H-53K FLIR Competition Industry Day 1 Technical Brief.pptx

PMA-261 Industry Day Forward Looking Infrared Radar (FLIR) Competition

21 September 2023 Presented to: Industry Presented by: PMA-261, CH-53K Avionics IPT Naval Air Systems Command Procurement Group "DISTRIBUTION STATEMENT D. Distribution authorized to Department of Defense and U.S. DoD contractors only Administrative or Operational Use, (21 Sep 23). Other requests shall be referred to Program Executive Officer Air (PEO(A)), PMA-261, 47123 Buse Rd, BLDG 2272, Suite 155 Patuxent River, MD 20670."

CONTROLLED UNCLASSIFIED INFORMATION

Agenda Registration Ground Rules Opening Remarks Purpose Disclaimer Communications Program Overview Process Overview, Protocol and One-On-One Instructions Draft Technical Requirements Scope of the DRAFT Statement of Work Contract Structure Acquisition Schedule Questions and Feedback Breakout – one-on-one sessions

As of Date: 11 Sep 2023 Title of Brief: PMA-261 Forward Looking Infrared (FLIR) Industry Day Date of Brief: 21 Sep 23 Draft Technical Specifications

The following slides outline some draft requirements from the Technical Specification. This document, along with the technical content regarding the Statement of Work (SOW) and Contract Data Requirement Lists (CDRLs) are in draft form and the final version may be materially different from the documents discussed in today’s Industry Day.

The below requirements are listed in their threshold form. Objectives may be designated in the final specification. Specification document will list all requirements.

Overarching Technical requirements:

The system shall be a Forward Looking Infrared (FLIR) sensor mounted in a slewable stabilized turret with target detection and tracking, servo control, video processing, digital data processing and signal conditioning functions.

It operates in the 3 to 5 micron band and is suitable for various operating environments, including tropical.

The FLIR is configurable in a 1553B multiplex bus configuration.

The new system should be configured such that the system minimizes impacts to the aircraft and installation.

The system can be configured in either a turret with a supporting electronics unit or a fully self-contained system.

Mechanical Interface Turret unit shall mount utilizing current mounting space on the aircraft. Adapter interfaces, to allow this to happen, are acceptable.

The Turret and associated sub systems shall meet the static and dynamic mounting requirements of the platform.

Weight The maximum weight of each WRA is as follows:

The total system shall not exceed 106 pounds.

The Turret shall not exceed 60 pounds.

If a EU is present, it shall not exceed 46 pounds.

Dimensions The outline dimensions of each WRA shall not be larger than the following:

Turret Height: 15.5” Turret Width: 14 5/8” Turret Depth:9” (Depth to the bottom of the cowling) If an EU is part of the system, WRA outline dimensions shall not be larger than the following:

EU Height 8” EU Width 12” EU Depth 16.5”

Power AC Power The FLIR shall require a maximum of 670 Volt-Amp (VA) single-phase steady state, 731 VA peak, from input 115 VAC, 400 Hz power.

DC Power The FLIR shall require a maximum of 210-Watts steady-state input 28 VDC power. Peak power shall be less than 1000 Watts from unregulated 28VDC.

Overload Protection The equipment input power circuits will be overload protected by a circuit breaker in the aircraft. All parts and circuits of the equipment that are likely to carry an overload caused by incorrect adjustments shall be proportioned to withstand such overload without permanent damage to the equipment or shall have suitable protective devices.

Bonding Bonding methods shall not interfere with the installation or removal of the equipment.

Interfaces Analog Video Interface One analog video output meeting SMPTE ST 170M shall be provided. Unused analog video outputs shall be properly terminated.

Digital Video Interface A minimum of two Digital video outputs meeting SMPTE 292 shall be provided. Additional unused Digital video outputs shall be properly terminated.

Multiplexed Data Bus The FLIR shall communicate over the MIL-STD-1553B Mux BU (1553 Bus) per document 6450950-400_C.

Display Target Tracker The FLIR shall automatically track both stationary and moving targets within the FOV. The tracker mode shall be selectable by the operator. The Tracker shall be initiated by the operator when to track or not track.

The System shall provide at a minimum the following annotation:

Time of Day in ZULU time.

Calculated Position of Target within the center of the FOV Calculated Target Range White Hot/Black Hot FOV Setting Laser Arm Status Laser Firing Status Laser LRF or LTM Selection Tracker Selection Tracker Gate Box Next Narrow FOV Box

Display – Cont.

Aircraft Position Position of the aircraft with Altitude in Latitude and Longitude shall be provided.

Relative North Indicator A carrot, arrow or chevron indicating true north on the imagery shall be provided.

Target Location Position of the target (Center of the FOV) operator selectable between Latitude / Longitude .

System Settings Primary system setting shall be displayed to the operator.

Image Processing Mode System selection for image processing mode shall be displayed Image Polarity Image polarity as selected by the operator shall be displayed in the annotation. This is commonly referred to as white hot or black hot.

Symbology Declutter The System shall allow to the operator to declutter the symbology to different levels to reduce impacts to imagery.

Symbology Positioning The FLIR shall provide the capability to select between symbol positioning compatible

Operational Modes STANDBY Mode STOW position shall be provided to protect the turret windows. The Turret shall go to this position (nominally 180° in azimuth and 85° in elevation) upon receipt of a STOW command.

Look Ahead Mode The system shall be slewable to a fixed forward position upon being commanded to a LOOK AHEAD (LA) position. The LA position of the LOS (line-of-sight) shall be adjustable throughout a range of ±10° elevation and ±10° azimuth. The specific LA position shall be software controlled and stored and read from nonvolatile memo Rate or Inertial Mode In the RATE or INERTIAL mode, the FLIR shall be capable of being continuously slaved to and stabilized in space within the angular travel limits of the turret excluding azimuth angles in nadir (–90 ±10°) elevate.

Scan Mode The FLIR shall be capable of periodic and continuous inertial slewing in azimuth. A FOV change can be made while in this mode, with the resulting scan speed change appropriate for the FO Position Mode A POSITION servo mode shall permit the turret LOS to be manually directed with an external analog signal, or by 1553 bus command, and to be automatically maintained to any azimuth and/or elevation angle relative to the aircraft axes within the turret pointing angle limits, excluding azimuth angles in nadir (-90 ± 10° elevation) OFF Mode In the OFF mode, power to the FLIR shall be removed. When the FLIR is in the STOW position immediately prior to power-down, it shall remain in the STOW position after power-down.

Turret Unit Alignment The TU shall provide bushings for alignment pin engagement to allow indexing to a mounting reference datum (pins and pads) of less than or equal to 2 milliradians.

Performance Power up Readiness With the exception of the IR imaging function, the FLIR shall be operational and capable of responding to operator commands within 60 seconds after power is applied.

Readiness Message When power is applied to the system, the FLIR shall indicate a Not Ready message over the 1553 data bus. This message shall be updated to a READY when system become fully functional with exception of the IR imager cool down.

Detector Cool Down Time The detector shall reach its operational temperature within 10 minutes after the application of power when the ambient temperature is 25° Celsius. When stabilized at the ambient operating temperature extremes of this specification, the cool down time shall not exceed 15 minutes.

Infrared Fields of View

Change of FOV Switching time between FOVs shall not exceed 0.5 Seconds.

Optical Focus Optical focus shall be maintained without operator adjustment.

Gimbal Limits Horizontal Rotation Limit Gimbal shall have a minimum horizontal range of +/- 200 degrees from nose of aircraft.

Vertical Limit Gimbal shall have a minimum vertical range of +77 degrees to –170 degrees (Up Positive).

Coincidence of the FOVs Multiband systems need to provide coincidence between center of FOV of each sensor to within 10 pixels of the MWIR imagery.

Noise Equivalent Temperature Difference (NETD) The average temporal NETD shall be less than 0.045 ° C when measured in ambient conditions and utilizing a blackbody with background temperature of 22.5° +/- 2.5° C.

Night Vision Imaging System (NVIS) Compatibility Illuminated indicators used on the turret, electronic unit or hand control that leak light outside of the WRA housing them shall be NVIS compatible to MIL-L-85762A Class A requirements.

Performance Range Detection The systems narrowest Optical MWIR FOV shall be able to detect a standing man-sized target at 3.8 km while operating at 5 kft in mid Atlantic summer atmospheric environment with a navy maritime aerosols, navy maritime visibility override 15.0KM, wind speed 0 m/s, and Navy Maritime Air Mass 5.

Recognition The systems narrowest optical MWIR FOV shall be able to recognize a standing man-sized target at 3.19 km while operating at 5 kft in mid Atlantic summer atmospheric environment with a navy maritime aerosols, navy maritime visibility override 15.0KM, wind speed 0 m/s and Navy Maritime Air Mass 5.

Operability The MWIR detector shall be operational 99.5% of the time while in use.

Overall Detector Defects The MWIR detector shall have no more than 10 adjacent pixel which are defective. In addition, no more than 5% of the total Defective pixels shall be within one column or row. Any pixels which has limited response in addition to those pixels which flash are considered bad pixels.

Center Detector Defects Within the central 100 x 56 pixels (vertical x horizontal) of the detector, there shall be no more than a total of 10 defective pixels. Within this zone, there shall be no group of vertically- or horizontally-adjacent defective pixels larger than 3 pixels total. A single group of 2 or 3 adjacent defective pixels which does not exceed 2 pixels in either direction is permitted within the zone.

Laser Energy Vulnerability The MWIR Sensor shall utilize state of the art filtering techniques to reduce damage from adversarial laser systems.

Image Fusion Multiband systems shall provide image fusion capabilities with the MWIR detector.

LASER Systems Laser Range Finder (LRF) The system shall have an eye safe laser range finder capable of measuring range to 3 ft accuracy at a slant range of 5km from 5kft during mid Atlantic mid-summer conditions.

Laser Target Marker (LTM) The system shall have a target marker that is only visible to Generation III night vision goggles.

Boresight LRF and LTM shall not require special calibration equipment to calibrate boresight at the operational level.

LTM Safety At least two separate operator commands (Arm and Fire) shall be required to cause the LTM or LRF to emit energy. Lasing any part of the aircraft shall be prohibited.

Avionics System Alerts Displayed symbology consisting of a string of up to 16 ASCII characters shall be displayed when commanded by the data bus controller.

Video Grayscale A grayscale pattern with a minimum of 256 shades of gray from black to white shall be provided over the analog video. A minimum of 12 bit over the digital video feeds. The grayscale is a reference pattern to allow adjustment of the display brightness and contrast for varying ambient lighting conditions. Selection of the Grayscale on or off shall be provided through the 1553 data bus and by using the HCU.

External Symbology Generation The data required to generate the FLIR Symbology shall be available on the 1553 Data Bus to facilitate generation of the FLIR Symbology by external devices.

Structural Requirements Fatigue Requirements The TU shall be designed to provide a fatigue life of 15,000 hours.

Reliability The FLIR shall have a predicted Mean Time Between Failure (MTBF) of greater than 900 hours.

Operational Stability The equipment shall operate with satisfactory performance, continuously or intermittently, for a period of at least one MTBF without the necessity for readjustment of any controls which are inaccessible to the operator.

Operating Service Life The equipment shall have a total operating life of xxx hours.

Storage Life The equipment shall be capable of withstanding a 24 month storage period in a storage environment of -57 to +85 degrees C. At the end of the storage period the equipment shall not require a maintenance action prior to operational use.

Maintainability Mean-Time-To-Repair The system mean-time-to-repair (MTTR) shall not exceed 60 minutes at the O-Level. O-Level MTTR refers to the removal and replacement of WRAs from the aircraft. Access time attributable to the aircraft installation and FLIR warm-up/cooldown time are excluded.

Built In Test Implementation The system shall provide a system Self-Test and Status Monitor Built In Test (BIT), and fault isolate between the TU and EU (if present) WRAs and Shop Replaceable Assemblies (SRA).

The requirements for BIT failure detection assumes that failures of 1553 input/output (I/O) circuitry, circuitry that prevents normal BIT reporting (e.g. power supplies, system clocks) and failures that do not affect system operation are excluded from these requirements.

Status Monitor BIT The Status Monitor BIT (background) shall operate automatically while the equipment is performing the current mission functions without inhibiting, interrupting or degrading the performance of the equipment.

Self-Test BIT The Self-Test BIT execution time shall not exceed 120 seconds after initiation. Self-Test BIT shall detect 95 percent of TU or EU (if present) failures down to SRA level.

Fault Isolation Self-Test and Status Monitor BIT, shall isolate at least 97 percent of the detected failures to the faulty WRA. Self-Test and Status Monitor BIT shall detect and isolate failures to the most probable faulty SRA.

False Alarms Built In Test false alarms shall not exceed 2%.

Design and Construction Prohibited Materials The following materials shall not be used:

Polyvinyl Chloride (PVC) Polychlorinated Biphenols (PCB) Asbestos Thorium or other radioactive Optical Materials Corrosion Prevention The equipment shall be designed to prevent corrosion effects during the life of the equipment.

Electromagnetic Compatibility The system shall operate without performance degradation while installed on the aircraft and during concurrent operation of other existing aircraft subsystems and equipment. Operation of the FLIR shall not degrade the performance of any other existing aircraft subsystems or equipment. The FLIR shall be compatible with friendly electromagnetic environments (EME) during flight operations near U.S. Carriers (CVs and CVNs), Cruisers (CGs), Destroyers (DDGs), or Frigates (FFGs). MIL-HDBK-235 provides guidance concerning these shipboard environments.

Electromagnetic Interference The FLIR shall meet requirements of MIL-STD-461E, CE102, RE102, and RS103 as modified in the specifications.

Nameplates And Marking Nomenclature and serial number assignment, nameplate approval, and identification marking shall be in accordance with MIL-N-18307. Marking shall be in accordance with MIL-STD-130.

Environmental Qualifications The equipment shall meet the requirements of MILSTD 810 as detailed in the following subparagraphs.

Vibration - Gunfire All components shall undergo gunfire vibration qualification testing in accordance with MIL- STD-810F(3), Method 519.5 Procedure IV for 1 hour per axis using the gunfire vibration test spectrum defined in specification document.

Explosive Atmosphere The FLIR shall not cause ignition of an ambient-explosive-gaseous mixture with air when operating in such an atmosphere in accordance with MIL-STD-810F, Method 511.4, Procedure I Rain The Turret shall be operable and sustain no physical damage during periods of heavy precipitation IAW MIL STD 801F, Method 506.4, Procedure I as defined in Spec.

Temperature/Altitude The Temperature and Altitude environmental requirements shall be verified by operation of the system under the conditions of MIL-STD-810F, Method 520.2, Procedure III. Test parameters shall reflect the requirements of this specification.

Humidity The FLIR shall be tested in accordance with MIL-STD-810F, Method 507.4, except the maximum temperature shall be +55° C. Test duration shall be 10 cycles.

Functional Shock The FLIR shall meet performance requirements and shall not be damaged after exposure to 18 impact shocks of 20g, consisting of 3 shocks in opposite directions along each of 3 mutually perpendicular axes, using MIL-STD-810F, Method 516.5, Procedure I and Figure 516.5-10 (sawtooth). Each shock pulse shall have a time duration of 11 milliseconds. The ‘g’ value should be within ±10 percent when measured with a 0.2 to 250 Hz filter.

Environmental Conditions and Qualifications Cont.

Vibration Performance Vibration The FLIR shall operate without degradation in specified performance when exposed to the steady-state linear flight (sine) g levels at the specified dwell frequencies in the X, Y and Z axes as defined in Tables in specification document. The specified performance shall be met when the Turret base is exposed to angular vibration as defined in Spec. The system shall be tested in accordance with MIL-STD 810F, Method 514.5, Procedure I, Category 14 except that the power spectral density values, frequencies and minimum RMS g levels for endurance and performance shall be based on Specification Tables.

Endurance Vibration If there is an EU, it shall sustain no physical damage when exposed to the maximum g levels specified in Spec with a flat random vibration from 8 to 500 Hz at 0.02 g2/Hz. The 16.6 and 39.7 Hz levels shall be tested as a pair, and, separately, the 19.8 and 33.3 Hz levels shall be tested as a pair. The FLIR shall exhibit no damage after exposure to vibration levels specified. Vibration testing shall be conducted in accordance with MIL-STD-810F, Method 514.5, Procedure I, Category 14. Test duration shall be 60 minutes per axis per dwell frequency set. Performance requirements shall be met before and after exposure to this vibration test.

The Turret shall sustain no physical damage when exposed to the maximum g levels specified in Specs.

Sand and Dust The equipment shall withstand, in an operational and non-operational condition, exposure to sand and dust. In accordance with MIL-STD-810F, Method 510.4, Procedure I (blowing dust – Both Turret and any EU) and Procedure II (blowing sand – Turret only). Any evidence of dust that has penetrated into the item in sufficient quantity to degrade system performance shall constitute a failure of this test.

Salt Fog The FLIR shall withstand exposure to a 5 percent salt fog environment alternating 24-hour periods of salt fog exposure and drying conditions for a minimum of four 24-hour periods (two wet and two dry) when tested in accordance with MIL-STD-810F, Method 509.2. Performance requirements shall be verified before and after exposure to this requirement.

Thermal Shock The system shall meet the performance requirements of this specification while exposed to the conditions of the Thermal Shock environment of MIL-STD-810F, Method 503.4, Procedure I, utilizing a high temperature of +55ºC and a low temperature of -40ºC.

Crash Safety The turret unit shall be analyzed to ensure that it meets crash safety loading equivalent to MIL-STD-810F, Method 516.5, Procedure V, limited to 20 Gs, using a saw tooth pulse. The electronics unit (if present) shall be tested in accordance with MIL-STD-810F, Method 516.5, Procedure V, limited to 20 Gs, using a saw tooth pulse..

Date of Brief: 21 Sep 23 Scope of the DRAFT Statement of Work (SOW)

The following slides outline draft requirements from the SOW. This document, along with the technical content regarding the Technical Specification (SPEC) and Contract Data Requirement Lists (CDRLs) are in draft form and the final version may be materially different from the documents discussed in today’s Industry Day.

Overarching requirement:

The Contractor shall provide a FLIR system capable of integration into the CH-53K and provide the technical data, forward, and retrofit kits to support CH-53K integration, production and retrofits.

Date of Brief: 21 Sep 23 DRAFT SOW Scope – Program Management Follow its established program management processes throughout the execution of this contract Utilize established Quality Assurance, Configuration, and Risk management processes throughout the period of performance of this contract Participate in a post contract award conference (PAC) at the Contractor facility. The PAC should occur within 30 calendar days of the contract award.

Implement and maintain an OPSEC program to protect controlled unclassified and classified activities, information, equipment, and material used or developed by the Contractor and any subcontractor during performance of the contract up to and including the level of SECRET

Date of Brief: 21 Sep 23 DRAFT SOW Scope – Engineering Support Produce and deliver a FLIR system capable of integration into a CH-53K Aircraft Conduct systems analysis of requirements, capabilities, performance and constraints and complete trades to optimize the weapon system design Utilize established Requirements management processes throughout the period of performance of this contract Participate in Technical Interchange Meetings.

Deliver applicable documents/CDRLS to support Integration, Test and Life cycle support Utilize existing software development practices and procedures in modification of the FLIR software for integration into the CH-53K

Date of Brief: 21 Sep 23 DRAFT SOW Scope – Test and Evaluation Document the verification of the design. Any requirements that are identified as verified by Analysis will be documented in a Design Verification Report.

Deliver Environmental Qualification Test Reports that shows compliance to CH53K EOSMS Performance Specification Deliver Functional Qualification Test Reports that verify all of the functional requirements of the FLIR.

Provide all necessary test equipment required to properly execute Acceptance test procedures.

Deliver Manufacturing Acceptance Test Procedures (ATP) for the FLIR. The Manufacturing ATPs shall describe the inspection and testing required ensuring manufacturing quality of the component Provide engineering test support for the developmental and operational testing phase of the FLIR. The Contractor shall be available by phone for teleconference for test meetings.

Deliver a E3 verification report and if required, perform testing in accordance with the requirements of the CH-53K FLIR Specification.

Deliver an Electromagnetic Interference Test report and if required, perform testing in accordance with the requirements of the CH-53K FLIR Specification.

Date of Brief: 21 Sep 23 DRAFT SOW Scope - Logistics Establish an Integrated Product Support/Engineering Partnership to identify key system attributes critical for supportability development (during design):

Maintainability (modularity, testability, accessibility) Human Factors Reliability Standardization Obsolescence Tolerance Conduct Product Support Analysis (PSA) required to field and maintain readiness and operational capability of CH-53K weapon systems, subsystems, and components, including all functions related to weapon system readiness.

Establish a Reliability, Availability, and Maintainability (RAM) and Integrated Supply Chain Management (ISCM) strategy Identify Technical data package requirements and sustainment strategy Ensure OEM Configuration Management requirements and supplier flow down Execute IUID Requirements Provide Prototyping / Validation (VAL) / Verification (VER) Support and deliverables Provide initial operator training as well as training materials Provide Technical data package image2.png image1.png