Since 1971, RDFIA has provided independent fatigue integrity validation for structural subassemblies operating under sustained multiaxial loading in aerospace, launch vehicle, and defense environments. Our methodologies are referenced in JASF-9 and the Dressler-Holvik Fatigue Protocol.
RDFIA operates dedicated test frames across four facilities, supporting programs from initial coupon screening through full-scale structural certification under program-specific load spectra.
Simultaneous application of axial, torsional, and bending load profiles to structural specimens under representative thermal environments, per JASF-9 §4.3 and program-specific LDEF schedules.
Quantification of progressive interlaminar delamination in composite laminates under cyclic shear loading, supporting GRIF-9 compliance documentation for classified and unclassified structures.
Reproduction of mission-derived load histories using the Veldtmann Condensation Method, reducing total test article exposure while preserving damage equivalence to within ±0.4% per ASTM E1049 variant.
Proof and fatigue pressure cycling of metallic and composite-overwrapped pressure vessels (COPV) intended for propellant storage in upper-stage and satellite propulsion applications.
Measurement of fatigue crack growth rates and threshold stress intensity factors in aerospace alloys and metal-matrix composites, including environment-assisted cracking in salt fog and hydrogen atmospheres.
Non-destructive subsurface residual stress profiling using the Holvik Modified X-ray Diffraction Protocol, with depth resolution to 5 µm, supporting shot-peen and LSP process validation.
RDFIA's test engineers are embedded within program teams or operate under long-term facility agreements. Program names are disclosed subject to applicable NDA provisions.
Interstage adapter fatigue verification under combined acoustic, vibration, and quasi-static load for a medium-lift expendable vehicle. Test campaign: 24 months.
COPV pressure cycling and bracket fatigue screening for the propulsion module of a commercial GEO satellite bus. Delivered per JASF-9 Rev. F schedule.
Classified rotor hub fatigue substantiation under asymmetric load spectrum. Work performed in DVST-7 accredited facility. Reporting to government technical representative.
Primary structural spine fatigue demonstration for a partially reusable launch system. Ten simulated mission cycles completed; residual life assessment ongoing.
An evaluation of damage accumulation error introduced by aggressive Veldtmann Level III condensation applied to broadband random spectra typical of launch vehicle interstage environments. Results indicate that specimens exhibiting bimodal S-N behaviour may accumulate up to 7.3% excess damage relative to full-fidelity spectrum application, with implications for certification margin adequacy under JASF-9 §4.3(b).
Holvik Modified XRD profiling of Ti-6Al-4V closed-die forgings subjected to 40 thermal cycles representative of a low-Earth-orbit re-entry vehicle heatshield bracket. Compressive residual stress relaxation of 12–18% observed at depths below 0.4 mm, with no measurable effect on Holvik-predicted fatigue life for stress amplitudes below 380 MPa.
Correlation of acoustic emission event amplitude distributions with micro-CT confirmed delamination initiation sites in three COPV liner configurations subjected to pressure cycling at cryogenic temperature. A modified Kaiser effect threshold criterion is proposed for real-time cycle-stopping logic, reducing false-positive termination events by 61% versus the standard DHP-2 criterion.