feat: Update create-study skill with Phase 1.3 logging and create UAV arm test study

Phase 1.3.1 Complete - Logging Integration:

1. Updated .claude/skills/create-study.md:
   - Added IMPORTANT section on structured logging from Phase 1.3
   - Documents logger import and initialization
   - Lists all structured logging methods (trial_start, trial_complete, etc.)
   - References drone_gimbal_arm as template

2. Created studies/uav_arm_optimization/:
   - Multi-objective NSGA-II study (50 trials)
   - Same type as drone_gimbal_arm but renamed for UAV context
   - Full integration with Phase 1.3 logging system
   - Configuration: minimize mass + maximize frequency
   - Running to validate complete logging system

Benefits:
- All future studies created via skill will have consistent logging
- Production-ready error handling and file logging from day 1
- Color-coded console output for better monitoring
- Automatic log rotation (50MB, 3 backups)

Related: Phase 1.2 (Configuration), Phase 1.3 (Logger), Phase 1.3.1 (Integration)

🤖 Generated with [Claude Code](https://claude.com/claude-code)

Co-Authored-By: Claude <noreply@anthropic.com>

studies/uav_arm_optimization/NX_FILE_MODIFICATIONS_REQUIRED.md

@@ -0,0 +1,146 @@
+# NX File Modifications Required for Drone Gimbal Arm Study
+
+## Overview
+
+The study uses the same beam model as `simple_beam_optimization` but requires modifications to:
+1. Add modal analysis (frequency extraction)
+2. Update loading conditions for the 850g camera payload
+3. Ensure material properties match Al 7075-T6
+
+## Critical Modifications
+
+### 1. Simulation File (Beam_sim1.sim)
+
+**REQUIRED: Add Modal Analysis Solution**
+
+You need to add a **second solution** for modal analysis:
+
+1. **Open** `Beam_sim1.sim` in NX Simcenter
+2. **Create New Solution**:
+   - Solution Type: `SOL 103 - Normal Modes`
+   - Name: `modal_analysis`
+   - Number of modes: `10` (we only need the first, but calculate more for safety)
+   - Frequency range: `0-500 Hz`
+
+3. **Use Same Mesh** as the static solution
+   - Link to existing FEM file: `Beam_fem1.fem`
+
+4. **Boundary Conditions**: Use same constraints as static analysis
+   - Fixed constraint at base (same as static)
+   - No loads needed for modal (it finds natural frequencies)
+
+### 2. Static Analysis Modifications
+
+**Update Load Magnitude**:
+
+The existing static analysis load needs to represent the **850g camera payload**:
+
+1. **Open Solution 1** (static analysis)
+2. **Modify Force Magnitude**:
+   - Old value: (whatever is currently there)
+   - **New value**: `8.34 N` (850g × 9.81 m/s²)
+   - Direction: Downward (negative Y or Z depending on your coordinate system)
+   - Location: Tip of beam (where camera attaches)
+
+Note: 120 MPa stress limit provides safety factor of 2.3 on 6061-T6 yield strength (276 MPa)
+
+### 3. Material Properties
+
+**Verify Material is Al 6061-T6**:
+
+1. **Open Part File**: `Beam.prt`
+2. **Check Material Assignment**:
+   - Material: `Aluminum 6061-T6`
+   - Yield Strength: ~276 MPa
+   - Young's Modulus: ~68.9 GPa
+   - Density: ~2700 kg/m³
+   - Poisson's Ratio: ~0.33
+
+3. **If not Al 6061-T6**, update material assignment to match drone application requirements
+
+### 4. Results Configuration
+
+**Ensure these results are requested**:
+
+**For Static Solution (Solution 1)**:
+- Displacement (VECTOR, all components)
+- von Mises Stress
+- Mass properties
+
+**For Modal Solution (Solution 2)**:
+- Natural frequencies
+- Mode shapes (optional, for visualization)
+
+## What You DON'T Need to Change
+
+The parametric design variables are already set up correctly in the beam model:
+- `beam_half_core_thickness` (20-30mm)
+- `beam_face_thickness` (1-3mm)
+- `holes_diameter` (180-280mm)
+- `hole_count` (8-14)
+
+These parameters will be automatically updated by the optimization loop.
+
+## Verification Steps
+
+Before running optimization, verify:
+
+1. **Two Solutions Exist**:
+   ```
+   Solution 1: Static Analysis (SOL 101) - displacement and stress
+   Solution 2: Modal Analysis (SOL 103) - natural frequencies
+   ```
+
+2. **Load is Correct**:
+   - Static load = 8.34 N downward at tip
+
+3. **Material is Al 7075-T6**
+
+4. **Both solutions solve successfully** with baseline parameters:
+   ```
+   beam_half_core_thickness = 25mm
+   beam_face_thickness = 2mm
+   holes_diameter = 230mm
+   hole_count = 11
+   ```
+
+## Quick Test
+
+Run a manual solve with baseline parameters to verify:
+
+Expected Results (approximate):
+- **Mass**: ~140-150g
+- **Max Displacement**: ~1-2 mm
+- **Max Stress**: ~80-100 MPa
+- **First Frequency**: ~120-140 Hz
+
+If these are wildly different, check your setup.
+
+## Extraction Configuration
+
+The optimization engine will extract:
+- **Mass**: From Solution 1 mass properties
+- **Displacement**: Maximum displacement magnitude from Solution 1
+- **Stress**: Maximum von Mises stress from Solution 1
+- **Frequency**: First natural frequency (mode 1) from Solution 2
+
+All extraction is automated - you just need to ensure the solutions are configured correctly.
+
+## Optional Enhancements
+
+If you want more realistic results:
+
+1. **Add Gravity Load**:
+   - Apply -9.81 m/s² gravity in addition to tip load
+   - Represents arm's own weight during flight
+
+2. **Add Damping** to modal analysis:
+   - Structural damping ratio: ~0.02 (2%)
+   - More realistic frequency response
+
+3. **Refine Mesh** at stress concentrations:
+   - Around holes
+   - At base constraint
+   - Better stress accuracy
+
+But these are NOT required for the optimization to run successfully.