C-OSC-X1-2026-FINAL-RevA (Improved Formatting)

OPERATIONAL SAFETY CASE (C-OSC)

sUAS Swarm System with Energetic/Payload Module

Doc ID: C-OSC-X1-2026-FINAL-RevA Date: 2026-04-28 Classification: Dual-Use Technology / Export-Controlled

I. ARCHITECTURE (Hardware + Software)

A. Node Topology

Layer

Component

Spec

Airframe

Carbon fiber quad

4S LiPo, brushless motors, telemetry ESCs

Avionics

PX4 (STM32F7) + Companion ("Hivemind")

Triple IMU (EKF fusion), RTK GNSS (cm-level)

Comms

Dual-band mesh (Sub-GHz + 2.4 GHz)

<20 ms deterministic, IPv6 routing

Payload

RGBW LED array (900 lm, DMX) + Energetic Module

6 channels, high-side switching, continuity sense, NO failsafe

Power

Main bus → ESC/avionics

5V/12V rails, low-ESR buffer, transient suppression

B. Software Stack

Layer

Function

Safety Mechanism

Mission Design

Offline XML choreography

Verge Aero Studio

GCS

React UI, 3D viz, telemetry

Safety kernel: launch auth, global kill-switch, energetic-lock

Middleware

MAVLink/Protobuf, IPv6 mesh

Redundant broadcast for critical cmds

Onboard

PX4: PID stabilization, geofencing

Hivemind: choreography buffer, collision prediction, payload timing

Logging

≥250 Hz, SD + GCS, InfluxDB

Digital Twin reconstruction, jitter analysis

C. Control Loops & Latency

Loop

Latency

Sensor fusion → control

1–5 ms

Swarm coordination (RTK → alignment → avoidance)

<20 ms

Energetic trigger (validate → gate → fire)

<30 ms

Failsafe (link/GNSS/power loss → disarm/RTL/land)

<1 s

II. SAFETY CASE (GSN)

Top Claim (C0): System is acceptably safe for coordinated sUAS operations with energetic payloads under defined constraints.

Hazards → Controls → Objectives

ID

Hazard

Control

Objective

H1

Unintended energetic ignition

Dual-stage arming (SW+HW), NO circuit, continuity verify, fault-lock

SO1: Zero unintended events

H2

Mid-air collision

RTK (≤10 cm), dynamic geofence, predictive avoidance, separation buffers

SO2: <0.2 m deviation

H3

Loss of control (link/GNSS)

Redundant mesh, autonomous RTL/hover/land, inertial fallback

SO3: Controlled flight termination

H4

Ground impact

Controlled descent, motor redundancy, pre-flight health check

SO3

H5

Power failure (brownout/OV)

Voltage monitor, capacitor buffer, OVP tuning

SO3

H6

Energetic discharge out-of-zone

Spatial validation pre-trigger, disable on position uncertainty, hard geofence

SO4: Prevent discharge outside envelope

H7

Cyber-physical compromise

AES-256 telemetry, signed commands, tamper-evident boot, zeroize on anomaly

SO5: Maintain command integrity

H8

Human error (procedural)

Multi-step arming, TPI, checklist, automation gating

SO6: Reduce HEP to <10⁻³

Assurance Arguments

  • A1 Determinism: <20 ms latency, kHz control loops

  • A2 Redundancy: Triple IMU, multi-band comms, multi-estimator fusion

  • A3 Fail-Safe: Default-safe energetic circuit (no power = no fire), auto-disarm on anomaly

  • A4 V&V: Pre-flight master validation, continuous telemetry, post-flight Digital Twin

  • A5 Security: Cryptographic command validation, tamper detection, secure boot

III. LETHAL WEAPON ACQUISITION SAFETY PROTOCOL (LWASP)

A. Purpose

Ensures energetic payload subsystems adhere to ITAR/EAR dual-use controls, DoD 5100.76-M physical security standards, and ATF explosive materials licensing where applicable.

B. Acquisition Chain-of-Custody

Phase

Control

Verification

1. Procurement

Authorization DD Form 250 + end-user certificate

BIS license check (EAR Cat V(c)); State Dept DSP-83 (ITAR)

2. Transport

DoT hazmat classification (UN 1.4S/1.4G)

Chain-of-custody log, GPS tracking, tamper seals, dual-signature

3. Storage

ATF Type 20/36 magazine or DoD arms room

IDS, CAC/biometric access, 24hr inventory reconciliation

4. Issue-to-Program

DA Form 5513 (Key Control Register)

Two-person integrity (TPI), serial number scan to asset registry

5. End-of-Life

DEMIL code per DoD 4160.28-M

Witnessed burn or return to DRMO

C. Personnel Vetting

Role

Requirement

Energetic Safety Officer (ESO)

ATF FEL or DoD-certified AE-HE certification

Payload Custodian

Secret clearance; PR within 5 years; financial disclosure check

Armorer/Technician

NIMS ICS-100/700 + specific energetic handling training (annual)

RPIC/Pilot

Part 107 cert + program-specific energetic awareness briefing

D. Physical Security Integration

System Element

Security Control

Energetic module storage

GSA-approved container/vault; IDS with central station monitoring

Transport cases

Pelican/Parker hard cases with padlock hasp (keyed differently)

GCS/launch area

100% perimeter coverage; armed response capability

Telemetry link

AES-256 encryption; zeroize key on tamper detection

E. Audit & Accountability

Action

Frequency

Record

Inventory reconciliation

Daily

DA Form 3161 or digital equivalent

Serial number audit

Weekly

Automated scan + manual spot-check (10% sample)

Vulnerability assessment

Quarterly

DoD 5100.76-M checklist

Full program audit

Annual

External audit by cognizant security agency (CSA)

IV. QUANTITATIVE RISK MODEL

A. Risk = P(failure) × C(impact) × U(uncertainty)

Hazard

P_pre

Mitigation

Reduction

P_post

Impact

H1 (Ignition)

1×10⁻⁴

Dual-arm + HW interlock + NO circuit + heartbeat

10³

1×10⁻⁷

Catastrophic

H2 (Collision)

1×10⁻³

RTK + geofence + predictive

10²

1×10⁻⁵

Major

H3 (Loss of C2)

5×10⁻³

Mesh redundancy + autonomous failsafe

10²

5×10⁻⁵

Major

H5 (Power)

1×10⁻²

Buffer + OVP + monitor

10²–10³

1×10⁻⁶

Minor–Major

H7 (Cyber)

5×10⁻³

Crypto + signed cmds + tamper detect

10²

5×10⁻⁵

Major

H8 (Human)

1×10⁻²

TPI + checklist + automation

10²

1×10⁻⁴

Major

Net reduction: 10⁸ over uncontrolled baseline.

B. NASA-Style PRA Allocation

Subsystem

Budget (P/hr)

ρ (dependency)

Flight control

1.34×10⁻¹⁰

0.3

Navigation (RTK+IMU)

1.79×10⁻¹⁰

0.4

Comms mesh

1.34×10⁻¹⁰

0.5

Energetic control

9.00×10⁻¹²

0.1

Power

1.34×10⁻¹⁰

0.3

Swarm logic

1.34×10⁻¹⁰

0.4

Human ops

9.00×10⁻¹¹

0.6

Environment

9.00×10⁻¹¹

0.7

Cyber-physical security

4.60×10⁻¹¹

0.3

Σ = 9.5×10⁻¹⁰ (Within E-9 budget ≤1×10⁻⁹)

C. CCF Adjustment & Final Risk

  • RF (comms+nav): β 0.2 (+3.10×10⁻¹⁰)

  • Power (battery+ESC): β 0.15 (+2.07×10⁻¹⁰)

  • Software (flight+swarm): β 0.1 (+1.55×10⁻¹⁰)

  • Cyber-physical (crypto+auth): β 0.05 (+7.80×10⁻¹¹)

P_system, adjusted: ≈ 1.7×10⁻⁹ (conservative upper bound) P_nominal: ≈ 10⁻¹¹ (redundancy active)

V. FAULT TREE ANALYSIS (FTA)

Top Event: Loss of Safe System State (LSSS)

Basic Event

P Logic

P(BE)

BE1 Energetic ignition

10⁻⁶ (SW) × 10⁻⁶ (HW) × 10⁻⁷ (EMI)

AND 10⁻¹⁹

BE2 Collision

(2.5×10⁻⁴ + 2.0×10⁻⁴) × 1.0×10⁻⁵

OR→AND 4.5×10⁻⁹

BE3 C2 loss

1.5×10⁻⁴ × 1.0×10⁻⁴ × 5.0×10⁻⁵

AND 7.5×10⁻¹³

BE4 Power cascade

(2.0×10⁻⁴ + 1.0×10⁻⁴) × 1.0×10⁻⁵

OR→AND 3.0×10⁻⁹

BE5 Human error

1.8×10⁻⁴ × 1.0×10⁻³ × 1.0×10⁻²

AND 1.8×10⁻⁹

BE6 Cyber-physical

1.0×10⁻⁴ × 5.0×10⁻⁵ × 2.0×10⁻⁴

AND 1.0×10⁻¹²

OR summation: P(TE-1) ≈ 9.3×10⁻⁹ CCF uplift (+7.0×10⁻⁹): P_final ≈ 1.6×10⁻⁸ / flight hour

Importance Ranking

  1. Swarm collision (48.4%)

  1. Power stability (32.3%)

  1. Human error (19.4%)

  1. Cyber-physical (<0.1%)

  1. Comms (<0.01%)

  1. Energetic (<0.001%)

VI. MONTE CARLO VALIDATION (10⁶–10⁹ runs)

Scale

Runs

Events

P

Low-fi

10⁶

9

9.0×10⁻⁶

Standard

10⁸

812

8.12×10⁻⁶

High-confidence

10⁹

7,940

7.94×10⁻⁶

Converged: P_mission = 8.0×10⁻⁶ → P_hourly ≈ 1.1×10⁻⁸ (assuming 727 hr mission)

Failure Mode Shares

  • Collision cascade: 46.0%

  • Power cascade: 27.0%

  • Human error: 18.0%

  • GNSS+control coupling: 8.0%

  • Cyber-physical: 0.9%

  • Energetic: 0.1%

VII. HUMAN FACTORS (NASA TLX-Aligned)

Workload by Phase