Attachment2TMRSSRD6Apr22.pdf

CUI

SYSTEM REQUIREMENTS DOCUMENT

E-9A TELEMETRY RELAY SYSTEM (TMRS)

4 March 2021

Prepared for:

Mobility Directorate, Legacy Training Aircraft Division Tinker AFB, OK E-9A Programs

Prepared by:

E-9A Integrated Product Team

Legacy Training Aircraft Division Program Office Tinker AFB, OK

Distribution Statement D: Distribution authorized to the Department of Defense and U.S. DoD contractors only; CUI unclassified documents; 23 November 2020. Other requests shall be referred to E-9A Program Office.

Controlled by: United States Air Force

Controlled by: E‐9A Program Office

CUI Category: General Procurement and Acquisition

Distribution/Dissemination Control: D

POC: herman.brandon.1@us.af.mil

Approved by:

// signed – rmsg // 5 March 21 MR. RANDY GALLOWAY Date

ACC A589/A5TT

LT COL TRAVIS WINSLOW Date

82 ATRS/CC 53 WEG

MR. HERMAN BRANDON III Date Specialized Trainers Aircraft Branch Chief

5 March 21

Table of Contents

1. SCOPE

1.1. System Overview

2. 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. REQUIREMENTS

3.1. Required States and Modes

3.2. System Capability Requirements

3.3. System Interface Requirements

3.4. System Internal Data Requirements

3.5. Safety Requirements

3.6. System Environment Requirements

3.7. Computer Resource Requirements

3.8. System Quality Factors

3.9. Design and Construction Contraints

3.10. Personnel Related Requirements

3.11. Logistics Related Requirements

3.12. Other Requirements

3.13. Packaging Requirements

4. VERIFICATION PROVISIONS

4.1. Verification Methods

4.1.1. Demonstration

4.1.2. Test

4.1.3. Analysis

4.1.4. Inspection

5. REQUIREMENTS TRACEABILITY

5.1. Traceability to Capability Document or System Specification

5.2. Traceability to Subsystems Requirements

6. APPENDIX SECTION

6.1. Appendix A - Acronyms and Definitions

6.2. Appendix B - Key Performance Parameters/Key System Attributes

E-9A with TMRS Antenna

1. SCOPE

This Systems Requirement Document (SRD) describes attributes, performance parameters, processes, objectives, and other requirements needed for an E-9A Telemetry Relay System (TMRS) upgrade.

1.1. System Overview

The primary requirement for the E-9A is to receive S-Band telemetry (TM) for over-the-horizon (OTH) missions in order to track and record a minimum of five (5) aerial S-band targets and relay them via L-band to ground stations. The telemetry relay system (TMRS) system consists of a Synthetic Beamforming Antenna (SBA) array mounted on the right side of the aircraft along the length of the fuselage. This system is based on digital beamforming for azimuth tracking and a re-configurable array for elevation coverage. It operates from 2.2 to 2.4 gigahertz (GHz) and is designed to simultaneously form 10 independently steered beams with 2 orthogonal linear polarizations per beam. The Antenna Control Computer (ANCC) is designed to simultaneously search for, acquire, and track 10 independent targets while dynamically selecting the best combinations of orthogonally polarized inputs, to maximize the signal-to-noise ratio (SNR) of each active track.

E-9A Mission Profile

The SBA array does not require any external receivers or demodulation hardware to extract the digital information from the TM data stream. The original phased array antenna was designed for data rates of 2Mb/s. The E-9A usually operates at 8,000-20,000 feet Mean Sea Level (MSL) for telemetry collection and relay. Performance characteristics of the E-9A’s original Telemetry Relay System was determined, published, and approved in Specification number SP8408 0001 (in 1986), and the modernized system as currently configured is documented in Telemetry Phased Array Antenna Specifications Document 0405-2001 (in 2004).

The original TMRS included the following subsystems: Telemetry Phased Array Antenna, Telemetry Receiver, Data Distribution, Record, Inter-range Instrumentation Group (IRIG) Timing, Telemetry Operator Console (TOC), Re-transmission, Diagnostic Equipment, and Auxiliary Rack. The original TMRS Tracking, Equipment Control, Platform Status, and Diagnostic Functions are part of the Airborne Platform/Telemetry (AP/TM) Control System. The control system is divided into three functional subsystems: Telemetry Operator Console (TOC), Antenna Control Computer (ANCC), and Beam Steering Processor (BSP).

2. APPLICABLE DOCUMENTS

This section lists the number, title, revision, and date of all documents referenced herein.

2.1. General

Documents listed in this section are specified in sections 3, 4, or 5 of this SRD. 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 warfighter’s are cautioned that they should meet all specified requirements of documents cited in sections 3 or 4 of this specification, whether or not they are listed.

2.2. Government Documents

The following sections list government documentation applicable to this SRD.

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.

2.2.2. Other Government Documents, Drawings, and Publications The following documents 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.

Original required drawings are prepared in accordance with the standards defined in DRM- 31000. The original mounting details conform to drawing 8408-0005 and the DC power connectors and pin assignments are shown in drawing 8408-0005.

2.3. Non-Government Publications

The following documents 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.

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 (except for related specification sheets), 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. REQUIREMENTS

In recent years the TMRS has been suffering from extremely high unreliability rates and poor data collection. The major contributing factor for these issues are the single points of failure contained within the system’s ANCC. This computer is bulky, emits excessive levels of heat, and is highly unreliable due to antiquated equipment. The full set of signal characteristics and performance requirements of the E-9A’s original Telemetry Relay System, which must be met or exceeded, are described in Paragraph 3.7.3.2 of Specification number SP8408 0001.

3.1. Required States and Modes

The TMRS upgrade shall meet the following requirements:

Receive S-band and retransmit L-Band telemetry data Interface with existing antenna Provide interfaces specific to both operators and maintainers Eliminate unneeded equipment from equipment racks Eliminate unneeded equipment from the TOC Alleviate cooling issues in the rear of the aircraft Eliminate single points of failure with built in redundancy Support higher data rates and modern error correction methods

3.2. System Capability Requirements

The TMRS originally provided the capability to simultaneously receive, record and relay telemetry data from up to five spatially separated dual emitter telemetry sources ranging from 25 NM to 150 NM at altitudes from sea level to 70,000 feet Mean Sea Level (MSL) minimum. The telemetry receive section consisted of Radio Frequency (RF) input patch panel, power splitters, RF output patch panel and Receivers. The RF input patch panel provided the capability to connect the desired beam to power splitter inputs, or connect directly to receiver inputs, or to polarization rotation hybrids. The capability for 10 receivers was provided in the frequency range of 1435.5 MHz to 1535.5 MHz, however only six receivers were normally installed. A maximum of two receivers could be connected to each beam (one tracking and one data). Each receiver was configured as a dual channel receiver with an integral pre-detection optimal ratio diversity combiner and a Best Signal Selector for tracking Amplitude Modulation (AM) output. An integral Frequency Modulation (FM) demodulator was provided for the pre-detection combined Intermediate Frequency (IF) output.

The original relay system linearly converted the S-Band input signals to selectable L-Band output signals. The relay system consisted of three major subassemblies (IF up-converter, power amplifier, and multi-coupler). Each power amplifier provided five L-band signals to the selected multi-coupler. The selected multi-coupler output fed a directional coupler used to monitor both forward and reflected power. Two L-Band antennas were mounted on the aircraft fuselage, one for each selected multi-coupler output. These antennas and associated input cables provided a maximum Voltage Standing Wave Ratio (VSWR) of 2.0:1. Both antennas provide a linearly polarized radiated signal. The azimuth pattern was within 1 dB of omni-directional. The elevation pattern was less than 3 dB below maximum gain at 80 degrees.

The original Time Code Reader Input System Inter-Range Instrumentation Group (IRIG)-G time was fed to the TOC through a coaxial cable from the TMRS distribution subsystem to Channel one on the Time Code Reader controller card. The controller maintained current range time and time tagging of data by the real-time control software that was displayed the Central Processing Unit (CPU). A Global Positioning System (GPS) synchronized IRIG time code generator consists of a GPS receiver with an integral precision quartz clock and an IRIG time code generator.

The original Telemetry Operator Console (TOC) was a ruggedized system housed in two chassis;

one for the computer and the other for the operator keyboard. It read receiver S-band frequency selections as entered manually on the receiver front panels through each of five separate RS-422 connections. The receiver status cables for the five tracking receivers of the 10 installed receiver pairs were connected to the five beam frequency input connectors in the System Interface Drawer (SID). In accordance with the receiver interface requirement, the TOC transmitted a handshake pulse to all connected receivers once per second. The receivers, in turn, transmit the frequency in ASCII code back to the TOC.

The original TM receiver provided six dual channel receivers with integral pre-detection combiners and post detection best signal selectors. Any receiver could be selected as a tracking and/or data receiver. An integral FM demodulator was provided for each channel and the pre-detection combined IF. Each channel included 20 MHz Linear IF outputs and a 20 MHz output at the diversity combiner output. An RS-422 compatible, remote control interface was also provided. Operational parameters of the receiver were: Received Frequency, Receiver bandwidth, AGC time constant, Tape Carrier Frequency, Video gain, and Video bandwidth.

The original data distribution subsystem allowed the operator to route outputs from the TM receiving section to the record, relay, tracking, and timing subsystems. This section consisted of a distribution patch panel and three video distribution amplifiers chassis. All receiver signal outputs, video distribution amplifier and monitor outputs, preprocessor inputs, were available at the patch panel. Each amplifier module provided one input and four outputs.

The original record subsystem provided a fourteen track analog recorder capable of 2.0 MHz BW at 120 inches per second (IPS). This recorder provided the capability of remote control via an RS-232/RS-485 adapter mounted at the rear of the recorder. The remote interface provides complete status and control from the TOC. The Digital recorders were also capable of being controlled from the TOC. A computer chassis with ten (10) M b/s bit synchronizers were added to provide the interface between receiver analog video and the digital recorders.

The original ANCC performed the antenna tracking loop function. The ANCC initiated a search for a Radio Frequency (RF) signal, acquires that signal, and automatically tracks the signal with an alpha-beta tracking filter. The inputs to the ANCC needed to support the tracking loop were

Automatic Gain Control (AGC) and track errors from the preprocessor, through a multiplexed Analog to Digital (A/D) converter in the ANCC. The range of values were from 2200.5 to

2399.5 MHz. The output of the tracking loop was a computed composite angle sent to the BSP for individual Phased Array Module (PAM) phase calculation and distribution to the TOC.

The Antenna Control Computer (ANCC) requires improved cooling and connectors

The original BSP was comprised of three cards sharing access with the ANCC chassis on the Multi-bus. One card communicated with the ANCC through the Multi-bus-Input/Output (I/O) and, from the composite beam angle, calculates the beam forming phase values for each PAM with an Advanced Micro Devices (AMD) micro-sequencer and three AMD bit slice processors.

The other two cards supported the interface to the System Interface Units (SIU) for the left and the right side of the array. The BSP also provided the 10 kHz clock to the preprocessor synchronous demodulator in delayed synch with the phase shift and dither commands to the

PAM.

The original diagnostic capabilities allowed the operator to monitor selected functions real-time and provide a limited maintenance capability in the system. These capabilities were provided by a combination of rack mounted test equipment (Spectrum Analyzer, Oscilloscope, and RF signal generator) and hardware/software resident in the TOC. Time domain -and frequency domain analysis of RF, IF, and baseband signals were provided by an oscilloscope and spectrum analyzer. The oscilloscope provided the operator a real-time monitor of selected IF and baseband signals at the test patch panel. The spectrum analyzer provided the capability to perform real-time frequency domain analysis of received signals, retransmitted signals, and IF signals being fed to the Re-transmission system. An RF signal generator provided stimulus signals for stand-alone checkout of antenna, receivers, distribution amplifiers, analog recorders and the Re-transmission system.

The original auxiliary rack was configured with mission specific equipment, as needed, in accordance with temporary modification packages, submitted for local Aircraft Change Control Board (ACCB) approval.

E-9A Telemetry Relay System (TMRS) block diagram

3.3. System Interface Requirements

The TOC is the original primary interface between the Telemetry System and the Telemetry Operator. It controls and monitors peripheral TM equipment and the ANCC. It also records all diagnostic and mission tracking data, and provides real-time displays of the aircraft position and all beam tracking data. The TOC interfaces to: TM receivers, instrumentation recorders, GPS sensor output, GPS IRIG time, and aircraft Aeronautical Radio, Inc. (ARINC)-429 data bus.

Connections to these interfaces are made either directly to the TOC chassis or to connectors in the System Interface Drawer (SID). The original TOC provides a two-way interface to the ANCC for the Ground Support Van (GSV) antenna control functions through a RS-422 connector in the SID to the GSV, and the TOC direct connection to the ANCC with its high speed RS-422 port. This interface accommodated the unique serial parameters, to record and display the GSV dialogue. This interface also acted as a pass-through and data rate converter from the fixed low serial data rate of the GSV to the higher data rate of the ANCC. Note: the GSV is no longer in use or required.

3.4. System Internal Data Requirements

The original TOC provides single point control of the Telemetry (TM) receive and record function and provides the capability to record all TM control and diagnostic data. Power is controlled for the ten receivers and for instrumentation recorders.

3.5. Safety Requirements

All newly designed equipment items incorporated into TMRS are designed and fabricated to meet the requirements of MIL-STD-454, Requirement 1 and MIL-STD-1472.

3.6. System Environment Requirements

The original equipment installed in and on the aircraft is designed to withstand the following environmental conditions:

Internal equipment External Equipment Temperature/ Altitude

Operating: 10°C (50°F) and 36°C (97°F); 0 to 10,000 feet Non-operating: -55°C (-67°F) to 85°C (185°F); 0 to 30,000 feet

Operating: -55°C (-67°F) and 71°C (160°F); 0 to 10,000 feet Non-operating: -55°C (-67°F) to 85°C (185°F); 0 to 30,000 feet

Humidity Operating: 75% humidity without condensation Non-operating: 95% humidity including condensation

100%, including condensation operating and non-operating

Shock Operating: 6 G's, 11 msec half sine pulse in each of the six principle axis directions Non-operating: 15 G' s, 11 msec half sine (crash safety) pulse in each of the six principle axis directions

Operating: 6 G's, 11 msec half sine pulse in each of the six principle axis directions.

Non-operating: 15 G's, 11 msec half sine pulse in each of the six principle axis directions

Vibration Continuous operation while sustaining normal aircraft induced vibration levels and withstand normal flight motions during takeoff and landing.

Continuous operation while sustaining aircraft induced vibrations and withstands normal flight motions, including takeoff and landing. In addition, this equipment meets the following sinusoidal vibration levels:

0.010 in., 1.5 G, 5-55 Hz

Explosion N/A N/A Waterproofness Continuous operation when exposed to Gulf Range environmental conditions

External equipment mounted to the aircraft fuselage within radome structures designed to continuously operate when exposed to dripping water and condensation in the course of normal aircraft operation.

Fluids Susceptibility

Fluids susceptibility requirements are met due to aircraft cabin protection and Environmental Control Unit (ECU)

All externally exposed materials (radomes, radome gaskets, support structures, exposed antennas, etc.) shall not be affected by fluids (fuel, hydraulic fluid, lubricating oil, alcohol, de-icing fluid and water) commonly encountered in airborne and ground operations

Sand And Dust Continuous operation when exposed to Gulf Range environmental conditions

Continuous operation when exposed to Gulf Range environmental conditions

Fungus Resistant to promotion or growth of fungus

Resistant to promotion or growth of fungus

Salt Spray Continuous operation when exposed to Gulf Range environmental conditions

Continuous operation when exposed to Gulf Range environmental conditions

Acoustic Environment

Inherent acoustic conditions in aircraft captive carriage

Inherent acoustic conditions in aircraft carriage. The acoustic level is 140 dB (dB referenced to 2 x 104 dynes /cm2 )

3.7. Computer Resource Requirements

The original TOC provided the ability to execute all post mission analysis software as well as providing a compatible platform for software development and configuration control for the TOC, ANCC, and BSP software and firmware. The TOC incorporated processors that are pre-assembled and off-the-shelf. Microprocessors contained in the TOC are available from multiple sources, including an Electrical Erasable Programmable Read-Only Memory (EEPROM) programmer, a complete set of software development support tools (including a program text editor), linking loader and runtime support routines, and Peripheral Equipment compatible with the hardware and software. The original computer/processor provided memory throughput and input/output channel capacity.

3.8. System Quality Factors

The original TMRS had the following quality factors:

Reliability - Mean time between failure (MTBF) of at least 100 hours.

Availability - Calculated using the formula: Availability = Mean Time Between Failures

(MTBF) + Mean Corrective Time (Mct). The system availability rate of 99% for a scheduled six hours per day, five days per week, and twelve months per year, not to exceed a total yearly time of 1000 hours.

Maintainability – Mean corrective maintenance time (MCMT) of 60 min and a maximum mean corrective maintenance time (MaxMCMT) of 120 min at the 90th percentile. Two maintenance technicians and a scheduled preventative maintenance (PM) period occurs no more frequently than once every five days.

3.9. Design and Construction Constraints

The original order of precedence in the design and development of the TMRS is as follows:

Equipment Existing equipment in the Department of Defense (DOD) inventory shall be considered for use to the fullest extent possible for any suitable application within the system.

New equipment shall be considered if existing military or commercial equipment is not available to satisfy the performance requirements of this specification; new equipment shall be in accordance with the applicable military specification list.

Selection of materials and processes for newly manufactured equipment shall be in accordance with (IAW) MIL-STD-1587 and MIL-STD-1568. The program office shall approve materials that are not specified herein. Electronics shall conform to MIL-E-5400.

Printed circuit/printed wire boards shall be conformal coated per MIL+46058 using Quality Products List (QPL) materials.

Interchangeability - The design of each assembly is such that the operation of that assembly is not be degraded when a Line Replaceable Unit (LRU) is replaced. In addition, the LRU is designed to operate without degradation when a component part of that LRU is removed and replaced by an identical spare part meeting the same procurement specification.

Interchangeability and replace-ability is compliant with requirements of MIL-STD-454, Requirement 7.

The following limitations apply to electronic parts selected for use on newly designed equipment:

• All parts and circuits shall be representative of a general class available from more than one source.

• No germanium devices shall be used.

• Wet tantalum capacitors shall not be used in the design without specific written approval.

• Custom designed integrated and hybrid circuits shall be avoided unless no reasonable alternative exists.

• Electrical connectors requiring potting compound material shall not be used.

• Certain chemicals have been identified in the Occupational and Safety Health Act

(OSHA) as cancer producing substances (carcinogens). Before using any materials which might contain these chemicals, they should be evaluated IAW the Code of Federal Regulations, Title 29, Part 1990. Consideration of the toxicity of a substance shall be given priority in material selection. Materials that contain polychlorinated biphenols (PCBs) shall not be used.

• Edge card connectors shall not be used.

• Polyvinyl chlorides (PVC) shall not be used in any application including, but not limited to, insulation, wire/cable sheathing, sleeving and/or as a structural material for part or component fabrication. PVC insulated wire and/or cable shall not be used; rather, the contractor shall select one of the many suitable non-PVC insulated wires arid/or cables.

Electromagnetic Radiation/Compatibility/Interference Electromagnetic Radiation (EMR) - The Telemetry antenna is protected against radiation from other RF emitters aboard the aircraft. Band-pass filtering is provided within the TM antenna and protects it from external out-of-band emitters over the frequency range of 10 MHz to 18 GHz. Maximum in-band radiation should be kept to a maximum equivalent input of -30 dBm.

Electromagnetic Compatibility (EMC) - TMRS instrumentation equipment is designed to be compatible with other electronic equipment installed in the aircraft and with the Gulf Range ground and sea electromagnetic environment (EME). The airborne (flight) environment includes the electromagnetic environment created by RF transmitters and receivers. The Gulf Range ground or sea EMC data will be furnished upon request.

Electromagnetic Interference (EMI) - The TMRS upgrade is designed to meet the EMI control requirements of MIL-STD-461.

Materials Prohibited Materials: Vinyl, polyvinyl chloride, household/architectural type caulking compounds and corrosive type RTV (yields acetic acid during curing) materials are prohibited for use in all forms, interior or exterior.

Flammable Materials - Flammable materials shall not be used except as permitted by MIL-STD-454, Requirement 3. Interior coated fabrics, seat cushion coverings, carpeting, etc., shall be self-extinguishing materials. Interior materials containing wool, polyvinyl chloride (PVC), PVC coated fabrics, modified Aramid, and phosphorous based fire retardant treated cotton are prohibited due to the toxic level of their thermal decomposition products should a fire occur.

Arc-resistance Material - Material used for insulation of electrical power circuits, where arcing is possible (connector inserts, relays, circuit breakers, etc.) shall be IAW MIL- STD-454, Requirement 26.

Fibrous Material, Organic - Selection and use of organic fibrous material shall be IAW MIL-STD-454, Requirement 44. Use of wood and wood products are prohibited in all structural applications, interior or exterior.

Fungus Inert Material - Selection of materials for the control of moisture and fungus shall be IAW MIL-STD-454, Requirement 4.

Insulating Materials, Electrical - Electrical insulating materials shall be selected and used IAW MJL-STD-454, Requirement 11.

Lubrication - Criteria for the choice of lubricants shall be as established by MIL- STDA54, Requirement 43.

Magnesium - All magnesium alloys shall be subject to approval by the procuring activity.

Rubber - Rubber materials shall conform to criteria defined in MIL-R-3065 and MIL-R- 6855.

Fasteners - Ferrous alloy components and inside/outside-threaded assemblies/fasteners shall be cleared and plated with cadmium per QQ-P-416 to a minimum of 0.0003 inches unless thread tolerances dictate a different thickness. Aluminum fasteners shall be anodized per MIL-A-8625.

Sandwich Core Material - If polyurethane is used as a foamed, skin stabilizing sandwich core material in structural areas such as walls, only the polyether, non-reverting type shall be used.

Parts:

Parts Standardization - For newly designed equipment, standard parts shall be selected IAW the requirements of MIL-STD-5400. The use of nonstandard parts, as defined in MIL-STD- 965, shall require program office approval.

Electronic parts within Group 1, or MIL-STD-143, shall qualify to the following specifications and standards and shall be selected from sources listed on current QPLS.

Deviation from the quality levels will require prior written approval from the program office.

Microelectronics for newly designed equipment shall be selected from those devices listed in MIL-STD-1562, screened and qualified to a minimum quality level of Class B, IAW the requirements and procedures contained in MIL-M- 38510. If micro-electronic devices are proposed for use that are not from MIL-STD-1562/MIL-M-38510 qualified sources, as listed on QPL-38510, the devices shall be screened IAW MIL-STD-883, Notice 5, Method 5004, Class 8, prior to use. All microelectronics used in the unit shall be packaged in hermetic packages, and no "plastic" (i.e., epoxy, silicone, phenolic, or other organic materials) encapsulated devices shall be used.

Semiconductors for newly designed equipment shall be selected from those devices listed in MIL-STD-701, screened and qualified to a minimum quality level of Class Joint Army Navy (JANTX) or, IAW the requirements and procedures contained in MIL-S- 19500. If semiconductor devices are proposed for use that are not selected from MIL-STD-701/MIL-S- 19500 qualified sources listed on QPL-19500, the devices shall have transition burn-in IAW MIL-S-19500 as a minimum. All semiconductors used in the unit shall be packaged in hermetic packages, and no "plastic" (i.e., epoxy, silicon, phenolic, or other organic material) encapsulated devices shall be used.

Processes Conformal Coating - Printed circuit/printed wire boards shall be conformal coated with coatings that meet the requirements of MIL-1-46058, using materials selected from sources listed in current QPLS.

Brazing - Brazing shall be IAW MIL-STD-454, Requirement 59.

Finishing - Surfaces shall be given a protective finish IAW MIL-STD-808, MIL-S-5002 and MIL-F-7179 for new equipment. The metals shall be of the corrosion resistant type treated to resist corrosion due to atmospheric conditions likely to be encountered in storage or normal service IAW MIL-STD-810 and MIL-STD-210. Unless suitably protected against electrolytic corrosion, dissimilar metals shall not be used in contact with each other IAW MIL-STD-889.

Soldering - Soldering shall be IAW MIL-STD-454, Requirement 5.

Welding - Welding shall be IAW MIL-STD-454, Requirement 13.

Aluminum Surface Treatments - Chemical conversion coating with anodizing of aluminum alloys shall conform to MIL-C-5541 and MIL-A-8625.

Workmanship - Workmanship shall be IAW MIL-HDBK-454, Requirement 9.

Nameplates and Product Marking - TMRS design is compliant with MIL-STD-454, requirement 67 and MIL-STD-27733. Marking does not adversely affect leakage paths between conductors or any other factor of equipment performance. Marking is in accordance with the requirements of MIL-STD-130.

Electrical Bonding/Grounding/Lightning Protection - TMRS is designed IAW the requirements of MIL-B-5087 as it applies to the control of electrical bonding for current return paths, antenna installation, lightning protection, reduction of precipitation static, and corona discharge.

3.10. Personnel Related Requirements

Field level maintenance tasks is intended to be implemented by Air Force Instrumentation & Telemetry technicians or equivalent contractor personnel. Maintenance tasks requiring more than one person are minimized. Human engineering design criteria and principles have been applied in the design of all new equipment items incorporated into the TMRS subsystem and allows effective performance by both operators and maintenance personnel.

3.11. Logistics Related Requirements

Maintenance:

The TMRS design is such that field level maintenance may be accomplished at existing facilities at Tyndall AFB. Maintenance is accomplished in the aircraft or in fixed shops as necessary and may consist of repairing, modifying, overhauling, reclaiming, or rebuilding parts, assemblies, subassemblies, components; and end items. Diagnostic commercial test equipment is calibrated in accordance with procedures and recommendations contained within the individual equipment manuals. Equipment for TMRS are based upon commercial off-the-shelf designs. These designs utilize plug-in module assemblies. Fault isolation is provided by Built-In Test (BIT) equipment and diagnostic capabilities provided by the TOC.

Maintenance and Repair Cycles - TMRS equipment requires a minimum of scheduled maintenance such as inspection, alignment, adjustment, and cleaning. These activities will be scheduled to minimize interference to operations. Provision will be made for scheduled downtime for preventive maintenance, Preventive maintenance that forces performance to drop below the specified level is classified as a relevant failure of the equipment. The equipment is designed to require a minimum of site or depot maintenance/overhaul.

Levels of Repair - The level of repair will normally be by replacement of the LRU. This is normally a printed circuit card, subassembly, or assembly. Repair of printed circuit boards will normally be accomplished off-line. Other functional elements such as modules that may be repaired by replacement in the field are "plug-in" designs. Non-Government Furnished Property (GFP) assemblies will be returned to the vendor for repair.

Failure Detection and Isolation - Capabilities are provided for fault detection and isolation to a LRU. Mission Tracking Data (MTD) files are generated from each operational mission and will enhance the capability to rapidly determine system discrepancies. MTD files will provide the capability to determine which combinations of tests are needed to further isolate faults. Tests will consist of automated, semi-automated, and manual procedures that permit compliance with the specified Mct. These techniques, in conjunction with operator observations, reported in post mission de-briefs, or discrepancies noted in aircraft forms, enable the following fault detection and isolation steps:

Recognition that a fault exists.

Isolation of the fault to a point of repair.

Service and Access - Equipment design and construction is such that it can be maintained within the specified maintainability requirements and IAW the Design for Maintainability requirements of MIL-STD-1472. The equipment is maintainable at the field level by normal maintenance techniques using U.S. Air Force Instrumentation & Telemetry technicians, or contractor personnel. To the maximum extent possible, the design facilitates maintenance as follows:

Components and electrical contact points that require frequent servicing, repair, or replacement are readily accessible.

Major and high-failure rate components and modules are removable from their enclosures without excessive disassembly when the equipment is installed in its operating location.

Assemblies and subassemblies are removable from their enclosures without disassembly.

Subassemblies are designed to permit maximum interchangeability and provide test accessibility.

Test points are accessible without disassembly of the subassemblies.

Access to subassemblies and circuit cards through the use of access doors, swing-out units, or pullout drawers having drawer slides.

When required, cable extenders, cable retractors, cable supports, and circuit card extenders are provided as part of the individual equipment to allow operation in the open position.

All components, connectors, and assemblies are identified with reference designations and locations.

Circuit breakers are accessible from the front of the cabinet. Individual equipment fuses are accessible for replacement.

A minimum of test equipment and special tools are required.

Where possible, connectors are appropriately keyed to prevent improper insertion or connection to the wrong terminal.

3.12. Other Requirements

Existing commercial manuals, in conjunction with documents generated by the TMRS upgrade will be used to generate a TMRS system maintenance manual. A Telemetry Operator manual will also be generated that describes in detail the interaction with other aircraft systems and the mission specific procedures needed by the Telemetry Operator to successfully Receive, Record, and Relay telemetry data.

3.13. Packaging Requirements

Transportability - Equipment in the TMRS upgrade has been designed to meet the transportability requirements of MIL-P-9024 (USAF).

4. VERIFICATION PROVISIONS

Program requirements stated within this SRD must be verified to show they have been met. The following methods will be utilized to perform requirement verification in accordance with the Statement of Work (SOW).

4.1 Verification Methods

4.1.1. Demonstration

Verification by demonstration involves the operation, movement, or adjustment of an item. The item may be instrumented and its performance may be monitored, but only as an indirect function in support of the demonstration. Performance monitoring may have quantitative limits for satisfactory operation.

4.1.2. Test

Verification by test involves operation of the item with instrumentation to determine that specific quantitative performance requirements are met. These verifications will use special test equipment or instrumentation to obtain very accurate quantitative data for analysis. The analysis of data derived from tests is an integral part of the test program.

TMRS testing is performed IAW the requirements specified herein. System, subsystem, and equipment testing is performed IAW a Government approved system test plan and demonstrates compliance of TMRS equipment with all applicable performance specifications.

Vendor acceptance tests consist of in-plant tests performed at vendor facilities to verify compliance with the quality of material, workmanship and electrical performance requirements of the specification. Government representatives as applicable and/or O&M contractor representative verify all testing. Vendors provide test data to the O&M contractor for submission to the government as required.

Ground tests and Flight Tests provide validation of performance and capabilities of the TMRS.

All TMRS equipment is integrated into the aircraft and inspections/tests performed to verify the quality of workmanship and electrical performance prior to final flight tests. These tests are performed using approved test procedures. If the system, facility, or equipment is tested and fails any tests, the extent and cause of the failure is determined. After corrections have been made, all tests failed are then re-tested. In addition, any previously passed tests affected by corrections are repeated.

4.1.3. Analysis

Verification by analysis will show that the item meets specific requirements by technical evaluation of equations, charts, simulations, circuit diagrams, and other relevant data or by comparison with previously qualified equipment. The data evaluated may include specific parameters from component, module, or sub-assembly specifications, which may be subject to verification by other methods.

4.1.4. Inspection

Verification by inspection involves examination and review of descriptive documentation, including design documentation, and/or hardware or software listings to determine conformance with specified requirements.

Quality Assurance Provisions - TMRS upgrade quality assurance plan submitted at the Critical Design Review defined the responsibilities for inspection that is used during the implementation of the TMRS upgrade. If a major component is off-the-shelf and unmodified and has existing documented performance test data that satisfies the test requirements, this data may be offered.

Quality Conformance Inspection (In Process Inspection): The Operations & Maintenance (O&M) contractor provides in process inspection as required.

5. REQUIREMENTS TRACEABILITY

5.1. Traceability to Capability Document or System Specification Traceability to this SRD and contractual requirements shall be provided via a requirements correlation matrix to be delivered by the contractor.

5.2. Traceability to Subsystems Requirements

Traceability to this SRD and contractual requirements shall be provided via a requirements correlation matrix to be delivered by the contractor.

6. APPENDIX

6.1. Appendix A – Acronyms and Definitions

A/D Analog to Digital

ANCC Antenna Control Computer

ACCB Aircraft Change Control Board

AM Amplitude Modulation

AMD Advanced Micro Devices

AGC Automatic Gain Control

AP/TM Airborne Platform/Telemetry

ARINC Aeronautical Radio, Inc.

BER Bit Error Rate

BIT Built-In-Test

BSP Beam Steering Processor

CPU Central Processing Unit

DOD Department of Defense

ECU Environmental Control Unit

EMC Electromagnetic Compatibility

EME Electromagnetic Environment

EMI Electromagnetic Interference

EEPROM Electrical Erasable Programmable Read-Only Memory

FM Frequency Modulation

GFP Government Furnished Property

GPS Global Positioning System

I/O Input/Output

IF Intermediate Frequency

IPS Inches Per Second

IRIG Inter-Range Instrumentation Group

JAN Joint Army Navy

LDPC Low Density Parity Check code

LRU Line Replaceable Unit

MaxMCMT Maximum Mean Corrective Maintenance Time

MCMT Mean Corrective Maintenance Time

Mct Mean Corrective Time

MIL-HDBK Military Handbook

MIL-STD Military Standard

MSL Mean Sea Level

MTBF Mean Time Between Failures

MTD Mission Tracking Data

NM Nautical Miles

O&M Operations & Maintenance

OSHA Occupational and Safety Health Act

PAM Phased Array Module

PCB Polychlorinated Biphenols

PCM / FM Pulse Code Modulation / Frequency Modulation

PM Preventative Maintenance

PVC Polyvinyl Chlorides

QPL Quality Products List

RF Radio Frequency

R/T Receiver/Transmitter

S/N Signal to Noise

SBA Synthetic Beamforming Antenna

SID System Interface Drawer

SIU System Interface Unit

SOQPSK Shaped-Offset Quadrature Phase Shift Keying

SRD Systems Requirement Document

TM Telemetry

TMRS Telemetry Relay System

TOC Telemetry Operator Console

VSWR Voltage Standing Wave Ratio

6.2. Appendix B – Key Performance/Key System Attributes

E-9A Key Performance Parameters (KPPs) # Capability Threshold Objective Justification 1 Airborne

Telemetry # of Beams

Receive TM data and Track a minimum of 5 dual emitter objects in S- Band and relay in L- Band (1435 - 1535 MHz)

Primary: Receive and track 10 separate objects from 1-20 MHz. All beams must have same aspect and field of view.

Secondary: Note, if able to upgrade to new capability within stated cost constraints, receive and track 10 objects in any combination of L- , S- and C- Bands

Necessary to create telemetry shoot box for air-to-air weapons

2 Antenna Frequency: 2200 – 2290 MHz, 2310 – 2390MHz

Bandwidth: up to 3 MHz

Primary: Receive & track in S-Band (2200 - 2395 MHz) TM data sources @ 20 Mb/Sec

Secondary: Note, if able to upgrade to new capability within stated cost constraints, Receive & track in L-Band (1435 - 1535 MHz) TM data sources @ 20 Mb/Sec, and C- Band (4.4-4.94 GHz, 5.091-5.25 GHz)

To support over-the-horizon telemetry requirements

3 Antenna Azimuth Accuracy

-5 to +5 degrees Less than 5 degrees Necessary to create telemetry shoot box for air-to-air weapons

4 Antenna Elevation Accuracy

30 degrees Greater than 30 degrees Necessary to create telemetry shoot box for air-to-air weapons

5 Antenna Field of View

-60 to +60 degrees from boresight

Greater than 60 degrees Necessary to create telemetry shoot box for air-to-air weapons

6 Data Rate 2 Mb/Sec Up to 20 Mb/Sec Higher data rates required for new weapon systems

7 Receive, Record and Re-transmit TM Data

Demodulation, processing, recording and distribution streams of data

Onboard record capability of TM data

Re-transmit S-Band TM data streams

Demodulation, de-commutation, processing, recording and distribution up to 4 streams of data

Redundant onboard record capability of TM data

Re-transmit L- or S-Band TM data streams in real time via line of sight re-radiation

Necessary to create telemetry shoot box for air-to-air weapons

8 Supporting Documents

Technical orders and operations instructions

Academic syllabus and course ware for classroom instruction

Necessary for system operations and maintenance

9 Telemetry Operators Console

Provides operator with ability to control, monitor, analyze and correct system operation inflight

Higher speed - higher refresh rate console

Necessary for system operations and maintenance

10 Telemetry Range

100 NM for S band

200 NM for L band 500 NM for S band

To support over-the-horizon telemetry requirements

511 Telemetry Source Altitude

Surface to 20,000 feet Greater than 20,000 feet Necessary to create telemetry shoot box for air-to-air weapons

E-9A Key System Attributes (KSAs) # KSA Threshold Objective 1 Built-in-test Report Reports system status on demand Auto-reporting for system failures 2 Modulation Capabilities Need to be able to downlink legacy PCM / FM Improved waveform and bandwidth efficiency SOQPSK and STC / LDPC capable

3 Controls and displays High System usability (Human machine interface) same as threshold

4 Software Capabilities Modular and upgradeable design

PCM / FM capable (software)

Able to turn on/off filters

SOQPSK and STC / LDPC capable

5 Standards IRIG 106 capable / Chapter 10 compatible same as threshold

6 System Availability Available 90% of the time for airborne envelope

Available 95% of the time for airborne envelope

7 System Cooling Constraints 70°C limitation within antenna control computer same as threshold

8 System Quality 90% usable data after reduction and analysis

95% usable data after reduction and analysis

9 System Reliability Reliable 90% of the time for airborne envelope

Reliable 95% of the time for airborne envelope

10 System Stability Capable of tracking 90% of airborne targets

Capable of tracking up to 95% of airborne targets

11 Target acquisition 15 seconds Less than 15 seconds 12 Target Tracking Speed Track up to Mach 5 same as threshold 13 Telemetry Channel Frequency 30 MHz per channel same as threshold 14 Telemetry Output Frequency 70 MHz same as threshold 15 Telemetry Recorder Need way to offload data from airplane to TM shop and customers same as threshold