THEMIS IDPU PDR I&T REQUIREMENTS- 1 UCB, October 16, 2003 I&T REQUIREMENTS Ellen Taylor University of California - Berkeley

THEMIS IDPU PDR I&T REQUIREMENTS- 2 UCB, October 16, 2003 Environmental Specification Environmental Specification being developed by Swales Defines the design and test environments for THEMIS instruments Captures all requirements governing the environments to be used in the development, analysis, and test of THEMIS instruments Includes launch structural loads, on-orbit thermal environments, and other environments that may affect end-of-life reliability and performance as well as ground handling and transportation environments Design Loads are defined, expecting some changes in test levels with Coupled Loads Analysis Detailed Integration and Environmental Test Flow will be developed by CDR

THEMIS IDPU PDR I&T REQUIREMENTS- 3 UCB, October 16, 2003 Launch Loads Resonant Frequency The minimum resonant frequency required for THEMIS instruments, probes, and probes carrier assembly (PCA) are list on the Table 3.1 Table 3.1 Minimum Resonant Frequency PCALateral > 15 Hz Axial > 35 Hz Probes> 35 Hz ComponentsStowed > 75 Hz Deployed > 0.25 Hz Propellant Tank Antenna > 200 Hz

THEMIS IDPU PDR I&T REQUIREMENTS- 4 UCB, October 16, 2003 Static-Equivalent Accelerations THEMIS Instruments and components shall be designed to static-equivalent accelerations at their center-of-mass as shown in Table Launch Loads Table Design Limit Load for All Components & Instruments Weight (lbs) Load Factor (G) <

THEMIS IDPU PDR I&T REQUIREMENTS- 5 UCB, October 16, 2003 Random Vibration All instruments, components and probes shall be capable of full operational performance after exposure to the random vibration loads due to the launch environment described in Table – Launch Loads Table For Components Less Than 50 Lbs Frequency (Hz) Qualification ASD (G^2/Hz) Acceptance ASD (G^2/Hz) dB/Oct dB/Oct Overall14.1 Grms10.0 Grms Duration2 minutes1 minutes For components weight greater than 50 lbs, the input level may be scaled down based on weight ratio. Table Probe Frequency (Hz) Qualification ASD (G^2/Hz) Acceptance ASD (G^2/Hz) dB/Oct dB/Oct dB/Oct dB/Oct Overall 7.4 Grms 5.7 Grms Duration2 minutes1 minutes

THEMIS IDPU PDR I&T REQUIREMENTS- 6 UCB, October 16, 2003 Sine Vibration All instruments, components, probes and PCA shall be capable of full operational performance after exposure to the sine vibration loads due to the launch environment described in Table – Launch Loads Table Protoflight Sinusoidal Vibration Level For S/C AxisFrequency (Hz) LevelSweep Rate Thrust5 to to " Double Amplitude 1.4 G 4 octaves/min Lateral5 to to " Double Amplitude 1.0 G 4 octaves/min * Notch CG responses not to exceeded 1.25 times design limit load. Table Sinusoidal Vibration Level For Probe And Components TestAxisFrequency (Hz) LevelSweep Rate QualificationX, Y, Z5 to to " Double Amplitude 8.0 G 2 octaves/min ProtoflightX, Y, Z5 to to " Double Amplitude 8.0 G 4 octaves/min AcceptanceX, Y, Z5 to to " Double Amplitude 6.4 G 4 octaves/min * Notch CG responses not to exceeded 1.25 times design limit load.

THEMIS IDPU PDR I&T REQUIREMENTS- 7 UCB, October 16, 2003 Shock All instruments, components, probes and PCA shall be capable of full operational performance after exposure to the shock environment due to the pyro actuation of probe separation described in Table No attenuation of the shock levels internal to the probe should be used in the design of instrument and components. Launch Loads Table Shock Level Frequency (Hz)QualificationAcceptance 10040G30G dB/Oct+6.8 dB/Oct G1400G

THEMIS IDPU PDR I&T REQUIREMENTS- 8 UCB, October 16, 2003 Thermal-Vacuum Testing Components shall be subjected to a minimum of 4 hot-cold cycles Hot temperature shall be at 10°C above the maximum operating predictions and the cold temperature 10°C below the minimum operating predictions Test duration shall be based on the time required to perform performance/ functional testing of the component at each hot and cold temperature plateau (minimum two-hour soak periods shall be conducted) Components shall be operated during the transition times and turn-on demonstrations shall be made at both cold and hot extremes For components that are determined by analysis to be insensitive to vacuum effects, the test requirements may be satisfied by temperature cycling at normal room pressure in an air Cycling at ambient pressure shall be increased (both the temperature range and the number of cycles) to account for uncertainties. The qualification margin of  10  C (in vacuum) shall be increased to  15  C if testing at ambient pressure is performed. Likewise, the number of thermal cycles shall be increased by 50 percent if testing at ambient pressure (e.g., from 4 cycles in vacuum to 6 cycles at ambient pressure). Project approval is required if testing at ambient pressure is implemented. Thermal

THEMIS IDPU PDR I&T REQUIREMENTS- 9 UCB, October 16, 2003 CSR Environmental Test Matrix

THEMIS IDPU PDR I&T REQUIREMENTS- 10 UCB, October 16, 2003 IDPU I&T Requirements All IDPU flight components shall be integrated before the start of IDPU Integrated Functional Testing A Flight Software Acceptance Test shall be repeated to ensure compatibility with flight hardware A full IDPU functional test procedure shall be developed for used before and after all IDPU environments, and as much as possible during probe level functionals. This test shall include: Verification of all data paths and functions against Instrument Requirements Measurement of power consumption versus Instrument Modes System Throughput Tested with ETU and Flight Instruments as early as schedule permits Environmental tests of the IDPU shall include: Mass Properties Random Vibration (ETU-qualification, Flight-acceptance) Conducted Emission and Susceptibility Testing (ETU-test, Flight-self compatibility) Thermal Vacuum (ETU-2 cycles, Flight-4 cycles, Integrated Instrument Payload-4 cycles)