STARLight PDR 3 Oct ‘01 F.1.1 Rashid STARLight STARLight Mechanical Tahir Rashid STARLight Mechanical Engineer (734) 764-7210

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Presentation transcript:

STARLight PDR 3 Oct ‘01 F.1.1 Rashid STARLight STARLight Mechanical Tahir Rashid STARLight Mechanical Engineer (734)

STARLight PDR 3 Oct ‘01 F.1.2 Rashid STARLight Mechanical Requirements – Instrument to be used on Husky A-1B 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 Y- arrangement – 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.1.3 Rashid STARLight Sensor Module Design & Structure

STARLight PDR 3 Oct ‘01 F.1.4 Rashid STARLight Sensor Module Design & Structure Dwg#: X5

STARLight PDR 3 Oct ‘01 F.1.5 Rashid STARLight Sensor Module Section Dwg#: X5 (Exploded View)

STARLight PDR 3 Oct ‘01 F.1.6 Rashid STARLight Sensor Module Section Dwg#: X5 (Top & Side View)

STARLight PDR 3 Oct ‘01 F.1.7 Rashid STARLight Sensor Module Section Dwg#: X5 (Side View)

STARLight PDR 3 Oct ‘01 F.1.8 Rashid STARLight Y-Thermal Plate / Manifold Dwg#: X1

STARLight PDR 3 Oct ‘01 F.1.9 Rashid STARLight Control Module Design & Structure Dwg#: X2

STARLight PDR 3 Oct ‘01 F.1.10 Rashid STARLight Structural Analysis Plans Preliminary aerodynamic load analysis (Doc#: X1) Results indicate profile drag force of 130lb f (500N) with sensor height=5.7” (7° tilt w.r.t ground)

STARLight PDR 3 Oct ‘01 F.1.11 Rashid STARLight Structural Analysis Plans 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.1.12 Rashid STARLight Weight Estimate Summary Doc# X2 (10% Margin)

STARLight PDR 3 Oct ‘01 F.1.13 Rashid STARLight Weight Estimate Summary X

STARLight PDR 3 Oct ‘01 F.1.14 Rashid STARLight Schedule (Efforts to CDR) 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:  Receiver component layout  A/D component layout  Antenna design details  Dewar assembly configuration – Can be completed 4 weeks after above items have been finalized

STARLight PDR 3 Oct ‘01 F.1.15 Rashid STARLight Schedule (Efforts to CDR) 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#: ) (02/08/01) Update Weight Report (Doc#: ) (02/08/01)