Computer-Operated Hook Assembly for Helicopter Sling-Load Stability
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Helicopter sling-load systems face challenges with load stability during flight, lengthy pick-up and attachment processes that expose aircraft and ground crew to hostile fire, and delays during delivery and release, especially in adverse weather conditions.
Innovation Solution
A computer-operated hook assembly that provides automated load engagement, navigation, and delivery, using sensors like gyroscopes, accelerometers, and GPS for real-time data transmission to the aircraft autopilot to maintain load stability and navigate to designated points, with a local network for communication and tactical data net for mission control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a long tether is used to keep the aircraft away from terrain obstacles and rotor-induced visibility problems, then the aircraft safety is improved, but the load stability deteriorates due to oscillation and center-of-gravity shifts
Solution Approach 1:
The system uses sensors (gyroscopes, accelerometers, load cells) to continuously monitor load position, orientation, and forces, feeding this data back to the autopilot which automatically adjusts flight controls to maintain load stability and keep the load within center-of-gravity limits
Solution Approach 2:
The patent replaces manual mechanical control of the tether and load with an automated computer-controlled system that uses electronic sensors and autopilot integration to actively manage load stability, substituting human operator actions with automated feedback control
2Device complexity
If manual pick-up and attachment procedures are used, then the system complexity is reduced, but the operation time increases exposing the aircraft to hostile fire
Solution Approach 1:
The hook assembly is equipped with sensors and automated control systems that enable it to independently detect loads, determine optimal attachment points, and execute pick-up procedures without requiring extensive manual intervention from ground crew or pilot actions
Solution Approach 2:
The patent introduces a computer control system as an intermediary between the pilot/ground crew and the actual pick-up operations, automating the coordination of sensors, hook mechanisms, and flight control to streamline the attachment process
3Stability of the object's composition
If automated sensors and control systems are integrated into the hook assembly, then the load stability control is improved, but the device complexity increases
Solution Approach 1:
The hook assembly integrates multiple functions into a single system: load detection, position monitoring, stability control, and communication with the aircraft, allowing one device to perform what would otherwise require separate systems
Solution Approach 2:
The patent combines sensors (gyroscopes, accelerometers, load cells), communication systems, and control electronics into an integrated hook assembly unit that works in unison with the aircraft's existing autopilot and flight director instruments
4Reliability
If ground crew actions are delayed during delivery and release, then the aircraft safety is improved by reducing exposure to hostile action, but the productivity decreases
Solution Approach 1:
The system pre-positioning and pre-aligns the load and aircraft before the actual release moment, using automated navigation and positioning systems to ensure everything is ready for immediate release, minimizing the time ground crew need to remain in hazardous positions
Solution Approach 2:
The automated system rapidly executes the release sequence once conditions are met, quickly transitioning from approach to release to separation, minimizing the duration of the critical phase where ground crew are exposed to potential threats
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
Enables stable and automated sling-load operations in instrument meteorological conditions, reduces exposure to hostile fire, and ensures precise load delivery and pick-up without human intervention, maintaining aircraft control and safety.
Implementation Method 1
The sensors include a 3-axes gyroscope providing pitch, roll, yaw
Implementation Method 2
a MEMS 3-axes accelerometer, providing 3-plane acceleration
Implementation Method 3
a magnetometer providing heading data
Data Source
AI summary
A sling load computer-operated hook assembly for helicopter or unmanned aerial vehicle (UAV) use is provided. The hook assembly allows automated pick-up and delivery. The computer hook assembly also (1) directs navigation of the aircraft, (2) finds and engages loads for pickup, (3) controls stability of the sling load enroute, and (4) releases the load at the delivery point. The self-contained feature allows the hook assembly to be moved from aircraft to aircraft. The hook assembly senses weight, motion and position of the load for stability control. An integral GPS unit is used to direct navigation. These data are transmitted to the aircraft autopilot and flight director instruments to provide navigation to the designated points and to control load stability enroute. Mission data for pick-up and release points can be received remotely from a command and control tactical data net. Alternately, mission data can be locally entered.