# Prototype v0 — technical specification (DLE-170 baseline)

**Programme:** AEROSCOPE ISR  
**Configuration:** ASR-V0-B-DLE170  
**Status:** Engineering release for factory build — pre-type-certificate  
**Engine baseline:** DLE-170 (Class B), alternatives DA-150 / 3W-170i for bench gate only

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## 1. Purpose

Demonstrate **Profile A** corridor mission (300 km round-trip planning) and **Profile B** area surveillance (transit + 2 h loiter) with traceable acceptance logs for commercial sale of **P2 Border** SKU.

## 2. Design targets (v0)

| Parameter | Target | Verification method |
|-----------|--------|---------------------|
| MTOW | 42 kg (nominal) | Weighing before each flight |
| Payload | 5 kg EO (fixed or light gimbal) | Mass balance sheet |
| Wingspan | 3.6 m | Drawing ASR-V0-GA |
| Cruise speed | 95–110 km/h | GPS + pitot, flight test card |
| Endurance | ≥ 5 h @ cruise, 5 kg payload | Fuel burn log + Hobbs |
| Operational radius | ≥ 280 km demonstrated (no wind) | Sortie log, RTL at 30% fuel |
| Service ceiling | 3000 m density altitude | Incremental envelope step |
| Engine | DLE-170, 2-blade carbon prop | Bench SFC, CHT/EGT limits |

## 3. Airframe

- Configuration: high-aspect-ratio fixed wing, conventional tail.
- Structure: carbon/epoxy wing skins, foam core; fuselage composite + plywood bulkheads.
- Landing: belly skid + optional field runway; catapult interface TBD v0.2.
- Fuel: 18–22 L baffled tank, 30% reserve warning in GCS.

## 4. Propulsion (DLE-170)

- Bench run-in: 10 h on stand; record SFC, vibration spectrum, max continuous RPM.
- Limits: CHT max per OEM; abort if vibration > baseline + 20%.
- EFI upgrade: Phase v0.3 optional (ArduPilot ICE/EFI path).

## 5. Avionics (Phase 1)

- FC: ArduPilot-compatible (Cube Orange class or equivalent).
- Sensors: dual GNSS where budget allows, pitot-static, baro, RPM, fuel flow, CHT.
- GCS: Mission Planner / QGC + AEROSCOPE HQ ingest (MAVLink).
- Geofence + RTL + engine failsafe: mandatory before beyond-line-of-sight tests.

## 6. Payload (v0)

- Minimum: 1080p EO fixed forward, 3-axis isolation pad.
- Optional v0 flight: lightweight EO gimbal ≤ 2.5 kg.
- Video: H.265 encoder, adaptive bitrate; separate C2 vs video radio.

## 7. Communication

- Primary: long-range LOS digital link (buyer band plan).
- Relay: optional LTE or Starlink on **GCS only**.
- Acceptance: telemetry continuity ≥ 98% on 50 km loop test.

## 8. Flight test programme (minimum)

1. **T0** — Ground checks, control surface throw, engine start matrix.  
2. **T1** — 5 sorties, pattern work, stall approach to 2 m AGL.  
3. **T2** — 60 min endurance, repeated takeoff/land.  
4. **T3** — 120 min with payload, fuel curve validation.  
5. **T4** — 280+ km round trip, full telemetry archive.  
6. **T5** — Night / IR package (if P2 sensor fitted).

## 9. Deliverables

- Sortie logs (`.tlog` / MAVLink export).
- Bench report (DLE-170).
- Configuration baseline ASR-V0-BOM-001.
- Acceptance checklist signed for P2 gate.

## 10. Schedule (indicative)

| Week | Milestone |
|------|-----------|
| 1–2 | OML freeze, wing/fuselage mould |
| 3–4 | Bench ICE, avionics integration |
| 5–6 | T0–T2 flights |
| 7–10 | T3–T4, documentation |
| 11–12 | Buyer demo / P2 contract gate |

## 11. Budget envelope (prototype only)

| Item | USD (planning) |
|------|---------------:|
| Airframe materials + labour | 28,000 |
| DLE-170 + prop + fuel system | 6,500 |
| Avionics + radios | 12,000 |
| EO payload (v0) | 8,000 |
| GCS bench | 15,000 |
| Test range + logistics | 10,000 |
| **Total v0** | **~79,500** |

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Commercial contact: ventusmeridian@proton.me  
Configurator: https://ventusmeridian.duckdns.org/configurator.html