{"schema_version":1,"research_id":"eoa_inverse_innovation_exp06_external_evaluation_20260803","source_assessment_id":"predictive_residual_processing__aviation_aeronautics:P3:v0","cell_id":"predictive_residual_processing__aviation_aeronautics","search_queries":["active gust load alleviation fault detection command conditioned residual structural response aircraft","NASA active load alleviation gust load control fault detection residual aircraft","FAA active load alleviation system certification guidance gust load alleviation","EASA active load alleviation certification special condition","\"Fault Tolerant Control of an Experimental Flexible Wing\" residual filter actuator","aircraft gust load alleviation fault detection observer residual control input actuator sensor fault","aeroservoelastic active load alleviation fault detection isolation residual","aircraft active load alleviation command response monitoring patent residual","site:easa.europa.eu \"load alleviation\" certification memorandum","site:faa.gov AC 25.1309-1B system design analysis pdf","site:sae.org ARP4754B aircraft systems development assurance","site:ntrs.nasa.gov active load alleviation fault detection flexible wing residual","FAA AD Tamarack ATLAS load alleviation system uncommanded roll 2024","NTSB active load alleviation system failure Tamarack CitationJet","Tamarack active load alleviation system failure safety directive FAA"],"sources":[{"source_id":"S1","title":"Airworthiness Directives; Textron Aviation Inc. Airplanes—AD 2024-15-09","publisher":"U.S. Department of Transportation / Federal Aviation Administration","url":"https://www.transportation.gov/regulations/federal-register-documents/2024-21112","source_class":"GOVERNMENT_OR_REGULATOR","publication_date":"2024-09-17","accessed_at":"2026-08-03","claims_supported":["An installed active load-alleviation system can fail without annunciating loss of load alleviation.","FAA considered the condition unsafe and required an AFM revision and physical placards.","FAA is an identifiable authorizer for operational changes affecting such systems."]},{"source_id":"S2","title":"AC 25.671-1—Flight Control Systems","publisher":"Federal Aviation Administration","url":"https://www.faa.gov/documentLibrary/media/Advisory_Circular/AC_25.671-1.pdf","source_class":"OFFICIAL_GUIDANCE","publication_date":"2024-08-30","accessed_at":"2026-08-03","claims_supported":["Load-alleviation systems are treated as part of the flight-control system and can affect structural performance.","Applicants must evaluate failures, structural integrity, transient response, recognition delays, automatic degraded modes, and interactions among automatic functions.","FAA guidance explicitly calls for balancing needed awareness against nuisance alerting and minimizing nuisance alerts.","Gust-load-alleviation surface jams and continued-safe-flight-and-landing consequences require assessment."]},{"source_id":"S3","title":"Survey of Applications of Active Control Technology for Gust Alleviation and New Challenges for Lighter-weight Aircraft","publisher":"NASA","url":"https://ntrs.nasa.gov/citations/20120013450","source_class":"PRIMARY_RESEARCH","publication_date":"2012-04-01","accessed_at":"2026-08-03","claims_supported":["Active gust alleviation has been demonstrated on multiple aircraft and is motivated by structural-weight reduction, ride quality, and fatigue-life objectives.","Lighter and more flexible aircraft increase aeroelastic coupling and gust sensitivity.","Active load alleviation is an established aviation research and application area."]},{"source_id":"S4","title":"Disturbance Observer for Gust Load Alleviation (DOGLA)","publisher":"NASA TechPort","url":"https://techport.nasa.gov/projects/34140","source_class":"OFFICIAL_ORGANIZATION_DATA","publication_date":"2015","accessed_at":"2026-08-03","claims_supported":["NASA funded development of a disturbance observer that estimates gust loading and rejects it in a nonlinear high-altitude-long-endurance aircraft model.","NASA identified relevance to aviation safety, assurance of flight-critical systems, and aeronautics test operations.","A public funder and plausible research adopter exists for observer-based load-alleviation work."]},{"source_id":"S5","title":"Fault Tolerant Control of an Experimental Flexible Wing","publisher":"MDPI Aerospace","url":"https://doi.org/10.3390/aerospace6070076","source_class":"PRIMARY_RESEARCH","publication_date":"2019-07","accessed_at":"2026-08-03","claims_supported":["A wind-tunnel-validated gust-load-alleviation architecture already uses a residual filter, residual evaluator, threshold, and decision module to detect actuator faults.","Its residual filter processes commanded control-surface inputs and measured wing accelerations and mathematically decouples known commands from the residual.","The paper reports false-alarm testing, approximately 0.1-second detection in one stuck-actuator experiment, and real-time fault-triggered control reallocation.","The authors report practical limits: model uncertainty and sensor noise impede fault isolation, and residual magnitude rises when closed-loop commands are present."]},{"source_id":"S6","title":"Resilient Control for a Flexible Wing Aircraft: An Active Output Feedback Approach","publisher":"Elsevier, Aerospace Science and Technology","url":"https://www.sciencedirect.com/science/article/pii/S1270963825008831","source_class":"PRIMARY_RESEARCH","publication_date":"2026-01","accessed_at":"2026-08-03","claims_supported":["A recent simulation study addresses gust-load alleviation under actuator faults, sensor faults, and model uncertainty.","Resilient output-feedback control is a rival that can tolerate faults without explicit fault detection and diagnosis.","The proposal must outperform simpler fault-resilient control, not merely demonstrate that faults can be handled."]},{"source_id":"S7","title":"ARP4754B—Guidelines for Development of Civil Aircraft and Systems","publisher":"SAE International","url":"https://saemobilus.sae.org/standards/arp4754b-guidelines-development-civil-aircraft-systems","source_class":"STANDARD","publication_date":"2023-12-20","accessed_at":"2026-08-03","claims_supported":["Civil-aircraft system development requires requirements validation and implementation verification for safety, certification, and product assurance.","The standard applies across aircraft functions and operating environments and links to separate software, hardware, and safety-assessment processes.","Configuration-controlled validation and verification are material workflow and cost requirements for any operational supervisor."]},{"source_id":"S8","title":"AC 25.1309-1B—System Design and Analysis","publisher":"Federal Aviation Administration","url":"https://www.faa.gov/regulations_policies/advisory_circulars/index.cfm/go/document.information/documentID/1043037","source_class":"OFFICIAL_GUIDANCE","publication_date":"2024-08-30","accessed_at":"2026-08-03","claims_supported":["FAA identifies active guidance for showing compliance with 14 CFR 25.1309 for equipment, systems, and installations.","Certification evidence must supplement, rather than replace, engineering and operational judgment.","An operational implementation would require applicant-controlled safety analysis and FAA compliance findings; a research prototype has no independent operational authority."]}],"problem_evidence":{"support":"STRONG","rationale":"The problem is visible at three levels. FAA documented an unsafe unannunciated loss of an installed load-alleviation function. FAA flight-control guidance requires assessment of load-alleviation failures, structural effects, degraded modes, recognition delay, and nuisance alerting. Most directly, the experimental flexible-wing study found that closed-loop control commands elevate the residual and therefore explicitly incorporated command inputs into a model-based residual filter. Evidence does not establish the frequency or fleet-wide prevalence of the candidate's exact commanded-versus-external attribution ambiguity.","source_ids":["S1","S2","S5"]},"stakeholder_evidence":{"support":"MODERATE","rationale":"FAA is an identifiable authorizer and has exercised authority over unsafe load-alleviation behavior. NASA has funded disturbance-observer load-alleviation research and named flight-critical assurance and test operations as intended applications. This establishes institutional pull for safe, fault-aware load alleviation, but no source expresses demand for this exact hierarchical, precision-weighted residual supervisor or identifies an aircraft program prepared to adopt it.","source_ids":["S1","S2","S4","S8"]},"prior_art":{"proximity":"SUBSTANTIAL_COLLISION","closest_analogues":[{"name":"Experimental flexible-wing residual-filter fault detection and tolerant control","similarity":"Very close: it uses commanded control-surface inputs, measured wing accelerations, an aeroelastic model, a command-decoupled residual, threshold evaluation, fault detection, and a downstream reconfiguration decision in a gust-load-alleviation wind-tunnel system.","remaining_difference":"The candidate expands the residual across strain, pressure, actuator, spatial, and modal channels and specifies uncertainty weighting, independent raw-window audits, protected raw limits, configuration checks, and deterministic fallback. Those are safety-governance additions; the core command-conditioned residual mechanism is already demonstrated.","source_ids":["S5"]},{"name":"NASA Disturbance Observer for Gust Load Alleviation","similarity":"Uses a model-based observer to estimate the uncommanded gust component in an active load-alleviation aircraft model and supports flight-critical assurance objectives.","remaining_difference":"DOGLA estimates disturbances for rejection rather than proposing the candidate's reconstructive sensor-level cancellation, raw audit stream, and bounded supervisory advisory.","source_ids":["S4"]},{"name":"Resilient active-output-feedback gust-load controller","similarity":"Addresses the same flexible-wing load-alleviation setting under actuator faults, sensor faults, and model uncertainty.","remaining_difference":"It deliberately avoids explicit FDD; this makes it a strong simpler comparator rather than the same architecture.","source_ids":["S6"]},{"name":"Established active gust/load-alleviation systems","similarity":"Operational and experimental systems already use sensors, aircraft models, and commanded surfaces to reduce gust and maneuver loads.","remaining_difference":"The candidate concerns attribution and supervision of the controller's self-generated structural signatures, not load reduction alone.","source_ids":["S1","S2","S3"]}],"distinctive_claim_remaining":"For one frozen aircraft configuration and load-alleviation function, a synchronized multichannel command-conditioned residual supervisor with protected raw limits, independent raw audits, and deterministic fallback will reduce nuisance supervisory transitions and improve attribution latency relative to scheduled raw thresholds, rule-based command-conditioned thresholds, a conventional observer, and resilient output feedback, while causing no additional miss of any injected protected event, no material over-cancellation of external-response energy, and no unacceptable deadline or fallback occupancy. This is a contrastive, falsifiable performance-and-safety claim, not a world-novelty claim.","confidence":"HIGH"},"implementation_evidence":{"support":"MODERATE","rationale":"Technical implementability is credible: command-and-measurement residual filters have already run in real time on an experimental flexible wing, and disturbance observers and fault-resilient control are established alternatives. Offline simulation and HIL shadow evaluation can avoid immediate operational risk. However, evidence is absent for the candidate's multichannel/modal reconstruction fidelity, clock-skew tolerance, rare combined-event recall, independence of the raw audit path, computational timing on target avionics, and net advantage after fallback and verification overhead. Operational use would require configuration-controlled development assurance, safety assessment, software/hardware assurance as applicable, applicant authority, and regulator acceptance.","source_ids":["S2","S4","S5","S6","S7","S8"]},"scores":{"meaningful_impact":{"score":4,"rationale":"Failure or misclassification in a structure-affecting flight-control function can have consequential structural and controllability effects, while a successful supervisor could reduce nuisance disengagement without desensitizing protection. Realized impact is unmeasured.","source_ids":["S1","S2","S3"]},"stakeholder_pull":{"score":3,"rationale":"FAA action and NASA funding show strong category-level need and authority, but no aircraft manufacturer, certification applicant, or test program has requested this exact intervention.","source_ids":["S1","S4","S8"]},"incremental_advantage":{"score":2,"rationale":"The core known-input/measurement residual and fault decision are already demonstrated experimentally; incremental advantage rests mainly on broader sensing, audit, uncertainty, and fallback governance and has not been compared empirically.","source_ids":["S4","S5","S6"]},"distinctiveness_plausibility":{"score":2,"rationale":"A narrow combined architecture may differ from individual published implementations, but its central causal mechanism substantially collides with established model-based FDI. World novelty and patentability remain unmeasured.","source_ids":["S5","S6"]},"technical_implementability":{"score":4,"rationale":"Real-time residual generation using commands and flexible-wing sensors has experimental support. The candidate's larger sensor/model scope and timing requirements remain unvalidated.","source_ids":["S4","S5"]},"adoption_authority_feasibility":{"score":3,"rationale":"Offline and HIL shadow studies fit ordinary engineering authority. Connection to a flight-control or protection path requires formal applicant configuration authority, safety and development assurance, and regulator acceptance.","source_ids":["S2","S7","S8"]},"evidence_readiness":{"score":3,"rationale":"Comparators, fault classes, metrics, and a bounded shadow study can be specified now, but representative aircraft models, HIL facilities, synchronized traces, and safety-domain judgments are proprietary or partner-controlled.","source_ids":["S5","S7"]},"safety_net_benefit":{"score":3,"rationale":"Protected raw limits and deterministic fallback could bound model failure, consistent with regulator concern about unannunciated failures and automatic degraded modes. Their effectiveness has not been tested, and added complexity can itself create latent failures.","source_ids":["S1","S2","S7"]},"scalability":{"score":2,"rationale":"The software pattern is reusable, but each aircraft configuration, control law, sensor map, envelope, latency budget, and safety classification would require new modeling, verification, and approval.","source_ids":["S2","S7","S8"]}},"score_confidence":"MODERATE","costs":{"first_evidence":{"band_2026_usd":"250K_TO_1M","scope":"Preregister, implement, and execute the single-configuration simulation/HIL shadow study; prepare frozen models and comparators; inject up to 30 scenario families; retain independent raw windows; analyze reconstruction, latency, nuisance, over-cancellation, fallback, and deadlines.","confidence":"LOW","assumptions":["Existing representative aeroelastic model and HIL rig are available from a partner.","Approximately 3-6 engineer-years are consumed across controls, loads, avionics, safety, test, and independent analysis.","No flight testing, certified target-hardware redesign, or operational display integration is included.","This is a resource-equivalent estimate, not a vendor quotation."],"source_ids":["S5","S7"]},"initial_deployment_startup":{"band_2026_usd":"1M_TO_5M","scope":"Develop a target-hardware shadow implementation for one aircraft configuration, establish synchronized data interfaces and configuration management, perform independent verification, expand HIL coverage, and prepare a safety-assessment change package without operational authority.","confidence":"LOW","assumptions":["One existing aircraft program supplies interfaces, data rights, rigs, and engineering authority.","The supervisor remains non-interfering and does not alter alerts or commands.","Software and complex-hardware assurance costs are limited to the shadow implementation level.","This is a resource-equivalent estimate, not a certification-program bid."],"source_ids":["S2","S7","S8"]},"operational_launch":{"band_2026_usd":"5M_TO_25M","scope":"For one aircraft type and function, complete certifiable requirements, safety assessment, software/hardware assurance as applicable, integration verification, regression, flight-test authorization and execution, compliance documentation, and production configuration release.","confidence":"LOW","assumptions":["No major airframe redesign or new sensor installation is required.","Existing raw protection remains independent and unchanged.","Certification credit for model-based evidence is limited and substantial test evidence is required.","A single type-design or STC program is included; fleet-wide retrofit is excluded."],"source_ids":["S1","S2","S7","S8"]},"annual_recurring":{"band_2026_usd":"250K_TO_1M","scope":"Maintain one approved configuration family: regression and replay testing, configuration/model checks, audit-window review, safety monitoring, issue investigation, documentation, and approval of changes.","confidence":"LOW","assumptions":["A small multidisciplinary sustaining team is retained.","Major control-law, structural, sensor, or avionics changes trigger separate nonrecurring revalidation.","Aircraft data acquisition already exists.","This is a resource-equivalent estimate without public labor-rate or program-cost evidence."],"source_ids":["S1","S7","S8"]}},"verified_pipeline_gates":{"externally_supported_problem":{"status":"YES","reason":"FAA documented unsafe unannunciated loss of active load alleviation, and experimental research directly shows closed-loop commands affecting residual behavior and motivates command decoupling.","source_ids":["S1","S2","S5"]},"externally_credible_adopter_or_authorizer":{"status":"YES","reason":"FAA is the identifiable operational authorizer; NASA is an identifiable research funder and potential shadow-test sponsor. No committed aircraft-program adopter was found.","source_ids":["S1","S4","S8"]},"distinct_testable_incremental_claim":{"status":"YES","reason":"The candidate can be compared against raw scheduled thresholds, command-conditioned threshold widening, a conventional residual observer, and resilient output feedback on nuisance transitions, protected-event capture, latency, over-cancellation, reconstruction, deadlines, and fallback occupancy.","source_ids":["S5","S6"]},"bounded_next_evidence_step":{"status":"YES","reason":"A single-configuration, maximum-30-family simulation/HIL shadow study with frozen models, comparators, metrics, and rejection rules is bounded and cannot authorize live use.","source_ids":["S5","S7"]},"no_unresolved_safety_or_authority_stop":{"status":"YES","reason":"The proposed next step is non-interfering shadow evaluation. Existing raw limits remain authoritative, and outputs cannot command surfaces, alter displays, inhibit alerts, or enter protection logic. Any later operational connection requires a separate safety and certification process.","source_ids":["S2","S7","S8"]},"credible_cost_scope_and_range":{"status":"UNCERTAIN","reason":"Scopes and broad resource-equivalent bands are explicit and consistent with the documented development-assurance burden, but no public source provides program-specific labor, HIL, avionics-integration, flight-test, or certification cost data.","source_ids":["S7","S8"]}},"next_evidence_step":"With an aircraft-program or research partner, preregister one frozen-configuration study capped at 30 scenario families and 1,500 simulation runs, followed by a bounded HIL confirmation matrix on the same configuration. Compare (A) scheduled raw thresholds, (B) rule-based command-conditioned threshold widening, (C) a conventional known-input residual observer, (D) resilient output feedback without explicit FDD, and (E) the candidate. Include nominal commands, gusts, actuator lag/stuck/runaway behavior, sensor bias/dropout, aeroelastic perturbation, bounded clock skew and loss, version mismatch, and combined command-plus-disturbance cases. Retain raw data independently. Proposed preregistered falsifiers are: any injected protected event captured by a baseline but missed or delayed beyond the allowed safety deadline by the candidate; more than 5% cancellation of independently labeled external-response energy; less than 25% nuisance-transition reduction without a predeclared compensating latency advantage; reconstruction-budget breach; computational deadline miss; structured residual bias after correction for multiple tests; or fallback occupancy above 20% in in-envelope nominal-plus-gust cases. Passing authorizes only expanded shadow research, not flight-control integration.","blocking_evidence":["No representative simulation or HIL results compare the candidate with the four named rivals.","No evidence establishes separability of commanded response from simultaneous external gusts and faults across a declared envelope.","No rare-event evidence shows that cancellation preserves every event captured by protected raw monitoring.","Clock-skew tolerance, reconstruction error, computational deadlines, and fallback occupancy are unmeasured.","No aircraft applicant or test organization has committed proprietary models, traces, HIL access, configuration authority, or safety personnel.","The independent raw-audit path and absence of correlated model blind spots are unverified.","Program-specific cost evidence is unavailable.","World novelty, patentability, freedom to operate, market size, and realized impact remain unmeasured."],"research_disposition":"PARTNERED_RESEARCH_PROGRAM","world_novelty_boundary":"The search establishes substantial prior art for active gust/load alleviation, disturbance observers, known-input command-decoupled residual filters, thresholded fault decisions, and fault-resilient flexible-wing control. It does not establish whether one publication or product combines the candidate's full multichannel/modal hierarchy, precision weighting, independent raw audits, protected raw limits, model-version gating, and deterministic fallback. That unresolved combination must not be represented as world-new. Patentability, freedom to operate, market size, and world novelty were not measured.","arm":"COMPLETE_PROPOSAL_PORTFOLIO","candidate_version":0,"controller_recommendation":{"action":"STOP_EMPIRICAL_RESEARCH_NEEDED","repairable":false,"material_progress_observed":true,"progress_targets":["Secure one aircraft-program, NASA, DLR, or equivalent partner with rights to a representative aeroelastic model, synchronized traces, and HIL facilities.","Freeze quantitative reconstruction, latency, nuisance, protected-event, over-cancellation, deadline, and fallback acceptance criteria before accessing test outcomes.","Run the preregistered five-arm simulation/HIL comparison, including simultaneous command-plus-disturbance and bounded mismatch cases.","Demonstrate that no protected event captured by a baseline is suppressed or materially delayed and that the raw audit path is independent.","Obtain independent controls, loads, avionics, and safety review of failure containment and of any claimed incremental advantage.","Replace resource-equivalent cost estimates with partner work breakdown, labor assumptions, rig charges, assurance scope, and contingency."],"reason":"Web evidence verifies a consequential problem, a credible authorizer/funder, technical feasibility, and substantial collision with existing command-input residual fault detection on an experimental flexible wing. The remaining value claim is comparative performance and safety under synchronized combined events. It cannot be resolved through further bounded web search; it requires proprietary aircraft data, simulation/HIL execution, and live multidisciplinary judgment. Under the required controller rule, this empirical stop is terminal and therefore repairable is false."},"proposal_index":3}