CHMD_Spec_3_Oct_2013_Rev_B_14_April_2016.pdf

PDF 1 MB Posted Apr 18, 2016

Attached to: Common Helmet Mounted Display (CHMD) Production
Solicitation number: W58RGZ-16-R-AS11
Issued by: Department of the Army Materiel Command Aviation and Missile Life Cycle Management Command

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AVNS-DTL-10868B

CAGE Code: 81996

DRAFT 13 April 2016

SUPERSEEDING

ANVS-DTL-10868A

27 AUG 2012

DETAIL SPECIFICATION

ITEM SPECIFICATION

FOR

THE AIR SOLDIER

Common Helmet Mounted Display

DISTRIBUTION STATEMENT A: Approved for public release; distribution unlimited.

DETAIL SPECIFICATION

ITEM SPECIFICATION

FOR THE

AIR SOLDIER

Common Helmet Mounted Display (CHMD)

Prepared for:

US Army Aviation and Missile Command

Redstone Arsenal, Alabama 35898

Prepared by:

Product Manager – Air Warrior (PM-AW)

Huntsville, Alabama 35806 iii

REVISION HISTORY

CHANGE RECORD

This sheet is a record of each issue of this document. When the revised document is issued, the previous issue is automatically superseded.

Version Date Configuration

Management

Pages

Changed

Reason for

Change

Initial Rel.

Rev. A

06/21/2012

08/27/2012

David Rabb

N/A

Pg. 10

N/A

Update to specification to clarify technical issues

Pg. 15

Pg. 35

Remove Ozone from list of battlefield contaminants

Change verification method from test to analysis

Rev. B Steve Sanders 11 Para. 3.6.1.3, Update to altitude requirements.

Para. 3.6.8, Update to altitude requirements.

31 Para. 4.6.1.3, Update to altitude requirements.

Para. 4.6.7, Add additional verification method (analysis).

Para. 4.6.8, Update to altitude requirement.

11-12,22,&

31-32

Pg.12

Clarified Horizontal and Vertical

Change of KHz to kHz

Para 3.6.10, Updated Vibration

Requirement

Par 4.6.7, added “analysis” as a verification methodology

Para 4.6.10, Updated Vibration

Requirement

Para. 4.6.8, increased altitude requirement for Combined

Environmental Effects

DETAIL SPECIFICATION, ITEM SPECIFICATION FOR THE

AIR SOLDIER COMMON HELMET MOUNTED DISPLAY

Document Number:

AVNS-DTL-10868

Version Date Configuration

Management

Pages

Changed

Reason for

Change

45-46

VCRM table, updated requirement

3.6.7 to allow Analysis

Replaced Cable Interface diagram, Fig

A-2

Updated Table A-IV

49-50

Appendix A

Modified A.2.3.1

Added A.2.3.2.1 and A.2.3.2.2

Added Fig A-3 and A-4

Added Table A-VII and Table A-VIII

Added Appendix A

DETAIL SPECIFICATION, ITEM SPECIFICATION FOR THE

AIR SOLDIER COMMON HELMET MOUNTED DISPLAY

Document Number:

AVNS-DTL-10868

Table of Contents

1.0 SCOPE

1.1 Background

1.2 Item description

2.0 APPLICABLE DOCUMENTS

2.1 General

2.2 Government documents

2.2.1 Specifications, standards, and handbooks

2.2.2 Other Government documents, drawings, and publications

2.3 Non-Government publications

2.4 Order of precedence

3.0 REQUIREMENTS

3.1 Physical characteristics

3.1.1 Weight

3.1.2 Center of Mass

3.1.3 CHMD Type

3.1.4 Impact Protection

3.2 Marking & Identification

3.3 Performance Characteristics

3.3.1 Transmittance

3.3.2 Color

3.3.3 System Resolution

3.3.4 Field of View (FOV)

3.3.5 Luminance

3.3.6 Contrast to the Eye

3.3.7 Exit Pupil/Eye Box

3.3.8 Latency

3.3.9 Focus

3.3.10 Combiner Prismatic Deviation

3.3.11 Combiner Refractive Power

3.3.12 Combiner Optical Distortion

3.3.13 Combiner Haze

3.3.14 ANVIS Compatibility

3.3.15 Flicker/ Jitter

3.3.16 CHMD Luminance Uniformity

3.3.17 CHMD Linear Distortion

3.3.18 CHMD Field Curvature

3.3.19 CHMD Contrast Transfer Function (CTF)

3.3.20 Day/Night Transition

3.4 Night Vision Compatibility

3.5 Interfaces

3.5.1 HGU-56/P Helmet and ANVIS Interface

3.5.2 ASDC Interface

3.6 Environmental Performance

3.6.1 Temperature

3.6.2 Blowing Dust

3.6.3 Dripping Rain

3.6.4 Blowing Rain

3.6.5 Salt Fog

3.6.6 Humidity

3.6.7 Fungus

3.6.8 Combined Environmental Effects

3.6.9 Mechanical Shock

3.6.10 Vibration

3.6.11 Explosive Atmosphere

3.6.12 Electromagnetic Interference (EMI)/ Electromagnetic Compatibility (EMC).

3.6.13 Electrostatic Discharge (ESD)

3.7 Integrated Logistics Support (ILS)

3.7.1 Reliability and Maintainability (R&M)

3.7.2 Maintenance

3.8 Manpower & Personnel Integration (MANPRINT)

3.8.1 System Safety

3.8.2 Health Hazards

3.8.3 Human Factors Engineering

3.9 Materials

3.9.1 Resistance to Battlefield Contaminants

4.0 VERIFICATION

4.1 Physical Characteristics

4.1.1 Weight

4.1.2 Center of Mass

4.1.3 CHMD Type

4.1.4 Impact Protection

4.2 Marking & Identification

4.3 Performance Characteristics

4.3.1 Transmittance

4.3.2 Color

4.3.3 System Resolution

4.3.4 Field of View (FOV)

4.3.5 Luminance

4.3.6 Contrast to the Eye

4.3.7 Exit Pupil/Eye Box

4.3.8 Latency

4.3.9 Focus

4.3.10 Combiner Prismatic Deviation

4.3.11 Combiner Refractive Power

4.3.12 Combiner Optical Distortion

vii

4.3.13 Combiner Haze

4.3.14 ANVIS Compatibility

4.3.15 Flicker/Jitter

4.3.16 CHMD Luminance Uniformity

4.3.17 CHMD Linear Distortion

4.3.18 CHMD Field Curvature

4.3.19 CHMD Contrast Transfer Function (CTF)

4.3.20 Day/Night Transition

4.4 Night Vision Compatibility

4.5 Interfaces

4.5.1 HGU-56/P Helmet and ANVIS Interface

4.5.2 ASDC Interface

4.6 Environmental Performance

4.6.1 Temperature

4.6.2 Blowing Dust

4.6.3 Dripping Rain

4.6.5 Salt Fog

4.6.6 Humidity

4.6.7 Fungus

4.6.8 Combined Environmental Effects

4.6.9 Mechanical Shock

4.6.11 Explosive Atmosphere

4.6.12 EMI/EMC

4.6.13 Electrostatic Discharge (ESD)

4.7 Integrated Logistics Support (ILS)

4.7.1 Reliability and Maintainability (R&M) and Durability

4.7.2 Maintenance

4.8 Manprint & Personnel Integration (MANPRINT)

4.8.1 System Safety

4.8.2 Health Hazards

4.8.3 Human Factors Engineering

4.9 Materials

4.9.1 Resistance to Battlefield Contaminants

5.0 PACKAGING

5.1 Packaging

6.0 NOTES

6.1 Intended Use

6.2 Government-furnished property

6.3 Acronyms and Abbreviations

viii

LIST OF TABLES

TABLE I: Diurnal cycle table TABLE II: Verification Cross Reference Matrix

TABLE A-III. Connectors Definition TABLE A-IV. HDM Pin Assignment TABLE A-V. OEM HDM Video Output Characteristics TABLE A-VI. CHMD XGA Video Output Characteristics TABLE A-VII. Brightness Commands

TABLE A-VIII. Manufacturing Data

LIST OF FIGURES

Figure 1 Helmet Display and Tracking System Block Diagram

Figure 2 USAARL Head Worn Mass Criteria for Neck Fatigue Figure 3 USAARL Head Worn Mass Criteria for Neck Injury

Figure 4 C.I.E. 1976 U.C.S. Chromaticity Diagram Figure 5: Representation of Horizontal and Vertical

Figure 6 System Resolution Test Pattern Figure 7 FOV Test Pattern Figure 8 Luminance Test Pattern

Figure 9 Contrast Test Pattern (Ls) Figure 10 Contrast Test Pattern (Lb)

Figure 11 24 Line Spoke Pattern Figure 12 Flicker/Jitter Test Pattern Figure 13 5x5 White Box Test Pattern

Figure 14 Linear Distortion Test Pattern

Figure 15 Field Curvature Test Pattern Figure 16 Air Force 1951 Medium Contrast Resolution Chart Figure A-1. DUI, HTK and CHMD Module Interface

Figure A-2. DIU, HTK and CHMD Interface Cables Figure A-3: Oscilloscope View of the Last Horizontal Line 37.8us

Figure A-4: CHMD Display Characteristics Figure A-5. I2C Protocol

APPENDIX

A HELMET DISPLAY AND TRACKING SYSTEM (HSDC) INTERFACE

CONTROL DOCUMENT (ICD)………………………………………….44

1.0 SCOPE

This specification defines the requirements for the Engineering and Manufacturing Development

(EMD) phase for the Common Helmet Mounted Display (CHMD). The CHMD is an advanced, see-through, high-definition, digital helmet mounted display (HMD) to support all Army Rotary

Wing platforms (except the AH-64D). The display is intended to replace the current Aviator’s

Night Vision Imaging System/Heads Up Display (ANVIS/HUD). The display will be integrated onto a HGU-56/P modified to include a magnetic head tracker and other head borne Aviation

Life Support Equipment (ALSE) equipment.

1.1 Background. Air Soldier is the next generation aircrew mission and protective ensemble that will replace the legacy Air Warrior (AW) system currently being used by Army rotary and select fixed wing aircrew members. Air Soldier encompasses all clothing and individual equipment worn or carried by the pilot and aircrew members, including ancillary aircraft mounted hardware and components, that serve the primary objectives of physiological sustainment, personal protection, and enhanced mission performance; while operating in all environmental and threat conditions, including crash and post crash escape, survival and evasion scenarios. The Air Soldier System (Air SS) consists of four subsystems that provide:

A fully integrated suite of personal electronics (PE) equipment that replaces stovepipe legacy components and provides improved data processing, control, and presentation technologies to reduce overall pilot workload while providing a minimum 30% reduction in weight and 70% reduction in bulk

A modular integrated helmet and display system (MIHDS) featuring increased crash and laser eye protection, enhanced durability, head tracking and a high resolution display.

A revolutionary personal protective clothing ensemble and gear carriage system that provides protection equal to or better then the legacy AW system, while providing a minimum 25% reduction in bulk and weight through a reduction in layering and utilization of active thermal regulation

A fully optimized man/machine interface that maximizes the use of wireless interfaces to enhance aircrew mobility and the ability to safely ingress/egress the A/C in all mission configurations

1.2 Item description. The CHMD is part of the Air Soldier Modular Integrated Helmet and Display System (MIHDS), more specifically the Helmet Display and Tracking System

(HDTS). The CHMD is a helmet mounted display system that overlays symbology onto a see-through display that allows the aviator to view pertinent flight parameters without looking down at aircraft instrumentation. The CHMD will receive power and information via an aircraft mounted Advanced Sight and Display Computer (ASDC). The CHMD will be mounted on the

HGU-56/P helmet and connected to the ASDC through a quick disconnect (QDC), Display

Interface Unit (DIU) and associated cables that are aircraft mounted. Figure 1 provides a block diagram that shows how the CHMD will integrate into the HDTS.

Figure 1 Helmet Display and Tracking System Block Diagram

2.0 APPLICABLE DOCUMENTS

2.1 General. The documents listed in this section are specified in sections 3, 4, or 5 of this specification. This section does not include documents cited in other sections of this specification or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified requirements of documents cited in sections 3, 4, or 5 of this specification, whether or not they are listed.

2.2 Government documents.

2.2.1 Specifications, standards, and handbooks. The following specifications, standards, and handbooks form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract.

DEPARTMENT OF DEFENSE SPECIFICATIONS

MIL-PRF-83282 Hydraulic Fluid, Fire Resistant, Synthetic Hydrocarbon Base, Metric, NATO Code Number H-537

MIL-PRF-87257 Hydraulic Fluid, Fire Resistant; Low Temperature, Synthetic

Hydrocarbon Base, Aircraft and Missile

A-A-52557 Fuel Oil, Diesel, for Posts Camps and Stations

MIL-DTL-5624 Turbine Fuel, Aviation Grades JP-4 and JP-5

MIL-DTL-32173 Gloves, Flyer's, Intermediate Cold, HAU-15/P

MIL-DTL-43511 Detail Specification Visors, Flyer’s Helmet, Polycarbonate

MIL-DTL-83133 Turbine Fuels, Aviation, Kerosene Types, NATO F-34 (JP-8), NATO F-35, and JP-8 + 100

MIL-PRF-7808 Lubricating Oil, Aircraft Turbine Engine Synthetic Base, NATO

Code 0-148

MIL-STD-3009 Lighting, Aircraft, Night Vision Imaging System (NVIS) Compatible, 02Feb2001

DEPARTMENT OF DEFENSE STANDARDS

MIL-STD-130 Identification Marking of U.S. Military Property

MIL-STD-461 Requirements for the Control of Electromagnetic Interference

Characteristics of Subsystems and Equipment

MIL-STD-464 Electromagnetic Environmental Effects Requirements for Systems

MIL-STD-882 System Safety

MIL-STD-810 Environmental Engineering Considerations and Laboratory Tests

MIL-STD-1472 Human Engineering

Copies of these documents are available online at https://assist.daps.dla.mil/quicksearch/.

https://assist.daps.dla.mil/quicksearch/

2.2.2 Other Government documents, drawings, and publications. The following other Government documents, drawings, and publications listed form a part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation or contract.

ADS-37A-PRF Aeronautical Design Standard, Electromagnetic Environmental

Effects (E3) Performance and Verification Requirements

SC 9999-01-SKO Consolidated Publication of Component Lists

NATICK/TR-91/040 1988 Anthropometric Survey of U.S. Army Personnel: Pilot

Summary Statistics.

USAARL Report 98-22 Optical and Biodynamic Evaluation of the Helmet Integrated

Display Sight System (HIDSS) for the RAH-66 Comanche

Development and Validation Program Phase.

1680-ALSE-100 HGU-56/P Helmet System

1680-ALSE-101 Helmet Assy

1680-ALSE-102 Additionally Authorized Items

1680-ALSE-105 Shell Sub Assy

1680-ALSE-112 Liner, Helmet Shock Absorbing

1680-ALSE-120 Lens, Inner

1680-ALSE-121 Lens, Outer

1680-ALSE-130 Thermoplastic Liner

1680-ALSE-192 Maxillofacial Shield

1680-ALSE-200 Dual Visor Assy

AIHS-FS-0002 1680-ALSE-101 Aircrew Integrated Helmet System Fabrication

Specification

MIL-PRF-A3279454A(CR) Performance Specification for Aviator’s Night Vision

Imaging System and AN/AVS-6(V)3

Copies of these documents are available from PM Air Warrior, 6726 Odyssey Drive, Huntsville, AL.

2.3 Non-Government publications. The following documents, drawings, and publications listed form a part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation or contract.

C.I.E. 1976 U.C.S. Chromaticity diagram

ASTM D 1003 Standard Test Method for Haze and Luminous Transmittance of

Transparent Plastics

ANSI/ISEA Z87.1 Industrial Eyewear Impact Standard

2.4 Order of precedence. Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

3.0 REQUIREMENTS

3.1 Physical characteristics.

3.1.1 Weight. The total head supported weight of the CHMD, mounting hardware, to include 12 inches of cable beyond the helmet, shall not exceed 1.05 lbs (0.476kg).

3.1.2 Center of Mass.

Center of Mass (Neck Fatigue) The CHMD total head borne weight and center of mass, when combined with the helmet, and other ancillary Aviation Life Support Equipment (ALSE) shall be compliant with the curve provided in Figure 2.

Figure 2 USAARL Head Worn Mass Criteria for Neck Fatigue

Center of Mass (Neck Injury) The CHMD total head borne weight and center of mass, when combined with the helmet and other ancillary Aviation Life Support Equipment (ALSE) shall be compliant with the curve provided in Figure 3, or the CHMD shall be frangible under an acceleration of 10G(±2G). The frangible components shall not come in contact with the wearer’s forehead, eye sockets, or facial regions during separation.

Figure 3 USAARL Head Worn Mass Criteria for Neck Injury

3.1.3 CHMD Type.

3.1.3.1 The CHMD shall have a see-through display monocular for the right eye

[Threshold (T)]; switchable to either eye or biocular [Objective (O)].

3.1.3.2 The CHMD shall support both day and night operation [T]; with a single display

[O].

3.1.4 Impact Protection.

3.1.4.1 Impact Protection, Headband and Crown. Modifications to the HGU-56/P helmet in order to accommodate the CHMD shall not degrade from the HGU-56/P’s impact requirements. The HGU-56/P limit peak deceleration to 150 G in the crown and 175 G in the headband area when subjected to impact velocities of 4.88 m/sec and 6.0 m/sec respectively.

3.1.4.2 Impact Protection, Ear. Modifications to the HGU-56/P helmet in order to accommodate the CHMD shall not degrade from the HGU-56/P’s impact requirements. The

HGU-56/P shall limit peak deceleration to 150 G in the earcup area when subjected to impact velocities of 6.0 m/sec.

3.2 Marking & Identification.

The CHMD shall include the nomenclature, part number, serial number, National Stock Number, the manufacturer’s CAGE Code, and Date of Manufacture stamped or silk-screened on the outside of each enclosure in accordance with (IAW) the requirements for markings in MIL-STD-

130. The data plate shall be marked with 2-D Item Unique Identification (IUID) data matrix, construct 2, encoded information. The IUID data matrix shall be no less than one centimeter (1

cm) wide and no less than forty percent (40%) in contrast. All applications shall be permanently affixed, as well as human and machine-readable.

3.3 Performance Characteristics.

3.3.1 Transmittance. The CHMD combiner shall have a D65 illuminant photopic transmittance of greater than 62 %, but not less than 75% for the P43 phosphor spectrum.

3.3.2 Color. The CHMD shall be capable of displaying tri-color (RGB) with 5 [T];

8 [O] addressable bits per color and a minimum color separation (Δu’ and Δv’) of 0.2 between each of the primes on the C.I.E. 1976 U.C.S. chromaticity diagram (Figure 4), where white balance falls within defined U.C.S. white locus.

Figure 4 C.I.E. 1976 U.C.S. Chromaticity Diagram

3.3.3 System Resolution. The CHMD shall provide a system resolution of 16 cycles/deg [T]; 18 cycles/deg [O].

3.3.4 Field of View (FOV). The CHMD shall have a field of view, at a physical eye relief of 25mm, equal to or greater than 22.5° vertical by 30° horizontal [T]; 30º vertical by 40º horizontal [O]. The FOV horizontal and vertical requirements are as seen by the pilot’s eye as shown in Figure 5.

Figure 5: Representation of Horizontal and Vertical

3.3.5 Luminance. Day and Night Luminance requirements are defined in 3.3.5.1 through 3.3.5.3.

3.3.5.1 Day Mode. The CHMD, if mounted inside the day visor, shall have an adjustable luminance from a minimum of ≤10 fL x combiner transmittance to a minimum peak of ≥1000 fL x combiner transmittance [T]; ≥2000 fL x combiner transmittance [O].

3.3.5.2 Day Mode. The CHMD, if mounted outside the day visor, shall have an adjustable luminance from a minimum of ≤10 fL x combiner transmittance to a minimum peak of ≥7000 fL x combiner transmittance [T]; ≥14000 fL x combiner transmittance [O].

3.3.5.3 Night Mode. The CHMD luminance setting shall be adjustable from maximum peak luminance of 50 fL ±5fL to a minimum of ≤0.01 fL.

3.3.6 Contrast to the Eye. The CHMD shall have a contrast at the eye greater than

100:1.

3.3.7 Exit Pupil/Eye Box. At a physical eye relief of 25mm, the CHMD exit pupil shall have a minimum diameter of 15mm.

3.3.8 Latency. The CHMD shall have a display latency of equal to or less than

1/frame rate. The minimum frame rate shall be at least 50 hertz.

3.3.9 Focus. The CHMD imagery shall be fixed at infinity (+0.00/-0.125 diopter)

[T]; adjustable (+0.125 to -1.0 diopter) [O].

3.3.10 Combiner Prismatic Deviation. Prismatic deviation stated herein includes the inherent prismatic power resulting from nonparallel surfaces of the material. The combiner prismatic deviation shall be no greater than 0.18 prism diopter vertical or horizontal.

3.3.11 Combiner Refractive Power. The refractive power shall not exceed ±0.125 diopters within the combiner field of view.

v ertical horizontal

3.3.12 Combiner Optical Distortion. The optical distortion within the combiner field of view shall conform to the acceptable standards shown on figure 2 of MIL-DTL-43511D.

3.3.13 Combiner Haze. The haze value of the combiner shall not exceed 2.0 percent.

3.3.14 ANVIS Compatibility. When used with the ANVIS goggles, the CHMD active display area shall be overlaid and centered within the ANVIS field of view.

3.3.15 Flicker/ Jitter. There shall be no visually discernable flicker/jitter of the imagery over the adjusted intensity range of the CHMD.

3.3.16 CHMD Luminance Uniformity. Non-uniformity in luminance of the CHMD shall be within ± X [T]; ±X/2 [O], from the mean. Where X=maximum half angle field of view

(diagonal measurement in degrees) x 1%.

3.3.17 CHMD Linear Distortion. Residual distortion shall be less than 4 % [T], ≤3% [O].

3.3.18 CHMD Field Curvature. The variation in focus across the full field of view shall deviate no more than 0.375 diopter [T]; 0.25 diopter [O].

3.3.19 CHMD Contrast Transfer Function (CTF). At the Nyquist frequency, the

CHMD shall have a modulation depth or a Michaelson contrast of ≥0.2 for both the vertical and horizontal orientation.

3.3.20 Day/Night Transition. The CHMD shall transition between day and night capabilities with no more than two hardware configuration changes and without interruption of the other pilot’s CHMD.

3.4 Night Vision Compatibility.

Any light emitted from the CHMD shall be compatible with a AN/AVS-6 (V)3, Class A night vision goggles (NVGs) as per the requirements of MIL-STD-3009.

3.5 Interfaces.

3.5.1 HGU-56/P Helmet and ANVIS Interface.

3.5.1.1 Tool Free Mounting. The CHMD shall be attachable to the helmet (Drawing

1680-ALSE-100) without the use of tools.

3.5.1.2 Stow/Deploy. The pilot shall have the capability to stow and deploy the

CHMD.

3.5.1.3 Quick Disconnect Capability. The CHMD shall have a quick disconnect capability.

3.5.1.4 CHMD Compatibility with Visors (Day Configuration). The CHMD in the day configuration shall be compatible with deploying of the helmet visors.

3.5.1.5 Non-Interference with Aviation Life Support Equipment (ALSE). The

CHMD shall not interfere with the operation of the M-45 mask, the PHODS and spectacles [T];

maxillofacial shield (Drawing Number 1680-ALSE-192) and the Joint Service Aircrew Mask

(JSAM) [O].

3.5.1.6 ANVIS Compatibility. The CHMD shall not affect the ANVIS (MIL-PRF-

A3279454A(CR)) eye relief or the 40 degree field of view.

3.5.1.7 ANVIS Look Around Compatibility. The CHMD shall not interfere with the look around capability of the AN/AVS-6 ANVIS.

3.5.1.8 ANVIS Attribute Compatibility. The CHMD shall not adversely affect the following ANVIS attributes: eyepiece lens focusing, objective lens focusing, interpupillary distance (IPD) adjustment, vertical fore/aft adjustment, tilt adjustment, automatic breakaway and flip-up/flip-down adjustments.

3.5.1.9 ANVIS Operation with Failed CHMD. In the event of failure of the CHMD there shall be no interference with the normal function of the ANVIS system.

3.5.2 ASDC Interface. The interface between the CHMD and the ASDC shall be

IAW the Appendix A (Helmet Display and Tracking System (HDTS) Interface Control

Document (ICD)).

3.6 Environmental Performance.

3.6.1 Temperature.

3.6.1.1 Operating Requirements. The CHMD shall operate according to the requirements of this specification in the temperature range of -25°F to +125°F.

3.6.1.2 Transport/Storage (Non-Operating). The CHMD shall perform according to the requirements of this specification after exposure to transportation and storage temperatures ranging from -80°F to +185°F.

3.6.1.3 Operating Requirement - Altitude. The CHMD shall perform according to the requirements of this specification during operations from Mean Sea Level (MSL) up to

25,000 feet elevation.

3.6.1.4 Transport (Non-Operating) - Altitude. The CHMD shall perform according to the requirements of this specification after being transported in its non-operating configuration

(with power not applied) at pressure altitudes from MSL up to 50,000 ft elevation.

3.6.1.5 Temperature Shock. The CHMD shall perform according to the threshold requirements of this specification after exposure to temperature shock from -80°F to +185°F for a minimum of 6 hours for a minimum of three temperature shock cycles.

3.6.2 Blowing Dust. The CHMD shall perform according to the requirements of this specification during and after exposure to blowing dust specified in MIL-STD-810, Method

510.5 Procedure I with the combiner and/or eyepieces covered.

3.6.3 Dripping Rain. The CHMD shall perform according to the requirements of this specification during and after being exposed to dripping rain at a rate of 280 l/m2/hr (7 gal/ft2/hr) for a minimum of fifteen (15) minutes.

3.6.4 Blowing Rain. The CHMD shall perform according to the requirements of this specification after exposure to blowing rain at a rate of 1.7 mm/min.

3.6.5 Salt Fog. The CHMD shall perform according to the requirements of this specification after exposure to salt fog conditions of 5% NaCl with a specific gravity of 1.027 to

1.034 with each cycle consisting of a 24-hour exposure to the salt fog environment, followed by a 24-hour dry time.

3.6.6 Humidity. The CHMD shall perform according to the requirements of this specification during and after exposure, while being operated, or following storage, in a humid environment from +86 oF to +140oF, with a relative humidity of 95% ( ± 4%) for a minimum of ten 24-hour cycles.

3.6.7 Fungus. The CHMD shall not support fungal growth when exposed to the fungi specified in MIL-STD-810, TABLE 508.6-I.

3.6.8 Combined Environmental Effects. The CHMD shall perform according to the requirements of this specification during and after exposure to the combined effects of an operational temperature of -25F to +125F, with a relative humidity of 30% to 95%, and in an altitude of Mean Sea Level (MSL) up to 25,000 feet elevation, for a minimum of ten cycles.

3.6.9 Mechanical Shock.

3.6.9.1 Transit Drop Shock. The CHMD shall perform according to the requirements of this specification after exposure to a transit drop shock environment incurred from 26 drops from a height of 48 inches ± 1.2 inches in its shipping container to a concrete surface.

3.6.9.2 Functional Shock. The CHMD shall perform according to the requirements of this specification during and after exposure to three shocks applied in each direction along three orthogonal axes of the CHMD for a maximum of 18 shocks with minimum peak acceleration of

20Gs, and with an effective duration (Te) of 15 to 23 ms, and a crossover frequency of 45 Hz.

3.6.10 Vibration. The CHMD shall perform according to the requirements of this specification during and after exposure to the vibration levels and durations specified in MIL-

STD-810, Method 514.6E-2 Procedure I CAT 24 for no less than 30 minutes per axis.

3.6.11 Explosive Atmosphere. The CHMD under normal operation at maximum loads and during switching power on and off (including quick disconnect) shall not ignite an explosive gaseous-air environment at both 14.667 Pounds per Square Inch Absolute (PSIA) and

5.083 PSIA.

Explosive atmosphere shall be defined for this requirement as a Volume of 95% n-hexane (ml) =

(4.27 X 10^-4) * Net Chamber Volume *Chamber Pressure/ (Chamber temp *.655).

3.6.12 Electromagnetic Interference (EMI)/ Electromagnetic Compatibility

(EMC).

3.6.12.1 EMI Emissions.

3.6.12.1.1 CE101. The CHMD shall comply with CE101 for EMI emissions IAW Figure

CE101-4, limit curve #2, 30 Hz to 10 kHz of MIL-STD-461.

3.6.12.1.2 CE102. The CHMD shall comply with CE102 for EMI emissions IAW Figure

CE102-1, 10 kHz to 10 MHz of MIL-STD-461.

3.6.12.1.3 RE101. The CHMD shall comply with RE101 EMI emissions IAW Figure

RE101-1, 30 Hz to 100 kHz of MIL-STD-461.

3.6.12.1.4 RE102. The CHMD shall comply with RE102 EMI emissions IAW Figure

RE102-3, 10 kHz to 18GHz of MIL-STD-461.

3.6.12.2 EMI Electromagnetic Susceptibility.

3.6.12.2.1 CS101. The CHMD shall meet all performance requirements when the input power line is exposed to interference levels of CS101, IAW Figure CS101-1, limit curve #2, 30

Hz to 150 kHz of MIL-STD-461.

3.6.12.2.2 CS114. The CHMD shall meet all performance requirements when all cable bundles and power lines are exposed to interference levels of CS114 IAW Figure CS 114-1, aircraft (Army Aircraft), limit curve #5, 10 kHz to 200 MHz of MIL-STD-461.

3.6.12.2.3 CS115. The CHMD shall meet all performance requirements when all cable bundles and power lines are exposed to a pre-calibrated signal having rise and fall times, pulse width, and amplitude as specified in MIL-STD-461, Figure CS115-1 at a 30 Hz rate for one minute.

3.6.12.2.4 CS116. The CHMD shall meet all performance requirements when all cable bundles and power lines are exposed to interference levels IAW CS116 Figures CS116-2, 10 kHz to 100 MHz of MIL-STD-461.

3.6.12.2.5 RS101. The CHMD shall meet all performance requirements when all sides of the CHMD and all cables are exposed to a magnetic field IAW RS101 Figure RS101-2, U.S.

Army limit, 30 Hz to 100 kHz of MIL-STD-461.

3.6.12.2.6 RS103. The CHMD shall demonstrate no evidence of degradation of performance when the unit and associated cables are exposed to electric fields of 200 Volts per meter over the frequency range of 2 MHz to 40 GHz using the modulations shown in ADS-37A-

PRF, Table I parts A and B.

3.6.12.3 Electromagnetic Compatibility (EMC). The CHMD shall perform according to the requirements of this specification, without causing the CHMD or aircraft subsystems and equipment from meeting their specified performance requirements while operated simultaneously with any single or multiple combinations of aircraft subsystems and equipment, including ground support equipment, for all modes of operation for each subsystem and equipment required to complete the mission.

3.6.12.4 Electromagnetic Vulnerability (EMV). The CHMD shall meet all performance requirements when exposed to the worldwide electromagnetic environment defined in Table I, parts A and B, of ADS-37A-PRF. This requirement shall include electromagnetic energy coupled to the aircraft through ground support equipment, aerial re-fuelers, and any other equipment external to the aircraft.

3.6.13 Electrostatic Discharge (ESD). The CHMD shall meet all performance requirements during handling or operations associated with exposure to ESD.

3.7 Integrated Logistics Support (ILS).

3.7.1 Reliability and Maintainability (R&M).

3.7.1.1 Mean Time Between Failures (MTBF). The CHMD shall provide a MTBF of no less than 4000 hours.

3.7.1.2 Mean Time To Repair (MTTR). The CHMD shall provide a MTTR of no greater than 0.5 hours at Aviation Unit Maintenance (AVUM) Level.

3.7.1.3 Maintenance Ratio (MR). The CHMD shall provide a MR of no more than

0.059 maintenance man-hours per operating hour.

3.7.2 Maintenance.

3.7.2.1 Special Tools/Support Equipment. The CHMD shall require no new, unique, or special tools, or support equipment for CHMD maintenance. Current Aviation Life

Support Equipment tools and support equipment are identified in SC 9999-01-SKO.

3.7.2.2 Aviation Maintenance Concept. The CHMD shall be maintained by the two-level Aviation Maintenance Concept of AVUM and Contractor Logistic Support (CLS) depot for selected components. The CHMD shall require no in-field intermediate maintenance actions.

3.7.2.3 Army Organic Maintenance System. The CHMD shall be maintainable within the structure of the standard Army Organic Maintenance System with functions including:

cleaning, inspection, functional checkout, and repair (consisting of limited piece part replacement). The CHMD shall not require a new Military Occupational Specialty be established. The CHMD shall not increase the current manning levels of the maintenance function.

3.8 Manpower & Personnel Integration (MANPRINT).

3.8.1 System Safety. The CHMD shall comply with the safety requirements of

MIL-STD-882.

3.8.2 Health Hazards. The CHMD shall not expose personnel to the following health hazards associated with: mechanical forces including shock and vibration; pressures; toxic allergenic, pathogenic organisms, or irritating substances; ionizing or non-ionizing radiation;

noise or other emissions; combustion products; trauma; or extreme temperatures and humidity.

The CHMD shall not introduce hazards throughout anticipated climatic conditions, either in operation, or maintenance support IAW the requirements for safety and health in MIL-STD-882.

3.8.3 Human Factors Engineering. The CHMD shall comply with the human engineering design criteria of MIL-STD-1472.

3.8.3.1 The CHMD shall have a minimum physical eye relief (i.e., eye clearance) of 15 mm.

3.8.3.2 The CHMD shall not increase the risk of injuries to pilot or aircrew members during crash or hard landing profiles.

3.8.3.3 The CHMD controls shall not be susceptible to inadvertent activation.

3.8.3.4 The CHMD shall be donned or doffed in less than 30 seconds [T]; 15 seconds

[O].

3.8.3.5 The CHMD controls shall be identifiable and meet human size and strength limitations by aircrew member with and without Intermediate Cold, HAU-15/P Flyer’s Glove

MIL-DTL-32173 IAW section 5.1 “Controls” of MIL-STD-1472. Arrangement, size, shape, spacing, and grouping of the controls shall permit tactile identification and use under all light conditions, with and without gloves.

3.8.3.6 The CHMD connectors shall be keyed to prevent incorrect insertion.

3.8.3.7 The CHMD shall not impede the aircrew member’s ability to ingress/egress in normal operations, snag/interfere with components, or impede the ability for each aircrew member to emergency egress the aircraft within 30 seconds using half the exits.

3.8.3.8 The CHMD shall accommodate and be operable by the anthropometric range of 5th percentile female pilot to 95th percentile male pilot as defined in Natick/TR-91/040, 1988

Anthropometric Survey of U.S. Army Personnel: Pilot Summary Statistics.

3.8.3.8.1 The CHMD shall allow for fore-aft adjustment range of at least 15 mm.

3.8.3.8.2 The CHMD shall allow for interpupillary adjustment of 55 mm to 72 mm.

3.8.3.8.3 The CHMD shall allow for vertical adjustment range of at least 15 mm.

3.8.3.9 Visible, infrared, RF, optical/radar cross section and noise signatures of the

CHMD components shall be detected less than 10% of the time.

3.9 Materials.

3.9.1 Resistance to Battlefield Contaminants. The CHMD shall perform according to the requirements of this specification, during and after a 24-hour exposure to any of the battlefield contaminants listed below:

MIL-PRF-83282, Hydraulic Fluid, Fire Resistant, Synthetic Hydrocarbon Base, Metric, NATO Code Number H-537

MIL-PRF-87257, Hydraulic Fluid, fire Resistant; low temperature, synthetic hydrocarbon base, aircraft and missile

A-A-52557, Fuel Oil, Diesel; For Posts, Camps and Stations

MIL-DTL-5624, Turbine Fuel, Aviation Grades JP-4 and JP-5

MIL-DTL-83133, Turbine Fuel, Aviation, Kerosene Types, NATO F-34 (JP-8), NATO F-35, and JP-8 + 100

MIL-PRF-7808, Lubricating Oil, Aircraft Turbine Engine Synthetic Base

Methylethyl Ketone

Varsol Naphtha

M291/M295, NBC Cleaner Kit

Engine Waterwash Solution R-MC-G-21-Premix, (P/N 4070)

4.0 VERIFICATION

This section establishes the verification requirements to verify the Section 3 requirements. The verification methods shall be those shown in the Verification Cross Reference Matrix, TABLE

II. Verification methods shall be limited to the following.

Method Description

Analysis Involves a technical evaluation of design information such as equations, charts, graphs, drawings, schematics, and other data. If actual tests were conducted for a related or unrelated purpose, and utilization of these data will prove that requirement has been met, it should be considered “analysis”. Analysis methods include the use of modeling and simulation with a government-accredited model.

Demonstration Observable functional operation, under controlled conditions not requiring subsequent analysis of data, is used to verify that a given requirement is met.

Examination An element of verification and inspection consisting of investigation, without the use of special laboratory appliances or procedures, of items to determine conformance to those specified requirements which can be determined by such investigations. Examination is generally nondestructive, and typically includes the use of sight, hearing, smell, touch, and taste; simple physical manipulation;

mechanical and electrical gauging and measurement; and other forms of investigation.

Test Involves observation or recording of data during operation of an item. Where

“test” is the designated verification method, it is understood that some degree of analysis is inherent in the verification process and need not be so identified on the verification cross-reference matrix.

4.1 Physical Characteristics.

4.1.1 Weight. Verification of requirement 3.1.1 shall be by examination.

4.1.2 Center of Mass.

4.1.2.1 Center of Mass (Neck Fatigue). Verification of requirement 3.1.2.1 shall be by test in a lab environment in accordance with the procedures identified in USAARL Report 98-

22. Center of Mass shall be verified in both a day configuration and a night configuration. Both configurations shall be done on a medium size HGU-56/P helmet. The day configuration shall be defined as: medium HGU-56/P with dual visor assembly and ANVIS mount, CEPS, and the

CHMD and mounting hardware in the deployed configuration. Cabling for the communications and the CHMD shall be cut 12 inches beyond the edge of the helmet. The night configuration shall be the same as the day configuration but with the addition of a deployed set of ANVIS and low profile battery pack attached via hook and loop to the rear of the helmet.

4.1.2.2 Center of Mass (Neck Injury). Verification of requirement 3.1.2.2 shall be by test in a lab environment in accordance with the procedures identified in USAARL Report 98-

4.1.3 CHMD Type.

4.1.3.1 Verification of requirement 3.1.3.1 shall be by demonstration that the display is see-through, monocular and mountable to the right eye or that the display is biocular and mountable to either eye.

4.1.3.2 Verification of requirement 3.1.3.2 shall be by demonstration that the CHMD operates in day mode and in night mode.

4.1.4 Impact Protection.

4.1.4.1 Impact Protection, Headband and Crown. Verification of requirement

3.1.4.1 shall be by test in a lab environment in accordance with AIHS-FS-0002. The

Government reserves the right to define the impact location based on the design of the CHMD.

4.1.4.2 Impact Protection, Ear. Verification of requirement 3.1.4.2 shall be by test in a lab environment in accordance with AIHS-FS-0002. The Government reserves the right to define the impact location based on the design of the CHMD

4.2 Marking & Identification. Verification of requirement 3.2 shall be by examination to show that the nomenclature, part number, serial number, NSN, the manufacturer’s CAGE

Code and date of manufacture is stamped or silk-screened on the outside of the CHMD IAW

MIL-STD-130. Verification of the data plate marked with a 2-D Item Unique Identification

(IUID) data matrix encoded information IAW paragraph 3.2 shall be by demonstration using

IUID scanning.

4.3 Performance Characteristics.

4.3.1 Transmittance. Verification of see-through transmittance (TP) as required in

3.3.1 shall be by test for light with a 6500K color temperature (SD65) and for the color spectrum of a P43 phosphor (SP43) (i.e., ANVIS light output). Using a broad band calibrated light source

(e.g., tungsten), measure the light transmittance with a calibrated spectrophotometer over the range from 380nm to 720nm (in a minimum of 10nm increments) where light transmittance is defined as filtered light/unfiltered light. Once the transmittance is calculated for a broadband light source, the photopically weighted D65 light spectrum is calculated by multiplying the D65 spectrum with the normalized visual response function (Vλ) spectrum and using this spectrum with the measured broadband transmittance (TC) of the see-through combiner.

𝑻𝑷𝑫𝟔𝟓 =

∫ 𝑺𝑫𝟔𝟓(𝛌) ∗ (𝐕𝛌) ∗ 𝑻𝑪(𝛌)𝒅𝛌

𝟕𝟐𝟎𝒏𝒎

𝟑𝟖𝟎𝒏𝒎

∫ 𝑺𝑫𝟔𝟓(𝛌) ∗ (𝐕𝛌)

𝟕𝟐𝟎𝒏𝒎

𝟑𝟖𝟎𝒏𝒎 𝒅𝛌

𝑻𝑷𝑃43 =

∫ 𝑺𝑷𝟒𝟑(𝛌) ∗ (𝐕𝛌) ∗ 𝑻𝑪(𝛌)𝒅𝛌

𝟕𝟐𝟎𝒏𝒎

𝟑𝟖𝟎𝒏𝒎

∫ 𝑺𝑷𝟒𝟑(𝛌) ∗ (𝐕𝛌)

𝟕𝟐𝟎𝒏𝒎

𝟑𝟖𝟎𝒏𝒎 𝒅𝛌

4.3.2 Color. Verification of threshold requirement 3.3.2 shall be by demonstration in a lab environment. Verification of objective requirement 3.3.2 shall be by test through the use of a calibrated colorimeter. Drive the display to maximum day and maximum night luminance for each of the three prime red, green, blue color channels, measuring u’ and v’ coordinates for each color prime. Compute Δu’ and Δv’ as the vector distance between each of the primes.

Drive the display to full red, green, blue and measure the u’ and v’ coordinates and verify white coordinates fall within the U.C.S. locus for white.

4.3.3 System Resolution. Verification of requirement 3.3.3 shall be by test in a lab environment. The display test patterns consist of repeating three pairs of one on, one off lines followed by three off lines, both vertical and horizontal as shown in Figure 6. A technical observer with 20/20 Snellen acuity or better in both eyes with the eye positioned in the exit pupil determines if the three line pattern can be discerned throughout the field of view. The vertical and horizontal resolutions in cycles/degree are determined by the number of (visible display pixels/2)/FOV in degrees. If the single pixel lines cannot be discerned throughout the field of view, then the three line pattern is generated using two pixel widths on and two pixel widths off, which halves the calculated resolution. The display brightness at the center should be initially set at 10 fL, +/- 5 fL, with either a uniform field or with a checker pattern target. The limiting resolution shall also be determined with the display brightness set at least ¾ of the maximum or higher. Observer may use up to a 2 ND filter (10 percent neutral transmission) for these observations to avoid any discomfort.

Figure 6 System Resolution Test Pattern

4.3.4 Field of View (FOV). Verification of requirement 3.3.4 shall be by test in a lab environment. Equipment shall include any angle measuring device such as a theodolite or an angular measuring apparatus with azimuth and elevation outputs in degrees combined with a telescope or camera with cross hairs and a 5 mm or smaller entrance pupil. The device should have output increments of 1/3 degree or less. The FOV could also be determined subjectively with a technical observer’s eye positioned in the display eye box and the FOV limits marked on a background at least one meter away from the display. The FOV is calculated as a trigonometric function from the location of the pupil of the observer. The FOV should be measured with a test pattern using an image that marks the outer edge of the display with a one or two-pixel box. This box should contain a centered vertical and centered horizontal lines, one or two pixels wide each, crossing through the center of the box and the display as shown in Figure 7.

Figure 7 FOV Test Pattern

The distances from center point “E” to B, D, F, and H are measured. The vertical FOV is calculated as the average of the measured distances from B to H and the average of (A to G) and

(C to I):

Vertical FOV =

BH +

AG + CI

The horizontal FOV is measured and calculated in the same manner:

Horizontal FOV =

DF +

AC + GI

If the CHMD FOV is not rectangular such as circular, elliptical, or clipped diagonals, then sufficient angular measurements from the center of the display should be taken to determine the shape, dimensions and area of the FOV.

4.3.5 Luminance. Verification of requirement 3.3.5 shall be by test in a lab environment. Set the laboratory ambient lighting such that the ambient illumination measured through the CHMD is reduced to less than 0.001 fL. Luminance measurement shall be performed by a calibrated spot photometer with a 5 +/-0.5 mm aperture at the photometer entrance pupil position. Measure a standard, preferably a calibrated light source, with and without the 5mm aperture to determine the correction factor to calculate the absolute CHMD luminance. The photometer entrance pupil is positioned at 25+/-3mm from the optical element closest to the design eye position along and perpendicular to the CHMD optical axis where the

CHMD optical axis is defined in the optical design as the chief ray traced from the center of the

CHMD image source through the CHMD optics. Using a video generator capable of driving the

CHMD display per the video electrical interface requirement, generate the luminance test pattern. The luminance test pattern consists of a square white box on a black background in which the area of the white box is 10-15% of the total display active area, as shown in Figure 8, and all pixels within the white box region are driven to full on (video drive level set to 255 DN) and all pixels values in the black background set to full off (video drive level set to 0 DN). With

A B C

D E F

G H I the CHMD brightness adjustment set to the appropriate maximum or minimum adjustment position, rotate the CHMD or spot photometer about the center of the spot photometer entrance pupil until the spot photometer measurement field is fully contained and nominally centered the white box region. Measure and record the luminance of the white box region in accordance with the procedures described in 4.3.5.1, 4.3.5.2, 4.3.5.3.

4.3.5.1 Day Mode Luminance. Verification of requirement 3.3.5.1 shall be by test in a lab environment. Set the CHMD to “Day” mode. Using the video generator adjust position of the white box in the black background, as shown in Figure 8, to correspond with the lowest luminance CHMD field position determined in the luminance uniformity test performed in

4.3.12. Adjust the spot photometer to measure the luminance of the white box. Set the CHMD brightness control to maximum and record the value as minimum peak luminance. Using the video generator adjust position of the white box in the black background to the CHMD field position corresponding to the highest luminance field position determined in the luminance uniformity test in 4.3.12. Adjust the spot photometer to measure the luminance of the white box.

Visually verify that the white box can still be seen against the black background. If the white box is not visible adjust the CHMD brightness control the next incremental step higher until the white box becomes visible. Measure and record the luminance as the minimum luminance.

4.3.5.2 Day Mode Luminance. Verification of requirement 3.3.5.2 shall be by test in a lab environment. Set the CHMD to “Day” mode. Using the video generator adjust position of the white box in the black background, as shown in Figure 8, to correspond with the lowest luminance CHMD field position determined in the luminance uniformity test performed in

Visually verify that the white box can still be seen against the black background. If the white

4.3.5.3 Night Mode Luminance. Verification of requirement 3.3.5.3 shall be by test in a lab environment. Set the CHMD to “Night” mode. Using the video generator adjust position of the white box in the black background, as shown in Figure 8, to correspond with the lowest luminance CHMD field position determined in the luminance uniformity test performed in

Visually verify that the white box can still be seen against the black background. If the white

Figure 8 Luminance Test Pattern

4.3.6 Contrast to the Eye. Verification of requirement 3.3.6 shall be by test in a lab through the CHMD is reduced to less than 0.001 fL. Luminance measurement shall be performed by a calibrated spot photometer with a 5 +/-0.5 mm aperture at the photometer entrance pupil position. The photometer entrance pupil is positioned at 25+/-3mm from the optical element closest to the design eye position along and perpendicular to the CHMD optical axis where the CHMD optical axis is defined in the optical design as the chief ray traced from the center of the CHMD image source through the CHMD optics. Using a video generator capable of driving the CHMD display per the video electrical interface requirement, generate the

Contrast Test Pattern (Ls) (Figure 9). With the CHMD brightness adjustment set to the maximum adjustment position, move the CHMD or spot photometer about the center of the spot photometer entrance pupil until the spot photometer measurement field is fully contained and nominally centered in the white box region. Measure and record the luminance of the white box region as Ls. Leaving the photometer measurement field in the same viewing position within the display active region, change the test pattern to the Contrast Test Pattern (Lb) (Figure 10).

Measure and record the luminance of the center of the black region as Lb.

Compute the contrast ratio as:

𝐶𝑟 = 𝐿𝑠

𝐿𝑏

Figure 4.3.5 Luminance Test Pattern

Display Active Area Horizontal Pixels (M)

Background Pixel Values: 0 DN

Foreground Pixel Values: 255 DN

Background

Foreground

M/10

Figure 9 Contrast Test Pattern (Ls)

Figure 10 Contrast Test Pattern (Lb)

4.3.7 Exit Pupil/Eye Box. Verification of requirement 3.3.7 shall be by test in a lab environment. The eye motion box (exit pupil size) can be defined by an optical ray trace diagram. In the laboratory the dimensional limits of the eye box shall be verified and determined

Figure 4.3.5a Contrast Test Pattern (Ls)

Display Active Area Horizontal Pixels (M)

Background Pixel Values: 0 DN

Foreground Pixel Values: 255 DN

Background

Foreground

M/10

M/2

D is p la y A c ti v e

A re a V e rt ic a l P ix e ls

N/2

Figure 4.3.6b Contrast Test Pattern (Lb)

Display Active Area Horizontal Pixels (M)

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