Helicopter Emergency Flight Support Wing Deployment
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Solution Overview
Problem
Helicopters face a high risk of crash landing due to rotor failure, as existing escape systems lack control over descent and rely on parachutes that require significant altitude to deploy effectively.
Innovation Solution
A helicopter flight support system that deploys a wing-like configuration using a motor-driven threaded shaft to extend outer and inner supports, tensioned by support cables, providing horizontal stability and control over the descent.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a parachute escape system is deployed from the top of the helicopter, then the pilot and passengers can be evacuated, but the descent cannot be controlled and hundreds of feet of altitude are required for effective deployment
Solution Approach 1:
The patent introduces a stabilizing surface (parachute-like structure) deployed from the bottom of the helicopter as an intermediary element. This surface interacts with the airflow to provide aerodynamic stability and drag, enabling controlled descent without requiring traditional top-deployed parachute systems. The stabilizing surface acts as a mediator between the helicopter and the air, creating controllable aerodynamic forces.
Solution Approach 2:
The patent inverts the conventional parachute deployment approach by deploying the stabilizing surface from the bottom of the helicopter rather than from the top. This inversion allows the stabilizing surface to extend downward and interact with the airflow in a manner that provides both drag for descent control and stability for attitude management, eliminating the need for traditional top-deployed parachutes.
2Adaptability or versatility
If the helicopter flies at lower altitudes during routine use, then operational flexibility is improved, but rotor failure leads to crash landing due to reduced height
Solution Approach 1:
The patent implements a pre-deployed stabilizing surface that is prepared in advance and can be rapidly deployed from the bottom of the helicopter. This preliminary preparation ensures that when rotor failure occurs at low altitude, the stabilizing surface is already positioned to provide immediate aerodynamic control, allowing the helicopter to achieve controlled descent without requiring high altitude for parachute deployment.
3Ease of operation
If a stabilizing surface is deployed from the bottom of the helicopter, then controlled descent is achieved, but the structure must withstand significant aerodynamic forces
Solution Approach 1:
The patent employs a deployable stabilizing surface that can be rapidly extended and positioned to achieve controlled descent. The dynamic deployment mechanism allows the structure to transition from a compact stowed configuration to an extended operational configuration, enabling the helicopter to achieve aerodynamic control without requiring the structure to permanently withstand maximum aerodynamic forces.
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 system allows for a controlled, slower descent of the helicopter, providing stability and the ability for the pilot to manage the landing, thereby reducing the risk of a crash landing.
Implementation Method 1
a motor (204) which causes a threaded shaft (214) to turn which is coupled to an underside of the helicopter (102). This causes outer supports (206) and inner supports (208) to be deployed
Implementation Method 2
The interior of the wing comprises a plurality of support cables (702) for tensioning the wing. The helicopter flight support further comprises upper and lower support cables (404, 406) mounted to the tips of the wing to provide horizontal stability.
Implementation Method 3
a helicopter flight support that can be safely deployed in the case of rotor failure that prolongs the descent, thus slowing the helicopter
Data Source
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AI summary
Disclosed herein is a helicopter flight support for use in case of emergencies. The helicopter flight support comprises a motor which causes a threaded shaft to turn which is coupled to an underside of the helicopter. This causes outer supports and inner supports to be deployed until they reach a wing-like configuration. The interior of the wing comprises a plurality of support cables for tensioning the wing. The helicopter flight support further comprises upper and lower support cables mounted to the tips of the wing to provide horizontal stability.