# Solution Draft (Rev 04) — Launch & Recovery Assessment

## Assessment Findings

| Old Component Solution | Weak Point | New Solution |
|------------------------|------------|-------------|
| No launch/recovery method specified | Aircraft cannot operate without a defined takeoff/landing approach | Two viable options analyzed: Quad VTOL (recommended for field ops) or Catapult + Parachute (recommended for maximum endurance) |
| Y-3 tricopter VTOL (user proposed) | Zero motor redundancy, tilt servo failure risk, no production platforms use Y-3 | Quad (4+1) VTOL — industry standard used by DeltaQuad, YUAV Y37, WingtraOne |
| YUAV Y37 listed as 17-20 kg MTOW | Product page confirms TOW 22-26 kg; 10 kg empty weight with VTOL system | Corrected Y37 specs: TOW 22-26 kg, empty 10 kg (with VTOL), 4+1 config, $16,900 PNP |
| 18 kg MTOW design (Draft 03) | Cannot accommodate VTOL within 18 kg — VTOL system adds 2.5-3.2 kg | Option A: raise MTOW to 21-22 kg for VTOL variant; Option B: keep 18 kg for catapult variant |

## Product Solution Description

Two platform variants from the same S2 FG airframe, optimized for different operational needs:

**Variant A — Quad VTOL** (recommended for forward/mobile operations):
Scaled-up modular S2 FG fixed-wing with 4+1 quadplane VTOL. Wingspan 3.8m, MTOW 21-22 kg. 4 dedicated VTOL motors on carbon fiber tube booms + 1 pusher for cruise. Separate VTOL battery (12S 5500 mAh). Endurance 6.5-7.5 hours. Launches and recovers from any 5m × 5m flat area. No ground equipment needed.

**Variant B — Catapult + Parachute** (recommended for maximum endurance from established bases):
Same S2 FG fixed-wing, no VTOL hardware. Wingspan 3.8m, MTOW 18 kg. Pneumatic catapult launch (ELI PL-60 class). Parachute recovery (Fruity Chutes 20 kg bundle). Endurance 8-8.5 hours. Requires 108 kg catapult system and 8m launch space.

```
VARIANT A — QUAD VTOL (4+1)
┌───────────────────────────────────────────────────────────┐
│                                                           │
│   VTOL Motor 1              VTOL Motor 2                  │
│     (front-left)              (front-right)               │
│     ⟐ 15" prop               ⟐ 15" prop                  │
│      \                        /                           │
│       \     CF tube boom     /                            │
│        \                    /                             │
│    ┌────────────────────────────┐                         │
│    │   LEFT     FUSELAGE   RIGHT│                         │
│    │   WING     [VTOL bat] WING │                         │
│    │   1.9m     [Cruise    1.9m │                         │
│    │            batteries]      │       Pusher motor      │
│    │            [Payload]  ─────┤────── ⊕ (cruise)        │
│    └────────────────────────────┘                         │
│        /                    \                             │
│       /     CF tube boom     \                            │
│      /                        \                           │
│     ⟐ 15" prop               ⟐ 15" prop                  │
│   VTOL Motor 3              VTOL Motor 4                  │
│     (rear-left)               (rear-right)                │
│                                                           │
│   Motor booms: CF tubes (narrow, minimal RF impact)       │
│   Boom-wing joints: aluminum brackets with S2 FG layup    │
└───────────────────────────────────────────────────────────┘

VARIANT B — CATAPULT + PARACHUTE
┌───────────────────────────────────────────────────────────┐
│                                                           │
│    ┌────────────────────────────┐                         │
│    │   LEFT     FUSELAGE   RIGHT│                         │
│    │   WING     [Parachute WING │                         │
│    │   1.9m      bay + hatch]   │       Pusher motor      │
│    │            [Cruise    1.9m │                         │
│    │            batteries]      │       ⊕ (cruise)        │
│    │            [Payload]  ─────┤───────                  │
│    └────────────────────────────┘                         │
│                                                           │
│   No motor booms = cleaner aerodynamics                   │
│   Parachute bay with spring-loaded hatch (top/bottom)     │
│   Catapult carriage mounting rails on belly               │
└───────────────────────────────────────────────────────────┘
```

## Why Not Y-3 (Tricopter)?

The user asked specifically about Y-3 (3-motor) VTOL. After research, Y-3 is **not recommended** for this application:

| Factor | Y-3 (Tricopter) | Quad (4+1) |
|--------|-----------------|------------|
| Weight saving vs quad | ~400g less | Baseline |
| Motor redundancy | **Zero** — any motor failure = crash | Partial — single motor loss survivable |
| Yaw control | Tilt servo on rear motor (mechanical failure point) | Differential thrust (no moving parts) |
| Production platforms using this | None found in 15-25 kg class | DeltaQuad, YUAV Y37, WingtraOne |
| ArduPilot support | Supported but less tested | Well-tested, widely deployed |
| Hover stability | Lower (3-point, asymmetric) | Higher (4-point, symmetric) |

The 400g weight saving (~2% of MTOW) does not justify the reliability and redundancy loss. For a $15,000-17,000 aircraft in a conflict zone, motor redundancy is critical.

## Architecture

### Component: Launch & Recovery System

| Solution | Weight on Aircraft | Ground Equipment | Endurance | Landing Precision | Cost (airborne) | Cost (ground) | Deployment Speed | Fit |
|----------|-------------------|-----------------|-----------|------------------|----------------|---------------|-----------------|-----|
| **Quad VTOL (recommended for field ops)** | +3.0-3.2 kg | None | 6.5-7.5h | 1-2m | $1,000-1,500 | $0 | < 2 min | ✅ Best for mobile ops |
| **Catapult + Parachute (recommended for max endurance)** | +0.95 kg | 108 kg catapult | 7.5-8.2h | 50-200m drift | $925 | $15,000-25,000 | 5-10 min | ✅ Best for endurance |
| Catapult + Belly landing | 0 kg | 108 kg catapult + 200m strip | 8-8.5h | On strip | $0 | $15,000-25,000 | 5-10 min + strip | ⚠️ Needs flat terrain |
| Y-3 VTOL | +2.5-2.7 kg | None | 7-7.5h | 1-2m | $800-1,200 | $0 | < 2 min | ❌ Reliability risk |

### Component: VTOL System (Variant A — Quad)

| Component | Specification | Weight | Cost |
|-----------|--------------|--------|------|
| VTOL motors (×4) | T-Motor MN505-S or equiv., ~5-6 kg thrust each on 15" prop | 880g total | $400-600 |
| VTOL ESCs (×4) | 40A BLHeli_32 or equiv. | 320g total | $120-200 |
| VTOL propellers (×4) | 15" folding (fold for cruise to reduce drag) | 200g total | $60-100 |
| Motor booms (×4) | Carbon fiber tubes 20mm OD, 400mm length + aluminum brackets | 700g total | $150-250 |
| VTOL battery | 12S 5500 mAh LiPo (dedicated) | 700g | $120-180 |
| Wiring + connectors | 12AWG silicone, XT60 connectors | 180g | $30-50 |
| **VTOL system total** | | **2,980g** | **$880-1,380** |

### Component: Catapult System (Variant B)

| Component | Specification | Weight/Size | Cost |
|-----------|--------------|-------------|------|
| Pneumatic catapult | ELI PL-60 or equivalent | 108 kg (2 cases) | $15,000-25,000 est. |
| Catapult carriage | Custom for UAV fuselage, quick-release | ~2 kg (stays on ground) | Included or $500 custom |
| Belly mounting rails | Aluminum rails on fuselage for carriage attachment | ~150g on aircraft | $50 |

### Component: Parachute System (Variant B)

| Component | Specification | Weight | Cost |
|-----------|--------------|--------|------|
| Fruity Chutes FW bundle 20 kg | IFC-120-S Iris Ultra + pilot chute + deployment bag + Y-harness | 950g | $925 |
| Servo-actuated hatch | Spring-loaded door on fuselage top/bottom, triggered by autopilot | 80g | $30 |
| **Recovery system total** | | **1,030g** | **$955** |

## Updated Weight Budgets

### Variant A — Quad VTOL (21 kg MTOW)

| Component | Weight (kg) | Notes |
|-----------|-------------|-------|
| Airframe (S2 FG, 3.8m, reinforced for VTOL loads) | 6.0-7.0 | +0.5 kg structural reinforcement at boom attach points |
| Wing joints (aluminum 7075) | 0.35 | Same as Draft 03 |
| Motor (800W cruise) + ESC + prop | 0.65 | Slightly larger to handle higher MTOW |
| Wiring, connectors (cruise) | 0.45 | Same as Draft 03 |
| **VTOL system** | **2.98** | **4 motors, 4 ESCs, 4 props, booms, VTOL battery, wiring** |
| **Platform subtotal** | **10.4-11.4** | |
| Payload (cameras + compute) | 0.89 | Same as Draft 03 |
| Cruise battery (4× Tattu 6S 33Ah) | 8.86 | Same as Draft 03 |
| **Total** | **20.2-21.2** | |

Conservative: 11.4 + 0.89 + 8.86 = **21.15 kg** (at 21 kg MTOW — tight)
Optimistic: 10.4 + 0.89 + 8.86 = **20.15 kg** (0.85 kg margin)

**To fit 21 kg MTOW**: reduce to 3× cruise battery packs (6.65 kg, 2198 Wh) → total 18.9-19.9 kg → endurance ~5.5-6.5h. Or accept 22 kg MTOW → endurance ~6.5-7h with 4 packs.

### Variant B — Catapult + Parachute (18 kg MTOW)

| Component | Weight (kg) | Notes |
|-----------|-------------|-------|
| Airframe (S2 FG, 3.8m) | 5.5-6.5 | Same as Draft 03 |
| Wing joints (aluminum 7075) | 0.35 | Same |
| Motor (700W cruise) + ESC + prop | 0.6 | Same as Draft 03 |
| Wiring, connectors | 0.45 | Same |
| Catapult belly rails | 0.15 | Aluminum mounting interface |
| Parachute system | 1.03 | Chute + hatch mechanism |
| **Platform subtotal** | **8.1-9.1** | |
| Payload (cameras + compute) | 0.89 | Same |
| Cruise battery (4× Tattu 6S 33Ah) | 8.86 | Same |
| **Total** | **17.9-18.9** | |

Conservative: 9.1 + 0.89 + 8.86 = **18.85 kg** (slightly over 18 kg; accept 19 kg MTOW or trim airframe)
Optimistic: 8.1 + 0.89 + 8.86 = **17.85 kg** (fits within 18 kg ✓)

## Endurance Comparison

### Variant A — Quad VTOL

| MTOW | Battery Config | Usable Energy | Cruise Power | Endurance (practical) |
|------|---------------|--------------|-------------|----------------------|
| 21 kg | 4× 6S 33Ah (2930 Wh) | 2344 Wh | ~310W | **7.0-7.5h** |
| 22 kg | 4× 6S 33Ah (2930 Wh) | 2344 Wh | ~330W | **6.5-7.0h** |
| 20 kg | 3× 6S 33Ah (2198 Wh) | 1758 Wh | ~295W | **5.5-6.0h** |

Cruise power increase vs Draft 03: higher MTOW (21-22 vs 18 kg) + ~3-5% additional drag from VTOL booms.

P_cruise (21 kg) = (21 × 9.81 × 17) / (17 × 0.72) × 1.04 = ~310W (including boom drag penalty)

### Variant B — Catapult + Parachute

| MTOW | Battery Config | Usable Energy | Cruise Power | Endurance (practical) |
|------|---------------|--------------|-------------|----------------------|
| 18 kg | 4× 6S 33Ah (2930 Wh) | 2344 Wh | ~275W | **8.0-8.5h** |
| 19 kg | 4× 6S 33Ah (2930 Wh) | 2344 Wh | ~285W | **7.5-8.0h** |

Parachute adds ~1 kg but no aerodynamic penalty (stowed internally).

### Summary

| Variant | MTOW | Endurance | vs Draft 03 (8-8.5h) |
|---------|------|-----------|---------------------|
| A: Quad VTOL (4 packs) | 21-22 kg | **6.5-7.5h** | -12-20% |
| A: Quad VTOL (3 packs) | 20 kg | **5.5-6.0h** | -30-35% |
| B: Catapult + Parachute | 18-19 kg | **7.5-8.5h** | -0-6% |
| B: Catapult + Belly | 18 kg | **8-8.5h** | 0% |

## Cross-Validation Against YUAV Y37

The Y37 is the closest production reference for our VTOL variant:

| Parameter | YUAV Y37 | Our Variant A (Quad VTOL) | Delta |
|-----------|----------|--------------------------|-------|
| Wingspan | 3.7m | 3.8m | +3% |
| Empty weight (with VTOL) | 10 kg | 10.4-11.4 kg | +4-14% (S2 FG heavier than carbon) |
| MTOW | 22-26 kg | 21-22 kg | Similar |
| Battery energy | 2700 Wh | 2930 Wh | +9% |
| Endurance (1 kg payload) | 8.5h | ~7h (est. at 0.89 kg payload) | -18% (S2 FG weight penalty) |
| Material | Full carbon | S2 FG + CF spar | S2 FG is ~2-3 kg heavier |
| RF transparent | No | Yes | Our advantage |
| Price (PNP) | $16,900 | ~$11,000-14,000 (DIY) | 18-35% cheaper |

The 18% endurance gap between Y37 and our Variant A is primarily due to the S2 FG weight penalty (~2-3 kg heavier airframe). If RF transparency is not required, a carbon airframe would close this gap.

## BOM Cost Impact (5 UAVs)

### Variant A — Quad VTOL

| Category | Total (5 UAVs) | Per UAV | vs Draft 03 |
|----------|----------------|---------|-------------|
| Draft 03 baseline | $77,481 | $15,496 | — |
| VTOL system hardware | $5,000-7,000 | $1,000-1,400 | +$1,000-1,400/unit |
| Structural reinforcement | $750 | $150 | +$150/unit |
| Larger cruise motor/ESC | $250 | $50 | +$50/unit |
| **Variant A total** | **$83,481-85,481** | **$16,696-17,096** | **+$1,200-1,600/unit** |

### Variant B — Catapult + Parachute

| Category | Total (5 UAVs) | Per UAV | vs Draft 03 |
|----------|----------------|---------|-------------|
| Draft 03 baseline | $77,481 | $15,496 | — |
| Parachute systems (×5) | $4,775 | $955 | +$955/unit |
| Catapult (ELI PL-60, ×1) | $15,000-25,000 | $3,000-5,000 (amortized) | +$3,000-5,000/unit |
| Belly rails + hatch mech. | $500 | $100 | +$100/unit |
| **Variant B total** | **$97,756-107,756** | **$19,551-21,551** | **+$4,055-6,055/unit** |

**Key insight**: VTOL is cheaper per fleet. The catapult is expensive one-time equipment that only amortizes well over large fleets (20+ UAVs).

## Recommendation Matrix

| Operational Scenario | Recommended Variant | Rationale |
|---------------------|--------------------|-----------| 
| **Mobile forward operations** (changing locations, no established base) | **A: Quad VTOL** | No ground equipment, instant deploy from any flat area, precision recovery |
| **Fixed base operations** (airfield or prepared area available) | **B: Catapult + Parachute** | Maximum endurance, no VTOL dead weight, lower per-unit complexity |
| **Mixed operations** (both scenarios) | **A: Quad VTOL** | VTOL works everywhere; endurance trade-off (6.5-7.5h vs 8h) is acceptable for operational flexibility |
| **Maximum endurance priority** (>8h critical) | **B: Catapult + Belly** | Zero weight penalty; but needs 200m landing strip |
| **Budget-constrained fleet** (5 units) | **A: Quad VTOL** | $83-85k total vs $98-108k for catapult variant |

## Risk Assessment (New Items for Draft 04)

| Risk | Impact | Probability | Mitigation |
|------|--------|------------|-----------|
| VTOL motor failure during hover landing | Aircraft loss ($17k) | Low | Quad config allows single-motor-out survival; redundant ESC power feeds |
| VTOL boom attachment failure on S2 FG | Boom separation → crash | Low | Aluminum through-bolt brackets; static load test to 5× hover thrust |
| Catapult malfunction | No launch capability | Low | Carry spare seals and Makita batteries; ELI PL-60 is simple design |
| Parachute deployment failure | Aircraft loss + ground damage | Very Low | Dual deployment triggers (autopilot + RC manual); pre-flight chute check |
| Wind drift on parachute recovery | UAV lands in inaccessible area | Medium | Select recovery area with margin; GPS tracking; contingency recovery team |
| VTOL adds drag → endurance less than calculated | Endurance only 6h instead of 7h | Medium | Folding VTOL props reduce cruise drag; boom fairing; accept margin |
| S2 FG structure insufficient for 21-22 kg VTOL loads | Structural failure | Low | Full FEA analysis; static wing load test at 3.5g; boom attachment cycling test |

## Testing Strategy (Additions for Draft 04)

### VTOL-Specific Tests (Variant A)
- Hover stability test: 60-second hover at 21 kg, measure motor temps and vibration
- Transition test: full transition from hover to cruise and back, measure altitude loss and energy
- Single-motor-out test: kill one VTOL motor at 30m altitude, verify safe emergency landing
- Boom attachment cycling: 200× VTOL power-on/off cycles, inspect boom joints for fatigue
- VTOL battery endurance: verify 2+ full VTOL cycles (takeoff + landing) on single charge
- Drag measurement: compare cruise power with VTOL booms vs clean airframe

### Catapult-Specific Tests (Variant B)
- Catapult launch: 10 consecutive launches, verify consistent exit speed and UAV integrity
- Launch acceleration: measure g-forces on airframe and payload during catapult stroke
- Parachute deployment: 5 test deployments at various speeds and altitudes (min 50m AGL)
- Parachute reliability: 20 pack-deploy cycles, verify consistent opening
- Landing impact: verify payload cameras survive 4.6 m/s descent impact

## References

1-57: See Draft 03 references (all still applicable)

Additional sources:
58. YUAV Y37 product page (updated specs): https://www.airmobi.com/product/yuav-y37-3700mm-vtol-fixed-wing-uav-pnp/
59. YUAV Y37 engineering blog: https://www.airmobi.com/yuav-y37-a-new-standard-in-long-endurance-vtol-fixed-wing-uavs/
60. DeltaQuad Evo TAC specs: https://docs.deltaquad.com/tac/vehicle-specifications
61. DeltaQuad Evo VTOL takeoff: https://docs.deltaquad.com/tac/flight/quick-takeoff/vtol-takeoff
62. ELI PL-60 pneumatic catapult: https://eli.ee/products/catapults/pl60/
63. Fruity Chutes FW bundle 20 kg: https://shop.fruitychutes.com/products/fixed-wing-recovery-bundle-44lbs-20kg-15fps
64. Robonic pneumatic launcher advantages: https://www.robonic.fi/advantages-of-pneumatic-launch/
65. Starlino power-to-thrust analysis: http://www.starlino.com/power2thrust.html
66. T-Motor U13II specs: https://store.tmotor.com/product/U13-v2-KV130-Power-Type-UAV-Motor.html
67. Belly landing research: https://www.scientific.net/AMM.842.178
68. Aeromao Talon belly landing: https://aeromao.com/2018/10/18/talon-fully-autonomous-belly-landing/
69. SCL bungee launcher specs: https://uascomponents.com/launch-and-landing-systems/bungee-catapult-scl2
70. UkrSpecSystems SCL-1A: https://ukrspecsystems.com/uascomponents/bungee-uav-launching-system-scl-1a
71. VTOL weight penalty research: https://hal.science/hal-03832115v1/document
72. VTOL configuration endurance comparison: https://mediatum.ub.tum.de/1462822

## Related Artifacts
- Previous drafts: `solution_draft01.md` through `solution_draft03.md`
- Research artifacts: `_standalone/UAV_frame_material/00_research/UAV_frame_material/`
