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oai:www.ideals.illinois.edu:2142/98438 2023-07-11 col_2142_5131 col_2142_14800 com_2142_5130 com_2142_14799 com_2142_234

Putnam, Zachary R. Sepulveda, Jose 2017-09-29T17:57:12Z 2017-09-29T17:57:12Z 2017-07-21 2017-08 Independently articulated aerodynamic flaps on a blunt-body entry vehicle may provide a feasible alternative to current state-of-the-art bank-angle steering control while introducing additional benefits during entry, descent, and landing. Flaps provide direct control of the vehicle’s lift and drag vectors, eliminating the need for a center of gravity offset and enabling a relatively constant vehicle attitude. A near-constant attitude may allow the use of relative navigation sensors and regional-scale science instruments during the hypersonic portion of entry. Direct aerodynamic vector control also enables active regulation of heating and reduces or eliminates the need for a reaction control system in the hypersonic regime. The Configuration-Based Aerodynamics tool was used to predict the trim angle of attack, trim lift-to-drag ratio, lift coefficients, and drag coefficients for variations in the number of flaps, individual flap configurations, and deployment angles. Aerodynamic data is validated against static trim-tab data from the literature. Results for one flap above the entry vehicle are presented for the hypersonic regime with the angle of attack ranging from -4 degrees to 20 degrees. These results demonstrate the effects of a flap on the aerodynamic performance of an entry vehicle and will inform the development of guidance, navigation, and control systems for various flap configurations on entry vehicles. Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2017-09-29 without embargo terms The student, Jose Sepulveda, accepted the attached license on 2017-07-20 at 23:19. The student, Jose Sepulveda, submitted this Thesis for approval on 2017-07-20 at 23:27. This Thesis was approved for publication on 2017-07-21 at 08:46. DSpace SAF Submission Ingestion Package generated from Vireo submission #11569 on 2017-09-29 at 11:32:27 Made available in DSpace on 2017-09-29T17:57:12Z (GMT). No. of bitstreams: 3 SEPULVEDA-THESIS-2017.pdf: 1088211 bytes, checksum: 218e0ae718c8f2c138985b6c20cfbb72 (MD5) Sepulveda Thesis 2017.docx: 1198667 bytes, checksum: 5f87d31dbe751e9ad2767d13f8be36fd (MD5) LICENSE.txt: 4211 bytes, checksum: d356f2cd66a4361266e79b1c70676a57 (MD5) Previous issue date: 2017-07-21 application/pdf http://hdl.handle.net/2142/98438 en Copyright 2017 Jose Sepulveda Flaps Trim-tabs Blunt-bodies Hypersonic trajectory control Aerodynamic modeling and assessment of flaps for hypersonic trajectory control of blunt bodies text text Aerospace Engineering Aerospace Engineering University of Illinois at Urbana-Champaign Thesis M.S.