Autorotating Payload Rotor Control for Precise Airdrop Descent
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing air drop devices struggle to accurately and safely deliver payloads to predetermined targets on land, water, or structures, due to limitations in control and navigation systems, particularly in ensuring stable and controlled descent.
Innovation Solution
The development of a payload delivery device equipped with a support member, a flight control and navigation system module, a control surface assembly module, a rotor assembly with collective and cyclic pitch control, and a collective control assembly module, allowing for precise control of the payload's orientation and descent.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If traditional air drop devices are used without advanced rotor control, then the device complexity is reduced, but the payload delivery precision and descent stability deteriorate
Solution Approach 1:
The rotor assembly incorporates dynamic pitch control mechanisms that allow real-time adjustment of blade angles during descent. The collective pitch control system modifies all blades simultaneously to control descent rate, while cyclic pitch control creates asymmetric blade angles for directional steering, enabling precise payload delivery through dynamic adaptation to changing flight conditions
Solution Approach 2:
The flight control system continuously monitors payload position, descent rate, and rotor performance, then automatically adjusts pitch control inputs to maintain optimal descent trajectory. This closed-loop feedback mechanism compensates for disturbances and ensures precise payload delivery without requiring overly complex mechanical structures
2Speed
If autorotation configuration is used for deceleration, then the descent speed is reduced, but the control precision over trajectory deteriorates
Solution Approach 1:
The flight control system continuously monitors payload position, descent rate, and rotor performance, then automatically adjusts pitch control inputs to maintain optimal descent trajectory. This closed-loop feedback mechanism compensates for disturbances and ensures precise payload delivery without requiring overly complex mechanical structures
Solution Approach 2:
The system transitions between autorotation and controlled rotation modes dynamically. During most of the descent, autorotation provides stable deceleration, but the control system can introduce cyclic pitch variations to steer the payload horizontally and adjust the descent path, maintaining trajectory precision throughout the flight
3Stability of the object's composition
If collective and cyclic pitch control systems are implemented, then the descent stability is improved, but the device complexity increases
Solution Approach 1:
The pitch control system integrates collective and cyclic control mechanisms into a unified rotor assembly. The collective pitch control modifies all blades simultaneously for vertical descent rate control, while cyclic pitch control creates asymmetric blade angles for horizontal steering, both acting on the same rotor system to provide coordinated stabilization and navigation
Solution Approach 2:
The rotor assembly serves multiple functions: it provides aerodynamic drag for deceleration, generates lift for descent rate control through collective pitch, and enables horizontal steering through cyclic pitch. This multi-functional design achieves comprehensive descent stability without requiring separate control systems for each function
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The device enables precise navigation and controlled descent of payloads to predetermined landing destinations, ensuring stability and accuracy through advanced control and navigation systems.
Implementation Method 1
The pararotor is a device like an unpowered helicopter rotor that spins in an autorotation configuration when the attached payload is descending through an airstream impinging upon the pararotor
Implementation Method 2
A drag force in the direction of the incident airstream flow is generated over the autorotating rotor, where the drag exerted over the rotor is greater if the rotor is spinning in an autorotating configuration
Implementation Method 3
the rotational motion of the pararotor assembly is effective to slow down or exert a downwardly directed thrust vector relative to a falling body or payload in the airstream and also stabilize the payload's trajectory
Data Source
AI summary
A payload delivery device configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination includes a support member configured to be removably attached to the payload, a flight control and navigation system module configured to control orientation of the plurality of control surfaces while the payload is travelling along the flight path to the predetermined landing destination, a control surface assembly module including a plurality of control surfaces, a rotor assembly including a plurality of rotor blades having a central axis of rotation, and a collective control assembly module including at least one collective servomotor configured to control a plurality of control linkages connected to the plurality of rotor blades.