DTIC ADA262524: Test and Evaluation Report of the Airborne Life Support Systems Infant Transport Incubator, Model 20-H

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by  Defense Technical Information Center

USAARL Report No. 93-7
AD-A262 524
Test and Evaluation Report
of the Airborne ;.Ufe Support Systems
Infant Transport Incubator, Model 20-H
By
Brendan E. Squire (Project Officer)
James E. Bruckart (Project Officer)
Martin D. Ouattlebaum (Project Officer)
Blodynamics Research Division
fl ICr
and(cid:127) "L FC.T Pr
and
Bill Olding (UES, Inc.) PýR0 7 1993
Reproduced From
Best Available Copy
. 98 4 06 1-15 93-07269
(
January 1993
Appoed for public release; distrlbttloi unlimfted.
United States Army Aeromedical Research Laboratory
Fort Rucker, Alabama 36362-5292
NoiQce
Qxpalified reaueste-ra
Qualified requesters may obtain copies from the Defense Technical
Information Center (DTIC), Cameron Station, Alexandria, Virginia
22314. Orders will be expedited if placed through the librarian
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Disposition
Destrcy this document when it is no longer needed. Do not return
it to the originator.
Discl.aimer
The views, opinions, and/or findings contained in this report are
those of the author(s) and should not be construed as an official
Department of the Army position, policy, or decision, unless so
designated by other official documentation. Citation of trade
names in this report does not constitute an official Department
of the Army endorsement or approval of the use of such commercial
items.
Reviewed:
H V. BARSON
LTC, MC, SFS
Director, Biodynamics
Research Division
Released for publication:
D.. Ph.D. DAVID H. KARNE
Chrman, Scientific Colonel, MC, S S
eview Committee Commanding
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No. DAMD 17-86-C-6215
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PROGRAM PROJECT TASK WORK UNIT
ELEMENT NO. NO. NO. JACCESSION NO.
.0603807A 3M463807D8 6 LC 201
11. TITLE (Include Se.urrty Clawtfication)
Test and Evaluation Report of the Airborne Life Support Systems Infant Transport Incubator,
Model 20-H
12. PERSONAL AUTHOR(S)
Brendan E. Squire, James E. Bruckart, Martin Quattlebaum, and Bill Olding
I)&. TYPE OF REPORT 13b. TIME COVERED 4. DATE OF REPORT (Year, Month, Day) IS. PAGE COUNT
Final I FROM _ TO 1993 January 67
16. SUPPLEMENTARY NOTATION
17. COSATI CODES 1. SUBJECT TERMS (Continue on reverse of necessary and identify by block number)
FIELD GROUP SUB-GROUP Electromagnetic compatibility, test and evaluation,
01 03 aeromedical equipment
14 02
19, ABSTRACT (Continue on reverse if neceSsary and idenvfy by block number)
The Airborne Life Support Systems Infant Transport Incubator, Model 20-H, was tested for
environmental and electromagnetic interference/compatibility in the UH-60A helicopt.-r under
the U.S. Army Program for Testing and Evaluation of Equipment for Aeromedical Operations.
The tests were conducted using current military and industrial standards and procedures fo
environmental tests and electromagnetic interference/compatibility and human factors. The
Airborne Life Support Systems Infant Transport Incubator, Model 20-H, was found to be compa
!ble with the U.S. Army MEDEVAC UH-60 Black Hawk.
Ci
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M UNCLASSIFIEDIUNLIMITED 0 SAME AS RPT. 0 DTIC USERS UNCLASSIFIED
228. NAIME OF RESPONSIBLE INDIVIDUAL 22b. TELEPHONE (Include Area Code) 22c. OFFICE SYMBOL
Chief, Scientific Information Center (205) 255-6907 SCRD-UAX-SI
DD Form 1473, JUN 86 Pmvlus editionso r* Obsolete. SECURITY CIA$SIFICATION OF THIS PAGE
UNCLASSIFIED
Table of contents
SECTION PAGE
1. EXECUTIVE DIGEST
1
1.1 Test objectives . . . . . . . . .-
1.2 Testing authority 1-2
1.3 scope 1-I2
1.4 Material description . . . . . . . . . . . . . .1-3
1.5 Summary . . . . . . . ... . . 1-3
1.6 Conclusion . . . . . . . . . . . . . . . 1-5
2. SUBTESTS
2.1 Initial inspection ....... ........ 2-1
2.2 Battery life evaluation . . . . . . . . . . . . . 2-1
2.3 Electrical safety evaluation . . . . . . . . . . 2-2
2.4 Human factors evaluation (laboratory) . . . . . . 2-3
2.5 Altitude (low pressure) test...*-.. .... 2-3
2.6 Vibration test ............ . ..... 2-4.
2.7 High temperature test . . . . . . . . . . . . .
2.8 Low temperature test . . . ........... 2-7
2.9 Humidity test .t.... .2-8
2.10 Electromagnetic characteristics test . . . . . . 2-9
2.11 In-flight human factors evaluation . . . . . . . 2-11
2.12 In-flight EMI/EMC characteristics test . . . . . 2-12
3. SUPPORTING DOCUMENTATION
3.1 Detailed test information. . . . . . . . . . . .3-1
3.2 Test data . . . . . . . . . . . . . . . . . . . . 3-3
i
3.3 Criteria, significant problems, and
suggested improvements . . . . . . . . . . . 3-36
3.4 References . . . . . . . . . . . . . . . . . . . 3-39
3.5 Abbreviations .................. 3-40
3.6 List of manufacturers. . . . . . . . . . . . . . .3-42
3.7 Distribution list . . . . . . . . 3-43
'9
A4oe u Fror "(cid:127)"
SDTIC TAB M
Justifticat ion. . .. -
Diatribution/
DsS peia
Availability Codes
IAvail sandor
Section 1. Exeu djgeJs
The Army program for Test and Evaluation of Aeromedical
Equipment uses existing military standards (MTL-STD) and collec-
tive professicnal expertise to teut and evaluate selected medical
equipment proposed for use aboard Army aircraft. Equipment
meeting these standards ensures the safety of the crew, patients,
and aircraft by eliminating risks due to: (1) Interference by
the medical equipment with aircraft systems/subsystems operation,
(2) the airczaft system's interference with the operation of the
medical equipment, (3) the medical equipment a susceptibility to
environmental exposure, or (4) physical and/or :unctional incom-
patibility while in use on board selected rotary-wing aircraft.
This program tests both developmental and nondevelopmental (off
the shelf) medical equipment destined foz use aboard Army medical
evacuation (MEDEVAC) aircraft.
1.1 TEST OBJECTIVES
1.1.1 To determine if the medical equipment is complete and
operational per the manufacturer's operating instructions.
1.1.2 To ensure the electrical safety of the medical equipment.
1.1.3 To ensure the equipment will function as designed through-
out the rated battery operation time.
1.1.4 To ensure the safety of the operator, the patient, and the
aircrew.
1.1.5 To assess design considerations which could potentially
contribute to an operator error.
1.1.6 To determine if the medical equipment can function as
designed in a low pressure environment.
S1..7 To determine the ability of the -medical equipment to with-
stand the vibrational stresses expected in a rotary-wing flight
environment without degradation or malfunction.
1.1.8 To determine the ability of the medical equipment to be
stored and operated in a high temperature environment.
1.1.9 To determine the ability of the medical equipment to be
stored and operated in a low temperature environment.
1.1.10 To determine the ability of the medical equipment to
operate satisfactorily for short periods during exposure to high
humidity conditians.
1-1
1.1.11 To assess the levels of electromagnetic emissions pro-
duced by the medical equipment within selected frequency ranges.
1.1.12 To assess the minimum electromagnetic susceptibility
levels of the medicý1 equipment within selected frequency ranges.
1.1.13 To assess the physical and/or functional compatibility of
the medical equipment while in use on board the aircraft.
1.1.14 To assess the electromagnetic interference (EMI) and
electromagnetic compatibility (EMC) characteristics of the
medical equipment with the host aircraft and its installed
systems.
1.2 TESTING AUTHORITY
Research and Technology Work Unit Summary, dated 5 October
1989. Project number 3M463807D836, titled, Army Program for
Testing and Evaluation of Eauipment for Aeromedical Operations.
1.3 SCOPE
1.3.1 This test was conducted at the United States Army Aeromed-
ical Research Laboratory (USAARL), Cairns Army Airfield (CAAF),
and designated test flight areas in and around Fort Rucker,
Alabama.
1.3.2 The USAARL UH-60A aircraft, serial number 88-26069, with
subsystems delineated in paragraph 3.2.2, was configured with the
Airborne Life Support Systems Infant Transport Incubator* (ALSS),
model 20-H and used as the test aircraft for the in-flight
evaluation. The in-flight evaluation required 3.0 flight hours.
1.3.3 Laboratory testing was accomplished at USAARL using
government furnished equipment (GFE) by Universal Energy Systems,
Inc. (UES), under contract No. DAMD 17-86-C-6215.
1.3.4 Prior to flight testing, the following tests were accom-
plished: Acceptance inspection, equipment training, electromag-
vrtic compatibility, humani factors and safety, environmental
compatibility, and in-flight compatibility.
1.3.5 An airworthiness release (AWR) dated 24 Feb 1992 was
received from the U.S. Army Aviation Systems Command (AVSCOM)
prior to the in-flight testing of the ALSS Transport Incubator.
i
* See list of manufacturers
1-2
1.4 MATERIAL DESCRIPTION
The Airborne Life Support Systems Transport Incubator 20-H
is an incubator system designed to maintain a stable thermal
environment for infants during intensive care and transport
applications. The transport incubator is one of six subcompo-
nents which make up the incubator system. The incubator may be
* operated from externally supplied 12 volts do and 105-125 volts
ac, 50/60 Hz power sources. An internal, 12 volts dc, 24 amp-
hour rechargeable sealed lead acid battery provides a rated 3
* hours operation on a fully charged battery.
The incubator is mounted on a modular cart-with four swivel
mounted rubber wheels. Wheel locks are installed on the two
front wheels. The cart frame is constructed of aluminum and has
provisions for mounting and securing two size "'M-60"1 oxygen
cylinders.
The lower module of the incubator (77.7 x 95.3 x 48.8 cm) is
secured to the cart by four metal latches located on the ends of
the module. The lower module houses the accessory power supply.
'The accessory power supply is rated at 105-125 Vac, 3 A with a 3-
amp circuit breaker and four accessory power outlets. The
remainder of the lower module houses various system accessories.
The upper module consists of the incubator, the incubator
control panel, and the incubator power supply. The remainder of
the upper module can house additional system accessories. Two
handles are mounted at each end of the upper module to maneuver
the incubator. The upper module is secured to the lower module by
fo ur metal latches located on the ends of the upper module.
The incubator has a removable double canopy plexiglass hood
which covers the infant compartment (71.12 cm 1 x 38.1 cm w x
27.94 cm, h). The front .f. the canopy consists of two 13.97 cm
diameter hinged circular doors mounted to a larger 22.9 cm x
53.34 cm hinged rectangular door to allow access to the infant
from the side. The canopy is secured by four lock pins located
on the side corners. Three sealed tubing portals 3.8 cm in
diameter are also located an the canopy front. A fourth hinged
trapezoidal access door is located on the left side panel of the
canopy to allow access to the infant's head dnd shoulders. A
five watt examination light is mounted outside the canopy on a
* flexible extension arm. The incubator is equipped with a remov-
able infant support platform that is secured to the unit by flip
type latches. The support platform includes a vinyl mattress pad
for infant comfort and protection.
The incubatox control panel is located on the center front
of the incubator cart., The panel controls power to the system,
by a labeled on/off toggle switch. Four green LED readouts on
1-3
the right side of the. panel indicate the power source used by the
system. The four lights are labeled BAT CHG, ac OP, dc OP, BAT
OP. A red LED below these lights is labeled LOW BAT and provides
a low battery warning. On the left hand side of the panel is a
series of four alarm indicators and a power fail warning indica-
tor. The four alarm LEDs are labeled HIGH TEMP, SYS FAIL, AIR
FLO, and SENS FAIL. The temperature within the canopy is con-
trolled by a microprocessor and a solid state heater. The
temperature is selected by a series of thumb wheel switches on
temperature control panel centered between the two rows of LEDs.
Below the thumbwheel selector switches is a red digital LED
readout of the temperature within the canopy calibrated to
degrees Celsius. The control panel has provisions for a skin
temperature probe and a momentary push button to show infant skin
temperature on the digital display. The control panel performs a
built-in test cycle when power is applied to the unit. During
the test all LEDs will illuminate, the digital display will show
83.8 and the alarm will sound. The test lasts approximately 2.5
seconds and the unit begins normal operation upon completion of
the test.
The incubator power supply unit has provisions for 105-125
(cid:127)Vac, 3 A and 12 VDC, 10 A power input connections. The unit has
-
six 105-12b Vac accessory power outlets with the combined current
drain for the six outlets rated at 3 A. The power supply has
four circuit breakerb, a 10 A battery, a 10 A external dc, a 3 A
incubator, and a 3 A accessory outlet.
1.5 SUMMARY
1.5.1 Initial Inspection
1.5.2 Battery Life Evaluation: The manufacturer specifies a
battery life up to 3 hours on a fully charged battery. Three
tests ware conducted using a fully charged battery for each
trial. The average operation time in testing was 4 hours, 51
minutes at room temperature (25 OC and 55% RH). The results
exceed the manufacturer specification.
* 1.5.3 Electrical Safety Evaluation: Grounding conductor resis-
tance was 57.8 mn. Maximum case leakage current was 3.5
microamperes. These measurements are within the standards
specified in TB-3e-750-2, April 1987.
1.5.4 Human Factors Evaluation: The ALSS Transport Incubator
20-H was found to be satisfactory in all categories of the
evaluation.
1.5.5 Environmental Tests: The ALSS 20-H can be expected to
perform in a variety of environmental conditions. Its perfor-
mance was found to be satisfactory in all stages of the
1-4
*/*
environmental testing except the high temprerature and low temper-
ature operation tests. When placed in a high temperature, the
high temperature alarm did not activate. This indicated the high
temperature alarm limit on this unit was not calibrated correctly
at 1000F. The unit was not able to maintain 90OF inside the
incubator when the ambient terperature was 320F. The incubator
temperature dropped to 730F. The requirements for environmental
tests are established in MIL-STD-810D, Methods 500.2 (altitude),
514.3 (vibration), 501.2 (high temperature), 502.2 (low tempera-
4 ture), and 507.2 (humidity).
1.5.6 Altitude (low pressure) Test: The ALSS Transport Incuba-
tor 20-H was found to be satisfactory in all categories of the
evaluation.
1.5.7 Vibration Test: The ALSS 20-H Incubator was not adversely
affected before, during or after exposer to the vibration test
signature.
1.5.8 High Temperature Test: One failure was noted during
testing. The temperature control for the Incubator was not able
to regulate the temperature in the canopy (set to 310C) during
exposure to the high temperatures reached during the test (490C).
There are no provisions to cool the air inside the canopy,
therefore the unit is unable to maintain canopy temperatures
below ambient. During the test the system correctly responded
with an overtemperature alarm condition.
1.5.9 Low Temperature Test: One failure occurred during test-
ing. The Incubator was unable to maintain the canopy temperature
set at 310C while the system was operating on battery power and
the chamber temperature was 0°C. The system was able to maintain
canopy temperature using ac power.
1.5.10 Humidity Test: The ALSS Transport Incubator 20-H was
found to be satisfactory in all categories of the evaluation.
1.5.11 Electro Magnetic Characteristics Test:
1.5.11.1 Conducted Emissions Test (CE01, CE02, and CE04):. The
unit produced narrowband (NB) emissions while operating on
external dc power. The system failures are listed below in
tabular format. No emissions that exceeded limits were detected
from the ALSS Transport Incubator during this test while the unit
was operated on ac or battery power.
EXTERNAL DC OPERATION: Conducted Emissions Failures
Fr (cid:127)Failugre Levels
30 - 78 Hz exceeded system measurement capability of dB
8.7 - 50 kHz 0.1 - 36.3 dB (NB)
5.78 - 50 kHz 0.1 - 35.6 dB (NB)
1-5