STARLight Mechanical Tahir Rashid STARLight Mechanical Engineer 734
- Slides: 15
STARLight Mechanical Tahir Rashid STARLight Mechanical Engineer (734) 764 -7210 trashid@umich. edu STARLight PDR 3 Oct ‘ 01 F. 1. 1 Rashid
Mechanical Requirements STARLight • Mechanical Requirements – – – Instrument to be used on Husky A-1 B aircraft (or similar) Low weight (Must be within allowable aircraft weight & c. g balance) Structural integrity Maintainability (Easy field replacements) Antenna dipoles must point in the same direction and be placed in a Yarrangement Antenna spacing must be 0. 68 = 5. 6” Height of sensor module < 9” to avoid interference with ground and excessive aerodynamic drag Minimal interference between aircraft structure and antenna FOV Material selection with appropriate heat transfer properties Moisture control Simple and cost-effective STARLight PDR 3 Oct ‘ 01 F. 1. 2 Rashid
Sensor Module Design & Structure STARLight PDR 3 Oct ‘ 01 F. 1. 3 Rashid
Sensor Module Design & Structure STARLight • Dwg#: 086 -0045 X 5 STARLight PDR 3 Oct ‘ 01 F. 1. 4 Rashid
Sensor Module Section STARLight • Dwg#: 086 -0046 X 5 (Exploded View) STARLight PDR 3 Oct ‘ 01 F. 1. 5 Rashid
Sensor Module Section STARLight • Dwg#: 086 -0046 X 5 (Top & Side View) STARLight PDR 3 Oct ‘ 01 F. 1. 6 Rashid
Sensor Module Section STARLight • Dwg#: 086 -0046 X 5 (Side View) STARLight PDR 3 Oct ‘ 01 F. 1. 7 Rashid
Y-Thermal Plate / Manifold STARLight • Dwg#: 086 -0078 X 1 STARLight PDR 3 Oct ‘ 01 F. 1. 8 Rashid
Control Module Design & Structure STARLight • Dwg#: 086 -0050 X 2 STARLight PDR 3 Oct ‘ 01 F. 1. 9 Rashid
Structural Analysis Plans STARLight • Preliminary aerodynamic load analysis (Doc#: 086 -0067 X 1) • Results indicate profile drag force of 130 lbf (500 N) with sensor height=5. 7” (7° tilt w. r. t ground) STARLight PDR 3 Oct ‘ 01 F. 1. 10 Rashid
Structural Analysis Plans STARLight • Perform a complete finite-element structural analysis using FEMAP • Static analysis will provide – – – Confidence in structural design Confidence in material selection High stress concentration areas Undesirable structural deflections Areas of improvement (if necessary) • Vibration analysis will provide – Fundamental frequencies of structure. STARLight PDR 3 Oct ‘ 01 F. 1. 11 Rashid
Weight Estimate Summary STARLight • Doc# 086 -0068 X 2 (10% Margin) STARLight PDR 3 Oct ‘ 01 F. 1. 12 Rashid
Weight Estimate Summary STARLight X STARLight PDR 3 Oct ‘ 01 F. 1. 13 Rashid
Schedule (Efforts to CDR) STARLight • Prototype design of Receiver/DA assembly (Mechanical parts only) – Complete detail level drawings for 2 -channel prototype (10/26/01) – In-house manufacturing of assemblies (11/09/01) • Detail level drawings for complete sensor assembly (flight hardware) – Will depend upon: Ø Receiver component layout Ø A/D component layout Ø Antenna design details Ø Dewar assembly configuration – Can be completed 4 weeks after above items have been finalized STARLight PDR 3 Oct ‘ 01 F. 1. 14 Rashid
Schedule (Efforts to CDR) STARLight • Mechanical detail level drawings for : – Control Module (01/11/01) – Pilot Control Box (01/31/01) – Mechanical GSE (02/08/01) • Complete Structural Analysis (12/14/01) • Update Mechanical ICD (Doc#: 086 -0003) (02/08/01) • Update Weight Report (Doc#: 086 -0068) (02/08/01) STARLight PDR 3 Oct ‘ 01 F. 1. 15 Rashid
