Xcelerator · Digital Thread → Acquisition
We reverse-engineered a realistic USAF solicitation — the Advanced Small UAS (ASUAS) program, modeled on the real T-X System Specification — and then answered it with the QX-250. The proposal's compliance matrix is generated from the same design data as the rest of this thread, so it updates as the design updates.
The solicitation
Modeled section-for-section on the real T-X / Advanced Pilot Training System Specification (MIL-STD-961E) — fictional program, authentic structure.
The ASUAS is a notional USAF Group-1 electric-VTOL reconnaissance quadrotor acquisition (solicitation FA8620-26-R-2500, spec PRF ASUAS-AV-1001). The System Specification carries Sections 1–6 with 85 verifiable requirements, a full Verification Cross-Reference Matrix, and appendices for the mission profile, the reliability/safety basis (traced to the MADe model), and the trade space. A light RFP wrapper adds the SF-1449-style cover, CLINs, Statement of Objectives, and Sections L & M.
The answer
Generated from proposal_data.py joined to the specification's requirement tree — the same source of truth as the proposal PDF.
The proposal
A best-value technical proposal built to Section L, evaluated against the Section M factors.
System description + the full requirement-by-requirement compliance matrix and trade-space responses.
The MADe RAM/FTA/FMECA case: R = 0.99998, loss-of-thrust 1.85×10⁻⁴/hr, MIL-STD-882E, airworthiness approach.
Notional ROM CLIN pricing and contract documentation, Blue-UAS/§848 assertion.
Full traceability
All 85 verifiable requirements of PRF ASUAS-AV-1001, with the QX-250 approach, status, and evidence artifact. Scrolls; regenerated on every build.
| Para | Requirement | QX-250 approach | Status | Evidence |
|---|---|---|---|---|
| 3.1.2.1 | Hover Endurance | 8.0 min hover at the as-built 0.65 kg GTW on the dual 4S 1100 mAh energy system (2200 mAh installed; the ≥1500 mAh usable of REQ-PWR-005 is the system total across the two OR-ed packs, not per-pack). Objective 20 min via the extended-energy option, App. C. | Compliant | RFLP REQ-PERF-002; MADe Nominal Sortie; 6-DOF v3 @0.65 kg |
| 3.1.2.2 | Mission Endurance | Completes the 10.5-min App. A reference sortie with ≥20% reserve retained. | Compliant | MADe “QX-250 Nominal Sortie” (7 phases) |
| 3.1.2.3 | Operational Radius | ~2.0 km C2/video radius on the 2.4 GHz link (Threshold); 5 km Objective via the directional-antenna option. | Compliant | Link budget; RFLP IF set |
| 3.1.2.4 | Dash Speed | 60 km/h (32 kt) level dash — exceeds the 30 kt Threshold. | Compliant | RFLP REQ-PERF-003 |
| 3.1.2.5 | Cruise Speed | 15 kt sustained transit cruise with payload imaging. | Compliant | Performance analysis |
| 3.1.2.6 | Rate of Climb | >3 m/s vertical climb retained on the 3.83:1 thrust margin at the as-built 0.65 kg vs 3 m/s required. | Compliant | Amesim 6-DOF v3; performance analysis |
| 3.1.2.7 | Hover Ceiling (OGE) | OGE hover to high density altitude on the 3.83:1 thrust margin (Objective). | Meets Objective | Amesim 6-DOF v3; performance analysis |
| 3.1.2.8 | Thrust-to-Weight Ratio | 3.83:1 static thrust-to-weight at the as-built 0.65 kg GTW, flight-verified in the 6-DOF model, vs 2:1 required — large gust-rejection margin (peak 43° tilt recovered). | Compliant | RFLP REQ-PERF-001; Amesim 6-DOF v3 (T/W 3.83) |
| 3.1.2.9 | Wind and Gust Tolerance | Position hold in 15.5 kt (8 m/s) steady wind (Threshold); 20 kt Objective under evaluation. | Compliant | RFLP REQ-PERF-004 |
| 3.1.2.10 | Vertical Launch and Recovery | Inherent VTOL: unassisted vertical launch and precision landing, no launch/recovery gear. | Compliant | Functional F-set; RFLP REQ-SYS-002 |
| 3.1.2.11.1 | Stabilized Flight Modes | Self-leveling (Angle), position-hold (GNSS) and Acro modes with bumpless transitions. | Compliant | RFLP REQ-SYS-004 / CTRL set |
| 3.1.2.11.2 | GPS-Denied Attitude Hold | Auto-reverts to attitude hold on GNSS loss with unambiguous operator cueing. | Compliant | RFLP REQ-CTRL set |
| 3.1.2.11.3 | Operator Skill Level Handling | Self-level mode + student-fault tolerance sized to a minimally-trained operator. | Compliant | RFLP REQ-SYS-004 |
| 3.1.2.11.4 | Loss of Control Resistance | Dual flight control + deterministic contingencies; rotor loss → controlled descent (see 3.3.5). | Compliant | MADe RBD; RFLP REQ-CTRL |
| 3.1.2.12 | Acoustic Signature | ~62 dBA at 100 m predicted for the 5-in rotor set; to be confirmed by MIL-STD-1474E measurement. | Compliant (planned) | Acoustic analysis (to be tested) |
| 3.1.3.1 | Gross Takeoff Weight | GTW ~0.65 kg incl. energy source and Standard Payload — beats the 0.70 kg Objective. | Meets Objective | NX mass properties; RFLP REQ-SYS-006 |
| 3.1.3.2 | Transport Configuration | Air vehicle + GCS + consumables stow in a single man-portable case. | Compliant | Design / transport concept |
| 3.1.3.3 | Rapid Assembly | Tool-less arm/prop assembly to ready-to-launch in <2 min. | Compliant | RFLP REQ-STR; design |
| 3.1.3.4 | Configuration | Symmetric Quad-X, 250 mm motor-to-motor diagonal; realized as the QX250_v3_final 53-component NX assembly on the parametric datum. | Compliant | NX QX250_v3_final (53 comp.); RFLP REQ-STR-001 |
| 3.1.3.5 | Design Service Life | Carbon airframe sized to ≥500 h / 2000 cycles; substantiated by durability analysis and test. | Compliant (planned) | MADe MTTF; structural analysis (planned) |
| 3.1.3.6 | Structural Load Factors | -2/+4 G limit envelope, ultimate = 1.5× limit; confirmed by NX FEA and static test. | Compliant (planned) | NX; structural analysis (planned) |
| 3.1.3.7 | Materials, Processes, and Corrosion | 3K carbon-fiber arms ≥4 mm; corrosion-tolerant materials and HAZMAT program. | Compliant | NX; RFLP REQ-STR-002 |
| 3.1.3.8 | Drop Survivability | Survives 1.5 m drop onto each face without primary-structure fracture; realized as-built by the LandingLeg (STR-002) landing gear. | Compliant | RFLP REQ-STR-002; NX landing gear (analysis→physical) |
| 3.1.3.9 | Structural Dynamics | First bending mode ≥80 Hz, decoupled from the control bandwidth. | Compliant | RFLP REQ-STR-007 (analysis) |
| 3.1.3.10 | Propeller Clearance and Frangibility | ≥5 mm prop tip clearance; impact-tolerant frangible propellers. | Compliant | NX; RFLP REQ-STR-006 |
| 3.2.1 | Standard Payload | 100 g Standard-Payload provision with mechanical/electrical/data interfaces. | Compliant | RFLP REQ-SYS-005 |
| 3.2.2 | Electro-Optical Sensor | Payload bay provisioned; production stabilized EO zoom gimbal to be integrated to meet 300 m recognition. | Partial — closure plan | Integration plan |
| 3.2.3 | Infrared Sensor (Growth) | IR channel offered as the App. C growth payload with SWaP-C provisioning. | Compliant (planned) | Trade study (App. C) |
| 3.2.4 | Gimbal Stabilization | 2-axis stabilized gimbal, ≤150 µrad jitter by analysis. | Compliant (planned) | Payload analysis (planned) |
| 3.2.5 | Target Geo-Location | GNSS + gimbal geo-pointing, ≤50 m CE90 by error-budget analysis. | Compliant (planned) | TLE analysis (planned) |
| 3.2.6 | Imagery Metadata | MISB ST 0601 KLV metadata embedded in the payload stream. | Compliant (planned) | Payload SW plan |
| 3.3.1 | Electric Propulsion | Four independent BLDC / 4-in-1 ESC / propeller channels, DShot600 digital command. | Compliant | Capital electrical architecture |
| 3.3.2 | Per-Channel Current Capacity | 45 A continuous / burst per channel 4-in-1 ESC. | Compliant | RFLP REQ-PWR-002; Capital |
| 3.3.3 | Propellers | 5043 tri-blade set, 2×CW + 2×CCW, tool-less swap. | Compliant | NX; RFLP REQ-STR |
| 3.3.4 | Energy Reserve | ≥20% usable energy reserve retained at end of the App. A sortie. | Compliant | MADe Nominal Sortie |
| 3.3.5 | Single-Rotor Failure Response | Failed-channel detection → controlled descent/termination; hexa-rotor growth removes the 24 order-1 SPOFs (App. C). | Compliant | MADe FTA (24 order-1 cut sets) |
| 3.3.6 | Propulsion Health Monitoring | Per-channel current + vibration-signature health monitoring (PHM). | Compliant | RFLP REQ-REL-006 |
| 3.4.1.1 | Energy Source | Two 4S LiPo packs, 12.0-16.8 V, 1100 mAh each (2200 mAh installed), OR-ed via PWR1 — ≥1500 mAh usable at the system level. | Compliant | RFLP REQ-PWR-001/005; Capital LBOM v3 |
| 3.4.1.2 | Battery Redundancy | Two independent energy sources in a 1-of-2 group, OR-ed via PWR1 — right-sized to 2×1100 mAh so dual redundancy fits under the 0.70 kg cap (dual 1500 mAh → ~0.74 kg violated REQ-REG-001/SYS-006): a traceable reliability↔regulatory trade. | Compliant | MADe RBD; Capital LBOM v3 (QX-BT2) |
| 3.4.1.3 | Regulated Avionics Power | Regulated 5.0 V ±5%, ≥2 A BEC isolated from propulsion transients. | Compliant | RFLP REQ-PWR-003 |
| 3.4.1.4 | Reverse-Polarity and Over-Current Protection | Reverse-polarity + propulsion-bus over-current protection. | Compliant | RFLP REQ-PWR-006 |
| 3.4.1.5 | Battery Management and Thermal Runaway | Cell-level BMS (OV/UV/imbalance) with thermal-runaway containment design. | Compliant (planned) | RFLP REQ-REL-002 (containment planned) |
| 3.4.2.1 | Inertial Sensing | F7 FC, MPU-6000 IMU at 8 kHz, DPS310 baro; 25 Hz closed-loop bandwidth. | Compliant | RFLP REQ-CTRL-001 / PERF-006 |
| 3.4.2.2 | Flight Control Redundancy | Dual-redundant flight control (Rev-2), standby assumes control with no operator action. | Compliant | MADe RBD; Capital LBOM v2 (QX-U1B) |
| 3.4.2.3 | Arming Interlocks | Arm only on link + IMU cal + idle throttle + attitude within 25°. | Compliant | RFLP REQ-CTRL-005 |
| 3.4.3 | Navigation Subsystem | GNSS-aided nav ≤3 m CEP via the integrated GNSS module. | Compliant (planned) | Nav integration plan |
| 3.4.4 | Command and Control (C2) Data Link | 2.4 GHz frequency-agile C2 baseline; FIPS 140-3 encryption added on the production link. | Partial — closure plan | Crypto integration plan |
| 3.4.5 | Payload Data Link | Digital video/metadata downlink, ≤200 ms end-to-end by analysis. | Compliant (planned) | Datalink analysis (planned) |
| 3.4.6 | Lost-Link Behavior | Lost-link >1 s → return-to-home; auto-resume on link restore. | Compliant | RFLP REQ-SYS-007 |
| 3.4.7 | Lighting | Visible arming indicator present; NVIS/covert light to be added per MIL-STD-3009. | Partial — closure plan | RFLP REQ-REG-002 |
| 3.5.1 | Human Engineering | GCS human-engineered to MIL-STD-1472 for a dismounted operator. | Compliant (planned) | HE plan |
| 3.5.2 | Control Station Configuration | Single handheld GCS <1.5 kg, glove-operable. | Compliant | GCS design |
| 3.5.3 | Displays | Sunlight-readable map (MIL-STD-2525) + live video + health. | Compliant (planned) | GCS SW plan |
| 3.5.4 | Single-Operator Operation | Full single-operator plan/launch/employ/recover. | Compliant | CONOPS; design |
| 3.5.5 | Setup and Teardown Time | GCS transport-to-operational in <2 min. | Compliant | Design |
| 3.6.1 | Automatic Takeoff and Landing | Automatic takeoff and precision auto-land. | Compliant (planned) | Autonomy plan |
| 3.6.2 | Waypoint Navigation | ≥20-waypoint routes with loiter/orbit/POI patterns. | Compliant (planned) | Autonomy plan |
| 3.6.3 | Return-to-Home | Commanded/automatic return-to-home and land. | Compliant | RFLP REQ-SYS-007 |
| 3.6.4 | Geofencing | Operator lateral/vertical geofence enforcement. | Compliant (planned) | Autonomy plan |
| 3.6.6 | Contingency Behaviors | Deterministic contingencies: lost-link, low-energy, GNSS-loss, rotor-loss. | Compliant | MADe; RFLP REQ-CTRL |
| 3.7.1 | Flight Data Recording | Flight state / commands / energy / link logged ≥10 Hz for the full sortie. | Compliant | RFLP REQ-CTRL-006 |
| 3.7.2 | Imagery and Metadata Recording | Payload imagery + MISB metadata recorded and exportable. | Compliant (planned) | Payload SW plan |
| 3.7.3 | Built-In Test and Health Data | Initiated + continuous BIT across propulsion/power/FC/nav/links. | Compliant | RFLP REQ-CTRL; PHM |
| 3.8.1 | Operational Availability (Ao) | Ao ≥0.90 by RAM analysis; all 51 verification objects PASS in the native Teamcenter V&V thread. | Compliant | MADe RAM prediction; TC native V&V 51/51 PASS |
| 3.8.2 | Mission Reliability (Rm) | Mission reliability R(10.5 min) = 0.99998 predicted vs 0.9995 required. | Meets Objective | MADe RBD (dual redundancy) |
| 3.8.3 | Loss-of-Thrust Probability | Loss-of-thrust 1.85×10⁻⁴/hr predicted vs 2×10⁻⁴ allocation. | Meets Objective | MADe Fault Tree top event |
| 3.8.4 | Mean Time Between Failures (MTBF) | System MTTF ~4,673 h vs 250 h MTBF allocation. | Meets Objective | MADe RAM (redundant config) |
| 3.8.5 | Mean Time To Repair (MTTR) | Operator-level MTTR <30 min via tool-less LRU replacement. | Compliant | Maintenance concept |
| 3.8.6 | Diagnostics | BIT to 95% detection / 90% isolation with low false-alarm rate. | Compliant (planned) | Diagnostics plan |
| 3.8.7 | Two-Level Maintenance | Two-level maintenance; arms/motors/props/energy/avionics are tool-less LRUs. | Compliant | Maintenance concept |
| 3.8.8 | Turn-Around Time | <5 min turn-around incl. energy-source swap. | Compliant | Design |
| 3.8.9 | Nameplates and Product Marking | MIL-STD-130 identification marking on AV and LRUs. | Compliant | Marking plan |
| 3.9.1 | Natural Climate | -10 to +45 °C operating (Threshold); -20/+49 °C Objective under qualification. | Compliant | RFLP REQ-ENV-001 |
| 3.9.2 | Precipitation and Blowing Particulates | Aeroshell (ENV-002) realizes splash/light-precip protection as-built; full MIL-STD-810 sand/dust/blowing-rain still to be qualified. | Partial — closure plan | RFLP REQ-ENV-002; NX aeroshell (analysis→physical) |
| 3.9.3 | Induced Environment | Soft-mounted avionics isolate propulsion vibration from the IMU. | Compliant | RFLP REQ-ENV-003 / STR-004 |
| 3.9.4 | Electromagnetic Environmental Effects (E3) | MIL-STD-461/464 EMC/E3 qualification. | Compliant (planned) | EMC plan |
| 3.10.1 | Modular Open Systems Approach | Open modular architecture in place; STANAG 4586 UCS interface to be implemented for interoperability. | Partial — closure plan | Open-architecture plan |
| 3.10.2 | Cybersecurity | RMF authorization and FIPS 140-3 crypto delivered on the production configuration. | Partial — closure plan | Cyber/RMF plan |
| 3.10.3 | Supply Chain / Blue UAS | Production BOM built to the DIU Blue UAS / NDAA §848 baseline (dev article uses COTS FPV parts). | Partial — closure plan | Blue UAS BOM plan |
| 3.10.4 | Computing Resources and SWaP-C Margin | ≥25% spare compute/memory/power on the F7 avionics at delivery. | Compliant | SWaP-C budget |
| 3.11.1 | Transportability | Man-portable; carried by a single dismounted operator with combat load. | Compliant | Transport concept |
| 3.11.2 | System Safety | MIL-STD-882E system-safety FMECA complete; risks documented and mitigated. | Compliant | FMECA_MIL-STD-882E_QX250.pdf |
| 3.11.3 | Airworthiness Certification | Airworthiness per MIL-HDBK-516 tailored for light UAS / STANAG 4703. | Compliant (planned) | Airworthiness plan |
| 3.11.4 | Spectrum Supportability | DD-1494 spectrum supportability for the areas of operation. | Compliant (planned) | Spectrum plan |
| 3.11.5 | Frangibility and Ground Safety | Frangible props + 0.65 kg low kinetic energy — low ground-injury probability. | Compliant | MADe; design |