UAV SILM emblem UAV SILM
Self-built ISR fixed-wing concept

UAV SILM

Strategic Intelligence and Land Monitoring

A fixed-wing, pusher-type reconnaissance aircraft concept built around a low cost and a minimal field footprint. It's light enough to hand-launch, lands on its belly, and needs no runway or launch equipment.

Concept & development stage — unflown
UAV SILM CAD render, top view
1.4 m
wingspan
≈1.58 kg
all-up mass (calc.)
~100 min
target endurance
<$500
target unit cost

A cheap, repeatable ISR concept for small states

UAV SILM is a self-built fixed-wing reconnaissance UAV concept: a 1.4 m wingspan, roughly 1.6 kg pusher-type aircraft designed for ISR (Intelligence, Surveillance, Reconnaissance) use, built for long-endurance observation on a low budget and a minimal logistics footprint. It's light enough to hand-launch and lands on its belly, with no runway or launch equipment needed.

Current professional reconnaissance UAV platforms are expensive, often subject to export or trade restrictions, and hard to produce or adapt quickly in the field. Small states and civil-defence organisations lack affordable, quickly-built, easily-maintained reconnaissance platforms that can be built and repeated locally.

The target group is Estonia's defence and security sector: the Defence Forces, Kaitseliit, and the Police and Border Guard Board, plus more broadly European defence development programmes. No engagement with these organisations has taken place yet; this is the intended long-term audience for the concept. It matters because:

  • a low-cost, domestically-built airframe (target unit cost under $500) could put the platform within reach of organisations without a professional-system budget;
  • long calculated endurance (~100 min target flight time) would enable genuine observation and reconnaissance work;
  • a secure link concept (4G LTE / WireGuard MAVLink failsafe) is designed to keep data protected and the link operational even under GPS interference.
  • Most hobby-grade fixed-wing UAVs aren't optimised for ISR use. SILM's endurance target, airfoil selection and airframe design come from CFD analysis aimed specifically at that purpose.
  • It's designed to pair open-source flight control (ArduPilot-compatible) with an encrypted 4G/WireGuard backup link, an unusual combination for a student-scale build.
  • The whole design process (XFLR5 CFD analysis, centre-of-gravity calculations, materials selection) is documented and repeatable, which is the point: a base that can be extended, corrected, or used for training.

Swap the parts, not the airframe

The airframe is designed around modular components rather than a single fixed configuration, so the same base platform could be reconfigured for different missions.

A

Modular design

Swappable wings + nose cone
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  • Can swap for cheaper, higher aspect-ratio wings to complete lower-paced missions or deliver explosive payloads
  • Modular screw-on nose cone can carry either an explosive or an ISR payload
  • Centre of gravity can be adjusted easily by changing which modules are fitted
B

Versatile

One airframe, several roles
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  • 3D-printable airframe
  • Affordable — target unit cost under $500
  • Suited to military use, but equally to agricultural, urban, or forestry-related topographic survey work
  • Lightweight and launchable by hand

What the design is calculated to do

Every number below comes from XFLR5 vortex-lattice analysis (VLM1/VLM2) and hand calculation over the current geometry, not from a flight test. Treat it as a design target, not a spec sheet.

Performance

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  • Endurance target: ~100 min
  • Cruise L/D: low-to-mid 20s
  • Stall speed: ~9–10 m/s (calc.)

Stability

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  • Static margin: ~18.5% MAC
  • Positive Cm slope (stable)
  • V-tail lever arm: ~0.41 m

Autonomy & link

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  • ArduPilot-compatible autopilot
  • Mission trajectory planned on a map, flown as GPS waypoints
  • 4G LTE / WireGuard failsafe concept
Wingspan1.40 m
Wing area0.263 m²
Root / tip chord0.250 / 0.125 m
Taper ratio0.50
Aspect ratio7.46
MAC0.195 m
Wing dihedral
V-tail dihedral~30°
Wing loading~6.0 kg/m²
Cruise CL (3° AoA)~0.51
Airfoil: MH32, chosen over SD7037 and RG15 in XFLR5 comparison. See the analysis below.
Centre of gravity (X_CG)0.335 m from nose
Neutral point (X_NP)0.371–0.374 m
Static margin18.5%
All-up mass (calc.)1.58–1.60 kg
Aileron Cl (±10° / ±15°)~0.077 / ~0.115
Ruddervator Cm (10°)~0.150
V-tail incidence−4°
All values from XFLR5 VLM1/VLM2 analysis at 20–22 m/s, September 2026 model.

Long-shaft fixed-wing pusher motor on a 4S LiPo pack, sized against the 1.6 kg all-up mass with margin for material or battery changes. Full component models are listed under Tools & materials below.

ArduPilot-compatible autopilot with GPS and digital airspeed sensing, capable of autonomous waypoint flight. Mission routes are planned on a map in ground-control software (e.g. Mission Planner or QGroundControl) and uploaded to the autopilot before launch, so the aircraft can fly a pre-set trajectory without continuous manual control. A 4G LTE module paired with an encrypted WireGuard link is planned as a MAVLink failsafe channel, intended to keep telemetry and control available under GPS interference or beyond normal radio-link range. The concept is borrowed from professional encrypted-link systems, adapted here to commodity hardware.

The nose cone is designed to screw on and off, so the same airframe can carry an ISR sensor payload or be reconfigured, without redesigning the fuselage. Swapping the wing set for a cheaper, higher-aspect-ratio pair is intended to trade cruise performance for lower-cost, lower-tempo missions. Because the modules attach at fixed stations, moving the centre of gravity is mostly a matter of choosing which modules are fitted.

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lift / drag polar — XFLR5
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CFD pressure / streamline visualisation
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3D wing & fuselage CAD render
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centre-of-gravity & inertia diagram

Engineering-led, supported by five other fields

In focus

Engineering (aeronautical / aerodynamics) and technology (electronics, software).

Physics

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Aerodynamics: lift and drag calculations in XFLR5, centre-of-gravity and balance, flight dynamics.

Mathematics

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CG location calculations, wing and tail surface dimensions, static margin and load-factor calculations.

Materials science

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LW-PLA for 3D-printed parts, epoxy resin for sealing, carbon-fibre spar.

IT

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Flight control software (ArduPilot), encrypted link (WireGuard on a companion computer), GPS/telemetry.

Civics / defence

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Application context: Estonian and European defence capability, dual-use technology ethics and regulation.

Project management

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Task tracking, budgeting, procurement, and coordinating three people's work across a shared design.

Team and responsibilities

Hover or tap a card for what each person is actually working on.

01
Romet Salvador Lehari
also Romet Lehari, Romet Salvador
Project management & flight dynamics
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  • Full-aircraft XFLR5 CFD (wing, fuselage, complete model)
  • V-tail dimensioning and incidence/twist study
  • Wing structural analysis & rib design
02
Ludvig Janisk
3D modelling & research
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  • Nose cone camera compartment & mounting thread
  • Propeller research (10" diameter confirmed)
  • Ruddervator modelling & sectioning
03
Karl-Robin Koppel
Electronics
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  • Flight-controller programming research
  • Datalink research
  • Component confirmation & internal layout

"Fixed-Wing UAV Design: A Systems Engineering Approach" (ResearchGate)

Took — a systems-level approach to the design process: helped order the design stages (aerodynamics → structure → electronics → testing).

ScienceDirect article on fixed-wing UAVs

Took — background on aerodynamic approaches and airfoil selection.

"Development of a Hand-Launched Small UAV for Ground Reconnaissance" (ResearchGate)

Took — hand-launched small reconnaissance UAV design principles, a direct model for SILM's launch method.

UAS Components (uascomponents.com)

Took — a sourcing reference for components and specs for comparison.

IRE Journal (irejournals.com)

Took — background research on UAV technology applications.

Professional encrypted flight-controller literature (AES-256 link systems)

Took — the idea of adding an encrypted, secure failsafe link; adapted here into a cheaper 4G LTE + WireGuard concept.

GitHub project "Drone-Based Reconnaissance of Military Assets"

Took — an example of a similarly-aimed open-source project, for comparing software/data-handling approaches.

Claude (Anthropic)

Used — assisted in organising the website's content and writing the HTML/CSS/JS for this page.

Construction and electronics

Construction

MaterialUse
LW-PLA (lightweight PLA)3D-printed airframe and structure
Carbon-fibre tube (spar)Wing load-bearing structure
Epoxy resinSealing

Electronics — from the team's shopping list

ComponentModel
Flight controllerMatek H743-WING V3
ESCHobbywing Skywalker 60A V2
GPS / compassMatek M10Q-5883
Airspeed sensorMatek ASPD-4525 + pitot tube
4G link moduleWaveshare SIM7600E-H HAT
CameraSiyi A2 Mini (160° FPV gimbal, 1080p)
BatteryGens Ace G-Tech 7000mAh 4S 60C, XT90
MotorT-Motor AT2321 (1250KV, long shaft)

This table lists only components confirmed in the team's shopping-links document; servos, radio link, and companion-computer hardware are still being finalised.

Flight log

Ground and flight testing haven't started yet — this table fills in as tests happen.

Flight #DateDurationNotes
01PendingGround systems check
02PendingFirst hand-launch, straight flight
03PendingEndurance & range validation
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launch / flight test photo
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telemetry / ground-station screenshot

Five stages, design to presentation

Target dates below, working back from the presentation on 8 December 2026.

01
Done / in progressthrough 5 Oct 2026

Design & analysis

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  • Airfoil selection and CFD analysis in XFLR5
  • Full-aircraft geometry, mass and CG modelling
  • Control-surface (aileron, ruddervator) evaluation
02
Next6–19 Oct 2026

Procurement & components

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  • Ordering electronics components
  • Sourcing structural materials
03
Ahead20 Oct – 9 Nov 2026

Build

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  • 3D printing the airframe and wing
  • Electronics installation and wiring
  • Setting up the link / failsafe concept (4G/WireGuard)
04
Ahead10–27 Nov 2026

Testing

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  • Ground tests (electronics, link)
  • First flight tests (hand-launch, belly landing)
  • Endurance and range validation
05
Ahead28 Nov – 8 Dec 2026

Presentation & documentation

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  • Results summary
  • Finalising the project page and presentation
  • Presentation day: 8 December 2026

What's done, what's next

Done so far
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  • CFD analysis completed in XFLR5 (VLM1/VLM2); MH32 airfoil selected over RG15 and SD7037
  • Full-aircraft geometry finalised: 1.40 m span, 0.263 m² area, AR 7.46, high-wing / V-tail layout
  • Mass and CG modelling complete — X_CG 0.335 m, static margin 18.5% at ≈1.58–1.60 kg
  • Aileron and ruddervator control-surface response evaluated at multiple deflections
  • Electronics components selected and sourcing links collected
  • Cost target set — under $500 per unit

This is an ongoing student STEAM project, not a finished aircraft. Every figure on this page (mass, endurance, cost, control response) is a theoretical estimate derived from CFD analysis and hand calculation, not from flight test data. No formal discussions have been held with Kaitseliit or the Estonian Defence Forces; the platform is presented here as a design study and a longer-term aspiration toward a working, versatile aircraft.