DI-SAFT-82416
Data Requirements for Space Debris Mitigation Assessments
Specifies data the contractor must develop for Space Debris Assessment Reports and End-of-Life Plans, used by System Safety Managers to verify compliance with orbital debris mitigation standards.
Approval DateOctober 4, 2023
AMSC NumberF10431
Preparing Activity19
Project NumberSAFT-2023-002
OPR—
DTIC ApplicableNo
GIDEP ApplicableNo
Limitation—
Applicable Forms—
Approval Limitation—
Form Version—
DID Formatfree_text
963C CompliantYes
DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.
Supersedes
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Use & Relationship
Data Requirements for Space Debris Mitigation Assessments to support the development of a Launch Vehicle (LV)/Launch Service Space Debris Assessment Report (SDAR) and/or Space Vehicle (SV) Space Debris Assessment Report/End-of-Life Plan (SDAR/EOLP), IAW DAFI 91-202, The US Air Force Mishap Prevention Program including implementation changes per DAFI91-202_DAFGM2023-01, Department of the Air Force Guidance Memorandum dated 13 April 2023. Data will be used by the SSC AATS/LV or by the SSC/SV Program Office System Safety Managers (SSMs) to assess if contractors' United States (U.S.) Space Force LV or SV orbital system and mission design follows National Space Policy (NSP) and, U.S. Government (USG) Orbital Debris Mitigation Standard Practice (ODMSP). (The most current version of ODMSP and DAFI 91-202 in force can be obtained at: https://orbitaldebris.jsc.nasa.gov/mitigation/ and https://www.e-publishing.af.mil/, respectively.)
This Data Item Description (DID) contain the format, content, and intended use of the information for the data the contractor will need to develop and deliver to support assessment as defined by the contract statement of work (SOW).
In this document, "SV1" refers to space vehicles, and "LV" refers to launch vehicle stage(s) that become orbital. Both SVs and LV stages are addressed. "Orbital stage components" includes items released from the orbital stage, including adapters, spacer rings, etc.
Preparation Instructions
1Reference DocumentsThe applicable issue of the documents cited herein, including their approval dates and dates of any applicable amendments, notices, and revisions, shall be as specified in the contract.
2FormatData Requirements for Space Debris Mitigation Assessments shall be in contractor's format.
3ContentData Requirements for Space Debris Mitigation Assessments shall contain the following:
3.1A listing of all objects with longest dimensiongreater than 5 millimeters (mm) planned to be released into Earth orbit during normal operations of the SV or LV stage, along with the following information about each object:
3.1.1Rationale and a description of the necessity for release
3.1.2For an LV stagetime of release from launch for LV stage.
3.1.3For an SVtime of release from deployment of the SV from an LV stage.
3.1.4Release velocity with respect to the SV or LV stage
3.1.5Expected orbital parameters (apogee, perigee, and inclination)after release from the LV stage or SV.
3.1.6Calculated orbital lifetime until reentry into Earth's atmosphere
3.1.7Material composition, dimensions, and mass of object
3.2Total SV mass at the start of the missionat end-of-life prior to disposal, and at any events that separate distinct phases of the mission.
3.3Failure modes and effects analyses (FMEA) resultsdemonstrating that the integrated probability of explosion for all failure modes (excluding collisions) of each separate SV and orbital stage is < 0.001.
3.4Passivation methods and processes
3.4.1List of internal energy sources for the SV or orbital stagethat could cause an explosion (e.g., pressurized tanks, extra fuel or oxidizer, batteries, momentum wheels).
3.4.2Description of the plan for eliminating these internal energy sourcesas part of the end-of-life disposal plan.
3.5Expected timelines
3.5.1For the LVin appropriate units, from launch time (T-0), of the following events:
3.5.1.1Stage separation from the LV
3.5.1.2SV separation from the LV stage
3.5.2For the SV orbit transfer and flight profile planin appropriate units, from LV separation time (T-0), of the following events:
3.5.2.1SV mission events that cause changes in the orbital parameters(needed for assessment of Probability of Collision With Large Objects [PCWLO]).
3.5.2.2End-of-Life disposal
3.5.2.3Deployment of tether or atmospheric drag enhancement device (if equipped)
3.6The launch trajectory/flight profile plan
3.6.1Mission orbit(s) parameters (orbital elements) and time durationsspent in each mission orbit until initiation of disposal action.
3.6.2Disposal orbit(s) parameters (orbital elements) and time durationsspent in each distinct phase of the disposal profile until final disposal orbit is achieved.
3.6.3Planned trajectory fileif orbital elements or mass vary significantly due to frequent or constant maneuvering (e.g., during orbit transfer).
3.6.4Description of orbit maintenance or station-keeping plannedfor the mission duration. Describe how the orbit is going to be maintained via maneuvers or other means (e.g., electrodynamic tethers, solar sailing, differential drag control) during each phase of the mission.
3.6.5Description of any collision avoidance processthat is going to be performed during orbit transfer or mission operation, including controlled disposal (reentry or on-orbit). This description includes the criteria used to determine whether a collision avoidance action is performed, e.g., threshold on probability of collision at conjunction, miss distance, whether orbit transfer maneuver uncertainty is going to be accounted for (e.g., via covariance or Monte Carlo modeling).
3.7The SV and orbital stage components data (bill of materials)
3.7.1Physical dimensions (i.e., length, height, width, mass)of all dominant SV or LV stage components, to include: the SV bus or LV stage body, solar arrays, antennas, gravity gradient booms, adapter rings, etc.
3.7.2For items that have many gaps (e.g., trusses)effective projected area of solid portions or an accurate description of the item construction (e.g., a Computer-Aided Design (CAD) finite element model in a standard format).
3.8Data on SV components exposed to Micro-Meteoroids and Orbital Debris (MMOD)(not needed for LV stages):
3.8.1Tabulated list of components and surfaces exposed to MMODthat are needed to execute end-of-life disposal functionality (e.g., maneuvers, tether or sail deployment, propellant depletion), including components mounted to the inside of panels exposed to MMOD (since MMOD could penetrate through the panel and component wall).
3.8.2Description of redundancy of these components
3.8.3Data needed for each of these components to assess risk of damage by MMOD
3.8.3.1Criteria for MMOD to cause failure of the component(surface penetration depth, penetration hole diameter, number of penetrations or holes, probability of failure given a penetration has occurred, etc.)
3.8.3.2Exposed area of each component and surface
3.8.3.3Estimate of the fraction of the surface areaof each component and surface that is not blocked if an item is partially shielded from MMOD (e.g., less than 2*pi steradian field of view (FOV) for a flat surface).
3.8.3.4For each single exposed surface for which penetration could prevent disposalthickness and material (e.g., aluminum).
3.8.3.5For each single exposed surface on which cratering could prevent disposal(e.g., optical surfaces on sun sensors or star trackers): impact crater size or area that would prevent adequate operation of the component housing the optical surface for post-mission disposal, and material (e.g., fused silica glass, fused quartz glass, polycarbonate).
3.8.3.6For each dual-wall or multi-wall configuration(e.g., outer wall is shielding an inner wall whose penetration could prevent disposal): thickness and material of both walls, and spacing distance between walls. (This is needed to model the multiwall shock effect.)
3.8.3.7For each exposed panel that is a honeycomb sheetthickness and material of front and back panels and honeycomb panels connecting those two, and spacing distance between all panels.
3.8.3.8For each harness or cable that is exposed to MMODprovide a description of the cable design. For example, provide the Cable Type as described in D. Jex, A. Adkinson, J. English, and C. Linebaugh, "Hypervelocity Impact Testing of Cables," NASA TN D-7178, February 1973.
3.8.3.9For each surface covered with multi-layer insulation (MLI)that is exposed to MMOD, provide the mass per unit area of MLI (or description with sufficient detail to compute this) and spacing distance of MLI from covered surface.
3.8.3.10For pressurized vessels (e.g., Composite Overwrapped Pressure Vessel (COPV))Maximum penetration depth of vessel wall before wall rupture occurs due to pressurized fluid.
3.8.3.11Surface orientation in the SV bus frame (i.e., surface normal vector)
3.8.4Description of the SV bus attitude motionrelative to a relevant standard frame (e.g., local vertical/local horizontal frame, Earth-centered inertial frame, Sun-centered inertial (ecliptic) frame. (This is needed so that the fraction of time spent by the surface in each orientation can be determined.)
3.9Tabulated list of items needed to assure post mission disposal reliability
3.9.1Systems, subsystems, and components required to accomplish post mission disposal operations
3.9.2End of mission reliability assessment results for each system, subsystem, and vehicle (SV and upper stage) component
3.9.3Reliability assessments should account for failures occurringfrom start of mission to completion of disposal, including the entire mission design life.
3.10Data for uncontrolled reentry hazards assessment
3.10.1Tabulated list of parts(e.g., a master equipment list - see Example Space Vehicle Data Template on page 6) for each reentering vehicle (SV and upper stage), to include:
3.10.1.1Mass and quantity of each part
3.10.1.2Material composition of each part(e.g., 2024 Aluminum, 410 Stainless Steel, Kevlar, graphite-epoxy, titanium alloy Ti-6Al-4V)
3.10.1.3Physical dimensions for each part(including height, width, length, wall thickness; for honeycomb panels, also include face-sheet thicknesses, honeycomb density)
3.10.1.4Illustrations or graphics of the shape of each part
3.10.1.5Illustrations or graphics showing placement of the parts in relation to each other
3.10.1.6Parent/Child relationship for each part
3.10.2Classical orbital elements, or best estimatesat end-of-mission for each reentering vehicle.
3.10.3Expected year of reentry from an orbital lifetime analysisassuming a nominal atmospheric profile, for each reentering vehicle.
3.11Data for controlled reentry assessment
3.11.1Description of vehicle (SV and upper stage), to include
3.11.1.1Mass of the vehicle both pre-and-post reentry maneuver
3.11.1.2Propulsive capability of the vehicle (thrust and specific impulse)
3.11.1.3Delta-V and propellant mass required to accomplish post-mission disposal
3.11.1.4Physical dimensions of the vehicle (including length, width, height, or diameter)
3.11.1.5Illustration or graphic of the vehicle
3.11.1.6Expected debris casualty area (Ac) associated with reentry or breakup
3.11.2Reentry trajectory profile with targeted impact location
3.11.3Classical orbital elements, or best estimatesat end-of-mission for each reentering vehicle.
3.11.4Assessment of reentry maneuver reliability based on vehicle flight history
3.11.4.1List of the number of successes, failures, partial failuresor significant anomalies for all prior missions of the LV.
3.11.4.2List of previous controlled reentry attempts of the LV and associated outcomes
3.12Data for drag enhancement devices (if equipped) other than tethersfor controlled reentry assessment, including:
3.12.1Expected projected area after deployment and percent confidence level for this deployment for each device
3.12.2Dimensions, shape, material, and mass of each device
3.12.3Time of deployment of each device after mission start
3.12.4Procedure for drag device deployment and control until reentry
3.12.5Construction characteristics that make each drag enhancement device resilientto debris and meteoroid impacts (e.g., balloon rigidization, compartments), and the expected size of debris or meteoroid that could make it non-functional as a drag enhancement device.
3.12.6Expected change in ballistic coefficient/drag profile stemming from deployment of drag device
3.12.7Classical orbital elements, or best estimatesat end-of-mission for each reentering device.
3.13Data for tethers (if equipped)
3.13.1Expected tether length after deployment and percent confidence level for this deployment for each tether
3.13.2Width (if flat tape) or diameter (if round) of each tether
3.13.3Mass of each tether or device
3.13.4Tether end mass of each tether
3.13.5Time of deployment of each tether after mission start
3.13.6Tether construction that makes it resilient to debrisand meteoroid impacts (e.g., material, braiding, multiple strands), and expected size of debris or meteoroid that could sever the tether or make it non-functional as a drag enhancement device.
3.13.7Expected change in ballistic coefficient/drag profile stemmingfrom deployment of tether Classical orbital elements, or best estimates, at end-of-mission for each reentering tether or device.
3.13.8Data on prior on-orbit performance for each tether
3.13.8.1Data-based rationale for each tetheron the effect(s) any prior on-orbit performance has had on the current device design.
3.13.8.2Description of whether and how the device wasdamaged or severed by debris or meteoroid impacts or by collision with another object.
3.13.8.3Description of how successful the device was(e.g., did it successfully achieve expected reduction in orbital lifetime?)
3.13.8.4Description of orbit operations plan for an electrodynamic tether (if applicable)
References
Figures
Figure Table 1. Example Space Vehicle Data Template
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