SR User Handbook Final_July 2015.pdf

810-HB-SRP

NASA Sounding Rockets User Handbook Sounding Rockets Program Office

Sub-orbital and Special Orbital Projects Directorate

NASA Goddard Space Flight Center Wallops Flight Facility

Wallops Island, VA 23337 July 2015

Preface

This Handbook describes the capabilities of the Sounding Rocket program, the design and technology applications used by that program, and the processes established to integrate the customer (principal investigator/program user/scientist/experimenter) into the mission team to ensure the highest probability of a successful project. Neither the United States Government nor any person acting on the behalf of the Unites States Government assumes any liability resulting from the use of information contained in this document or warrants that the use will be free from privately owned rights. The use of a company name does not imply approval or recommendation of the product to the exclusion of others that may also be suitable.

Preface

List of Figures

List of tables

SECTION 1: The NASA Sounding Rocket Program (NSRP)

1.1 The Program: 1959 – the Present

1.2 NASA Organizational Responsibilities

1.2.1 Program Management

1.2.2 Sounding Rocket Working Group (SRWG)

1.3 Sounding Rocket Program Customer’s Role

1.3.1 Philosophy

1.3.2 Payload and Instrumentation

1.4 Sounding Rocket Project Support Elements

1.4.1 Program‐Provided Support Services

1.4.1.1 Flight Mission Management

1.4.1.2 Payload Analysis, Design, & Development

1.4.1.3 Launch Vehicle and Payload Support Systems

1.4.1.4 Payload Fabrication

1.4.1.5 Payload Assembly/Integration, Testing, & Evaluation

1.4.1.6 Launch and Flight Support Operations

1.4.1.7 Post‐Flight Data Processing and Analysis

1.4.1.8 Ground and Flight Safety

SECTION 2: The Sounding Rocket Mission Lifecycle

2.1 The Mission Initiation Conference (MIC)

2.1.1 Project Schedule

2.1.2 Mechanical Devices and Structural Elements

2.1.3 Flight Performance

2.1.4 Instrumentation

2.1.5 Attitude Control

2.1.6 Navigation

2.1.7 Data Reduction

2.1.8 Testing

2.1.9 Foreign Nationals

2.2 Requirements Definition Phase

2.3 The Requirements Definition Meeting (RDM)

2.4 Design Phase

2.5 Design Review (DR)

2.6 Payload Fabrication and Pre‐Integration Testing Phase

2.7 Pre‐Integration Review (PIR)

2.8 Integration and Testing (I&T) Phase

2.8.1 Payload Integration

2.8.2 Acceptance Testing

2.8.3 Final Checkout

2.9 Mission Readiness Review (MRR)

2.10 Flight Readiness Review (FRR)

2.11 Launch Operations Phase

2.12 Mission Closeout Phase

SECTION 3: Sounding Rocket Launch Vehicles and Performance Capabilities

3.1 NASA Mission Designation System

3.2 NASA Sounding Rockets

3.2.1 Performance Characteristics

3.3 Boost Guidance System (BGS)

3.3.1 Background & Capabilities

Section 4: Sounding Rocket Payload Design Considerations

4.1 Payload Design

4.2 Flight Performance

4.2.1 Mechanical Loads and Vibration

4.2.2 Thermal Considerations

4.2.3 Vacuum and Out‐Gassing

4.2.4 Aerodynamic Design Factors

4.3 Other Payload Design Considerations

4.3.1 Accessibility

4.3.2 Availability of Parts

4.3.3 Dynamic Balance

4.3.4 Cost

4.3.5 Redundancy

4.3.6 Weight

4.3.7 Testing

SECTION 5: Payload Systems

5.1 Telemetry Systems

5.1.1 Data Transmission Systems

5.1.2 PCM/FM Systems

5.1.3 WFF93 PCM Encoder System

5.1.4 MV Encoder

5.1.5 Mesquito Encoder

5.2 Attitude Instrument Systems Common to Several ACS's

5.2.1 GLN‐MAC Inertial Attitude Sensor

5.2.1.1 LN‐200

5.2.1.2 Function

5.2.2 The Bartington MAG‐03MS Magnetometer

5.2.3 Honeywell Magnetometers

5.2.4 ST‐5000 Star Tracker

5.2.4.1 Function

5.3 Onboard Sensors and Instruments

5.3.1 TTC Flight Recorder

5.3.2 Accelerometers

5.3.3 Vibration sensors

5.3.4 Magnetometer

5.3.5 Solar/Lunar Sensors

5.3.6 Wallops Accelerometer & Attitude Sensor Package (WAASP)

5.3.7 Horizon Sensor

5.3.8 Video Cameras

5.3.9 Rate Sensor

5.3.10 Strain gauges

5.4 Transmitters

5.5 Command Uplink Systems

5.6 Telemetry Antennas

5.7 Instrumentation and Experiment Power Systems

5.7.1 Nickel Cadmium

5.7.2 Voltage Output

5.7.3 Power Control Distribution (PCD)

5.7.4 Switching

5.7.5 Pyrotechnic Power Supply

5.8 In‐Flight Event Timing Systems

5.8.1 USB Reprogrammable Multifunction Timer (UMFT)

5.8.2 Barometric Switches

5.9 Trajectory Measurement Systems

5.9.1 Radar Transponders

5.9.2 Doppler Ranging

5.9.3 Global Positioning System (GPS)

5.10 Mechanical Systems & Mechanisms

5.10.1 Nosecones

5.10.2 Structures & Skins

5.10.3 Shutter Doors

5.10.4 Deployment Mechanisms

5.10.5 Vacuum/Water Sealing

5.10.6 De‐spin Systems

5.11 Recovery Systems

5.11.1 Land Recovery

Table 5.16.1‐1 Characteristics of Land Recovery Parachutes Type

5.11.2 Water Recovery

5.11.3 Recovery Aids

5.12 Attitude Control Systems (ACSs)

5.12.1 NSROC Solar Pointing Attitude Rocket Control System (SPARCS VII)

5.12.1.1 Capabilities

5.12.1.2 System Elements

5.12.1.3 Operation

5.12.1.4 Integration

5.12.2 NSROC Inertial Attitude Control System (NIACS)

5.12.2.1 Capabilities

5.12.2.2 System Elements

5.12.2.3 MaNIACS

5.12.2.4 Integration

5.12.3 NSROC Magnetic Attitude Control System

5.12.3.1 Operation & Capabilities

5.12.3.2 Integration

5.12.4 NSROC Celestial Attitude Control System

5.12.4.1 Capabilities

5.12.4.2 System Elements

5.12.4.3 Operation

5.12.4.4 Integration

5.12.5 Command Uplink System

SECTION 6: Environmental Testing Policies

6.1 General Requirements

6.1.1 Qualification Testing

6.1.2 Acceptance Testing

6.1.3 Principal Investigator Testing

6.1.4 Test Plan

6.2 Testing Equipment and Capabilities

6.2.1 Mass Properties Measurement Systems (WFF and WSMR)

6.2.2 Static and Dynamic Balancing Machines (WFF & WSMR)

6.2.3 Shakers (WFF and WSMR)

6.2.4 Vacuum Chambers (WFF and WSMR)

6.2.4.1 The Portable Vacuum System

6.2.4.2 The Vacuum Leak Detector – Helium Mass Spectrometer

6.2.4.3 Vacuum Bell Jars

6.2.5 Bend Test Fixtures (WFF and WSMR)

6.2.6 Spin Deployment and Separation Equipment (WFF)

6.2.7 Centrifuge Machine (WFF)

6.2.8 Magnetic Test Facility (WFF & WSMR)

6.2.9 Spin Balance Facility (WFF, Wallops Island)

6.2.10 Facility Cleanliness (WFF & WSMR)

6.2.10.1 Wallops Flight Facility

6.2.10.2 White Sands Missile Range

6.2.11 Optics Capabilities (WFF & WSMR)

6.2.11.1 Capabilities at WFF

6.2.11.2 Capabilities at WSMR

6.3.1 Static and Dynamic Balance

6.3.2 Static Load (Bending)

6.3.3 Mass Properties

6.3.4 Vibration

6.3.5 Waivers

6.3.6 Test Times

6.4 Component Testing

SECTION 7: NASA/GSFC/WFF Safety Policy and Responsibilities

7.1 Safety Policy

7.2 The Range Safety Organization

7.2.1 Safety Responsibilities of the Mission Manager (MM)

7.2.2 Safety Responsibilities of the Principal Investigator (PI)

7.3 Ground Safety Plan (GSP)

7.4 Flight Safety Plan (FSP)

7.4.1 Impact Criteria:

7.4.2 Overflight Criteria:

7.4.3 Flight Termination Criteria:

7.4.4 Flight Termination System Design Requirements:

7.4.5 Flight Planning Criteria:

7.4.6 Range Clearance Criteria for GSFC/WFF Launch Range:

7.4.7 Operational Procedures:

7.5 Safety Analysis Report

SECTION 8: Launch Operations

8.1 Launch Ranges

8.2 Launch Operations

8.2.1 Rules to Remember

8.2.2 Role of the Mission Manager

8.2.3 The Flight Requirements Plan

8.2.4 Test and Evaluation

8.2.5 The Field Schedule

8.2.6 The Preflight Conference

8.2.7 Recovery

8.2.8 Post‐Flight Conference

8.3 Foreign Ranges

8.3.1 Experimental Techniques

8.3.2 Travel & Lodging

8.3.3 Access

8.3.4 Foreign Nationals

8.3.5 Shipping and Export Control

8.3.6 Postal Service

8.4 Mobile Range Operations

8.4.1 Remote Locations

8.4.2 Harsh Environment:

8.4.3 Limited Technical Facilities:

8.4.4 Limited Communications:

SECTION 9: Data Processing and Analysis

9.1 Computer Systems

9.1.1 Real‐Time Computer Systems (DQCA,DQCB)

9.1.2 Data Reduction Computer System (DRCS)

9.1.3 Engineering Computer System (ECS)

9.1.4 Launch Status Review System (LSRS)

9.1.5 Special Purpose Computers

9.2.4 Positional Data Policy

SECTION 10: Wallops Flight Facility

10.1 WFF Sounding Rocket Program Support Facilities

10.1.1 Engineering Support Facilities

10.1.2 Payload Integration Laboratory

10.1.3 Environmental Testing Laboratory

10.1.4 Payload Construction

10.1.5 Computer Support

10.1.6 Range Operations

10.2 Working at Wallops – Rules, Regulations, and Logistics

10.2.1 Access

10.2.2 Accommodations

10.2.3 WFF – Safety Rules and Regulations

10.2.4 Shipping/Receiving and Transportation of Sounding Rocket Components

10.3 Foreign Nationals

APPENDICES

Appendix A: SCIENCE REQUIREMENTS DATA PACKAGE

Electrical Engineering

Guidance Navigation and Control

Mechanical Engineering

Performance Analysis

Vehicle Systems

Appendix B: Principal Investigator's Data Package for Mission Initiation Conference (MIC)

Appendix C: Principal Investigator's Data Package for a Design Review

Appendix D: Principal Investigator's Data Package for a Mission Readiness Review

Appendix E: Descriptions & Flight Performance Characteristics for NASA Sounding Rockets and

Special Projects Launch Vehicles

E.1 Black Brant Launch Vehicle (21.XXX)

General

Vehicle Performance

Payloads

Performance Graph

E.2 Improved Orion Launch Vehicle (30.XXX)

General

Vehicle Performance

Payloads

Performance Graph

E.3 Black Brant X Launch Vehicle (35.XXX)

General

Vehicle Performance

Payload

Performance Graph

E.4 Black Brant IX Launch Vehicle (36.XXX)

General

Vehicle Performance

Payload

Performance Graphs

E.5 Terrier‐Improved Orion Launch Vehicle (41.XXX)

General

Vehicle Performance

Payloads

Performance Graphs

E.6 Terrier‐Improved Malemute Launch Vehicle (46.XXX)

General

Vehicle Performance

Payloads

Performance Graphs

E.7 Black Brant XI‐A Launch Vehicle (51.XXX)

General

Vehicle Performance

Payloads

Performance Graph

E.8 Black Brant XII‐A Launch Vehicle (52.XXX)

General

Vehicle Performance

Payloads

Performance Graph

Appendix F: PCM/FM and FM/FM Telemetry Systems

F.1 WFF93 Encoder System

F.2 Mesquito Encoder System

Appendix G Comparison and Performance of Various Battery Systems

Appendix H: GSFC/WFF Safety Data Requirements

Payload Description Data ‐ Hazardous Materials

Appendix I: Sounding Rocket Launch Ranges

I.1 U.S. Army White Sands Missile Range

I.2 Poker Flat Research Range

I.3 Andøya Space Center, Norway

Appendix J: Wallops Flight Facility Digital Telemetry System ‐ Chapter 10

Ulyssix Technologies and Dewesoft

PTP CD‐ROM Data Format

PTP PCM FORMAT

PTP MUX Header Format

NASA PB‐4 Time Code Format

PTP Data Field Format

Appendix K: Radar Data Format 1.1.2155

Acronyms

List of Figures Figure 2-1. Typical Sounding Rocket Mission Life Cycle 23 Figure 2.6.1 The Labelle payload, 40.025 UE, during testing at Wallops, launched on Feb 15, 2010 from Poker Flat, Alaska. 27 Figure 2.6.2 Payload integration in one of three ground stations at Wallops. 27 Figure 3.2-1 NASA Sounding Rocket Launch Vehicles 33 Figure 3.2.1-1 Sounding Rocket Vehicle Performance 34 Figure 5.2.1-1: GLN-MAC 46 Figure 5.2.4-1: ST5000 Star Tracker 49 Figure 5.3.6-1: Wallops Accelerometer & Attitude Sensor Package (WAASP) 51 Figure 5.12.1.2-1: Miniature Acquisition Sun Sensor (MASS) 61 Figure 5.12.1.2-2: Lockheed Intermediate Sun Sensor (LISS) 62 Figure 5.12.1.2-3: SPARCS VII operation payload pointing at the Sun with an arbitrary roll attitude. 63 Figure 5.12.1.2-4: Same as above but looking along the payload axis at the Sun. 63 Figure 5.12.1.2-5: SPARCS with valve #4 firing to produce a positive pitch moment. 64 Figure 5.12.1.2-6: SPARCS with pair of valves V1 generating identical thrust in opposite directions. 65 Figure 5.12.1.-1: SPARCS alignment to the target. 66 Figure 5.12.1.4-1: SPARCS integration chart. 67 Figure 5.12.5-1: Graphics User Interface 75 Figure 5.12.5-2: Absolute Target Specification 76 Figure 5.12.5-2: Target Specification 76 Figure 6.2.1-1 Airdyne Mark 8 Mass Properties Measurement System at WFF 80 Figure 6.2.2-1 Gisholt Rocket Balancing Machine at WFF 81 Figure 6.2.3-1: Ling Electronics B335 Thrust Axis Shaker at WFF 82 Figure 6.2.4-1 PV/T Vacuum Chamber (left) and Tenney Space Simulation System Thermal Vacuum Chamber at WFF 83 Figure 6.2.4-1 PV/T Vacuum Chamber (left) and Tenney Space Simulation System Thermal Vacuum Chamber at WFF 83 Figure 6.2.5-1: Bend Test Fixture at WFF 84 Figure 6.2.6-1: Spin Deployment Chamber at WFF 85 Figure 6.2.8-1 The Magnetic Test Facility at Wallops 86 Figure 6.2.10-1 Clean Room at Wallops, Bldg. F-7. 89 Figure 6.3.4-1 Vibration Decision Flow Chart 93 Figure 8.3-1. Range Facilities at Woomera, Australia 107 Figure 8.4-1 Range Support Operations in Kangerlussuaq, Greenland 108 Figure 8.4-2 Woomera, Australia 109 Figure 9.1.1-1 RTBS, RTCS in Operation at WFF 111 Figure 10-1: Wallops Flight Facility Map 114 Figure 10-2. Wallops Main Base 115 Figure 10-3. Wallops Island 115 Figure 10-4. Wallops Mainland 116 Figure 10.1.2-1 Plasma Physics Payload (49.002 UE) During Payload Integration 117 Figure 10.1.4-1: Machine Shop 118 Figure 10.1.6-1: WFF Fixed Radar System 119 Figure E.1-1: Black Brant Launch Vehicle 137 Figure E.1-2: Black Brant Launch Vehicle Performance 138 Figure E.2-1. Improved Orion Launch Vehicle 139 Figure E.2-2: Improved Orion Launch Vehicle Performance 140 Figure E.3-1: Black Brant X Launch Vehicle 141 Figure E.3-2: Black Brant X Launch Vehicle Performance 142 Figure E.4-1: Black Brant IX Launch Vehicle 143 Figure E.4-2(a): Black Brant IX (MOD2) Launch Vehicle Performance – WSMR 144 Figure E.4-2(b): Black Brant IX (MOD2) Launch Vehicle Performance – Sea Level 145 Figure E.4-3(a): Black Brant IX (MOD3) Launch Vehicle Performance – WSMR 146 Figure E.4-3(b): Black Brant IX (MOD3) Launch Vehicle Performance – Sea Level 147 Figure E.5-1: Terrier-Improved Orion Launch Vehicle 148 Figure E.5-2(a): Terrier MK12-Imp. Orion Launch Vehicle Performance – Sea Level 149 Figure E.5-2(b): Terrier MK70-Imp. Orion Launch Vehicle Performance – Sea Level 150 Figure E.6-1: Terrier-Improved Malemute Launch Vehicle 151 Figure E.6-2(a): Terrier MK12-Imp. Malemute Launch Vehicle Performance – Sea Level 152 Figure E.6-2(b): Terrier MK70-Imp. Malemute Launch Vehicle Performance – Sea Level 153 Figure E.7-1: Black Brant XI-A Launch Vehicle 154 Figure E.7-2: Black Brant XI-A Launch Vehicle Performance – Sea Level 155 Figure E.8-1: Black Brant XII-A Launch Vehicle 156 Figure E.8-2: Black Brant XII-A Launch Vehicle Performance – Sea Level 157 Figure I.1-1. White Sands Missile Range 167 Figure I.2-1 Aerial View of PFRR 169 Figure I.3-1: Launch Facilities at Andøya Rocket Range, Norway Photo: Kohlbjoern Dahle 173 Figure I.3-2: Launch at Andoya 174

List of tables

Table 3.1-1 Sounding Rocket Agency, Vehicle and Experiment Identification 35 Table 5.1.2-1: PCM System Characteristics 43 Table 5.12-1 shows the principal characteristics of the systems. 60 Table 6.2.3-1 NSROC Shaker Specifications 81 Table 6.2.4-1: NSROC Vacuum and Thermal Vacuum Chamber Specifications 82 Table 6.2.4-2 WSMR Vacuum and Thermal Vacuum Chamber Specifications 84 Table 6.2.5-1 NSROC Bend Test Fixture Specifications 84 Table 6.2.8-1: Instrumentation Available at the WFF Magnetic Test Facility 87 Table 6.2.8-2: Magnetic Test Facility Specifications 88 Table 6.3.1-1 Static and Dynamic Balance Specifications 91 Table 6.3.4-1 Vibration Test Levels for New Payload Designs 94 Table 8-1: Sounding Rocket Launch Sites Worldwide 103 Table F.1-1: Individual PCM Module Characteristics - WFF93 PCM System 158 Table F.2-1 Individual PCM Module Characteristics – Mesquito Encoder System 161 Table G-1: Comparison and Performance of NiCad Battery Systems 162

SECTION 1: The NASA Sounding Rocket Program (NSRP)

This Handbook was written to assist NSRP customers in developing payloads that meet the requirements necessary to achieve mission-specific, scientific objectives, and to serve as a guideline in defining NSRP quality standards and ISO 9001-2000 requirements. For the purposes of this document, “Customers” shall include principal investigators, program users, scientists, and experimenters.

1.1 The Program: 1959 – the Present

The NSRP is a suborbital space flight program that primarily supports NASA-sponsored space and earth sciences research activities, other government agencies, and international sounding rocket groups and scientists. Since its inception in 1959, some 2900 missions have flown with an overall science mission success rate in the previous 20 years exceeding 90 percent and launch vehicle success rate of over 97 percent. The program is a low-cost, quick-response effort providing approximately 20 flight opportunities per year to scientific and technology demonstration investigations. Science investigations are involved in upper atmosphere, plasma physics, solar physics, planetary atmospheres, galactic astronomy, high energy astrophysics, and micro-gravity research. These rockets are launched from a variety of launch sites throughout the world.

In mid-1980’s, the NSRP was consolidated at the Wallops Flight Facility of the Goddard Space Flight Center. The program has continued to grow in terms of average payload size, weight, complexity, and range.

NSRP flight systems are remarkably sophisticated spacecraft, capable of lofting 1000 pound payloads to 280 kilometers and 250 pound payloads to 1500 kilometers.

NSRP customers consist primarily of university and government research groups; however, some research activities involve the commercial sector. The program has contributed major scientific findings and research papers to the world of suborbital space science, validated satellite tracking and instrumentation, and served as a proving ground for space ship and space station components. Many new scientists have received training and developmental experience through NSRP internships and graduate study programs offered by participating educational institutions.

Systems and services provided to customers of the NSRP encompass the complete spectrum of support:

mission management, payload design and development, launch vehicles, recovery systems, attitude control systems, payload testing and evaluation, analytical studies, launch range operations/coordination, tracking, and data acquisition and data processing.

Customers are required to provide the scientific instruments/detectors for the payload, a comprehensive description of the support requested from NASA, and objective criteria that will used to determine the success or failure of the mission after all operations are completed.

The NSRP is conducted in compliance with ISO 9001-2000 but without the formal and expensive reliability and quality assurance employed in the larger and more costly orbital and deep space programs. This informal approach, combined with the extensive use of surplus military rocket motors, is instrumental in enabling the program to complete approximately 20 - 30 missions per year, using available resident WFF and WSMR resources. The NSROC program is required to maintain an 85% success rate (complete mission, vehicle, payload and science) although the program goal is 100%.

Effective communications between the NASA project support team and the customer are vital to the success of individual sounding rocket missions and to the overall program. Project meetings, reviews, and the requisite post flight assessments of mission results by the customer are all feedback mechanisms which provide observation, comment and constructive criticism for problem solving and future programmatic improvements. The NASA approach to team-customer interaction is included in this Handbook to foster a better understanding of the thinking behind current Program procedures. From design and development of the payload through launch and data retrieval, the customer is the essential source of information on how well the NSRP is working.

1.2 NASA Organizational Responsibilities

The NSRP is funded through the Heliophysics division of the Science Mission Directorate (SMD).

1.2.1 Program Management

The NSRP at Goddard Space Flight Center (GSFC) falls under the Sounding Rockets Program Office (SRPO), Code 810, Suborbital and Special Orbital Projects Directorate (SSOPD), Code 800. The SRPO and SSPOD are located at Wallops Flight Facility (WFF) Wallops Island, VA. The program is implemented under the NASA Sounding Rocket Operations Contract (NSROC) which is administered by the SRPO.

NASA retains overall management of the NSRP including certain programmatic elements such as mission selection, funding, international agreements, grant administration, oversight and approval of the ground and flight safety process, and ownership of program assets.

1.2.2 Sounding Rocket Working Group (SRWG)

The SRWG is appointed by the Director of Goddard Space Flight Center to provide counsel and a forum for exchange of information on sounding rocket systems, operational support, and developments in science as they affect the program. The NASA Sounding Rocket Project Scientist, GSFC, chairs the Group which consists of over 10 members from the principal scientific disciplines served by sounding rockets. The NASA SRPO reports to this Group in the areas of technical and management support.

1.3 Sounding Rocket Program Customer’s Role

Once selected for flight participation, the customer becomes a member of the assigned Mission Team and is responsible for the preparation of the scientific experiment portion of the payload. Customers assist in establishing and conducting the operational program. Customers are responsible for defining the investigation, providing the necessary scientific instrumentation, completing timely processing and analysis of recovered data, and publishing the results. The customer is expected to participate in a number of scientific and technical planning functions and formal reviews described later in this document.

1.3.1 Philosophy

The customer’s role is critical to the success of the mission. NASA procedures are designed to support the customer and facilitate the best possible scientific return from the mission. Information regarding past experiences with the reliability of specific components and techniques is made available. While the assigned mission support team may recommend the use or avoidance of certain procedures and practices, final decisions on the internal details of the scientific instrumentation are normally left to the customer. Each payload is required to successfully complete a series of environmental tests which measure, test and evaluate the ability of the scientific instrumentation to survive the flight environment. Determination of the ability of the scientific instrumentation to make the required measurements is normally made by the customer.

1.3.2 Payload and Instrumentation

Equipment provided as part of the Program’s customary mission support functions is described in Section

1.4 – Sounding Rocket Project Support Elements. The customer is normally responsible for developing and providing all other scientific instrumentation and related support equipment. They are also responsible for ensuring that it conforms to all required mechanical, thermal, and electrical interface specifications; meets all required safety standards; and is capable of surviving the predicted flight environment. Scientific instrumentation and related support equipment may be built within the customer’s own laboratories or by associated contractors. To help ensure a safe operation, the customer is required to furnish the data specified in Section 7 - Safety and Appendix H - GSFC/WFF Safety Data Requirements.

1.4 Sounding Rocket Project Support Elements

The NSROC contractor, provides the programmatic, technical, and business management functions necessary to plan, organize, implement, control, track, report, and deliver the goods and services required for implementation of the NSRP.

The NSROC contractor provides individual mission management for all assigned sounding rocket missions;

this includes all planning and scheduling associated with individual mission requirements. Each mission is planned to meet science objectives and scheduled to avoid interference with the timely and cost efficient completion of other ongoing missions. The Mission Database is a programmatic schedule for all missions and is maintained on the NSROC server.

At minimum, the Mission Database reflects the planned schedule for the following milestones:

Launch Date

Launch Time

Integration Site/Date

Mission Initiation Conference (MIC)

Requirements Definition Meeting (RDM)

Critical Design Review (CDR)

Pre-Integration Review (PIR)

Mission Readiness Review (MRR)

Mission Close-out Report (MCR)

The NSROC contractor also provides services and supplies necessary for implementation of the individual missions and the overall program. As such, the contractor designs, fabricates, integrates, and performs flight qualification testing of suborbital payloads, provides launch vehicles, systems, and associated hardware, and provides various activities associated with subsequent mission launch operations. All relevant information is updated and maintained in the Mission Database.

1.4.1 Program-Provided Support Services

Customers of the Sounding Rocket Program are provided with a variety of support services. The assigned Mission Team is typically responsible for implementation of the mission utilizing their individual efforts and the extensive support capabilities provided by the Program.

A typical Mission Team is composed of the customer or his representative(s), applicable support staff, and additional team members provided by the support elements at WFF.

Team includes the following positions:

Mission Manager

Customer & Staff

Mechanical Engineer

Electrical Engineer

Instrumentation Engineer

GNC (Guidance, Navigation & Control) Engineer

Performance Analysis Engineer

Mechanical Technician

Electrical Technician

GNC Technician

Launch Vehicle Technician

Flight Safety Representative

Ground Safety Representative

The general categories of effort necessary for implementation of a mission include:

Flight Mission Management

Scientific Instrumentation (typically provided by the customer)

Payload Analysis, Design, & Development

Launch Vehicle and Payload Support Systems

Payload Fabrication

Payload Assembly/Integration, Testing, & Evaluation

Launch & Flight Support Operations

Post Flight Data Processing and Analysis

Ground & Flight Safety.

The following is a brief description, including organizational responsibility, of the individual support elements provided by the Program for the typical mission. A detailed discussion of how sounding rocket flight projects are conducted with respect to a typical mission is included in Section 2 of this Handbook.

1.4.1.1 Flight Mission Management

NSROC management is generally responsible for selecting a Mission Manager (MM) for each mission. The MM has comprehensive, team leader responsibilities throughout the mission lifecycle and serves as the central point of contact for the customer. MM responsibilities include:

1. Developing an approach (technical, schedule, and cost effective), in conjunction with the assigned mission team, for meeting the mission requirements defined by the customer. This activity generally occurs in the period between the MIC and the RDM as described in Section 2 of this Handbook.

2. Coordinating and establishing a mutually acceptable date for holding, conducting, and documenting the RDM and all associated mission requirements in the subsequent Requirements Definition Meeting Memorandum.

3. Working with the customer and the NSROC Mission Team to design, develop, fabricate, integrate, test and flight quality the payload. The MM is responsible for coordinating, directing, and managing this effort, as well as establishing and maintaining the project schedule.

4. Directing and coordinating all Mission Team activities, including formal presentations at Design Reviews and Mission Readiness Reviews and documenting the Mission Team’s responses to any action items resulting from these reviews.

5. Coordinating and directing all field operations including preparation of the launch vehicle and conducting launch operations. The MM is the focal point for all field activities and has final, real time go/no-go authority for the mission, including launch vehicle status (concurrence for launch by range safety, SRPO, and the customer is required). The MM has no authority to override a customer or range safety decision to halt a launch, but may stop a launch when, in his opinion, a condition exists that jeopardizes the success of the flight.

6. Assessing the results of the launch to the extent possible and submitting required reports to the SRPO.

7. Coordinating and directing post flight operations necessary to complete all mission requirements.

1.4.1.2 Payload Analysis, Design, & Development

The following activities are associated with the analysis, design, and development function and are generally provided by the NSROC contractor:

Electrical engineering support for payloads, launch vehicles, and associated flight systems includes electrical systems (power supplies, event timing, wiring harnesses, monitoring subsystems) and instrumentation systems (telemetry subsystems). Mechanical engineering support for payloads, launch vehicles, and associated flight systems includes all payload mechanical subsystems (overall layout and design, external skins, internal structures, bulkheads, component layouts, special mechanisms) and pyrotechnic devices (pin-pullers, bolt-cutters and thrusters).

GNC engineering support for payloads and associated flight systems includes all boost guidance systems, navigation systems and attitude control systems. Support includes requirement review, auxiliary attitude sensor selection, implementation of external interfaces to the payload, pneumatic system propellant selection and thruster locations.

Flight performance analyses include:

Launch vehicle performance and nominal flight trajectory analysis

Flight trajectory dispersion, wind-compensation parameters, and impact aim point considerations

Launch vehicle static and dynamic stability evaluation (including aeroelastic effects, payload dynamics analyses, payload re-entry trajectory and recovery analyses, ascent and re-entry aerodynamic heating analyses)

Other suborbital analyses.

These activities are performed during the pre-flight and post-flight analyses for each mission.

1.4.1.3 Launch Vehicle and Payload Support Systems

Launch vehicle and payload support systems are provided by the NSROC contractor and include rocket motors, pyrotechnics, and associated standard flight systems such as ejectable nose cones, payload/vehicle separation systems, upper stage ignition systems, and thrust termination systems. Activities associated with these systems include their inspection, modification, storage, shipment, assembly, launcher mating, umbilical rigging, and environmental control during launch operations. Other standard systems include payload recovery systems, special aerodynamic decelerators, payload attitude control and stabilization systems, and launch vehicle boost-guidance systems.

1.4.1.4 Payload Fabrication

Mechanical and electrical fabrication services are provided by the NSROC contractor. Electrical fabrication support includes specialized shops for electrical wiring assembly, printed circuit board fabrication, and electrical instrumentation development. The mechanical fabrication support includes the machine shop, welding shop, plastics and composite materials shop, sheet metal shop, and mechanical instrumentation shop.

1.4.1.5 Payload Assembly/Integration, Testing, & Evaluation

The development of a mission progresses from the fabrication and assembly of flight hardware, through the addition of customer-provided instrumentation and standard support systems, to a fully integrated payload.

The payload then proceeds through the testing and evaluation process which involves the entire Mission Team (engineering personnel, technical support personnel, and the customer who has the technical knowledge of, and responsibility for, his instrumentation) and the laboratory support personnel who operate the various facilities involved in the processes. These facilities include payload assembly shops, telemetry ground stations, and environmental testing lab. These processes include physical properties determination;

magnetic calibration; and vibration, shock, structural loads, spin-deployment, dynamic balancing, and vacuum testing. All of these services are generally provided to the customer by the NSROC contractor.

1.4.1.6 Launch and Flight Support Operations

A critical element of conducting the NASA Sounding Rocket Program involves performing launch operations from various locations worldwide. Several of these launch sites are existing, full-time launch ranges. Mobile sites can also be established at remote locations which satisfy particular science requirements, such as specific observations (solar eclipses, supernova) and operations in specific areas (auroral zones, equatorial zones, Southern Hemisphere).

The following are brief descriptions of the major applicable elements involved in supporting sounding rocket flight operations:

The SRPO utilizes an agreement with the NAVY at White Sands Missile Range to provide services for conducting launch operations from that location. The SRPO directs the NAVY to coordinate the provision of these services from the various service provider organizations and to support the specific requirements of each mission.

The SRPO utilizes a contract with the University of Alaska for the maintenance and operation of the Poker Flat Research Range. This mechanism provides support for launch operations conducted from this high latitude location. Additional support for tracking and data acquisition services is provided through the NASA remote range services contract.

The SRPO also utilizes inter-governmental and international agreements necessary for the provision of launch operational support for mobile campaigns such as from the Marshall Islands and Puerto Rico; and from established foreign ranges such as Esrange, Sweden and Andoya, Norway.

The Range and Mission Management Office (RMMO), Code 840 is responsible for planning and directing the support necessary to meet the objectives of projects conducted on the WFF range and mobile campaigns. The implementation of mobile campaigns for sounding rockets involves the support of several organizational elements within SSPOD. Additional support may also be provided by the AETD.

The RMMO schedules and directs flight test activities, provides test data packages to users, and coordinates range operations with various outside organizations for operations conducted from WFF and mobile campaigns. When conducting a mobile operation of sufficient magnitude, a "Campaign Manager" is usually assigned. This individual has overall responsibility for managing the campaign (which usually involves several separate sounding rocket flight missions) including interfacing with foreign government organizations, establishing the required launch support facilities, and coordinating launch operations.

The range from which the operations are being conducted provides launch pads, launchers, blockhouse systems, controls, and consoles. Mechanical and electrical/electronic ground support equipment; flight support instrumentation such as search, tracking, and instrumentation radars; telemetry receiving and data recording stations; television and photographic tracking cameras; special purpose photo-optical equipment;

surveillance and recovery operations aircraft; and facilities for payload preparation and check out are provided as part of the range services.

The NSROC contractor is generally responsible for conducting actual launch operations as well as all functions relating to the preparation of the launch vehicle and payload leading up to that event.

1.4.1.7 Post-Flight Data Processing and Analysis

The NSROC contractor is generally responsible for providing post flight processing and analysis of raw scientific data recovered from sounding rocket missions. This data is provided to the customer in the format specified at the RDM. Section 9 has additional information on available data processing and analysis support and procedures for obtaining that support.

1.4.1.8 Ground and Flight Safety

All work performed in support of the Sounding Rocket Program (SRP) is done in conformance with all WFF, GSFC, NASA, and other government regulations, requirements, and statutes. Ground and flight safety data requirements for sounding rocket vehicles and payloads are contained in the Range Safety Manual for Goddard Space Flight Center (GSFC)/Wallops Flight Facility (WFF), (RSM-2002). This manual contains specific design requirements for flight systems and describes data that must be supplied to the Wallops Flight Facility Safety Office (Code 803) to obtain NASA safety approval for launch systems.

Institutional safety requirements are contained in NPG 8715.3, NASA Safety Manual. The NSROC contractor is responsible for meeting these requirements as well as any additional safety requirements of other domestic or foreign ranges utilized during implementation of the SRP. Further, the NSROC contractor is responsible for maintaining awareness of all changes and modifications to statutes, regulations, and procedures impacting ground and flight safety.

The NASA Safety Office is responsible for oversight and approval of all ground and flight safety processes.

As such, the NASA Safety Office provides all necessary Safety Plans based on the data and analyses provided by the NSROC contractor. The NSROC contractor is contractually required to provide all data, analysis, and information necessary for the development of these, and any other, required plans. The NASA Safety Office plans and coordinates safety aspects of launch operations, establishes range clearance and range safety limitations, and reviews and approves hazardous assembly and pad procedures. The NSROC contractor is responsible for implementing all of the requirements of the Ground and Flight Safety Plans for NSROC-supported missions.

For hazardous operations (other than pad operations), the NSROC contractor is responsible for:

Providing Operational Safety Specialist(s) whose primary responsibility is safety oversight. This person or persons interfaces directly with the NASA Safety Office oversight authority in resolving real-time safety concerns.

Implementing all general operation (crane operation, forklift operation, etc.), personnel safety (explosives and ordnance, pressure vessels and systems, chemical, radiation, etc.) and facilities (equipment calibration, maintenance of safety devices, access control) requirements.

A detailed discussion of sounding rocket safety considerations and policies is provided in Section 7 of this Handbook; additional NSRP support capabilities are addressed in Section 2.

SECTION 2: The Sounding Rocket Mission Lifecycle

This Section describes the process NASA uses in conducting a sounding rocket flight project (mission) using the management and support elements at Goddard Space Flight Center's Wallops Flight Facility (WFF) discussed in Section 1.4.

The various phases and milestone reviews of a typical mission are outlined in the sections below and summarized in Figure 2-1.

2.1 The Mission Initiation Conference (MIC)

Flight projects must be approved by the appropriate science discipline chief at NASA Headquarters. Once this approval has been obtained, the customer will be contacted by the SRPO to establish a mutually acceptable date for a MIC between the customer and WFF personnel. The purpose of this first meeting in the mission lifecycle is for the customer to present a MIC Data Package which details requirements and specifies the support necessary for the mission. An outline of the information required in the MIC Data Package is provided in Appendix B.

The MIC is chaired and documented by the SRPO. Attendees include the customer, appropriate WFF supervisory and engineering personnel, NSROC supervisory, engineering, and technical personnel, as well as the assigned payload team. A well-conducted and documented MIC will result in a strong foundation on which to begin the mission. The MIC provides the basis from which all requirements for the mission are established. These include:

2.1.1 Project Schedule

The customer should be prepared to answer specific and detailed questions regarding the scheduling of major mission milestones such as launch window date and time.

Sounding Rocket Mission Life Cycle

MIC

Mission Initiation

Conference

NASA

MICM

Mission Initiation

Conference Memorandum

NASA

RDM

Requirements

Definition Meeting

NSROC

RDMM

Requirements

Definition Meeting Memorandum

NSROC

DR

Design Review

NSROC

DRM

Design Review Memorandum

NSROC

PIR

Pre-Integration

Review (~ 1 wk before

I&T)

NSROC

(informal)

MRR

Mission Readiness

Review

NSROC

MRRM

Mission Readiness

Review Memorandum

NSROC

MCR

Mission

Close-Out Report

NSROC

MIC Science Package

Mission Initiation Conference Inputs

PI

Requ. Def./Prelim Design Design Phase

DRAICO

DR Action Item

Closeout Memorandum

NSROC

Fab

Experiment Integration & Test

MRRAICO

Mission Readiness

Review Action Item Closeout Memorandum

NSROC

FRR

Flight Readiness

Review

NSROC

(informal)

Pad Prep/Stage

ATP

Authorization to

Proceed

NASA

Launch

Mission Results Memo

PI

Flight Data

NSROC

Fabrication, Assembly, Test

2.1.2 Mechanical Devices and Structural Elements

The requirements for mechanical work will be discussed in as much detail as possible. Mechanical items of interest include deployable nose cones (standard or special), doors (access, deployable or retractable), extendible booms, antennas, sensors, and any unique structural items or payload skin requirements. Any temperature limitation, vacuum requirements, or mechanical devices/systems (despin, air, land and water recovery) should also be discussed.

2.1.3 Flight Performance

All payload flight trajectory/timeline requirements such as apogee, altitude, or time-above-altitude should be reviewed and requirements for payload dynamics (spin rate and/or coning limits) included. Some payload designs involve long, flexible booms while others involve tethers and sub-payloads; dynamics requirements for this type of payload should be presented.

The best estimate of payload weight should be determined for the MIC, being careful not to eliminate any significant payload components. The flight performance characteristics of NASA sounding rocket launch vehicles are presented in Section 3 and Appendix E.

Figure 2-1. Typical Sounding Rocket Mission Life Cycle

2.1.4 Instrumentation

Experiment data requirements should be available at the MIC in sufficient detail to allow definition of the telemetry system for the payload. Experiment programming requirements (on-board timers, uplink commands, or special monitoring) should be discussed. A detailed description of standard instrumentation systems is included in Section 5 of this Handbook.

2.1.5 Attitude Control

Attitude knowledge, control and stabilization of space science payloads are key elements in many science experiments. Attitude system requirements should be fully discussed to determine the type of Attitude

Control System (ACS) required. The nature of celestial targets should be defined and any attitude maneuver sequences employed. Pointing accuracy and stability (jitter) should be specified. Known payload launch constraints are presented at the MIC. The types and capabilities of sounding rocket attitude control systems are presented in Section 5.

2.1.6 Navigation

Requirements frequently include detailed definitive knowledge of space/time during flight. Applicable requirements should be addressed in the MIC.

2.1.7 Data Reduction

The customer can obtain assistance in data processing and analysis from WFF. Specific data reduction requirements should be discussed at the MIC. A description of WFF capabilities for data processing and analysis, and guidance on requesting support, is provided in Section 9.

2.1.8 Testing

SRP testing policies are detailed in Section 7. In general, all flight payloads must be tested in accordance with the testing specifications. Any special testing concerns or requirements should be discussed at the

MIC.

2.1.9 Foreign Nationals

Sounding Rockets are considered Significant Military Equipment (SME) and are listed on the ITAR US

Munitions List (USML). If foreign nationals are involved with experiment design and testing or field operations, the MM must be notified at the MIC in order to allow enough time to process paperwork required for a Technical Assistance Agreement (TAA). This allows NSROC personnel to interact directly with non-US citizens to work design issues, conduct payload integration and complete field operations.

2.2 Requirements Definition Phase

Following the MIC, the NSROC payload team works with the experiment team to develop a mission design concept based on requirements provided at the MIC. The goal is to complete this phase in 45 days but for complex missions, much more collaboration with the experiment team may be required before a reasonable mission concept is designed. For a complex mission this phase may involve significant preliminary design effort in order to verify that requirements can be met. If requirements can’t be met within reasonable cost and time, modifications may have to be made.

2.3 The Requirements Definition Meeting (RDM)

Initiated by the NSROC contractor, the RDM includes representatives from NASA and the customer. All information necessary to define and demonstrate the feasibility of the mission and how the mission requirements can be achieved will be presented by the NSROC payload team. The experiment team attends the meeting to verify the mission requirements have been understood and are being met.

A Requirements Definition Meeting Memorandum (RDMM) is documented by the NSROC contractor and provided to NASA within 5 days of the RDM. It serves as the contractor’s task plan and documents mission technical requirements, the approach to satisfying those requirements, schedule, and cost information.

2.4 Design Phase

After the RDM the NSROC payload team typically holds regularly scheduled meetings with the experiment team in order to finalize and document all payload design details. Mechanical and electrical interface requirements are finalized. Detailed mechanical prints and electrical schematics are created as well as a mission timeline. If attitude control is required a detailed control plan is devised. A test plan that will qualify the complete payload for flight operations is created. Many times new designs are proven out by building and testing non-flight hardware. Once this process is complete the Design Review is held.

2.5 Design Review (DR)

The objective of the DR is for the payload team to present a comprehensive description of all aspects of the payload design to maximize potential for mission success.

The MM, in conjunction with the PI, schedules the Design Review and coordinates the Project Team’s preparedness.

The NSROC contractor establishes a Design Review Panel to review all aspects of the mission, vehicle, design, test plan, and integration activities. The Panel consists of NSROC personnel who are not directly involved with the mission but who have established expertise in the areas of technical support required for mission success. These include: Flight Performance, Mechanical Systems, Electrical Systems, Instrumentation Systems, Guidance, Navigation and Control Systems, Recovery Systems, Launch Vehicle Systems, and Ground and Flight Safety (NASA personnel).

During the DR, the Mission Team formally and systematically presents all information necessary to demonstrate that the proposed design and mission approach can meet all mission and safety requirements.

The customer should be prepared to discuss all details of the scientific instrument design and interface with the support systems.

The PI Data Package template for a Design Review can be found in Appendix C.

After completion of the meeting, the panel reconvenes to discuss the results, and formulate and document action items that are provided to the MM for disposition. The Review Panel Chairman generates a Design Review Memorandum (DRM) which summarizes the meeting and documents all assigned action items. The DRM documents that the DR package and presentation demonstrated the proposed design and mission approach is capable of meeting the mission success criteria once action items are addressed.

The MM is responsible for directing the Mission Team in responding to DR action items. This effort is formally documented with a memorandum to the Design Review Panel Chairman.

The panel reviews all responses and either concurs or asks for additional information and clarification.

Once all responses are deemed acceptable the process is officially closed out with a memo from the Panel Chairman to SRPO. At this point fabrication can begin. Although, some standard parts and systems, and those that didn’t generate actions at the Design Review, can begin their fabrication immediately after the meeting; or, in some cases, even earlier.

2.6 Payload Fabrication and Pre-Integration Testing Phase

Payloads are assembled with a mix of custom fabricated mechanical and electrical parts and assemblies from the NSROC shops, as well as a variety of purchased parts and assemblies. Mechanical hardware is assembled and fit-checked prior to integration with scientific instrumentation provided by the customer.

Electrical and telemetry instrumentation wiring and components are assembled and tested prior to integration with the customer's electrical/data systems to facilitate a smooth, trouble-free integration effort.

Special pre-integration design qualification tests are often performed for new separation/ejection/ deployment mechanisms, vacuum doors, and other devices. These special tests are in addition to the total payload post-integration testing that must be successfully completed before flight.

All NSROC provided sub-systems such as telemetry, recovery, ACS, and motor ignition systems are connected together to make sure they are all functioning properly prior to being connected to experiment systems.

Integration and testing of new payloads (except as described below) is usually conducted at WFF. General information concerning the integration and testing laboratories at WFF is presented in Section 10; Section 6 describes specific testing policies. Integration and testing of SPARCS payloads are performed at WSMR as these systems require special equipment that is resident only at that location. Section 6 provides a description of the facilities available for SPARCS payloads at WSMR.

2.7 Pre-Integration Review…