UAV Landing Container Parachute Rotation Mechanism
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Solution Overview
Problem
Existing parachute systems for unmanned aerial vehicles (UAVs) are complicated and prone to steering issues due to strong winds, and require large pneumatic bags for protection during landing, making them inefficient and costly.
Innovation Solution
A detachable container with a parachute is used, where the parachute forces the container to rotate 180 degrees, allowing the UAV to land safely while the main power supply batteries and surveillance equipment are removed, using auxiliary batteries for the flight control system to guide the lightened aircraft to a slide landing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a parachute system with servomechanisms is used to control the descend flight trajectory, then the cargo can land safely in a chosen target location, but the structure of the control system becomes complicated and strong winds may make it impossible to maintain correct parachute steering parameters
Solution Approach 1:
The patent extracts the heavy main power supply batteries and surveillance equipment into a detachable container that is jettisoned before landing. This separates the critical landing control functions (powered by lightweight auxiliary batteries) from the heavy components, simplifying the control system structure while maintaining reliable parachute-controlled landing of the lightweight airframe
Solution Approach 2:
The aircraft is segmented into two parts: a lightweight airframe with auxiliary batteries and flight control systems for controlled landing, and a detachable container with main batteries and surveillance equipment that is jettisoned and recovered separately by parachute. This segmentation resolves the contradiction by allowing simple controlled landing while enabling separate recovery of heavy equipment
2Reliability
If large pneumatic bags are used to protect the cargo and fuselage during landing, then the cargo and fuselage are protected, but the device structure becomes more complicated and larger
Solution Approach 1:
The patent removes the heavy main power supply batteries and surveillance equipment from the fuselage into a separate detachable container. This extraction eliminates the need for large protective pneumatic bags in the fuselage, as the lightweight airframe requires minimal protection, while the container itself serves as the protective structure for the equipment
Solution Approach 2:
The container is equipped with its own parachute system for controlled descent and landing. This beforehand cushioning approach protects the equipment through controlled deceleration during descent, eliminating the need for large protective bags during the main aircraft landing
3Weight of moving object
If the main power supply batteries are removed from the fuselage before landing, then the aircraft weight is reduced and slide landing becomes possible, but the equipment needs a safe recovery system
Solution Approach 1:
The aircraft system is segmented into a lightweight airframe for slide landing and a detachable container for equipment recovery. The container is equipped with its own parachute system, enabling independent recovery of the heavy equipment while the lightened airframe performs uncontrolled slide landing
Solution Approach 2:
A detachable container serves as an intermediary between the fuselage and the heavy equipment. It provides a dedicated platform with its own parachute recovery system, allowing the equipment to be safely recovered while the main aircraft structure remains lightweight for simple slide landing
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
This method simplifies the landing process, ensures safe return of expensive equipment, and reduces the complexity and cost of the landing system by allowing the UAV to land safely with the heaviest components removed, using auxiliary power for control.
Implementation Method 1
a parachute placed at the bottom part of the container on the side of the surveillance head
Implementation Method 2
with the help of parachute the container descends into a desired place
Implementation Method 3
the parachute fixed near the surveillance head forces the falling container to turn around its horizontal axis by 180 degrees causing the lens of the surveillance head to tilt up
Implementation Method 4
the propeller collapses along the axis of the fuselage
Data Source
Figure 1
Figure 2
Figure 3
AI summary
The mode of landing of an unmanned aerial vehicle driven by an electric engine, containing main power supply batteries, control systems of the surveillance head, transmitting and receiving systems, a flight control system, and a container (4) equipped with a surveillance head (1) with a looking down lens (9), placed in a recess (2) situated in the lower part of the fuselage (3) by which the vehicle is lightened at the last stage of flight shortly before landing, which means the container (4) placed in the recess (2) is detached, then moved outside the vehicle's body (3) and descended by means of a parachute (5) into a desired location, and the lightened vehicle lands in some other place. The recess (2) in the fuselage (3) contains an electrically controlled lock (8) which fixes detachably the container (4) equipped with at least one parachute (5) placed at the bottom section of the container (4), on the side of the surveillance head (1).