RIDE RFI - Legacy RSLP MA Requirements - Attachment 2.pdf

RIDE RFI Attachment 2 – Legacy RSLP Mission Assurance Requirements

Intent and Limitations: This Attachment supports the RIDE RFI by providing industry with an overview of the requirements for the Government Mission Assurance (MA) processes currently on the Sounding Rocket Program-4 (SRP-4), Small Rocket Program-Orbital (SRP-O), and Orbital Services Program-4 (OSP-4) contracts. This document is intended to be used as background information to aid in the development of industry suggestions and answers to RIDE RFI questions. This attachment does not include all requirements or details related to the Government Mission Assurance or Spaceflight Worthiness processes. If further information is desired, please refer to the SRP-4, SRP-O, and OSP-4 Performance Work Statements and Contract Data Requirements Lists contained in the respective Requests for Proposal previously posted on SAM.gov.

Figure 1: RSLP Mission Assurance Overview

Figure 2: RSLP Mission Assurance Category 1 Process Overview

Figure 3: RSLP Mission Assurance Category R Process Overview

Figure 4: RSLP Mission Assurance Category 2 Process Overview

Mission Assurance Support Service:

Category 1: These missions may be subject to the SSC spaceflight worthiness certification process and/or be licensed under Federal Aviation Administration (FAA) licensing guidelines with accompanying Government Mission Assurance (MA) activities. For spaceflight worthiness certified missions, the Launch Services Contractor (LSC) must analyze the launch system against each of the criteria listed in SMC-G-1202 “Spaceflight Worthiness Criteria” (SFWC), identify compliance or non-compliance, and cite confirming evidence and/or associated mitigations for non-compliances. For FAA licensed missions, the LSC obtains the FAA launch license and is responsible for fulfilling all requirements to obtain the license. In addition, the LSC is responsible for ensuring the applicable launch site meets FAA licensing requirements and any activities required to bring the launch site into licensing compliance. This LSC must demonstrate that all required FAA licenses have been obtained at the Pre-Ship Review (PSR). Additional analyses required for Category 1 missions include:

A1-1.1 Payload Trajectory and performance analysis

A1-1.2 RF Analysis (including intermod analysis)

A1-1.3 Antenna patterns and link analyses

Category R (Responsive): These missions are subject to the SSC spaceflight worthiness certification process. The LSC must provide additional information and support for the Government’s MA efforts. Responsive MA is tailored Category 2 MA, to enable a responsive launch timeline. Specifically, required data deliverables are not listed here; however, the Category 2 list below includes more data products than those required for Category R missions.

Figure 1 above provides a general overview of the Government MA activities required for Category R missions.

Category 2: These missions are subject to the SSC spaceflight worthiness certification process.

The LSC must provide additional information and support for the Government’s MA efforts. In addition, the following launch service requirements are applicable for these missions:

Analysis Requirement Title of Analysis Analysis Details

A1-2.1 Ordnance Design

Overview of Ordnance FTS system and components, with complete parts list of major components/subassemblies. Including schematic of location of ordnance components on the launch vehicle and interconnects.

A1-2.2 Critical Connections

Critical connections list is a list of connector matings that cannot be electrically verified (e.g. no electrical checkout) at the Range.

Documentation to include rationale for confidence in proper function of each critical connection.

A1-2.3 Vehicle Outer Mode Line

(OML)

Detailed dimensions of OML of booster with interstage and fairing. The dimensions should include all external protuberances including landing legs and movable fins. This data can be substituted with 3D CAD models in Pro-E and/or STEP format.

A1-2.4 Thermal Protection System

(TPS)

Provide dimensional analysis of TPS layout and TPS design.

A1-2.5 Descriptions & relationships of coordinate frames

Provide GNC Implementation guide including definitions of coordinate frames.

A1-2.6 IMU Interface Indicate orientation and location of IMU sensors with respect to the LV Body coordinate frame.

A1-2.7 Structural and Assembly Analysis

The intent of this request may be satisfied by sharing CAD data. ProE and STEP format are acceptable.

A1-2.8 Electrical Ground System Design

Describe system ground design – e.g. single point ground, chassis ground. Include grounding design approach, capabilities, and test performed to verify requirements.

A1-2.9 Wind Tunnel Test subscale model dimensions

Dimensional drawings of subscale WT test model. The drawings can be substituted with 3D CAD model in ProE and/or STEP format.

A1-2.10 Thermo-couple locations and installation methodology

Locations and range of sensors used for mission including analytical model function for conversion of data to engineering units (i.e.

conversion from mV to degree F in thermocouple)

A1-2.11 Assembly of Launch Vehicle Locates where the components are on the vehicle

A1-2.12 Flight computer software architecture

Describe common vehicle architecture as well as mission-unique elements. Must include all references. Include software flow charts, architecture diagrams, functional organization, hierarchy, interfaces, and data structures.

A1-2.13 GSE software architecture

Describe GSE architecture as well as mission-unique elements. Must include all references.

Include software flow charts, architecture diagrams, software design elements such as functional organization and hierarchy, interfaces, and data structures.

A1-2.14 Software Design Documents Traceability

Provide traceability from software requirements to software design.

A1-2.15 Software test planning procedures, data capture and analysis

Describe the software test environment, support applications, and support hardware/firmware, levels of testing, progression, data recording, and analysis.

Examples of key information are as follows:

Planning - types of tests; Procedures - pass/fail criteria; Analysis - review methods; Reports -traceability to requirements.

A1-2.16 (SRP-4) Test-Like-You-Fly Assessment

List of component/subsystem/system-level test configurations that are not same as the flight configurations. List of simulators/non-flight hardware used during tests. Justification of use of non-flight configurations and simulators.

A1-2.16 (OSP-

4) Test Planning

List of component/subsystem/system-level test configurations that are not same as the flight configurations. List of simulators/non-flight hardware used during tests. Justification of use of non-flight configurations and simulators.

A1-2.17 Field Test Procedures

Integration and test procedures used at the Range including GSE checkout procedures, LV integration and launch procedures (including launch countdown and mission constraints) and identification of hazardous procedures.

A1-2.18 Wind-Tunnel Test Plan with Test Matrix

Descriptions of test objectives, test setup, test matrix (including itemization/prioritize primary test vs. secondary test objectives), data collection methodology, data type, and sensors layout.

A1-2.19 Component Qualification and Acceptance test Plan/

Component-level Qualification Test Plan Including NDE inspection procedures for structures.

A1-2.20 Transportation and Handling procedures

T&H procedures to include logistics and transportation overview for all flight and critical hardware.

A1-2.21 Avionics Qualification matrix

Include component, component part number and dash number, as-mounted locations, mounting configuration, qual test requirements, qual test results. As applicable, include (1) thermal cycle, (2) vacuum thermal,

(3) random vibration, (4) sine vibration, (5) shock and (6) remaining useful life and life expiration date (as required).

A1-2.22 ACS Qualification matrix

Include component, component part number and dash number, as-mounted locations, mounting configuration, qual test requirements, qual test results. As applicable, include (1) thermal cycle, (2) vacuum thermal,

(3) random vibration, (4) sine vibration, (5) shock and (6) remaining useful life and life expiration date (as required).

A1-2.23 Pneumatics Qualification matrix

Include component, component part number and dash number, as-mounted locations, mounting configuration, qual test requirements, qual test results. As applicable, include (1) thermal cycle, (2) vacuum thermal,

(3) random vibration, (4) sine vibration, (5) shock and (6) remaining useful life and life expiration date (as required).

A1-2.24 Ordnance Qualification matrix

Include component, component part number and dash number, as-mounted locations, mounting configuration, qual test requirements, qual test results. As applicable, include (1) thermal cycle, (2) vacuum thermal,

(3) random vibration, (4) sine vibration, (5) shock and (6) remaining useful life and life expiration date (as required).

A1-2.25 Propulsion Qualification matrix

Include component, component part number and dash number, as-mounted locations, mounting configuration, qual test requirements, qual test results. As applicable, include (1) thermal cycle, (2) vacuum thermal,

(3) random vibration, (4) sine vibration, (5) shock and (6) remaining useful life and life expiration date (as required).

A1-2.26 Structural Qualification matrix

Include component, component part number and dash number, as-mounted locations, mounting configuration, qual test requirements, qual test results. As applicable, include (1) thermal cycle, (2) vacuum thermal,

(3) random vibration, (4) sine vibration, (5) shock and (6) remaining useful life and life expiration date (as required).

A1-2.27 Avionics System-Level Test Test results for all avionics system and subsystem level tests (including as-run procedures) executed on flight hardware

A1-2.28 Wind-Tunnel Post-Test Test results providing test objectives, as-run procedures and test results.

A1-2.29 Subsystem-Level Test Subsystem acceptance testing results.

A1-2.30 System-Level Test System acceptance testing results.

A1-2.31 System Level EMI/EMC Test

Test results to include description of test, test set up and test data plots.

A1-2.32 Vehicle Electrical Design Analysis

Derating analysis, transient circuit analysis, short circuit analysis, EMI/EMC compatibility analysis, bent pin analysis, pyro load box resistance analysis.

A1-2.33 Payload/SV(s) thermal analysis

Provide payload/SV(s) thermal environments report including time from leaving payload processing facility, during pad operation, liftoff, boost phase, coast phase and separation.

A1-2.34 (for liquid stages) Stage pressure vessels thermal analysis

Provide pressure, temperature, total mass, and volume (both equilibrium and transient states if applicable) inside a tank. Provide calculation methodologies and uncertainties.

A1-2.35 Linear Stability Analysis

Ascent controls analysis reports. As a preliminary delivery, deliver report for a similar vehicle configuration & mission, as well as a preliminary report for the current mission.

A1-2.36 Launch vehicle predicted environments derivation

Methodology used to define maximum predicted environment at tested component locations.

A1-2.37 Link Analysis

Analysis of link margin for all RF systems:

telemetry systems, flight terminating system, and range tracking system. Report to include LV RF system characteristics, LV antenna patterns, ground station RF characteristics and locations, 6-dof trajectory, and margin.

A1-2.38 Intermodulation Analysis

Intermodulation analysis of all known RF emitters on LV, payload, & ground. Report to include RF characteristics of emitters and receivers, and analysis results.

A1-2.39 Battery Margin Analysis

Analysis of battery margins remaining at the end of mission. Report to include analysis input data (list of power channels, power levels), analysis results, verification.

Scenarios to include nominal & anomalous power management.

A1-2.40 Methodology for Aero- Model Derivation

Provide description of aero model, including source data, methodology, results, uncertainties, and comparison to past mission data. Include aero-static and aero buffet environments and assumptions.

A1-2.41 Pad Ignition/lift-off analysis

Ignition overpressure and thermal loads environments on vehicle at lift-off including analysis methodology, source of data, and impact assessment of the system due to environments.

A1-2.42 Staging analysis The report includes descriptions of input parameters, methodology, and resulting conclusion related to moving body separation.

A1-2.43 LV/Fairing venting To include description of input parameters, methodology, and resulting conclusions for LV venting including the fairing.

A1-2.44 (for liquid engines) Engine combustion phenomenon analysis report

Combustion kinetic model, combustion products at various location in nozzle as well as at the turbo pump exit along with corresponding pressure and temperature, mass flow rate, O/F mixing ratio.

A1-2.45 LV TPS design analysis Including TPS designs, property data, adhesive bonding material type, bonding material properties and temp/pressure design limits. Provide margins calculations for predicted aero-heating.

A1-2.46 Payload/SV(s) contamination analysis

Provide assessment of encapsulated payload/SV(s) cleanliness environment.

A1-2.47 Collision Contamination Avoidance Maneuver Analysis (C/CAM)

Report assessing contamination to payload from LV to include type and quantity of contaminants. Report to include methodologies used in analysis.

A1-2.48 Launch availability analysis To include day of launch procedures and timeline.

A1-2.49 Structural Analyses Design summary and structural analyses for all major launch vehicle subsections, including fatigue analyses where applicable.

A1-2.50 Coupled Loads Analysis (CLA) Model

NASTRAN (or similar) coupled loads model for LV/payload.

A1-2.51 Flight computer and flight software interfaces

Define and document both the electrical and software interfaces to the flight computers and ground systems, including the user interface.

Includes details such as wiring schematics, protocols, message formats (headers, data, checksums), port assignments, clock information, serial/Ethernet data rates, discrete signals, etc. Also includes details on algorithms execute on an external device which may affect the interfaces (e.g., fault tolerance/voting logic).

A1-2.52 Software process and development

Flight and Ground Software Development Plans.

1) Software development management (including software planning, schedule, software tools and environment, software metrics)

2) Software development process (including software development phases, documentation, reviews, software reuse, coding standards etc.)

3) Software quality assurance (including organization/responsibilities, audits/evaluations, test participation, reporting, etc.)

4) Software configuration management (including configuration identification and control, software migration, software development library/tool, CM processes, etc.)

A1-2.53

Software load and initialization descriptions and procedures performed in the field

Provide software/firmware and configuration files load and verification procedures for the field. Provide formal artifacts required to prove that software is loaded correctly.

A1-2.54 Space Radiation Analysis Methodology and calculation of probability of system failure due to space radiation exposure.

A1-2.55 Comprehensive As- Designed/As-Built Analysis

Identifies all components installed in the launch vehicle by part number and serial number, location, and type of mounting (e.g.

shock mounted) if applicable; highlights any deviations from the as-designed launch vehicle.

A1-2.56 Discrepancy Identifies discrepancies encountered during assembly/integration/test and disposition/approval results.

A1-2.57 Material Non-conformance Identifies non-conformances found in material items during assembly/integration/test and disposition/approval results.

A1-2.58 Waiver Identifies waiver for any requirement not met during assembly/integration/test and disposition/approval results.

A1-2.59 Deviation Identifies deviation for any procedures during assembly/integration/test and disposition/approval results.

A1-2.60 De-commutated digital version of all telemetered data

Captures all telemetered data in de-commutated format for post-mission analysis.

A1-2.61 Failure Modes and Effects Analysis

Describes failure modes of subsystems and the effects on system operation.

A1-2.62

(OSP-4)

Specification and Requirements Documents

Identifies full set of derived requirements for the mission, including a system specification. Includes Requirement and Traceability Matrices for each document

A1-2.63

(OSP-4)

Documentation/Specification Tree

Identifies how all applicable requirements, specification and interface documents relate to each other

A1-2.64 (OSP-4) Interface Control Documents

Identifies full set of interface requirements, including for SV(s) and launch site/range.

Includes Requirement and Traceability Matrices for each document

A1-2.65

(OSP-4)

Requirements Traceability and Verification Matrix

Traces Government and customer requirements from contractual compliance documents including PWS, SPRD, SIS and MRD to mission specifications and interface documents. Identifies how each requirement will be verified and cites evidence of verification

A1-2.66

(OSP-4)

Spaceflight Worthiness Criteria Matrix

Provides status of compliance with each applicable SFWC criteria listed in SMC-G- 1202 Appendix I along with explanation of how criteria is met and evidence citation

Category 3: Category 3 MA support includes all items in Category 2. In addition, the LSC’s efforts are subject to increased depth and breadth of IV&V. RSLP has not historically had a Cat 3 mission.