Enclosure_BB_-_RTOs.pdf

RFP NNG17591526R

ESES-III RTO #1 –Single Instrument on a Spacecraft

Background

NASA Headquarters has assigned the Exo-planet Stellar Astronomy Satellite (ESAS) mission to Goddard Space Flight Center. The single instrument on this spacecraft, the

Earth-Like Integrated Organics Telescope (ELIOT), is an in-house build coronagraph instrument on a narrow field observing telescope and features four (4) 1K x 1K pixel array detectors in a Focal Plane Assembly (FPA). The FPA will be operated at a temperature range of 20 K to 50 K at a required stability of +/- 2 mK per each operational time. A Focal

Plane Electronics (FPE) box shall be developed to provide the following:

1. Power and clock signals to the FPA

2. Read out of eight channels per detector @ 10 seconds

3. Digitize the analog signals sent from each detector to 14 usable bits at 10 Mhz. The

S/C science data rate is limited at 30 Mbps average during the operational time from the instrument processor

4. Perform on orbit integration and compression of the data

The FPE shall operate between a temperature ranges of -35°C to 75°C and will be located 3 meters away from the cold FPA on the spacecraft primary structure.

Task Description

1. The contractor shall develop a plan to design, build, integrate, test and deliver a focal plane electronics and spacecraft bus interface unit. This plan shall address, at a minimum, the following areas:

a. Instrument Electrical Architecture and Requirements Definition (Instrument

Electronics Harness & Spacecraft Interface)

b. Preliminary Flight Hardware

Electrical Design & Electrical Electronic Electromechanical (EEE)

Parts Selection

FPGA Design

Packaging Concept

Harness Design

c. Electrical Systems Engineering (including Heritage Assessment and

Redundancy)

d. Assembly & Manufacturing Plan

e. Integration and Test

f. Concept of Operations

2. The contractor shall identify and perform two trade evaluations/analyses and describe the technical, cost, and schedule advantages and disadvantages of each trade.

Period of Performance (PoP): January 1, 2018 – April 30, 2018

Assumptions:

1. The ESAS mission risk classification shall be Class C, as per NPR 8705.4 Risk

Classification for NASA Payloads

2. Electronic Parts Program per EEE-INST-002, Grade 2

3. The ESAS mission shall operate for the Mission Lifetime at L-2

4. Minimum Technology Readiness Level: TRL-6 @PDR

5. Mission life time: 3 years

6. The following instrument parameters are not to be exceeded:

a. Mass requirement 35 kg

b. ELIOT Power: Average Orbital –110W, Instrument Operational – 80W, Peak

– 170W, Survival – 60W

c. Volume: 0.5m X 1m X 1m

d. FPE & S/C Interface Unit Reliability: Ps ≥ 0.9

ESES-III RTO #2 – Instrument Replacement

Six months before Mission Critical Design Review (CDR), NASA HQ received direction from the Congressional Science Advisory Council to replace the secondary instrument on the Astronomical Cosmic Magnetic Explorer (ACME) spacecraft. The Magnetospheric

Instrument Suite (MIS) contains a science grade fluxgate magnetometer with a Faraday

Cup solar wind analyzer. The MIS is managed by another NASA Center, developed by

ABC Incorporated, and will be delivered for integration to the spacecraft at GSFC.

The MIS will measure minute magnetic field variations, the data will be transmitted once per orbit to a ground station, and the spacecraft will have a communications link to the

Near Earth Network/Space Network (NEN/SN).

Task Description

The contractor is responsible for performing tasks related to the acceptance of the MIS, electrical integration to the ACME spacecraft, and any changes in the electrical systems and communication requirements. The contractor shall also identify and describe potential impacts of the MIS accommodation on the spacecraft.

The contractor shall develop or perform the following:

MIS Acceptance Criteria

EMI/EMC Analysis

EEE Parts Review

Integration & Test Outline

Communication Analysis

Period of Performance (PoP): March 1, 2018 – March 1, 2019

Assumptions

1. The MIS will be operated at a temperature range of -10°C to 55°C at a required stability of +/- 2°C and the electronics cards will utilize a modular design to maximize space and minimize power consumption.

2. Spacecraft Parameters:

a. Mass: 150kg (Dry Mass)

b. Power: Average orbital – 250W, Operational – 175W, peak – 350W, survival/essential services – 100W

c. Volume: 1.5m X 1.5m X 3m

d. Reliability: Ps ≥ 0.90

e. Data Rate (TT&C): 200kps using S-Band

f. Propulsion: Hydrazine 3-axis stabilization

3. Instrument Parameters (Primary):

a. Mass: 40kg

b. Power: Average orbital – 85W, Instrument operational – 65W, peak –

125W, survival – 55W

c. Volume: 1m X 1m X 1.5m

d. Reliability: Ps ≥ 0.90

e. Data Rate: 3Mbps

4. Instrument Parameters (Original Secondary):

a. Mass: 25 kg

b. Original Power: Average orbital – 55W, Instrument operational –

45W, peak – 105W, survival – 35W

c. Volume: 0.5m X 0.5m X 0.5m

e. Data Rate: 1.5Mbps

5. MIS Instrument Parameters (Replacement Secondary):

a. Mass: 25 kg

b. New Power: Average orbital – 70W, Instrument operational – 60W, peak – 125W, survival – 35W

c. Volume: 0.5m X 0.5m X 0.5m

e. Data Rate: Determined by the Contractor

6. Communication Maximum Bandwidth Allocations (Downlink Science Data):

a. X-Band: 375MHz

b. Ka-Band: 1500MHz

7. The mission risk classification shall be Class C

8. The ACME spacecraft shall operate in an elliptical orbit with the following parameters:

a. Perigee: 2,655 km

b. Apogee: 73,225 km

c. Inclination: 30°

9. Mission Life time: 3 years

ESES-III RTO #3 – Fiber Optic Development

The Europa Jupiter System Mission is a joint NASA/European Space Agency (ESA) unmanned space mission to explore Jupiter’s moon Europa. NASA Headquarters has directed Goddard Space

Flight Center (GSFC) to build the Europa Reconnaissance Orbiter as part of the joint effort with

ESA. The primary mission objective is to identify candidate sites for future lander mission on

Europa. The prime instrument onboard the Europa Reconnaissance Orbiter is a laser altimetry system, a space-based Light Detection and Ranging (LIDAR). A second instrument on-board the orbiter is an optical spectrometer that will be provided by a university. The optical spectrometer will study the content of reoccurring plumes observed on Europa by Hubble Space Telescope.

The LIDAR will time the flight of laser photons from the orbiter to Europa and back. An on-board computer will use the time of travel form multiple laser pulses to determine elevation. The Europa

Reconnaissance Orbiter will be launched in 2020 from Vandenberg Air Force Base in California into a near-circular orbit around Europa with an altitude of approximately 500 km.

The Europa Reconnaissance Orbiter’s laser will emit visible laser pulses at 532 nm wavelength. The laser will be developed and built in-house at GSFC. The laser will generate six beams arranged in three pairs, with the pairs 4 km apart, in order to determine the surface’s slope and provide adequate ground coverage. The orbiter will take elevation measurements every 25 cm along the satellite’s ground path.

The laser will fire at a rate of 10 kHz. Each pulse sends out about 10 trillion photons, some of which are reflected back from the surface of Europa back to the orbiter. The returned photons from each pulse are collected in a beryllium telescope and transmitted to the Optical Filter Assembly (OFA).

The Optical Filter Assembly filters the light from the telescope into several wavelength for the detector and spectrometer. The OFAs will output the 532nm wavelengths to the detector assembly and the other wavelengths to the optical spectrometer.

The detector assembly will operate between the temperature ranges of -35°C to 75°C and will be located four meters away from the receiver telescope. Six multi-mode optical fibers will guide the returned photons from the Telescope Assembly to six OFAs (See Figure 1). Six single mode optical fibers will transmit light from the OFA to the Detector Assembly.

A six channel multimode fiber array will transmit the other wavelengths from the OFAs to the optical spectrometer. The optical spectrometer will be operated at 70 K in a cryostat assembly located 4.5 meters away from the telescope.

Fiber Array End face Geometry Closely packed 6 in-Line Fibers

(Slit), 105 um core, 0.22NA fiber

Fiber array wavelength range 400 nm – 2400 nm

Optical transmission for OFA to detector fiber optic assemblies

≥ 98% at 532 nm

Maximum angular rotation of Fiber

Array endface

0.5 degrees along the optical axis at 70 K

Task Description and Deliverables

The contractor shall provide a technical plan that identifies the design, development, building and testing of the fiber optics subsystem, including the integration of the fiber optic assemblies in to the detector and optical spectrometer cryogenic assembly.

Subtasks Description

1. Development of an interface control document for fiber optic connection (See Figure 2) between the:

a) Telescope and Optical Filter Assemblies

b) Optical Filter Assemblies and Detector Assembly

c) Optical Filter Assemblies and Cryogenic Optical System

2. Provide plan(s) for building the following Engineering Test Unit (ETU) and flight units:

i) Six 600/630 µm multi-mode fiber optic assemblies (0.39 Numerical Aperture (NA))

ii) Six single mode Fiber Optic assemblies (0.13 NA)

iii) A six channel array Fiber Optic assembly

3. Provide fiber optic parts selection process and test plans for the above builds.

4. Provide an integration plan for:

a. Connecting flight fibers from telescope to OFAs ensuring that fiber core is centered within 2 µm of their respective telescope fiber adapter bore axis (Figure 1)

b. Connecting flight fibers from OFAs to the detector assembly

c. Connecting 6 channel fiber array from OFAs to optical spectrometer with a maximum angular rotation of 0.5 degrees along optical axis of the array at 70 K

Applicable Documents: ASTM-E595

Period of Performance (PoP): June 1, 2018 – February 1, 2019