Multi-Axis Rotary-Wing Integrated Design (MARID) Drone

 PATENT PENDING

Core Technical Mission Statement:

To pioneer a new category of high-endurance, ultra-stealth unmanned aircraft through the synergistic integration of three disruptive technologies:

- A Radically Simplified Airframe Control System 

- A High Density Hybrid Propulsion System 

- A Deeply Integrated Cryogenic Thermal Management System

This tri-focal approach ensures the advantages of each technology directly enable and amplify the benefits of the others. This platform will serve as the foundational testbed for the future evolution towards fully adaptive, continuous-morphing wings, representing the ultimate expression of efficient, multi-regime flight.

Fig1. Gazebo MARID simulation with Smoke Emitter Visual

Fig.2 RViz MARID Drone Display

Fig. 3 Top View

Primary Technical Goal:

To demonstrate a UAV platform that achieves a multi-day endurance with a significant operational radius, while maintaining a radar cross-section (RCS) radically lower than current assets in its class, validated through a full mission-cycle flight test of its novel, integrated control architecture.

Future Evolution Goal:

To leverage the lessons, infrastructure, and thermal management expertise from the MARID platform to develop and integrate second-generation continuous morphing wings. 

Fig. 4 Side View

Fig. 5 Front View

Technical Objectives & Key Provisional Results:

    Objective 4.1: Validate Rotary Control Authority and Stealth

    Objective 4.2: Achieve Endurance Through Hybrid Hydrogen-Electric Power

    Objective 4.3: Demonstrate Integrated Cryo-Thermal Management

       

    Objective 4.4: Establish the Morphing Wing Technology Foundation

        KR 4.4.1: Down select to a morphing technology pathway (e.g., compliant structures, hybrid                composites, distributed solid-state actuators) compatible with the cryogenic thermal system.

        KR 4.4.2: Design, build, and bench-test a sub-scale morphing wing section that demonstrates a                target of 10% change in camber or 5 degrees of continuous twist while maintaining a seamless                surface.

        KR 4.4.3: Develop and validate real-time optimization algorithms for the future morphing wing,            capable of minimizing drag by continuously adjusting shape to airspeed, altitude, and G-loading.

Fig. 6 General View

Fig. 7 Back View