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Appendix J: Launch Vehicle Systems

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Appendix J: Launch Vehicle Systems

APPENDIX J: LAUNCH VEHICLE SYSTEMS WORK BREAKDOWN STRUCTURE AND DEFINITIONS J.1 SCOPE This appendix provides the Work Breakdown Structure and Definitions Launch Vehicle Systems. This WBS applies to interplanetary and earth orbital missions. This WBS is not intended for weapon systems. Definitions for WBS elements common to all defense materiel items are given in Appendix L: Common Elements, Work Breakdown Structure and Definitions and common elements applied uniquely to Launch Vehicles are in Section L.5 of Appendix L.

J.2 APPLICABLE DOCUMENTS

J.2. 1 Non-Government publications. The following documents form a part of this document to the extent specified herein.

AMERICAN NATIONAL STANDARDS INSTITUTE (ANSI)

ANSI/IEEE STD 610.12-1990 (R2002), Standard Glossary of Software Engineering Terminology

ANSI Standards can be found online at:

http://webstore.ansi.org/ansidocstore/default.asp

ANSI Customer Service 25 W 43rd Street, 4th Floor New York, NY, 10036

or

The Institute of Electrical and Electronics Engineers, Inc. (IEEE) Service Center 445 Hoes Lane Piscataway, NJ 08855-1331 www.ieee.org

J.3 WORK BREAKDOWN STRUCTURE LEVELS

  • 1.0Launch Vehicle System
    • 1.1System Engineering, Integration, Test, Program Management (SEIT/PM)
      • 1.1.1System Engineering (SE)
      • 1.1.2Integration and Test
      • 1.1.3Program Management
    • 1.2Launch Vehicle
      • 1.2.1SEIT/PM
      • 1.2.2Stages 1…n (Specify)
        • 1.2.2.1SEIT/PM
        • 1.2.2.2Structures and Mechanisms
        • 1.2.2.3Propulsions System
        • 1.2.2.4Reaction Control System
        • 1.2.2.5Recovery System
        • 1.2.2.6Environmental Control System
        • 1.2.2.7Stage Peculiar Avionics
        • 1.2.2.8Other Systems 1…n (Specify)
      • 1.2.3Payload Accommodations 1…n (Specify)
        • 1.2.3.1SEIT/PM
        • 1.2.3.2Payload Fairing
        • 1.2.3.3Payload Adapter (Pedestals)
        • 1.2.3.4Mission Unique Hardware (Launch vehicle) 1…n (Specify)
      • 1.2.4Avionics
        • 1.2.4.1SEIT/PM
        • 1.2.4.2Guidance navigation and Control
        • 1.2.4.3Power
        • 1.2.4.4Data Acquisition and Telemetry
        • 1.2.4.5Range Tracking & Safety (Airborne)
        • 1.2.4.6Flight Software Release 1…n
        • 1.2.4.7Other Avionics 1…n (Specify)
    • 1.3Mission Integration and Analysis 1…f (Specify)
      • 1.3.1Mission Standard Integration & Analysis
      • 1.3.2Mission Unique Integration & Analysis 1…n (Specify)
    • 1.4Launch Operations Site 1…n (Specify)
      • 1.4.1SEIT/PM
      • 1.4.2Vehicle Processing and Checkout
      • 1.4.3Mission Services
        • 1.4.3.1Mission Unique Hardware (Launch Operations) 1…n (Specify)
        • 1.4.3.2Space Vehicle Processing
      • 1.4.4Launch
      • 1.4.5Flight Operations
      • 1.4.6Post Launch
        • 1.4.6.1Recovery Operations and Services
        • 1.4.6.2Post Launch Refurbishment
      • 1.4.7Site Maintenance
      • 1.4.8Base Support
      • 1.4.9Range Tracking & Safety (Ground)
        • 1.4.9.1Range Ground System
        • 1.4.9.2Range Operations
    • 1.5Launch Site 1…n (Specify)
      • 1.5.1SEIT/PM
      • 1.5.2Operational/Site Activation
      • 1.5.3Peculiar Support Equipment
      • 1.5.4Ground Command, Control and Communications (GC3)
        • 1.5.4.1SEIT/PM
        • 1.5.4.2Command, Control and Communication
        • 1.5.4.3Other Ground 1…n (Specify)
    • 1.6System Test and Evaluation
      • 1.6.1Development Test and Evaluation
      • 1.6.2Operational Test and Evaluation
      • 1.6.3Mock-ups/System Integration labs (SILs)
      • 1.6.4Test and Evaluation Support
      • 1.6.5Test Facilities
    • 1.7Training
      • 1.7.1Equipment
      • 1.7.2Services
      • 1.7.3Facilities
    • 1.8Data
      • 1.8.1Technical Publications
      • 1.8.2Engineering Data
      • 1.8.3Management Data
      • 1.8.4Support Data
      • 1.8.5Data Depository
    • 1.9Peculiar Support Equipment
      • 1.9.1Test and Measurement Equipment
      • 1.9.2Support and Handling Equipment
    • 1.10Common Support Equipment
      • 1.10.1Test and Measurement Equipment
      • 1.10.2Support and Handling Equipment
    • 1.11Industrial Facilities
      • 1.11.1Construction/Conversion/Expansion
      • 1.11.2Equipment Acquisition or Modernization
      • 1.11.3Maintenance (Industrial Facilities)
    • 1.12Initial Spares and Repair Parts

J.3.1 Application of Common WBS Elements (Appendix L). For Launch Vehicles, the common WBS elements must include, as a minimum, systems engineering, integration and test, and program management (SEIT/PM). Common elements are found throughout all levels of a WBS and are located one WBS level below the product oriented WBS they support (e.g., Launch Vehicle SEIT/PM would be captured at Level 3 under the Launch Vehicle element). Other common elements, such as training or data, as applicable, should be included in the WBS structure. The WBS structure is not complete without the application of common elements. Definitions for all common elements are in Appendix L. For the uniquely applied System Engineering, Integration and Test, Program Management (SEIT/PM) and Operational Site Activation for Launch Vehicles, reference Appendix L, section L.5.

J.3.2 Application of (1…n), and (1…f) convention. This document uses a (1…n) after WBS element titles where the element may have multiple unique occurrences. When creating the WBS for a specific program or contract, the (1…n) shall be replaced with a specific name for the item.

NOTE: The (1…f) convention is similar to the 1…n convention above, but is refers to different payload “flight” configurations.

J.3.3 Use of “Other” WBS Elements. The Other WBS elements at the system, subsystem, and element (product) levels are restricted to products that have not been envisioned or predicted in the other defined WBS elements. This element should only be used when all other elements have been thoroughly examined and do not fit the definition of the “other” product. In addition the WBS dictionary should clearly define the elements. The program WBS index shall describe the element(s) and avoid any reference to “other”.

J.3.4 Key Principles in Constructing a WBS. In the appendices of MIL-STD-881C, the WBS is defined to Level 3 of that structure and in some cases Level 4 or 5. In order to ensure consistency across all systems and developers, WBS elements in the appendices are extended to levels 4 and 5.

  • 1) The reporting level of the WBS is typically at Level 3 except for those items considered high cost, high risk, or high technical interest. For those elements, extension of the WBS to lower levels is necessary to get needed visibility, but only for those elements. Not all WBS elements should be extended to the lowest level. In addition, for each system being defined only those WBS elements that define the system shall be used. The purpose of going below level 3 within the appendix is to ensure that the higher level elements include the proper lower level elements and when required to report at a lower level, those elements at level 4 or 5 are consistent across all systems and developers.
  • 2) In each of the appendices, an element entitled “Other” is available to provide flexibility within the WBS for new or additional WBS elements that are not identified or defined in the Standard. These “other” elements would be used if, for example, a new subsystem or modified subsystem is defined and it does not currently appear in the appendices of MIL-STD-881C.
  • 3) A key to WBS development is the principle that if you can associate the WBS element with the element it supports, it should be included within that element. This is called the 100% rule, which states the next level of decomposition of a WBS element (child level) must represent 100% of the work applicable to the next higher level (parent level). For example, the parent level WBS (radar system) has three child elements – transmitter, antenna, and receiver. If the program manager decides he/she wants more visibility into the transmitter subsystem and pulls it out of the radar system and makes it a level equal to the radar, it distorts the effort and resources that are required to complete that radar system because it assumes the transmitter is not included (i.e., a child element to the radar is now missing within the WBS structure).
  • 4) In some cases, items cannot be specifically associated with the element they support. For example, software is a critical element of that transmitter subsystem. Under normal circumstances, software would be the child level to the parent level transmitter. However, depending on how software is developed, the software may include more functionality than just for the transmitter subsystem. It may include functionality for the receiver as well. In this case the software cannot be associated with the specific elements they support, due to an inability to determine the effort for each functionality developed. Therefore, it is appropriate to associate that software to the next highest level (radar system) of the WBS. It is still included as a part of the radar system at the child level, but we are not trying to allocate effort across multiple WBS elements where we are unable to determine what level of support each gets.
  • 5) Intelligence (Intel) efforts (security, threat, mission data) are often considered late in the acquisition cycle, even after contract award. Identifying where Intel is needed reduces risk and affords a much better opportunity to manage cost, schedule, and performance. The WBS Standard portrays systems in a product-oriented WBS, identifying and considering potential intelligence information and costs using the existing Component cost estimating processes.

J.3.5 Numbering of the WBS. In each appendix, the work breakdown structure for that commodity has been numbered for reporting purposes only. The purpose for the numbering is to provide a consistent approach to identifying and managing the WBS across like systems regardless of vendor or service. The numbering system is numeric; however, several unique issues arise across appendices which require the numbering system to be modified to accommodate the anomalies.

J.3.5.1. “Other” WBS Elements. All appendices contain a WBS element titled as “Other” at the subsystem, element (product) levels that are restricted for products that have not been envisioned or predicted within the defined WBS elements in the Appendix. If it is determined that the “other” WBS is not needed, this element and assigned WBS number should be deleted and not used in the WBS. If it is determined that the “other” element is needed, then each element must be defined and the word “other” replaced by the newly defined WBS element using the assigned WBS number from the appropriate appendix. The newly defined element must be approved by the Government Program Manager and the representative contracting officer.

J.3.5.2 (1…n) WBS Element Definitions. Several appendices identify WBS elements with (1…n) or similar to denote that one or more of that type of item may be used. Where this structure occurs, the parent WBS (e.g., 1…n) shall be decomposed to the next level and then each child WBS use the appropriate WBS title for each element as well as the WBS numbering identification. For example, if a missile system has multiple propulsion subsystems, each Propulsion Subsystem (1…n) shall have a WBS name designation (for example, “Solid Rocket Motor”), and the element Propulsion Subsystem 1 would be at the child level of the parent WBS element (Propulsion Subsystem 1…n) as would Propulsion Subsystem 2 (for example, “Liquid Rocket Engine”), and so forth. Each WBS should be detailed down to the element’s lower level (as defined in the appendices) whenever possible, and assigned the next available WBS number in sequence according to the parent child relationship as shown below.

  • 1.1.2. Propulsion Subsystem (1…n)
  • 1.1.2.1. Solid Rocket Motor
  • 1.1.2.2. Liquid Rocket Engine
  • 1.1.2.3. Backup Rocket Motor

J.4 DEFINITIONS

J.4.1 Launch Vehicle System. The complex of equipment (Hardware/Software), facilities and all of the resources associated with the design, development, production, refurbishment, integration, assembly, test, and operation of the entire payload lift Launch Vehicle System required to insert the Space Vehicle or probe into a space orbit/trajectory.

J.4.2. Launch Vehicle. Includes all resources associated with the design, development, production, refurbishment, integration, assembly, test and evaluation, and launch operations support of the entire Launch Vehicle. The Launch Vehicle is an earth-to-space transfer vehicle that is self propelled after leaving its launching platform. It can be expendable or reusable as it relates to the delivery of payloads to specific trajectories or orbits in space.

  • Includes, for example:
  • a. All applicable stages
  • b. Payload accommodations
  • c. Avionics
  • d. Requalification and inventory restock due to obsolescence and/or shelf life

NOTE: For lower level Common Elements, e.g., SEIT/PM, reference Appendix L section L.5.

J.4.2.1 Stages 1…n. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operations support and support of the Stages of the Launch Vehicle. A launch vehicle can be comprised of multiple (expandable and/or reusable) stages (1…n). The purpose of each stage is to propel the remaining portion of the Launch Vehicle and/or Space Vehicles to a certain elevation, trajectory and orbit.. During flight, as each stage is expended, it is typically separated from the active portion of the Launch Vehicle to improve efficiency and eliminate unnecessary mass.

As an example, a multi-stage Launch Vehicle could consist of a liquid core booster stage (Stage 1) with attached solid rocket motors (Stage 2), known as “strap-ons”, and with additional sequential numbered stages being liquid (or solid) propulsion system, (Stage 3). Stage 4, etc. The numeric “Stage” numbering continues until the stage below the payload and launch vehicle adapters.

The elements of a Stage may include a wide variety of sub-systems depending on the design, configuration and the specific mission.

  • Includes, for example:
  • a. Structures and mechanisms (including operational ordnances and range safety ordnances),
  • b. Propulsion system
  • c. Power systems
  • d. Reaction control system,
  • e. Recovery system (if required)
  • f. Environmental control systems deemed necessary
  • g. Stage peculiar avionics

J.4.2.1.1 Structures and Mechanisms. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operations support and support of the Structures and Mechanisms element of the Launch Vehicle.

  • Includes, for example:
  • a. The structural framework that provides the aerodynamic shape, mounting surfaces and physical structures and tanks such as environmental protection for the Launch Vehicle stage elements
  • b. Mechanical elements for the Launch Vehicle stages containing structural members that serve some functional mechanical movements that interfaces with other dynamic or static elements or subsystems. Mechanical elements may be actuated by electrical, gas, pyrotechnic or hydraulic forces
  • c. Stage separation mechanisms such as ordnance bolts and springs (e.g., retro rockets, staging motors, pyrotechnic valves and bolts)
  • d. Paint and corrosion control
  • e. Other mechanisms and support structures that are not defined elsewhere within the WBS and are cost separable
  • Examples of Structures include:
  • a. Wings, tails, fins, canards and other control surfaces that provide aerodynamic flight control in response to actuators, electro-mechanical signals and are attached to the air vehicle body
  • b. Structural body assemblies including the structure, pipe and tube lines, and fuel tanks that are integral with the structure
  • c. Electrical harnesses, cords and wiring with associated brackets, stays, fasteners and grommets
  • d. Thrust structure, heat shields, intertank adapters and connectors, interstage adapters, skirts, nose cones and miscellaneous mounting brackets and supporting structures
  • Examples of Mechanisms include
  • a. Miscellaneous deployment devices, landing gear and struts
  • Excludes, for example:
  • a. Adapters that fall under payload accommodations

J.4.2.1.2 Propulsion System. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operations support, and support of the Propulsion System element of the Launch Vehicle. The Propulsion System includes the equipment to provide thrust to propel the launch vehicle on its intended flight. The total propulsion system may be composed of one or more subsystems that ignite, burn, and may (or may not) be jettisoned sequentially over the course of flight. Individual subsystems may employ solid, liquid, and/or air-breathing technologies.

  • Includes, for example:
  • a. Primary propulsion elements such as solid rocket motors, liquid rocket engines, and/or air breathing engines
  • b. Subsystems required to generate propulsion such as manifolds, bell-housing, pumps, lines and tubing, fuel and oxidizer injectors, valves (mechanical, electro-servo, pyrotechnic etc.), start cartridges and engine/motor performance sensors
  • c. Components associated with Thrust Vector Control (TVC) and fuel/oxidizer liquid management (i.e., feed lines, pressurization system and/or pressure control, pumps, valves, actuators etc.)

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems. NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.2.1.3 Reaction Control System (RCS). Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support, and support of the RCS element of the Launch Vehicle. The RCS includes hardware resident on a stage used for attitude control and steering. The RCS is capable of providing small amounts of thrust in any desired direction or combination of directions, providing torque to allow control of rotation (pitch, yaw, and roll). The RCS often uses combinations of large and smaller (vernier) thrusters (e.g., cold gas, warm gas, liquid propellant, solid propellant), to allow different levels of response from the combination.

  • Includes, for example:
  • a. All of the thrusters, lines, valves, propellant tanks, gas tanks, manifolds, etc. associated with the RCS
  • Excludes, for example:
  • a. The control system or elements of the control system if these are separate from the RCS (i.e., included under the Guidance Navigation and Control element) with the only interface being a signal to a valve, actuators or distributor on the RCS
  • b. The thrust vector control (TVC) system associated with the main propulsion system, which is included within the Propulsion System

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems. NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.2.1.4 Recovery System. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support, and support of the Recovery System element of the Launch Vehicle.

  • Includes, for example:
  • a. Equipment required to control final descent velocity and attitude after separation,
  • b. Items used to protect hardware being recovered from adverse environmental elements
  • c. Equipment used to facilitate recovery and transport operations
  • d. Parachutes, methods of sequencing and deploying these parachutes and parachute separation components
  • e. Flotation and/or landing pad devices and/or landing gear
  • f. Impact resilient devices
  • g. Location aids that assist in the search and retrieval operations for the expended elements
  • Excludes, for example:
  • a. Recovery operations and services, which are included under Recovery Operations and Services

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems.

NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.2.1.5 Environmental Control System. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support, and support of the ECS for the Launch Vehicle. The ECS is used to maintain and control an appropriate heat balance between absorbed radiation, internal heat dissipation and emitted energy within the Stage(s). It includes both active and passive thermal control (as applicable).

  • Includes, for example:
  • a. Active thermal control elements that may include pumped-loop systems, heaters and mechanical refrigerators
  • b. Passive thermal control elements that may include radiator panels/fins, coatings, thermal paint, heat shield tiles, heat pipes, insulation, conductive structures and materials, and louvers and sunshields
  • c. Acoustic or shock absorbing materials or devices

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems. NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.2.1.6 Stage Peculiar Avionics. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment and support of any avionics elements whose functionality is specifically associated with Stages 1…n. Stage peculiar avionics is separate from the main launch vehicle avionics system.

  • Includes, for example:
  • a. Power elements such as batteries and harnesses that provide and distribute power to components located on a specific Stage
  • b. Instrumentation componentry used for collecting in-flight data form a specific Stage
  • c. Separate and independent avionics (power systems, telemetry, command and control) for an Upper Stage for transfer orbital insertions

J.4.2.1.7 Other Systems (Specify). This element should be replaced with other product-oriented stage subsystems that are either not listed above or that cannot be categorized into one of the above elements. Each additional element is to be clearly identified and defined.

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems. NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.2.2 Payload Accommodations 1…n (Specify). Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support, and support required to implement the physical integration of the Space Vehicle(s) with the Launch Vehicle, resulting in successful delivery of the Space Vehicle to the specified orbit to meet mission requirements. In order to deliver a payload to its intended orbit/trajectory certain considerations must be taken into account to protect the payload from unacceptable environmental conditions during flight. The purpose of the Payload Accommodations is to assure the payload arrives at its final destination safely. This element also includes all physical mechanical/electrical interfaces between the Launch Vehicle and Space Vehicle. Payload Accommodations includes the following elements, which vary as a function of mission requirements.

  • Includes, for example:
  • a. Payload fairing
  • b. Payload adapter
  • c. Mission unique hardware

J.4.2.2.1 Payload Fairings. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support, and support of the Payload Fairing element of the Launch Vehicle. The Payload Fairing consists of the aerodynamic shroud and equipment mated to the launch vehicle that protects the Space Vehicle from external environments and contamination. The Payload Fairing provides this protection from encapsulation of the Space Vehicle and its upper stage, as applicable, through atmospheric phase of the launch vehicle flight.

  • Includes, for example:
  • a. Payload fairing structure (e.g., panels, modules and nose assemblies) and mechanisms
  • b. Separation ordnance and other necessary mechanisms to assure that the payload fairing successfully separates from the launch vehicle and space vehicle
  • c. Environmental control systems, including thermal paint, insulation, heat shields and tiles or any other active or passive means necessary to maintain appropriate temperature of the shroud and mission equipment within it. structural interface required between the shroud and launch vehicle, such as an interstage adapter or boat tail
  • Excludes, for example:
  • a. The hardware production and installation activities associated with implementing mission unique hardware requirements to the Payload Adapter, which are included under WBS J.4.2.2.3 – Mission Unique Hardware (Launch Vehicle) 1..n (Specify))
  • b. The engineering and analysis activities performed to define mission unique hardware requirements (included under WBS J.4.3.2-Mission Unique Integration and Analysis 1..n (Specify)
  • c. Linear pyrotechnic separation cords
  • d. Thermal blankets and/or installations
  • e. Payload access windows and doors

J.4.2.2.2 Payload Adapter. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support, and support of the Payload Adapter element of the Launch Vehicle. This element may be called a payload adapter, booster adapter or payload attach fitting or pedestal. The Payload Adapter includes the physical mechanical and electrical interface between the Launch Vehicle’s uppermost stage and the Space Vehicle’s attach points. It can be as simple as a snap ring device, but it is typically a more complex shell or frame structural assembly.

  • Includes, for example:
  • a. Adapter structures and Space Vehicle(s) separation mechanisms for each payload
  • b. Hardware and brackets
  • c. Attachment and release devices/deployment devices
  • d. Umbilical provisions
  • e. Adapters located between Space Vehicles on a multi-launch configuration
  • f. Harnesses, cords and plugs
  • Excludes, for example:
  • a. The hardware production and installation activities associated with implementing mission unique hardware requirements to the Payload Adapter, which are included under WBS J.4.2.2.3 – Mission Unique Hardware 1..n (Specify)
  • b. The engineering and analysis activities performed to define mission unique hardware requirements (included under WBS J.4.3.2 Mission Unique Integration and Analysis 1..n (Specify)

J.4.2.2.3 Mission Unique Hardware (Launch Vehicle) 1…n (Specify). Includes all resources required to produce and install mission hardware necessary to meet mission unique (i.e., non-standard) Space Vehicle electrical/mechanical interface requirements with the Launch Vehicle (i.e., airborne) element.

  • Includes, for example:
  • a. Adapters for Space Vehicle
  • b. Spin table for Space Vehicle
  • c. Umbilical retract system
  • d. Air conditioning ducting
  • Excludes, for example:
  • a. The engineering and analysis activities performed to define mission unique hardware requirements (included under WBS J.4.3.2 -Mission Unique Integration and Analysis 1..n (Specify)
  • b. The hardware production and installation activities associated with implementing mission unique hardware requirements associated with Launch Operations , Mission Services included in WBS Element – J.4.4.2.1 Mission Unique Hardware (Launch Operations) 1..n (Specify)

J.4.2.3 Avionics. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support and support of the Avionics element of the Launch Vehicle. Guidance elements are used for generating or receiving telemetry data to produce command and control signals. Instrumentation elements are used for collecting specified vehicle performance and health data and relaying these data to the telemetry collection system.

  • Includes, for example:
  • a. Power, data acquisition, communications and other Avionics functions required for a specific Launch Vehicle
  • b. Flight software to support all processing activities associated with the power-up, prelaunch and flight states of the launch vehicle
  • c. The software resident within the on-board Inertial Navigation Unit (INU) (or equivalent) and Flight Control Subsystem (FCS) processor of the Launch Vehicle avionics system
  • d. The flight termination system(s) used to intentionally destroy the Launch Vehicle if needed and determined by Flight Range Safety
  • Excludes, for example:
  • a. Physical control such as Thrust Vector Control (TVC) and Reaction Control System (RCS)
  • b. Guidance Navigation and Control (GN&C)
  • c. Power systems and batteries

J.4.2.3.1 Guidance Navigation and Control (GN&C). Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support and support of the GN&C element. The purpose of the GN&C system is to achieve precise injection of the Space Vehicle into its required orbit while maintaining Launch Vehicle stability and control. During the Launch Vehicle flight trajectory, GN&C components determine and provide (autonomously) the following functions: 1) guidance – steering the vehicle to its final target, 2) navigation – determining the vehicle’s position, velocity and attitude and 3) control – implementing guidance commands to achieve propulsion deflections or changes in thrust vector.

  • Includes, for example:
  • a. Inertial measurement unit (IMU)
  • b. Inertial navigation unit (INU)
  • c. Gyros
  • d. Accelerometers
  • e. Altimeters
  • f. Flight computer
  • g. Control units
  • h. GPS receiver
  • Excludes, for example:
  • a. Control actuators such as the Thrust Vector Control (TVC) for the main propulsion system, which is included under WBS J.4.2.1.2 Propulsion Systems

J.4.2.3.2 Power. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support and support of the Power element of the Launch Vehicle. The Power element includes equipment required for generation, conversion, regulation, storage, distribution and switching of electrical energy to Launch Vehicle components.

  • Includes, for example:
  • a. Batteries
  • b. Generators
  • c. Power conditioners
  • d. Switches
  • e. Distribution harnesses and cables
  • f. Connectors.
  • Excludes, for example:
  • a. Power components (e.g., batteries) for the Flight Termination System (FTS), which are included under Range Tracking and Safety

J.4.2.3.3 Data Acquisition and Telemetry. Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support and support of the Data Acquisition and Telemetry element of the Launch Vehicle. The Data Acquisition and Telemetry system provides the means of collecting and transmitting measured instrumentation data either directly back to a ground receiving station or indirectly via an airborne or space-based relay communication asset.

  • Includes, for example:
  • a. The data acquisition system, which provides launch vehicle and payload conditioned, digitized, vehicle health and system performance information (e.g., guidance and navigation data, vibration, temperature, fuel and liquid levels, pressures and G-force) during pre-launch, launch and post-flight operations
  • b. The telemetry system, which, after receiving data from the data acquisition system, encrypts, encodes and modulates, and transmits the data via a telemetry transmitter

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems. NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.2.3.4 Range Tracking and Safety (Airborne). Includes all resources associated with the design, development, test and evaluation, integration, production, refurbishment, launch operation support and support of the Range Tracking and Safety system.

  • Includes, for example:
  • a. On-board tracking system (e.g., Global Positioning System, C-Band receivers and transmitters) that provides the necessary data to determine vehicle position in support of the Flight Termination System (FTS) from liftoff through park orbit insertion. The tracking system enables ground tracking and airborne/space radar systems to accurately track the vehicle through its flight
  • b. Transponders and antennas for telemetry data and for command and control instructions
  • c. Flight Termination System (FTS), which provides Range Safety, the capability to destroy the launch vehicle during non-nominal performance either by secure radio link (i.e., command destruct system), or autonomously after the detection of a vehicle break-up, or unintentional separation of launch vehicle stages (automatic destruct system)
  • d. Batteries, command receiver decoders (CRDs), antennas, safe/arm devices, pyrotechnic initiators, and destruct ordnance

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems. NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.2.3.5 Flight Software Release 1…n. All avionics flight software not associated with a specific Level 4 element.

NOTE: Refer to Appendix B, Electronic Systems for further breakout and definitions for Software.

J.4.2.3.6 Other Avionics (Specify). This element should be replaced with other product-oriented avionics subsystems that are either not listed above or that cannot be categorized into one of the above elements. Each additional element is to be clearly identified and defined.

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems. NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.3 Mission Integration and Analysis (1…f). Includes all resources associated with the design, development, dissemination and verification of requirements and schedules and for ensuring hardware configuration and schedule compliance with mission requirements. Includes both the Standard and Mission Unique integration and analysis efforts required to define integration requirements to unite the Space Vehicle with the Launch System to achieve the specified orbit.

J.4.3.1 Mission Standard Integration and Analysis. Includes engineering and services pertaining to “standard” mission integration tasks for all missions.

  • Includes, for example:
  • a. Mission Integration Control Documentation (ICD)
  • b. Mission design and performance definition
  • c. Flight software parameters
  • d. Environmental analysis
  • e. Guidance system analysis
  • f. Launch vehicle/Space Vehicle coupled loads analysis
  • g. Integrated launch vehicle/Space Vehicle thermal analysis
  • h. Space Vehicle separation analysis
  • i. electrical analysis
  • j. Post launch/flight analysis
  • k. Independent Verification and Validation (IV&V) is conducted for flight readiness

J.4.3.2 Mission Unique Integration and Analysis (1…n). Includes all engineering, analysis and management resources required to define the airborne and ground mission hardware and software necessary to meet mission unique (i.e., non-standard) Space Vehicle electrical/mechanical interface requirements with the Launch System.

  • Includes, for example:
  • a. Mission unique design modifications to Launch Vehicle hardware (engineering and analysis only)
  • b. Mission unique design modifications to Launch Operations hardware (engineering and analysis only)
  • c. Other engineering and analysis not considered to be part of J.4.3.1 Mission Standard Integration and Analysis element
  • d. Vault or sensitive compartmented information facility (SCIF) activities
  • Excludes, for example:
  • a. Modifications or updates to standard integration configurations
  • b. The hardware production and installation activities associated with implementing mission unique hardware requirements to the Launch Vehicle, which are included under WBS J.4.2.2.3 – Mission Unique Hardware (Launch Vehicle)1..n (Specify)
  • c. The hardware production and installation activities associated with implementing mission unique hardware requirements at the Launch Site, which are included under WBS J.4.4.2.1 – Mission Unique Hardware (Launch Operations) 1..n (Specify)

J.4.4 Launch Operations Site (1…n). Includes all activities at the launch operations site(s) required to receive, inspect, store, process, assemble, checkout, monitor, test, conduct launch operations, control, track, recover (as applicable), and logistically support the Launch System. It includes the maintenance and refurbishment of the facilities and equipment at the launch site in addition to the ongoing site maintenance and base support activities, which are not directly associated with the launch cycle. Activities included under the Launch Operations element are recurring in nature. Excludes sustaining engineering in support of the Launch Vehicle elements provided during launch operations, which is included under WBS J.4.2 Launch Vehicle elements.

J.4.4.1 Vehicle Processing and Checkout. Includes all technical and management resources required to receive and process the Launch Vehicle at the launch site prior to launch.

  • Includes, for example:
  • a. Receipt, inspection and testing of the individual Launch Vehicle elements (e.g., liquid rocket engine and/or solid rocket motor stages, strap-ons (solid rocket motor or liquids, payload fairing, etc.), following delivery from their production facility to the launch site
  • b. Launch Vehicle Assembly, Integration, Test and Check-out (AIT&CO), during which the Launch Vehicle elements (e.g., assembled Stages, encapsulated Space Vehicle and upper stage, etc.) are assembled into an integrated Launch Vehicle
  • c. Launch Vehicle subsystem checks and system verification, installing the encapsulated Space Vehicle, performing integrated system test and verification, final installations, and vehicle closeouts
  • d. Transfer (vertically or horizontally) between the assembly areas, processing areas and/or the launch pad (or runway) if required
  • e. Fueling of the Launch Vehicle
  • f. Final test and checkout including post assembly testing and verification of stack integration and flight readiness

J.4.4.2 Mission Services. Includes the hardware production and installation activities associated with implementing mission unique hardware requirements associated with Launch Operations, including Space Vehicle processing.

J.4.4.2.1 Mission Unique Hardware 1…n (Launch Operations) (Specify). Includes all resources required to produce and install mission hardware necessary to meet mission unique (i.e., non-standard) Space Vehicle electrical/mechanical interface requirements with the Launch Operations (i.e., ground) element.

  • Includes, for example:
  • a. Mission unique ground support equipment
  • b. Mission unique umbilicals

J.4.4.2.2 Space Vehicle Processing. Includes all resources for processing (e.g., fueling) of the spacecraft and encapsulation of the Space Vehicle within the Payload Fairing. It also includes Space Vehicle and upper stage (if required) transportation to the launch vehicle (if required).

J.4.4.3. Launch. Includes the resources associated with launch rehearsal activities, launch countdown operations, launch management functions and launch delays.

J.4.4.4 Flight Operations. Includes all resources required to command, control, track and communicate with the Launch Vehicle during its mission.

  • Includes, for example:
  • a. Real-time mission control
  • b. Telemetry processing
  • c. Communications
  • d. Data reduction and analysis

J.4.4.5 Post Launch. Includes all resources associated with Recovery Operations and Post Launch Refurbishment if applicable.

  • Excludes, for example:
  • a. Post launch analysis included in J.4.3.1 Mission Standard Integration and Analysis

J.4.4.5.1 Recovery Operations and Services. Includes all resources required to effect recovery of the applicable Launch Vehicle elements identified as reusable/recoverable.

  • Includes, for example:
  • a. Transportation to reentry site
  • b. Reentry site recovery operations
  • c. Transportation of recovered equipment to assigned facilities
  • d. Logistics support to recovery operations

J.4.4.5.2 Post Launch Refurbishment. The resources required for the inspection, cleaning, repair, refurbishment, replacement, testing and/or checkout of assets utilized during the launch operations cycle.

J.4.4.6 Site Maintenance. Includes ongoing planned maintenance, preservation, repair and calibration of physical launch operations-related assets utilized during the Launch Operations cycle.

  • Excludes, for example:
  • a. Maintenance of industrial facilities

J.4.4.7 Base Support. Includes the physical infrastructure and personnel resources resident at the Launch Site that provides support to, but is not directly attributable to Launch Operations activities.

  • Includes, for example:
  • a. Facilities
  • b. Security, fire and emergency medical support
  • c. Transportation
  • d. Roads
  • e. Food

J.4.4.8 Range Tracking and Safety (Ground). Includes all the resources associated with the design, development, test and evaluation, integration, acquisition, installation, monitoring of launch operations and maintenance of the Range Ground system.

J.4.4.8.1 Range Ground System. Includes all the resources associated with the design, development, test and evaluation, integration, installation and maintenance of the Range Ground system. This WBS Element includes the acquisition and maintenance of ground tracking radar systems (hardware and software) used to accurately track the launch vehicle through flight, analyze the data and issue a destruct command if necessary.

J.4.4.8.2 Range Operations. Includes all resources utilized during pre-launch and flight operations to used to accurately track and acquire telemetry data of the launch vehicle in during flight and up to flight termination. This WBS Element includes the operations and maintenance of ground tracking radar and telemetry systems.

J.4.5 Launch Site (1…n). Includes all the development, design, construction, conversion, or expansion of roadways, real estate, utilities, and buildings/facilities required to house, service, process, launch and support launch vehicle hardware/software. Included are the efforts due to environmental concerns or laws regarding impacts to the human, ecological, or biospherical environment. It includes installation design, system assembly, installation and checkout, and integrated system tests for ground command, control and communications mission equipment/software and support equipment/software.

J.4.5.1. Operational/Site Activation. Reference Appendix L Common Appendix for definition.

J.4.5.2 Peculiar Support Equipment. Reference Appendix L Common Appendix for definition.

J.4.5.3 Ground Command, Control and Communication (GC3). Includes all resources associated with the design, development, test and evaluation, integration, launch operations and support of the GC3 system. The system provides the communications, monitoring and ground control between the Launch Vehicle/Space Vehicle and ground processing stations. It consists of the hardware and software used to provide command, control communications and power for Launch Vehicle checkout and launch, and data display from launch vehicle checkout to launch and through flight operations.

J.4.5.3.1 Command, Control and Communication. Includes all ground hardware and software for communications, monitoring, and ground control and communication between the Launch Vehicle and ground processing capabilities.

  • Includes, for example:
  • a. Ground based sensors
  • b. Telemetry, tracking and control
  • c. External communications
  • d. Data processing equipment
  • e. Automated launch processing equipment
  • f. Software and auxiliary equipment required for conducing Launch Vehicle system mission planning, launch processing, health management, launch and flight operations
  • g. Range safety

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems. NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.5.3.2 Other GC3 (Specify). This element should be replaced with other product-oriented Ground Command, Control and Communication subsystems that are either not listed above or that cannot be categorized into one of the above elements. Each additional element is to be clearly identified and defined.

NOTE 1: If lower level information can be collected, use the structure and definitions in Appendix B, Electronic Systems. NOTE 2: All effort directly associated with the remaining Level 4 WBS elements and the integration, assembly, test, and checkout of these elements into the Launch Vehicle is excluded.

J.4.6 Common WBS Elements. Definitions for Common WBS elements applicable to the Launch Vehicle System, and all other defense materiel items, are in Appendix L: Common Elements, Work Breakdown Structure and Definitions and Appendix L, Section L.5 for unique applications for systems engineering, integration and test and program management (SEIT/PM) and Operational Site Activation.