Aerospace Projects
Metallic/composite airframe and spacecraft structural design for manufacturing, tooling and assembly engineering support
Metallic/composite airframe and spacecraft structural design for manufacturing, tooling and assembly engineering support
- metallic/composite/ LO structures
-thermoset vs. thermoplastic component builds
- looking inboard at forward fuselage air frame assembly
-Looking forward at aft bulkhead
-co-consolidation curing with dissolving mandrels
-Cypac / PEEK based laminate assemblies co-consolidated / co-cured
-out of autoclave cure development
-AS4/PEEK structural load testing
- AS4/PEEK structural load test article
-continuous high modulus fiber orientation / precursor to Z-pin systems
- GPS/X-band element/cavity/radome mechanical design engineering
- CFRP / KFRP / GFRP co-laminated air frame structures
- self heated co-curing of integrally stiffened skin
-b-stage pre-forming for co-curing
-sensor based internal pressure application
-directional / adjustable pressure curing system
- typical PCM design used on more intricate shapes than shown
- example of tool type used for tighter lofted fuselage shapes
-self heating ceramic / vacuum diaphragm press forming
-vacuum assisted resin transfer molding + reusable vacuum bagging
-integration troubleshooting/enhancement
-dual S/Ku band single access unfurlable mesh
- CR&D Lightweight structures program
-pre-flight check at KSC Launch Complex 39-B
-stowed 5m antenna close up (gold kapton)
- 5m folded mesh antenna pair at top
- similar to the DARPA Phoenix illustration shown
-metallic mesh/GFRP structural member innovation
Titan 4 Centaur T - KSC Launch Complex 40
- deployed by STS-44 mission from KSC Launch Complex 39A
-looking at center infrared imaging sensor tube
-deployment stage with high gain dish in center
-fabrication, assembly, adjustment and test
- fabrication and assembly
-parabolic antenna feed curvature
-co-cured assembly
- unidirectional/continuous graphite fiber
-lightweight satellite structures program
-kevlar/graphite spacecraft bus corner
- unidirectional/continuous fiber rtm processed
composite tape placement process development
- 3 variant fabrication time = 1 unit conventional fabrication
- hybrid mfg using simultaneous additive/subtractive steps
integral cooling channels - directed energy deposition
- directed energy deposition / minimal machining
-mandrel based sintering
short fiber nozzle extrusion with final mold compression
