About SALUS

About The Product, Technology Used & Production Process

Stabilizing Aerial Loads Utility System

Operationally Unobtrusive Anti-rotational Device

Medical evacuation, search and rescue, and cargo transport missions require that helicopter hoist operations be performed in the face of disadvantageous environmental conditions. Hoisted objects tend to spin while being lifted under a helicopter due to rotor downwash. Spinning is a potentially catastrophic event that leads to evacuee nausea, disorientation, and vertigo, and can be life-threatening.

SALUS automates spin stabilization for medical evacuation (MEDEVAC) missions. Upon receiving orders for patient pick-up, a MEDEVAC crew will fly to or near the site of the injury. In ideal circumstances, the helicopter lands, patients are moved inside the cabin, and take-off occurs in the direction of the nearest military treatment facility (MTF). One quickly finds that landing is a luxury. Patients must often be evacuated over water, above sloping terrain, and in hostile territory.
 

SALUS (Stabilizing Aerial Loads Utility System) introduces Operationally Unobtrusive Anti-rotational Device with Stability Manager, that consists a suite of electronics responsible for detecting motion and dictating motor behavior.

PROBLEM

Spin instability during helicopter hoist operations

6,500 government helicopters outfitted for hoist operations. Spin instability present on every hoist mission. Dangerous, uncontrolled spinning leads to vertigo, nausea, striking, and entanglement.

SOLUTION

Stabilizing Aerial Loads Utility System

SALUS employs a switch-enabled stability manager controlling a spinning reaction-wheel, to counter the angular momentum of a hoisted object.

Key Innovation - SALUS Features

Stabilizing

A switch-enabled stability manager controls a spinning reaction-wheel to counter the angular momentum of a hoisted object.

Universal

SALUS connects to the hoist hook and lift slings, ensuring stability regardless of load type or the external environment.

Unobtrusive

An intuitive UX and simplicity of operation ensure existing hoist standard operating procedures remain intact.

Modular

SALUS supports various modules, to include visual and infrared lighting for load illumination.

Technology - Science Background

CMG

Counter-torque capability with gyroscopic precession applied to intelligently stabilize on multiple axes

Momentum Wheel

Gyroscopic precession selectively applied to mitigate load oscillation and sway

Reaction Wheel

Counter-torque to reduce spin instability in either direction

Basics of Flywheel Mechanics

  • Verification: Check the energy of both a flywheel and simplified litter model spinning
  • Result: Comparable energy from both systems with reasonable values

PID Control

  • Controlling Spin: Algorithm required to inform how and when to spin the flywheel
  • PID: A tried and true method for holding a system to steady state
  • Usage: Desired state is zero angular velocity, and response variable is motor speed and direction

Intellectual Property

  • Device for Stabilizing a Hoisted Object
  • Aerial Hoist Stabilization System (I)
  • Aerial Hoist Stabilization System (II)
  • Flywheel-Based Mechanism for Stabilizing Helicopter Hoists
  • Control Moment Gyroscope Hoist Stabilization System
  • Helicopter Hoisted Load Lighting System

History

SALUS Development History

Proof of Concept, July 2018

Hypothesis proven TRL 2 & 3

  • Control System Established: A 1:10 scale load is effectively stabilized using a single flywheel, brushed motor with driver, and an inertial measurement unit (IMU).
  • Load: ≈ 17.5 pounds
  • Reaction-wheel: self-machined
  • Data-logging: micro-SD card
  • Power supply: eight AA in series
  • IMU: 6050
  • Controller: Arduino UNO
  • Motor: AmpflowE30
Prototype I, December 2018

Scaling up TRL 4

  • Discharge Mesh: Steel cables extend from hoist hook to lift slings, with device suspended in-between; this allows static electricity to discharge from the helicopter
  • Protective Shell: A thick PVC shell protects internal hardware from environmental conditions
  • Load: 185 pounds
  • Reaction-wheel: self-milled
  • Telemetry: HC-06 Bluetooth Power supply: 2x 12V 10Ah LiPo in series
  • IMU: 6050
  • Controller: Arduino MEGA 2560
  • Motor: AmpflowA28
  • Chassis: Schedule 80 PVC
  • Monocoque bottom chassis cap added
Prototype II, April 2019

Cutting size & weight TRL 5

  • Discharge Mesh: Steel cables extend from hoist hook to lift slings, with device suspended in-between; this allows static electricity to discharge from the helicopter
  • Protective Shell: A thick PVC shell protects internal hardware from environmental conditions
  • Load: 185 pounds
  • Reaction-wheel: 11lb S/B Chevy Damper
  • Telemetry: HC-06 Bluetooth Data-logging: micro-SD card
  • Power supply: 25.1V 18Ah LiPo
  • IMU: 9250
  • Controller: Arduino MEGA 2560
  • Motor: AmpflowA28
  • Chassis: 1/8” wall-thickness polycarbonate
  • Shaft couplers: same-size flexible, rigid adaptable
Prototype III, November 2019

Improving hardware TRL 5

  • Customized Electronics: Custom PCB designed and manufactured to reduce size of electronics package
  • Improved Flywheel: Larger flywheel selected to increase angular momentum production
  • Load: 185 pounds
  • Reaction-wheel: 14lb S/B Chevy Damper
  • Telemetry: HC-05/HC-06 Bluetooth modules
  • Data-logging: micro-SD card
  • Power supply: 25.1V 18Ah LiPo
  • IMU: 9250
  • Controller: Arduino MEGA 2560
  • Electronics: custom MEGA shield
Prototype IV, November 2019

Increasing structural integrity TRL 6

  • Constrained Shaft: Extended shaft now constrained on both ends, for added structural integrity
  • Over the Air Programming:Software updates pushed remotely; telemetry reliability increased by switching from Bluetooth to WiFi
  • End-User Requested Features: Ergonomic handles, load illumination with Army ANVIS compatible infrared option, and remote kill switch added
  • Load: 600 pounds
  • Reaction-wheel: Dodge, 5.9L Harmonic Balancer
  • WiFi-based telemetry (for testing)
  • Data-logging: micro-SD card
  • Power supply: 25.6V 9.9Ah LFP-26650 cells
  • IMU: 9250
  • Controllers: ESP8266 Node MCU, Arduino Nano
  • Electronics: custom flood board, main board
  • Chassis: Carbon Fiber skinned Fiberglass

Production
Process

Project Timeline

2018

1

Basic principles observed and reported: Lowest level of technology rediness. Scientific research begins to be translated into applied research and development. Examples might include paper studies of technology’s basic properties.
2018

2

Technology concept and/or application formulated: Invention begins. Once basic principles are observed, practical applications can be invented. Applications are speculative and there may be no proof or detailed analysis to support the assumptions. Examples are limited to analytic studies.

3

Analytical and experimental critical function and/or
characteristic proof of concept: Active research and development is initiated. This includes analytical studies and laboratory studies to physically validate analytical predictions of separate elements of the technology. Examples include components that are not yet integrated or representative.

2019

4

Component and/or breadboard validation in laboratory environment: Basic technological components are integrated to establish that they will work together. This is relatively “low fidelity” compared to the eventual system. Examples include integration of “ad hoc” hardware in the laboratory.
2019

5

Component and/or breadboard validation in relevant environment. Fidelity of breadboard technology increases significantly. The basic technological components are integrated with reasonably realistic supporting elements so it can be tested in a simulated environment.

6

System/subsystem model or prototype demonstration in a relevant environment: Representative model or prototype system, which is well beyond that of TRL 5, is tested in a relevant environment. Represents a major step up in a technology’s demonstrated readiness.

2020

7

System prototype demonstration in an operational environment: Prototype near, or at, planned operational system. Reperesents a major step up from TRL 6, requiring demonstration of an actual system prototype in an operational environment such as an aircraft, vehicle, or space.
2020

8

Actual system completed and qualified through test and demonstration: Technology has been proven to work in its final form and under expected conditions. In almost all cases, this TRL represents the end of true system development. Examples include developmental test and evalauation of the system in its intended weapon system to determine if it meets design specifications.

9

Actual system proven through successful mission operations: Actual application of the technology in its final form and under mission conditions, such as those encountered in operational test and evaluation. Examples include using the system under operational mission conditions.

Contact

Interested in partnering or learning more about SALUS product?

Fill out the form or email us at info@salus-works.com and we’ll get back
to you as soon as possible.

Contact Us

Subscribe to Our Newsletter

Subscribe below to receive updates and stay connected with the SALUS team.
Twitter
Linkedin
Copyright © 2020 SALUS | Designed by WebChimpy
Scroll to Top