAnne Walker entitled "Preliminary Design, Flight Simulation, and Task Evaluation of a Mars Airplane." I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the requirements for the degree of Master of Science, with a major in Aviation Systems. Stephen Corda, Major Professor We have read this thesis and recommend its acceptance: Borja Martos, U. Peter Solies Accepted for the Council: Carolyn R. Hodges Vice Provost and Dean of the Graduate School (Original signatures are on file with official studentecor r ds.) To the Graduate Council: I am submitting herewith a thesis written by Dodi DeAnn Walker entitled “Preliminary Design, Flight Simulation, and Task Evaluation of a Mars Airplane.” I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the requirements for the degree of Master of Science, with a major in Aviation Systems. Dr. Stephen Corda, Major Professor We have read this thesis and recommend its acceptance: Borja Martos U. Peter Solies Accepted for the Council: Carolyn R. Hodges Vice Provost and Dean of the Graduate School (Original signatures are on file with official student records) Preliminary Design, Flight Simulation, and Task Evaluation of a Mars Airplane A Thesis Presented for the Master of Science Degree The University of Tennessee, Knoxville Dodi DeAnn Walker December 2008 Abstract A limited aerodynamic, stability and control, and task evaluation of a new rocket-powered Mars airplane design was conducted. The Mars airplane design, designated the Argo VII, was patterned after the NASA ARES-2 design. The aerodynamic and stability and control parameters of the Argo VII were determined using analytical and computational techniques and were comparable to those of the ARES-2. The Argo VII was predicted to be statically stable and damped in all axes on Earth and Mars. A series of flight tests were performed using a MATLAB Simulink-based flight simulation program to assess the performance, longitudinal flying qualities, and mission effectiveness of the Argo VII flying on Earth and Mars. At an assumed Mars mission flight condition of 2 km (6,562 ft) altitude and 0.65 Mach, the Argo VII had a maximum range lift coefficient of 0.44, a maximum lift-to- drag ratio of 15.5, and a maximum endurance lift coefficient of 0.76. The Argo VII was dynamically stable and damped in the longitudinal axis. At the Mars mission flight condition, the long period had a damping ratio of 0.04, damped and undamped natural frequencies of 0.0423 rad/s (2.42 deg/s), and time to half of 409.6 sec. The short period had a damping ratio of 0.2, damped natural frequency of 7.39 rad/s (723 deg/s), undamped natural frequency of 7.54 rad/s (432 deg/s), and time to half of 0.46 sec. At the Mars mission flight condition, the aircraft had a specific excess power of 5.8 m/s (19.02 ft/s). At all Mars altitudes evaluated, the fastest way for the aircraft to change altitudes was to climb to the desired altitude at a constant equivalent airspeed. Mars mission aircraft task evaluations were performed using Mars simulation scenery to validate the predicted aircraft range and climb and descent performance. The aircraft range evaluation resulted in an aircraft maximum range of 373 km (232 mi). The predicted aircraft maximum range was 500 km (311 mi). The climb and descent evaluations resulted in aircraft performance that was similar to the predicted aircraft performance. This research illustrated that the Argo VII Mars aircraft design can provide a viable means of acquiring scientific data on Mars. ii Table of Contents I. Introduction ........................................................................................................................................................... 1 IA. WHY FLY ON MARS? ............................................................................................................................................ 1 IB. CHALLENGES OF FLYING ON MARS ...................................................................................................................... 1 IC. HISTORY OF MARS AIRCRAFT DESIGNS ................................................................................................................ 2 ID. OBJECTIVES OF RESEARCH ................................................................................................................................... 5 II. Mars Airplane Designs .......................................................................................................................................... 6 IIA. NASA AERIAL REGIONAL-SCALE ENVIRONMENTAL SURVEY (ARES) MARS AIRPLANE ................................... 6 IIA.1. Design Requirements and Philosophy ......................................................................................................... 6 IIA.2. Science Platform Selection .......................................................................................................................... 7 IIA.3. Preliminary Powered Airplane Design ........................................................................................................ 7 IIA.4. Design Refinement ....................................................................................................................................... 8 IIA.5. ARES-2 Performance Summary ................................................................................................................... 9 IIB. ARGO VII MARS AIRPLANE DESIGN ................................................................................................................... 9 IIB.1. General Argo VII Description ................................................................................................................... 10 IIB.2. Aircraft Geometry ...................................................................................................................................... 10 IIB.3. Airfoil Analysis .......................................................................................................................................... 11 IIB.4. Aerodynamic Model ................................................................................................................................... 13 IIB.5. Stability and Control Model ...................................................................................................................... 15 IIB.6. Performance Summary .............................................................................................................................. 16 IIC. COMPARISON OF ARGO VII AND ARES-2 ......................................................................................................... 17 IIC.1. Geometry ................................................................................................................................................... 17 IIC.2. Stability and Control ................................................................................................................................. 17 IIC.3. Cruise Performance .................................................................................................................................. 18 III. Theory and Approach .......................................................................................................................................... 19 IIIA. MARTIAN ATMOSPHERIC MODEL .................................................................................................................... 19 IIIA.1. Description ............................................................................................................................................... 19 IIIA.2. Calculation of Martian Atmospheric Properties ...................................................................................... 20 IIIA.3. Discussion of the Mars Atmosphere Model .............................................................................................. 22 IIIB. PITCHING MOMENT THEORY AND PARAMETER MATCHING TECHNIQUE ......................................................... 23 IIIB.1. Description ............................................................................................................................................... 23 IIIB.2. Calculation of Pitch Stability Moment, M ........................................................................................... 24 IIIB.3. Discussion Stability Derivatives, M and M q , on Earth and Mars ....................................................
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