Ground Test Refinement and CNC Readiness: Apr 8-15

Engineering work during this period focused on ground-test refinement and preparation for in-house carbon fiber manufacturing.

Subsystem work included propeller configuration review, antenna and mounting geometry decisions, spin-up testing without takeoff, and investigation of abnormal throttle behavior observed during arming tests. In parallel, Chenault Aerospace finalized workspace preparation for the incoming CNC machine, received tooling for the machine, and advanced CAD and carbon-fiber material planning required for frame production.

This phase materially improved both demonstrator readiness and manufacturing readiness by addressing integration issues at the bench while preparing internal tooling for rapid airframe iteration.

Firmware Bring-Up and First Integration Validation: Apr 1-7

Chenault Aerospace progressed into active system integration during this period, including flight controller firmware flashing, power-system bring-up, radio and receiver binding, ESC and motor wiring verification, capacitor installation, and initial video-system planning.

Bench-level validation during this phase was focused on confirming clean power-up behavior, establishing communications between control components, and resolving early integration faults before flight testing. This type of controlled debug work is critical for reducing risk during first-flight preparation.

By the end of the phase, the demonstrator program had advanced from parts and planning into a functioning integrated aircraft undergoing subsystem validation.

Assembly Planning and Manufacturing Path Development: Mar 25-31

Development work expanded from component inspection into detailed assembly planning and early manufacturing-path preparation for the demonstrator airframe.

During this phase, Chenault Aerospace established a formal assembly checklist for the initial build, secured access to an external test venue suitable for capability evaluation, and identified a low-cost CNC fabrication path for carbon fiber frame cutting. These actions directly support the program objective of developing a low-cost aircraft architecture that is also manufacturable at small scale.

The result was a more executable build plan supported by both prototype assembly documentation and an initial path toward repeatable frame production.

Component Intake and Inspection: Mar 18-24

With physical components beginning to arrive, Chenault Aerospace entered a component intake and inspection phase for the tactical FPV demonstrator platform.

Engineering attention during this period focused on logging received hardware, confirming part-condition and configuration alignment, and identifying any integration concerns prior to installation. This work is important for maintaining configuration control and reducing avoidable rework during assembly.

Completion of this intake phase improved readiness for build execution by converting procured hardware into a controlled engineering baseline rather than an untracked collection of parts.

Prototype Assembly Transition: Mar 11-17

Following completion of initial component procurement, Chenault Aerospace transitioned the tactical FPV demonstrator program from architecture definition into prototype assembly preparation.

Engineering activity during this phase centered on confirming that the selected 10-inch, 6S multirotor configuration could move into physical integration without introducing unnecessary complexity in layout, service access, or component replacement.

This period established the bridge between early configuration studies and hands-on build activity, positioning the demonstrator program to begin first-article assembly and subsequent system validation.

Demonstrator Component Procurement: Mar 7-10

Chenault Aerospace has completed procurement of the initial component set for the tactical FPV demonstrator platform.

The selected configuration utilizes a 10-inch multirotor architecture powered by a 6S propulsion system and modular flight control stack. Key propulsion components include 2806.5-class motors optimized for efficiency within the platform’s thrust envelope.

This procurement milestone marks the transition from architecture design to prototype assembly and system integration testing.

Assembly of the first prototype aircraft is scheduled for the upcoming development phase.

System Integration Planning: Mar 3-5

Following completion of the propulsion and avionics architecture studies, Chenault Aerospace began planning the integration and assembly approach for the demonstrator aircraft.

Engineering planning during this phase focused on:

• component layout and physical integration

• wiring management and service access

• structural reinforcement and vibration management

• assembly workflow for prototype builds

These integration considerations are intended to inform both prototype construction and future scalable assembly processes.

Avionics Architecture Definition: Mar 1-2

Development work progressed to defining the avionics architecture for the demonstrator platform.

The system architecture emphasizes modularity and maintainability. Key design principles include:

• standardized flight controller stack integration

• modular receiver and communications architecture

• simplified wiring and serviceability

• compatibility with commonly available control systems

The avionics configuration is intended to support rapid assembly and easy component replacement during testing.

Propulsion and Power System Selection: Feb 25-28

With the baseline airframe architecture defined, engineering efforts shifted toward propulsion and electrical system configuration.

Key considerations included:

• motor efficiency within the target thrust envelope

• compatibility with a 6S power system

• component reliability and availability within domestic supply chains

Following evaluation of several propulsion options, the development team selected a 2806.5-class motor paired with a 6S battery configuration for the initial demonstrator aircraft.

This propulsion architecture provides sufficient thrust margin while maintaining manageable system weight and electrical complexity.

Architecture Evaluation: Feb 21-24

Following program initiation, Chenault Aerospace evaluated several candidate airframe architectures suitable for the demonstrator platform.

Configuration studies focused on:

• compact multirotor geometries

• propulsion efficiency for short-duration tactical missions

• modular avionics stack integration

• structural durability and maintainability

The evaluation resulted in selection of a 10-inch class multirotor architecture as the baseline configuration for the demonstrator aircraft. This configuration provides a balance between payload capability, maneuverability, and component availability while remaining compatible with low-cost propulsion systems.

Program Initiation: Feb 18-20

Chenault Aerospace initiated an internal development program focused on evaluating low-cost unmanned aircraft architectures suitable for reconnaissance and precision effects missions.

The effort began with a survey of currently available commercial unmanned aircraft components and an analysis of recent battlefield employment trends involving small unmanned systems. Particular focus was placed on architectures that prioritize affordability, manufacturability, and field-replaceable components.

Initial program objectives were established:

• develop a compact multirotor architecture suitable for tactical employment

• maintain low unit cost through standardized components

• design around rapid assembly and simplified maintenance

• evaluate scalability for distributed manufacturing

This program forms the basis for the company’s current demonstrator aircraft development effort.