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Project Capstone Demo — AeroCinematic

PROJECTX AEROSPACE LAUNCH PROTOCOL
PROJECT ID: MECH-F22-01
SYSTEM: REMOTE CONTROL AIRCRAFT
AIRFRAME: F-22 RAPTOR SCALE MODEL
CORE MATERIAL: 5 MM DEPRON FOAM SHEET
STATUS: AERODYNAMIC PROTOTYPE // READY
ESTABLISHING AVIONICS LINK...
LiPo 3SRX 6CHESC 30A
SYS_ID: MECH-F22-01 // AERODYNAMICS PROTOCOL
AEROSPACE SCALE RESEARCH PROTOTYPE

BUILD. TEST. FLY.

DESIGN, DEVELOPMENT & PERFORMANCE EVALUATION OF REMOTE CONTROL AIRCRAFT

F-22 Raptor Scale Model. Engineered from virgin 5 mm Depron foam sheet, powered by an electric brushless powertrain, and validated through real flight envelope trials.

AIRFRAME CORE5 MM DEPRON FOAM
PROPULSIONBRUSHLESS MOTOR + PROP
FLIGHT CONTROLDUAL ELEVON SERVOS
RIGOR CLAUSE[Add Data] UNCALIBRATED
SCROLL TO INITIATE TAKEOFF ROLL
AIRCRAFT IS SENSITIVE TO SCROLL PROGRESS
01 // THE CONCEPT

THE IDEA

The Lockheed Martin F-22 Raptor represents the zenith of modern 5th-generation stealth combat aerodynamics: clipped diamond delta wings, leading-edge root extensions (LERX), and twin canted vertical fins.

Our central research objective was simple yet audacious: can a student engineering team fabricate an ultra-low-cost, high-alpha agile scale flight platform using only 5 mm Depron foam sheet, matched with hobbyist electric propulsion and dual elevon control?

HYPOTHESIS STATEMENT:
"Low wing loading achieved through closed-cell polystyrene enables high-angle-of-attack maneuverability without complex composite autoclaves."
02 // THE DESIGN

DESIGNED TO FLY

Notice the aircraft banking as you scroll. The planform geometry was mathematically extracted from 1:12 scale orthographic projections.

To maintain pitch stability without expensive fly-by-wire computers, the Center of Gravity (CG) was calculated precisely at 28% Mean Aerodynamic Chord (MAC), balanced by forward placement of the 3S LiPo battery.

Wingspan
720 mm
Clipped Delta Planform
Fuselage Length
940 mm
Stealth Chine Edges
Substrate
5 mm Depron
Extruded Polystyrene
CG Balance
28% MAC
Naturally Stable
03 // THE BUILD

BUILT FROM THE GROUND UP

Every component is installed intentionally into the Depron airframe. As you scroll, the internal architecture becomes visible:

01
5 mm Depron Foam
Isotropic 33 kg/m³ density, easily scored for folded aerofoils.
02
Carbon Fiber Spar
3 mm hollow carbon tube epoxied transversely across wing root.
03
2212 2200KV Brushless Motor
Mounted to 3 mm birch plywood firewall in mid-fuselage slot.
04
30A ESC with 5V BEC
Regulates high-RPM commutation and steps down 11.1V to 5V.
05
3S 11.1V LiPo Battery
1500mAh 30C high-discharge chemistry, ballast for CG.
06
Dual 9g Micro Servos
Installed on port & starboard wings driving 45° beveled elevons.
07
6-Channel 2.4GHz Receiver
Decodes pilot stick inputs into individual PWM channel signals.
04 // EXPLODED AVIONICS BAY

EVERY COMPONENT HAS A JOB

The aircraft is held stationary in center stage. Click any component hotspot on the aircraft or below to inspect its flight dossier.

05 // SIGNAL PULSE

CONTROL

FLIGHT SURFACE CONTROL PATH
TRANSMITTER (PILOT STICKS)
↓ 2.4 GHz RF Link
RECEIVER (DEMULTIPLEXER)
↓ 50Hz PWM Signal (CH1 + CH2)
2× SERVO MOTORS
↓ Pushrod Mechanical Deflection
ELEVON SURFACES → PITCH & ROLL ATTITUDE
PROPULSION THROTTLE PATH
RECEIVER (THROTTLE CH3)
↓ 1000µs - 2000µs PWM Pulse
ELECTRONIC SPEED CONTROLLER (ESC)
↓ 3-Phase AC High Frequency Commutation
BRUSHLESS OUTRUNNER MOTOR
↓ Propeller Aerodynamic Mass Flow
DYNAMIC FORWARD THRUST
06 // FLIGHT SORTIE

THEN WE FLEW IT.

Full-throttle hand launch into a 5-knot headwind. The 5 mm Depron airframe lifted smoothly, showing remarkable pitch stability and instant elevon roll response.

CRITICAL FLIGHT ENVELOPE VALIDATED
07 // PERFORMANCE & TESTING LAB

FLIGHT PERFORMANCE

SCIENTIFIC RIGOR POLICY: No experimental values are fabricated. Flight measurements remain marked as [Add Data] until field radar, pitot, and bench tests are formally cataloged.
Maximum Recorded Airspeed
[Add Data]
km/h
Flight Endurance / Time
[Add Data]
min
All-Up Weight (AUW)
[Add Data]
grams
Static Thrust Output
[Add Data]
grams
Effective RF Control Range
[Add Data]
meters
Discharge Current Draw
[Add Data]
Amperes (A)
Live Thrust-to-Weight CalculatorTEST STAND PREDICTOR
Static Thrust:480 g
All-Up Weight (AUW):380 g
Calculated T/W Ratio:1.26 : 1
08 // MODULAR AVIONICS EXPANSION

READY TO EVOLVE

The 5 mm Depron airframe contains an open mid-fuselage avionics bay designed to dock modular research payloads.

I2C / Differential PressureOPTIONAL

Pitot Airspeed Sensor

Measures dynamic vs static air pressure to calculate calibrated airspeed (CAS) independent of ground wind.

5.8 GHz Analog / HD VideoOPTIONAL

FPV Micro Camera & VTX

Transmits live first-person view cockpit perspective to ground station goggles for piloting Beyond Visual Line of Sight (BVLOS).

UART / NMEA ProtocolOPTIONAL

GPS Telemetry Beacon

Logs exact flight coordinate breadcrumbs, altitude above ground level, ground speed, and return-to-home waypoint locking.

I2C 400kHz Fast BusOPTIONAL

3-Axis Gyroscope

Monitors angular rate of change on pitch, roll, and yaw axes to counter aerodynamic turbulence and wind shear.

SPI / I2C BusOPTIONAL

3-Axis Accelerometer

Measures structural G-forces during high-speed bank turns and calculates gravitational down-vector for horizon leveling.

I2C / BMP280OPTIONAL

Barometric Altitude Sensor

High-precision barometric altimeter providing sub-meter vertical climb and descent rate (variometer) telemetry.

09 // MISSION HORIZON

THIS IS ONLY THE BEGINNING.

WHAT WILL YOU BUILD?
BUILT BY STUDENTS.
DESIGNED TO FLY.
READY FOR WHAT'S NEXT.
RESEARCH TEAM: Rahul Sisode & Team
SUPERVISOR: Dr. V. K. Sharma
DEPARTMENT: Mechanical Engineering

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