Helicopter Hoist Counterweight System for Load Balancing
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Solution Overview
Problem
Conventional helicopter winching systems on low-tonnage rotary-wing aircraft are limited by tilting and centering issues when carrying high loads, restricting the capacity to less than 150 kilograms, while heavy-tonnage helicopters can only carry loads greater than 250 kilograms due to the winch's lateral installation.
Innovation Solution
The implementation of a counterweight system where the winch cooperates with a beam extending from one side of the aircraft to the opposite side, allowing the winch and load to be positioned on either side of the aircraft's anteroposterior plane, thereby balancing the load without affecting the aircraft's roll attitude and improving aerodynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the winch is arranged on a lateral flank of the aircraft, then the installation is compact and simple, but the aircraft tilts during operation and the load capacity is limited to less than 150 kilograms
Solution Approach 1:
The patent applies the counterweight principle by positioning the winch on the opposite side of the aircraft relative to the load. When a load is suspended on one side, the winch mechanism on the opposite side acts as a counterbalancing mass, preventing the aircraft from tilting during hoisting operations. This enables low-tonnage aircraft to safely carry loads up to 300 kilograms without compromising flight stability, effectively doubling the load capacity compared to conventional lateral flank installations.
2Device complexity
If the winch is arranged on a lateral flank of the aircraft, then the installation is compact, but the centering of the aircraft is particularly impacted
Solution Approach 1:
The counterweight principle directly addresses the centering issue by distributing mass symmetrically across the aircraft. The winch mechanism positioned on the opposite side from the load creates a balanced mass distribution, maintaining the aircraft's center of gravity and preventing centering problems during hoisting operations.
3Device complexity
If the winch and load are positioned on the same side of the aircraft, then the cable routing is simple, but parasitic drag increases and aerodynamics deteriorate
Solution Approach 1:
The patent introduces a cable routing system that acts as an intermediary, guiding the cable through the aircraft structure from the winch on one side to the load on the opposite side. This intermediary routing mechanism allows the cable to pass through the fuselage or use guide pulleys, preventing the cable from creating parasitic drag outside the aircraft while maintaining functional connectivity between the winch and load.
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 configuration enables low-tonnage aircraft to carry high loads of up to 300 kilograms without tilting, improves aerodynamics by reducing parasitic drag, and allows for easier operation and maintenance by relocating the counterweight to a congested mechanical compartment.
Implementation Method 1
a counterweight (23) arranged on the first side of the aircraft, the counterweight (23) comprising the winch (21), wherein the winch (21) and the load are located on either side of the aircraft with respect to an anteroposterior plane of symmetry of the aircraft
Data Source
Figure 1~3
AI summary
The aircraft has a hoist unit (20) including a winch (21) provided with a drum for winding a hoist cable (22), where the hoist unit has a beam (30) e.g. hollow longitudinal tube, for guiding the cable. The beam is extended from an inlet end (31) to an outlet end (32) of the cable. The hoist unit has a counterweight (23) that includes a winch fastened to the inlet end. The outlet end is located on a side (12) of the aircraft. The winch and the inlet end are located on another side (11) of the aircraft. The counterweight includes a fairing (24) secured to the inlet end. : An independent claim is also included for a method for optimizing external load carried by a hoist unit of an aircraft. USE : Aircraft e.g. rotary wing aircraft. Can also be used for a helicopter e.g. rotorcraft. ADVANTAGE : The counterweight is obtained without excessively increasing the overall weight of the hoist unit. The design of the counterweight enables the aircraft to carry heavy loads without having influence on its attitude in roll. The design of the counterweight improves aerodynamics of the hoist unit. The design of the winch avoids generation of the unwanted drag on the outside of the aircraft. The outlet end avoids damage of the cable by abrasion. DESCRIPTION OF DRAWINGS : The drawing shows a face view of an aircraft. 11, 12 : Sides 20 : Hoist unit 21 : Winch 22 : Hoist cable 23 : Counterweight 24 : Fairing 30 : Beam 31 : Inlet end of cable 32 : Outlet end of cable.