Autorotating Payload Delivery Assembly for Precise Descent Control
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Solution Overview
Problem
Existing air drop devices struggle to safely and accurately deliver payloads to predetermined targets on land or water while maintaining control over descent trajectory and stability.
Innovation Solution
The use of a pararotor assembly with autorotation capabilities, combined with a flight control and navigation system, to guide the payload's descent and stabilize its trajectory, utilizing collective and cyclic pitch control mechanisms for rotor blades, and optionally a gimbal assembly for enhanced control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a pararotor assembly with autorotation capabilities is used to guide payload descent and stabilize trajectory, then delivery precision and stability are improved, but device complexity increases
Solution Approach 1:
The payload delivery system is divided into modular components: the pararotor assembly with rotor blades, the payload container, the control system with servomotors, and the navigation system. Each module can be independently designed, tested, and maintained, reducing overall system complexity while maintaining delivery precision
Solution Approach 2:
The patent introduces a control system with servomotors and linkages as an intermediary between the navigation system and the pararotor assembly. This intermediary layer enables precise control of blade pitch and rotor orientation without requiring direct mechanical coupling, simplifying the control architecture while improving delivery accuracy
2Speed
If collective and cyclic pitch control mechanisms are implemented for rotor blades, then trajectory control is improved, but device complexity increases
Solution Approach 1:
The patent implements dynamic pitch control mechanisms where the rotor blade pitch angles can be continuously adjusted during descent. Collective pitch control modifies all blades simultaneously to control descent speed, while cyclic pitch control creates asymmetry for directional control. This dynamic adjustment capability enables precise trajectory control without requiring overly complex mechanical structures
Solution Approach 2:
The control system incorporates feedback from navigation sensors and trajectory monitoring to continuously adjust the pitch control mechanisms. The servomotors receive real-time commands based on actual descent performance, enabling closed-loop control that simplifies the overall system architecture while maintaining precise speed and trajectory control
3Stability of the object's composition
If a gimbal assembly is added for enhanced control, then directional control and stability are improved, but device complexity and weight increase
Solution Approach 1:
The gimbal assembly is designed to perform multiple functions: stabilizing the rotor axis, enabling directional control, and accommodating pitch adjustments. By consolidating these functions into a single multi-functional component rather than separate mechanisms, the patent reduces overall system complexity while maintaining trajectory stability
Solution Approach 2:
The patent combines the gimbal mechanism with the pitch control linkages and servomotor mounting structures. This merging of components reduces the total number of separate assemblies, simplifies installation and maintenance, while still providing the necessary directional control and trajectory stability
4Speed
If autorotation is used to slow down payload descent, then descent speed control is improved, but device complexity increases
Solution Approach 1:
The pararotor assembly is designed to automatically generate autorotation when the payload begins descent. The rotor blades self-accelerate as air flows over them, creating lift and drag forces that naturally control descent speed without requiring external power sources or complex control mechanisms. This self-service capability simplifies the overall system while improving speed control
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
Ensures precise and controlled delivery of payloads to target destinations by managing descent speed and trajectory, enhancing stability and accuracy through autorotation and directional control.
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
a collective control assembly module including at least one collective servomotor, the collective control assembly module connected between the support member and the rotor assembly and in communication with the flight control and navigation module configured to control a plurality of control linkages connected to the plurality of rotor blades
Implementation Method 4
a control surface assembly module including a plurality of control surfaces, the control surface assembly module connected to the support member and in communication with the flight control and navigation module to receive commands to control orientation of the plurality of control surfaces
Data Source
AI summary
A method of assembling a delivery payload assembly configured to be deployed from an aircraft and travel along a flight path to a predetermined landing destination includes attaching a tail-kit assembly to a first end of a payload, the tail-kit assembly including a rotor blade assembly including a plurality of rotor blades having a central axis of rotation, and a flight control and navigation system configured to control a collective pitch angle of each of the plurality of rotor blades of the rotor blade assembly, configured to control an axial thrust force of the rotor blade assembly, the axial thrust force being at an angle with respect to the central axis of rotation of the rotor blade assembly, and configured to navigate the delivery payload assembly along the flight path to the predetermined landing destination.