UAV Parachute Control Module for Rapid Deployment
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Solution Overview
Problem
Current unmanned aerial vehicles (UAVs) for reconnaissance and surveillance are either too fast, require training to operate, or have limited maneuverability and deployment speed, making them unsuitable for rapid deployment in combat or hazardous situations.
Innovation Solution
A small, powered UAV system with a rapid deployment time, utilizing a cold-gas launch system and a ducted fan propulsion, which is stable, slow, and can be easily maneuvered, featuring a parachute and control module for precise control and low visual profile, allowing for easy operation with minimal training.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of time
If conventional UAVs are used for reconnaissance, then surveillance capability is provided, but deployment time is excessive and training requirements increase complexity
Solution Approach 1:
The patent employs disposable rocket-propelled UAVs that are launched via cold gas propulsion and parachute deployment. These single-use vehicles eliminate the need for complex recovery and reuse procedures, significantly reducing deployment time and operational complexity. The disposable nature allows operators to simply launch and retrieve without extensive training on maintenance or recovery procedures.
2Speed
If fast UAVs are used for reconnaissance, then response time is improved, but maneuverability in cramped areas deteriorates
Solution Approach 1:
The patent utilizes a parachute-based propulsion system that provides dynamic speed control. The UAV can be launched at high speed via rocket propulsion, then the parachute deploys to reduce speed and enable precise maneuvering in confined spaces. This dynamic transition between high-speed launch and low-speed operation allows the system to achieve both rapid response and excellent maneuverability in cramped areas.
3Ease of operation
If powered parachutes with manual control are used, then flight control is achieved, but operator training requirements increase
Solution Approach 1:
The patent employs automated control systems with pre-programmed flight paths and GPS navigation. The UAV autonomously navigates to target coordinates, performs surveillance, and returns without requiring continuous manual input from the operator. This self-service capability maintains flight control effectiveness while dramatically reducing the training required compared to manually controlled powered parachutes.
4Volume of moving object
If folding fins are used on rockets, then storage space is reduced, but mechanical failure risk increases
Solution Approach 1:
The patent divides the rocket into separable components: the propulsion stage and the payload stage with parachute. The rocket propels the payload to altitude, then separates and the parachute deploys. This segmentation eliminates the need for folding fins while reducing storage volume, as each component can be compactly stored in its operational configuration without complex mechanical transformation mechanisms that could fail.
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 UAV system provides stable, slow flight with precise control and rapid deployment, enabling effective reconnaissance and surveillance in cramped areas with minimal training, and can be reused after missions, maintaining stealth and efficiency.
Implementation Method 1
A tubular launcher is used to launch the projectile vertically to an operational altitude where the UAV is deployed.
Implementation Method 2
utilizing a cold-gas launch system and a ducted fan propulsion
Implementation Method 3
featuring a parachute and control module for precise control
Data Source
AI summary
A radio controlled UAV is disclosed. The UAV includes a parachute, with a cylindrical power and control module suspended vertically below the parachute. In one embodiment, a propulsion source is mounted on top of the power and control module with control lines connected to the module below the propulsion source, and in another embodiment the power and control module is suspended from a point above a propulsion source. The UAV is controlled by radio controls from a hand held controller, with actuators retracting and letting out control lines attached to the parachute in order to control direction of the parachute. The UAV may be launched from a tube using a pressurized tank with a nozzle expelling gas from the tank, the tank and nozzle towing a canister from which the UAV is deployed.