Flight Endurance
Extend useful survey time while carrying the required sensing and power hardware.
System Cost
Treat component cost as a design variable, not an afterthought.
Useful Image Quality
Keep imaging capable enough for agricultural analysis without overspecifying sensors.
01 — The Problem
Accessible aerial crop-health data for smaller farms.
Mission need
Project ECHO is a multidisciplinary engineering project focused on developing a lower-cost aerial imaging platform for agricultural surveying. The system is being designed for smaller farms that could benefit from aerial crop-health data but may not be able to justify the cost of existing commercial agricultural drone systems.
Design approach
Instead of optimizing the aircraft around a single performance metric, the project focuses on balancing endurance, cost, image quality, structural performance, and subsystem compatibility.
Aerospace, electrical, and software engineering develop the aircraft, sensing system, and supporting analysis tools as a complete system rather than optimizing each component independently.
- Requirements
- Trade studies
- Optimization
- CAD
- FEA
- Manufacturing
- Flight testing
- Validation
02 — Engineering Requirements
Requirements first — components later.
The project began by defining system requirements rather than immediately selecting motors, propellers, batteries, or sensors.
Useful survey time
The aircraft should maximize useful survey time while carrying the required sensing, navigation, propulsion, and power hardware.
Affordable platform
Component cost is treated as a design variable rather than an afterthought. The objective is a significantly more affordable agricultural survey platform than many existing specialized systems.
RGB + NIR capability
The aircraft is being designed around RGB and near-infrared imaging capable of supporting vegetation analysis such as NDVI while avoiding unnecessarily expensive commercial multispectral systems.
Integrated packaging
Camera, flight controller, GPS, compass, battery, power electronics, storage hardware, and structure must integrate without unacceptable center-of-gravity, packaging, weight, or serviceability issues.
Small-UAS operating context
The planned system and operating concept are being developed with FAA small-UAS operating requirements in mind. Exact compliance claims are reserved until the aircraft configuration and operating procedures are finalized.
03 — System Architecture
Major subsystems of the aircraft.
Image data is intended to be stored onboard for later processing. The current concept does not require onboard image processing or live image streaming.
- Airframe / Structure
- Motors
- Propellers
- ESCs
- Battery
- Flight controller
- GPS / Compass
- RGB + NIR imaging
- Onboard data storage
04 — System Optimization
Coupled endurance, mass, propulsion, and cost.
Why components cannot be chosen independently
Endurance cannot be optimized by selecting a motor, propeller, battery, or airframe in isolation. A larger battery increases available energy but also aircraft mass. Larger propellers can improve propulsion efficiency while changing motor requirements and geometry. Structural stiffening can improve integrity while adding weight.
Design principle
The goal is to select the aircraft configuration through quantitative trade studies rather than choosing components individually.
An optimization workflow compares real propulsion and battery combinations while accounting for system-level constraints.
Fixed aircraft mass
Battery capacity
Battery mass
Motor characteristics
Propeller diameter & pitch
ESC requirements
Estimated hover power
Estimated flight endurance
Component compatibility
System cost
05 — Mechanical Design
Complete-assembly CAD for packaging and structure.
The aircraft is modeled as a complete assembly to evaluate structural geometry, component packaging, accessibility, propulsion clearances, and center-of-mass placement before manufacturing.
The CAD model is intended to serve as the basis for structural simulation and physical prototyping. As propulsion and electrical configurations are refined, the airframe can be updated for motor size, propeller diameter, battery dimensions, electronics placement, and sensor configuration.
06 — Structural Analysis
FEA and modal evaluation before physical testing.
Analysis in progress
Structural & modal FEA underway
The airframe will be evaluated using structural and modal finite-element analysis to identify stress concentrations, excessive deformation, and potential vibration concerns before physical testing. Results will be published here when validated.
07 — Multidisciplinary Integration
Aerospace decisions constrained by electrical and software needs.
Project ECHO coordinates aerospace/mechanical, electrical, and software disciplines. My primary responsibility is the aerospace/mechanical system, but aircraft decisions must account for requirements from all three areas.
- Structure
- Propulsion
- Mass
- Aerodynamics
- Packaging
- Power system
- Flight controller
- Sensors
- Navigation
- Camera hardware
- Optimization
- Data handling
- Image processing
- Analysis
08 — Current Development
Project roadmap from mission definition to validation.
- 01Mission definition
Problem framing and agricultural survey need.
- 02System requirements
Endurance, cost, imaging, packaging, operating context.
- 03Component research
Motors, props, batteries, ESCs, sensing hardware.
- 04Propulsion optimization
Coupled endurance / cost trade studies in progress.
- 05Airframe CAD
Assembly model for packaging, CG, and structure.
- 06Structural analysis
Static and modal FEA in progress.
- 07Sensor integration
RGB + NIR payload packaging and interfaces.
- 08Manufacturing
Prototype fabrication — future work.
- 09Ground testing
Static / systems checkout — future work.
- 10Flight testing
Flight performance campaigns — future work.
- 11Performance validation
Compare predictions to measured data.
Closing the loop with flight-test data
The final phase of Project ECHO will compare predicted endurance, structural performance, and system behavior against physical test data. This will allow the analytical models and optimization workflow to be evaluated against real aircraft performance.
The strongest message of this project is not simply building a drone — it is developing the aircraft through requirements, quantitative trade studies, CAD, analysis, multidisciplinary integration, and eventually physical validation.