Enclosure BB - RTOs.pdf

Contract TBD

ENCLOSURE BB

Date 11-18-2021

NASA

GODDARD SPACE FLIGHT

CENTER

ENCLOSURE BB

REPRESENTATIVE TASK ORDERS (RTO)

FOR

OMNIBUS MULTIDISCIPLINE ENGINEERING

SERVICES (OMES) III

FOR THE

ENGINEERING AND TECHNOLOGY DIRECTORATE

(ETD)

PRELIMINARY

OMES NExIS Robotic Servicing Mission Concept

Period of Performance: January 1, 2024 – December 31, 2024

Background

The objectives of NASA’s Exploration and In-space Services (ExIS) Projects Division are to:

1 Promote U.S. leadership and new industries by collaborating with and transferring technologies to civil, security and commercial stakeholders.

2 Develop groundbreaking technologies to service spacecraft and pioneer in-space assembly and manufacturing, which enables exploration and science missions.

3 Usher in an era of more sustainable, affordable, and resilient spaceflight near Earth, the Moon, and deep into the solar system.

This RTO will focus on the capabilities and skills required to perform on-orbit servicing for a geostationary communications satellite. For this RTO, the spacecraft performing the on-orbit servicing shall be called Servicer 1. The Offeror shall demonstrate competencies for service scenarios including:

1. Proximity operations

2. Rendezvous and grapple

3. Robotic refueling

4. De-orbit with controlled re-entry

Task Description

Design and develop a mission which grapples the communications satellite with an option to refuel and de-orbit with a controlled re-entry to a non-populated region of the Earth.

Design the following mission components:

1. High level mission requirements

2. Concept-level design of a flight module that grapples the communications satellite (assume cooperative, i.e., target is under control and all instruments are safed). The flight module is defined as the components of Servicer 1 used to perform on-orbit servicing and does not include the Servicer 1 bus or the satellite being serviced.

a. Include list of trade studies with recommended solutions for approaches and hardware to accomplish this task.

b. Identify single-point failures and rationale for redundancy or no redundancy

3. Mission Operations Concept

a. Include a mission timeline

b. Develop a proximity operations plan with focus on GN&C sub-system definition

c. Develop a rendezvous and grapple operations plan with focus on robotic system definition. Also, describe any operational constraints on the communications satellite

d. Develop a refueling plan, assuming cooperative refueling

e. Develop ground operations concept for telemetry, tracking and control

4. Identify key enabling technologies for this mission and its development plan to i) Complete the task and/or ii) Make the existing approaches more efficient and/or iii) Minimize significant risks to the communication satellite.

Deliverables

Deliverable Due Date

1. High level mission requirements 4/28/2024

2. Flight module design concept 8/01/2024

3. Technology development plan 9/01/2024

4. Mission Con-Ops document, at a minimum to include

a. Mission timeline

b. Proximity operations plan

c. Grapple operations plan

d. Refuel plan

e. Ground control options

12/29/2024

Assumptions

1. The mission risk classification shall be a CLASS C, as per NPR 8705.4 Risk Classification for NASA Payloads.

2. The mission shall be capable of performing a controlled reentry, per the requirements of NASA-STD-8719.14 Process for Limiting Orbital Debris, from the mission orbit anytime up to 10 years from launch, when initiated by ground procedures.

OMES-III LEO/Ozone RTO

Task Name: Systems Engineering Support for OzoneSat PDR

Period of Performance: 6/1/2022 – 5/31/2023

Background

NOAA is developing the next generation JPSS weather satellite portfolio. This portfolio, named the Low Earth Orbit (LEO) Program, represents a monumental shift away from the large multi-instrument JPSS satellites in favor of multiple constellations made up of smaller single instrument satellites. The goals of these next generation satellites are to be developed, built, tested, and launched with less complexity, time, and cost while providing more useful scientific measurements than a JPSS-like follow-on mission. The LEO Program will be comprised of several multi-satellite constellations that are organized into projects. At a minimum the projects within the LEO Program will provide replacement data for all current JPSS instruments but may be called upon to provide replacement data that is currently provided through international agreements and/or third party private industry should those sources of data become unavailable in the future.

Similar to JPSS development, NOAA has delegated formulation authority to NASA Goddard Space Flight Center (GSFC) for system development, management, & eventual procurement.

GSFC LEO Program systems engineering is responsible for leading all technical aspects of the formulation activities of the projects/constellations.

NOAA has recently received authorization to begin development of a new ozone detecting “smallsat” constellation that will provide more robust science data than JPSS’s current ozone instrument, Ozone Mapping and Profiler Suite (OMPS). As part of this initiative the LEO Program has stood up the OzoneSat Project and has tasked the project with the following:

1. Explore the viability of a small constellation of ozone detecting satellites.

a. Conduct an operational demonstration mission, OzoneSat-1, before use in an operational mission.

b. OzoneSat-1 shall be a Class-D Mission per NPR-8705.4 Risk Classification of

NASA Payloads.

c. OzoneSat-1 shall be on-orbit within 24 months but no later than 36 months.

d. OzoneSat-1 shall have a minimum on-orbit mission life of at least 12 months.

2. Provide resiliency for the JPSS OMPS instrument in the event of an on-orbit failure.

a. The OzoneSat-1’s instrument, OzInst, shall have performance greater than or equal to OMPS.

b. Current OMPS specifications:

i. Coverage: Mapper- 0.3-0.38 µm; Profiler- 0.25-0.31 µm

ii. Nadir Resolution: Mapper- 50 km; Profiler- 250km

iii. Swath: Mapper- 2800 km

iv. Average Data Rate: 409,600 bps

Requirements Management Plan

Description of methods and tools used to decompose requirements, manage requirements, waivers and deviations and track requirement verification.

11/1/2022

System and Subsystem Architecture and

Requirement Documents

System architecture description and decomposition of all system and interface requirements allocated to the system and subsystem levels.

12/1/2022

Systems Engineering Management Plan

Description of the systems engineering approach, including organizational responsibilities, engineering management structure and configuration control.

10/1/2022

System Requirements Document

Document the new constellation requirements down to the detailed design level.

9/1/2022

Trade Studies Identification of major trade items which include considerations for OzoneSat

List of planned trades 7/1/2022

Studies completed 4/31/2023 Mission Concept Review

(MCR)

See GPR 7123.1C, Systems

Engineering and GPR 8700.6A, Engineering Peer

Reviews.

9/1/2022

System Requirements Review

(SRR)

See GPR 7123.1C, Systems Engineering and GPR

8700.6A, Engineering Peer Reviews.

1/1/2023

Preliminary Design Review

(PDR)

See GPR 7123.1C, Systems Engineering and GPR

8700.6A, Engineering Peer Reviews.

5/31/2023

Applicable Documents

• NASA Systems Engineering Handbook

• NPR 7120.5E NASA Space Flight Program and Project Management Requirements

• NPR 7120.8A NASA Research and Technology Program and Project Management

Requirements

• NPR 7123.1C NASA Systems Engineering Processes and Requirements

• GPR 7123.1C Systems Engineering

• GPR 8700.6A Engineering Peer Reviews

Assumptions

1. The OzoneSat-1 bus is assumed to be a vendor-built vehicle with Government levied requirements.

2. The OzInst is assumed to be a vendor-built instrument with Government levied requirements.

3. The procurement vehicle and time required for establishing a procurement vehicle with a vendor should be ignored.