We’re an early-stage humanitarian logistics project based in Goma, DRC, developing a drone system for the Goma-Masisi corridor (50-60 km one-way). The operational environment has no runways, unreliable roads, and a pressing need to deliver medical supplies.
Our validated Phase 2 technical requirements are:
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Payload: 10kg nominal, 5-20kg range
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One-way range: 60 km minimum
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Takeoff/Landing: VTOL mandatory (no runways)
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Environment: 1,500m altitude, mountain winds, dust, humidity, no reliable power infrastructure
Our Two-Phase Architecture:
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Phase 1: Heavy-lift hexacopter (2-5kg payload, 10-15km range) as a technology demonstrator.
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Phase 2: Production hybrid VTOL (fixed-wing forward flight, multirotor vertical lift) for the full 60km route.
We have a detailed 2-page technical snapshot covering mission requirements, architecture selection & risks, economics-driven specs, and the two-track build plan. The full document is available on request.
Our most pressing validation questions:
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We know a hexacopter cannot do 60km with 10kg. But what is the practical maximum range for a 10kg‑capable hexacopter at 1,500m altitude, assuming conservative battery use? (This helps us set realistic demo goals.)
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What is the single biggest system risk we are underestimating: VTOL transition stability, power & endurance at altitude, or flight control reliability in dusty/mountainous conditions?
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Does our “no field charging, all batteries cycled at a central base” strategy hold up for the production aircraft, or will we be forced to field-charge in a low‑infrastructure environment?
Additional context:
- I’ve received helpful feedback on Discord regarding motor redundancy and VTOL emergency landing constraints. Now I’d like the community’s perspective on these three specific questions.
Any quick feedback on these core assumptions would be invaluable before we launch our zero-capital build phase.
Thank you.