STP-S28_MRD.pdf

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OSP-4 STP-S28 MRD Rev-Draft 30 May 2019 Page 1 of 22

STP-S28 Launch Service

FA8818-19-F-00XX

Draft Mission Requirements Document

Basic: Draft 30 May 2019

OSP-4 STP-S28 MRD Rev-Draft 30 May 2019 Page 2 of 22

REVISION HISTORY

REVISION DATE SECTION AFFECTED COMMENTS

BASIC [Draft 30 May 19] N/A Initial Release

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TABLE OF CONTENTS

1.0 INTRODUCTION

1.1 MISSION OBJECTIVES AND OVERVIEW

1.2 SCOPE

1.3 ROLES AND RESPONSIBILITIES

2.0 LAUNCH SERVICE PROVISIONS

2.1 LAUNCH VEHICLE STANDARD REQUIREMENTS

2.2 LAUNCH VEHICLE ENHANCEMENTS

2.3 GOVERNMENT FURNISHED PROPERTY

2.4 LAUNCH SERVICE CONSTRAINTS

2.4.1 Launch Solution Maturity (FOPR Vol II, Subfactor 1: Element 1)

2.4.2 Mission Execution (FOPR Vol II, Subfactor 2: Element 1)

3.0 SPACE VEHICLE REQUIREMENTS

3.1 PAYLOAD MANIFEST (FOPR VOL II, SUBFACTOR 2: ELEMENT 5)

3.2 MASS TO ORBIT (FOPR VOL II, SUBFACTOR 1: ELEMENT 2)

3.3 ORBITAL INJECTION CONDITIONS

3.4 PAYLOAD INTERFACE (FOPR VOL II, SUBFACTOR 2: ELEMENT 2)

3.4.1 Mechanical Interface

3.4.2 Electrical Interface

3.4.3 Environments

3.5 SAFETY

3.6 TELEMETRY AND INSTRUMENTATION

3.7 FACILITIES

3.8 SECURITY

3.9 DOCUMENTATION TRANSFER

4.0 ACRONYMS AND ABBREVIATIONS LIST

5.0 REFERENCES

6.0 MRD REQUIREMENTS LIST

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1.0 INTRODUCTION

1.1 MISSION OBJECTIVES AND OVERVIEW

This document provides the spacelift mission requirements for the Orbital Services Program 4 (OSP-4) Contract launch of the DoD Space Test Program S28 (STP-S28) satellites. The U.S. Air Force Space and Missile Systems Center (SMC) Rocket Systems Launch Program (RSLP) Office, within the Launch Systems Enterprise Directorate (SMC/LE), will provide the Launch Vehicle(s) (LV(s)) and launch services for the STP-S28 mission through the OSP-4 contract. STP will be responsible for coordination of the Space Vehicle (SV) activities.

STP-S28 will be an OSP-4 Launch Vehicle Mission Assurance (MA) Category 2 mission, as defined in the OSP-4 Performance-based Work Statement (PWS).

The Initial Launch Capability (ILC) of the first launch of the launch solution will be No Later Than (NLT) December 2021.

The baseline launch location(s) for this mission is to be proposed (TBP) by the Launch Services Contractor (LSC).

The LV(s) will place the STP-S28 SVs into desired orbits and the SVs will separate from the LV(s) via separation systems, as defined in Section 3.1.

The purpose of the STP-S28 mission is to deliver technology demonstrations to orbit, to inform future space system development. The STP-S28 mission objective is to launch Complement 1, at a minimum, and as many SVs included in the other Complement manifests as feasible, into the orbits that comply with altitude and inclination constraints.

1.2 SCOPE

This Mission Requirements Document (MRD) is the controlling source and authority for the STP- S28 mission requirements. In addition to defining mission-specific requirements, this MRD will:

a. Identify roles and responsibilities and interfaces among the various contractors and Government agencies supporting the mission.

b. Document data provided by the agencies furnishing the SVs to be used by the LSC in developing the LV configuration, integrating the SVs, targeting the LV, processing the flight hardware, and conducting the mission.

c. Identify constraints and environments required by the SVs that must be met by the LSC.

d. Tailor any requirements as necessary for the OSP-4 task order for this mission from the

OSP-4 contract PWS, the Small Launch Interface Specification (SLIS), and the Small Launch Performance Requirements Document (SLPRD).

This MRD will be maintained by the RSLP office. In many cases, the detailed requirements and data will be specified in other documentation, which will be referenced herein. This documentation includes the following:

• OSP-4 PWS

• SV/LV Interface Control Document (SV-LV ICD), which identifies detailed SV interface requirements

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• Range requirements documentation developed in accordance with the Universal Documentation System (UDS)

• SLIS

• SLPRD

In the case of conflict between any of the documents referenced herein, the final signed SV-LV ICD will take precedence.

1.3 ROLES AND RESPONSIBILITIES

The roles and responsibilities among agencies and contractors that will support the STP-S28 mission are described below.

SMC/ADS: The STP office, operated by the SMC Advanced Systems and Development Directorate, Space Demonstrations Division (SMC/ADS), is the RSLP customer providing the SVs. STP may represent one or more Space Vehicle Program Offices (SVPOs) and/or Space Vehicle Contractors (SVCs) that are responsible for manufacturing and testing of the SVs and supporting SV to LV integration. STP will be the interface between RSLP and the SVPO and SVC, and will provide direction to RSLP as needed. STP’s activities and responsibilities include:

• Participation in program management (lead for payload segment)

• Facilitating SVPO or SVC provision of SV Range Safety documentation at the request of

RSLP

• Facilitating SVPO or SVC provision of SV data necessary to support the LSC in designing the desired mission

• Coordination of SVPO or SVC shipment of SV(s) to the LSC launch processing site

• Coordination and oversight of SVPO or SVC SV integration activities prior to integrated operations (unless otherwise stated herein)

• Provision of SV Do No Harm documentation, consistent with STP processes, at the request of RSLP

SMC/LEX: The RSLP office, operated by the SMC/LE Small Launch and Targets Division (SMC/LEX), located at Kirtland Air Force Base, New Mexico, is responsible for OSP-4 launch systems and launch operations. Its activities and responsibilities include:

• Participation in program management (lead for launch segment)

• Manage Range support at Government launch ranges

• Manage LV integration

• Coordinate SV interface and mating

• Manage LV MA Mission Assurance Contractor (MAC): A MAC, under contract to SMC/LEX, will provide MA and Independent Verification and Validation (IV&V) support for the LV.

LSC: The LSC is responsible for ensuring the mission SVs reach the designated orbits. The LSC will provide all launch solution hardware and software, integration, processing, facilities, and

OSP-4 STP-S28 MRD Rev-Draft 30 May 2019 Page 6 of 22 range coordination required to accomplish the spacelift mission. The LSC will also provide insight to SMC/LEX and other mission stakeholders on the technical solution, engineering and management processes, and status, as required by the OSP-4 PWS, Contract Data Requirements List (CDRL), and other standards, terms, and conditions levied by the contract.

In accordance with the OSP-4 PWS, the LSC will ensure that Associate Contractor Agreements (ACAs) or Non-Disclosure Agreements (NDAs) are completed for the following SMC/LEX support contractors and other stakeholders as identified by the Government:

• ASRC Space and Defense (AS&D)

• Tecolote Research, Inc

• Aero Thermo Technology, Inc

• LinQuest

• Jackson & Tull

• Integrity Applications, Inc. (IAI)

• The Aerospace Corporation

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2.0 LAUNCH SERVICE PROVISIONS

2.1 LAUNCH VEHICLE STANDARD REQUIREMENTS

Per the OSP-4 PWS, the proposed launch solution will meet the standard performance requirements of the RSLP SLPRD Section 3 and the standard interface requirements of the RSLP SLIS Section 3.

2.2 LAUNCH VEHICLE ENHANCEMENTS

The launch solution will include the following OSP-4 enhanced capabilities from the RSLP SLPRD Section 4. Details will be provided in subsequent sections.

Table 2-1: SLPRD Enhancements for STP-S28

Required SLPRD Enhancement # Title MRD Details

Yes E1-001 Increased Insertion Accuracy Section 3.2 No E2-001 GTO Injection – Ascending Node N/A No E2-002 GTO Injection – Descending Node N/A No E3-001, 002 Basing – Eastern Range N/A No E3-003, 004 Basing – Western Range N/A No E3-005 Basing – Wallops Flight Facility N/A No E3-006 Basing – Kodiak N/A No E4-001, 002 System Quality N/A No E5-001, 002 Protected GPS N/A No E6-001, 002 Payload Orientation N/A No E7-001 Over the Horizon Telemetry N/A No E8-001 Telemetry N/A Yes E9-001 Separation System Section 3.4.1

The launch solution will include the following OSP-4 enhanced capabilities from the RSLP SLIS Section 4. Details will be provided in subsequent sections.

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Table 2-2: SLIS Enhancements for STP-S28

Required SLIS Enhancement # Title MRD Details

Yes E1-001, 002, 003, 004, 005 Conditioned Air Section 3.4.3.2

Yes E2-001, 002 Nitrogen Purge Section 3.4.3.5 No E3-001, 002 Additional Access Panel N/A

No E4-001 Supplemental Aft Payload Compartment Gas Conditioning N/A

No E5-001 Additional Routine Access Doors N/A

No E6-001 Contamination Control Enhancement (CCE) N/A

No E6-002 CCE Material Selection N/A

Yes E6-003, 004, 005, 006, 007 CCE Air Quality Section 3.4.3.6

No E6-008 CCE Surface Cleanliness N/A

No E6-009 CCE Particulate Transfer Minimization N/A

No E6-010 CCE Molecular Transfer Minimization N/A

No E6-011 CCE Witness Plates N/A No E7-001 Payload Isolation System N/A No E8-001, 002 Increased Payload Envelope N/A No E9-001, 002 Hydrazine Servicing N/A No E10-001, 002 Nitrogen Tetroxide Servicing N/A No E11-001 Augmented Ordnance Support N/A

No E12-001 Video Coverage – Real-Time Coverage N/A

No E12-002 Video Coverage – Recorded Coverage N/A

No E13-001 Radio Frequency Links N/A No E14-001 Dipout Maneuver N/A

No E15-001 Mission Support Equipment Accommodations N/A

No E16-001, 002 Vertical Integration N/A

No E17-001 Flight Command and Telemetry Interface Enhancement (FCTIE) N/A

No E17-002, 003 FCTIE LV to PL Commands N/A No E17-004 FCTIE Discrete Commands N/A No E17-005 FCTIE Switch Closure Function N/A No E18-001 Serial Telemetry Interface N/A

Mission specific additional performance capabilities will be detailed in the SV-LV ICD.

2.3 GOVERNMENT FURNISHED PROPERTY

Government Furnished Property (GFP) will not be provided for the STP-S28 mission beyond that defined in the OSP-4 basic contract.

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2.4 LAUNCH SERVICE CONSTRAINTS

The launch solution shall include only dedicated launch(es) to provide the STP-S28 launch service.

(MRD 001)

The LSC may propose the launch solution as a multi-manifest mission, which will include compliance with the OSP-4 PWS section on multi-manifest mission requirements. The Integrated Payload Stack(s) (IPS) consists of all STP-S28 SVs and flight integration hardware, including separation systems and adapters, on each LV.

The LSC may propose more than one LV to meet the requirements for the launch solution. If multiple LVs are proposed, the Service Requirements Review (SRR), Mission Design Review (MDR)-1, and MDR-2 will address all LVs in the launch solution, and each individual LV will have a separate Pedigree Review (PR), Pre-Ship Review (PSR), and launch campaign, based on the planned launch date for each individual launch.

The launch solution will launch STP-S28 from TBP location(s).

2.4.1 LAUNCH SOLUTION MATURITY (FOPR VOL II, SUBFACTOR 1: ELEMENT 1)

There is no launch solution maturity requirement for STP-S28.

2.4.2 MISSION EXECUTION (FOPR VOL II, SUBFACTOR 2: ELEMENT 1)

The first launch of the STP-S28 launch solution shall have an ILC of NLT December 31, 2021.

(MRD 002)

The launch solution shall have an ILC(s) which supports the launch of each LSC-proposed SV No Earlier Than (NET) six months after that SV’s mission ready date referenced in Complement Payload Suites, Tables 3-1 through 3-7. (MRD 003) If more than one LV is used to provide the STP-S28 launch solution, then the ILC of each subsequent launch shall be NET four months after the previous launch. (MRD 004)

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3.0 SPACE VEHICLE REQUIREMENTS

3.1 PAYLOAD MANIFEST (FOPR VOL II, SUBFACTOR 2: ELEMENT 5)

The LV(s) shall integrate all Complement 1 SVs listed in Table 3-1 into the launch solution.

(MRD 005)

The LV(s) shall integrate all LSC-proposed additional Complement(s) SVs into the launch solution. (MRD 006)

3.2 MASS TO ORBIT (FOPR VOL II, SUBFACTOR 1: ELEMENT 2)

The LV(s) shall place all Complement 1 SVs into insertion orbit(s), with the SV masses and orbital parameters as defined in Table 3-1. (MRD 007) The LV(s) shall place all LSC-proposed additional Complement(s) SVs into insertion orbit(s), with the SV masses and orbital parameters as defined in Tables 3-2 through 3-7. (MRD 008) [Enhancement SLPRD E1-001] The LV(s) shall provide increased insertion orbit accuracy of within ± 10 nmi for both the apogee and perigee of the required orbits for the Complement 1 and additional Complement(s) SVs that require this enhancement, as specified in Tables 3-1 through

3-7. (MRD 009)

3.3 ORBITAL INJECTION CONDITIONS

STP-S28 has no mission-unique requirements for orbital injection conditions beyond the standard expectation that the launch solution be designed to safely deploy all STP-S28 SVs on orbit.

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The tentative STP-S28 payload manifest is shown in Tables 3-1 through 3-7 below.

Table 3-1: STP-S28 Complement 1 Payload Suite Complement 1 SVs Dispenser /

Separation System

Name Form Factor Apogee (km) Perigee (km) Inclination

(deg)

Estimated SV Mass

(kg)

Estimated Dispenser Mass (kg)

Total Known

Estimated Mass (kg)

Ready Date

Designed Type / Model

Provided By

Cube 1 6U 550 (±50) 550 (±50) 45 (+20/-0) 10.68 5.1 15.78 Nov-19 Tabbed LSC Cube 2 6U 550 (±50) 550 (±50) 45 10.68 5.1 15.78 Nov-19 Tabbed LSC Cube 3 3U 600 (+0/-100) 500 (+100/-0) 60 (+0/-15) 5.26 5.26 Aug-19 Railed LSC Cube 4 3U 600 (+0/-100) 500 (+100/-0) 60 (+0/-15) 5.26 5.26 Aug-19 Railed LSC Cube 5 3U 600 (+0/-100) 500 (+100/-0) 60 (+0/-15) 5.26 5.26 Aug-19 Railed LSC Cube 6 3U 600 (+0/-100) 500 (+100/-0) 60 (+0/-15) 5.26 5.26 Aug-19 Railed LSC Cube 7 6U 600 (±200) 600 (±200) 40 1.1 1.1 Sept-20 TBD LSC Cube 8 6U 600 (+200/-50) 600 (+200/-50) 45 (±45) 12 12 Dec-21 Railed LSC Cube 9 6U 600 (+200/-50) 600 (+200/-50) 45 (±45) 12 12 Dec-21 Railed LSC

Cube 10 6U 600 (+200/-50) 600 (+200/-50) 45 (±45) 14 14 Dec-19 Tabbed LSC Cube 11 6U 600 (+200/-50) 600 (+200/-50) 45 (±45) 14 14 Dec-19 Tabbed LSC Cube 12 6U 428 (±100) 428 (±100) 50 (+50/-30) 12 12 Oct-20 Tabbed LSC Cube 13 6U 428 (±100) 428 (±100) 50 (+50/-30) 12 12 Oct-20 Tabbed LSC Cube 14 6U 500 (±100) 500 (±100) 50 (±15) 10.58 10.58 Jun-20 Railed LSC Cube 15 6U 800 (±400) 400 (±150) 75 (±35) 8.45 8.45 Jun-20 Tabbed LSC Cube 16 6U Any Any 28 (+100/-0) 7 7 Jun-20 TBD LSC Cube 17 6U Any Any 28 (+100/-0) 7 7 Jun-20 TBD LSC Cube 18 6U 500 (+40/-125) 500 (+40/-125) 90 (±50) 8.48 8.48 Oct-19 Tabbed LSC Cube 19 6U 500 (±100) 500 (±100) 28 (+24/-0) 12.24 12.24 Apr-20 Railed LSC Cube 20 6U 500 (±100) 500 (±100) 28 (+24/-0) 12.24 12.24 Apr-20 Railed LSC Cube 21 6U 500 (±100) 500 (±100) 60 (+50/-20) 12.5 4.4 16.9 Jan-20 Tabbed LSC Cube 22 6U 550 (±50) 550 (±50) 55 (+85/-15) 9.14 9.14 Jan-20 TBD LSC

Cube 23 27U Any Any 98 (±15) 75 TBD 75 Sep-20 8” Light Band LSC

Cube 24 6U 500 500 98 (+0/-38) 12 12 Aug-20 TBD LSC Cube 25 6U 500 (±10) 500 (±10) 90 (±5) 9.22 4.4 13.62 Apr-19 Tabbed LSC Cube 26 6U 500 (±10) 500 (±10) 90 (±5) 9.22 4.4 13.62 Apr-19 Tabbed LSC Cube 27 3U 500 (+100/-150) 500 (+100/-150) 97 (+5/-47) 5 5 Oct-19 Railed LSC

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Cube 28 3U 500 (+100/-150) 500 (+100/-150) 97 (+5/-47) 5 5 Oct-19 Railed LSC Cube 29 3U 500 (+100/-150) 500 (+100/-150) (45 - 100) 5 5 Sep-19 Railed LSC Cube 30 3U 500 (+100/-150) 500 (+100/-150) (45 - 100) 5 5 Sep-19 Railed LSC Cube 31 3U 500 (+100/-150) 500 (+100/-150) (45 - 100) 5 5 Sep-19 Railed LSC Cube 32 6U 500 (+200/-100) 500 (+200/-100) 90 (+20/-25) 12 12 Jan-21 Railed LSC ESPA 2 ESPA 600 (±50) 600 (±50) 98 30 30 Jun-19 TBD LSC

Note: Eccentricity goal for each SV other than Cube 15 is 0. Cube15 eccentricity goal is 0.0287.

Table 3-2: STP-S28 Complement 2 Payload Suite

Complement 2 SVs Dispenser / Separation System

Name Form Factor Apogee (km) Perigee (km) Inclination

(deg)

Estimated SV Mass

(kg)

Estimated Dispenser Mass (kg)

Total Known

Estimated Mass (kg)

Ready Date

Designed Type / Model

Provided By

Cube 34 12U 700 700 98.2 20 TBD 20 Mar-21 TBD LSC

Cube 46 6U 800 (±100) 800 (±100) 98.5 (+0.5/- 0.3) 12 12 Jan-21 Railed LSC

Note: Eccentricity goal for each SV is 0.

Table 3-3: STP-S28 Complement 3 Payload Suite

Complement 3 SVs Dispenser / Separation System

Name Form Factor Apogee (km) Perigee (km) Inclination

(deg)

Estimated SV Mass

(kg)

Estimated Dispenser Mass (kg)

Total Known

Ready Date

Designed Type / Model

Provided By

OSP-4 STP-S28 MRD Rev-Draft 30 May 2019 Page 13 of 22

Estimated Mass (kg)

Cube 35 1.5U 500 (+100/-50) 500 (+100/-50) 45 (+15/-5) 3.65 3.65 Mar-19 Railed LSC Cube 36 1.5U 500 (+100/-50) 500 (+100/-50) 45 (+15/-5) 3.65 3.65 Mar-19 Railed LSC Cube 37 1.5U 500 (+100/-50) 500 (+100/-50) 45 (+15/-5) 3.65 3.65 Mar-19 Railed LSC Cube 38 1.5U 500 (+100/-50) 500 (+100/-50) 45 (+15/-5) 3.65 3.65 Mar-19 Railed LSC Cube 39 1.5U 500 (+100/-50) 500 (+100/-50) 45 (+15/-5) 3.65 3.65 Mar-19 Railed LSC Cube 40 1.5U 500 (+100/-50) 500 (+100/-50) 45 (+15/-5) 3.65 3.65 Mar-19 Railed LSC Cube 41 1.5U 500 (+100/-50) 500 (+100/-50) 45 (+15/-5) 3.65 3.65 Mar-19 Railed LSC Cube 42 1.5U 500 (+100/-50) 500 (+100/-50) 45 (+15/-5) 3.65 3.65 Mar-19 Railed LSC Cube 45 12U 500 (+100/-0) 500 (+100/-0) 45 (+10/-0) 50 TBD 50 Aug-20 TBD LSC Cube 48 3U 500 (±50) 500 (±50) 50 (+90/-10) 5 5 May-20 Railed LSC Cube 49 3U 500 (±50) 500 (±50) 50 (+90/-10) 5 5 Mar-20 Railed LSC Cube 50 3U 500 (±50) 500 (±50) 50 (+90/-10) 5 5 Mar-20 Railed LSC Cube 59 6U 500 (±50) 500 (±50) 50 (+90/-10) 11 11 Mar-20 Railed LSC Cube 60 6U 500 (+0/-50) 500 (+0/-50) 30 (+20/-0) 11 11 Feb-21 Railed LSC Cube 61 6U 500 (+0/-50) 500 (+0/-50) 30 (+20/-0) 11 11 Feb-21 Railed LSC

Table 3-4: STP-S28 Complement 4 Payload Suite

Complement 4 SVs Dispenser / Separation System

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Name Form Factor Apogee (km) Perigee (km) Inclination

(deg)

Estimated SV Mass

(kg)

Estimated Dispenser Mass (kg)

Total Known

Estimated Mass (kg)

Ready Date

Designed Type / Model

Provided By

Cube 43 3U 500 (±100) 500 (±100) 90 (±56) 5 5 Jul-19 Railed LSC Cube 44 3U 500 (±100) 500 (±100) 90 (±56) 5 5 Jul-19 Railed LSC Cube 47 1U 500 (+100/-50) 500 (+100/-50) 75 (+40/-10) 1 1 Aug-19 Railed LSC Cube 51 6U 500 (±60) 500 (±60) 80 (+3/-5) 10 10 Jul-19 Tabbed LSC Cube 52 6U 550 (±150) 550 (±150) 70 (±20) 9.8 9.8 Feb-20 Tabbed LSC Cube 54 3U 650 (±50) 600 (+100/-50) 63.4 (+60/-5) 3.95 3.95 Jan-20 Railed LSC

Note: Eccentricity goal for each SV other than Cube 54 is 0. Cube 54 eccentricity goal is 0.0036.

Table 3-5: STP-S28 Complement 5 Payload Suite

Complement 5 SVs Dispenser / Separation System

Name Form Factor Apogee (km) Perigee (km) Inclination

(deg)

Estimated SV Mass

(kg)

Estimated Dispenser Mass (kg)

Total Known

Estimated Mass (kg)

Ready Date

Designed Type / Model

Provided By

Cube 55 1U 500 (+100/-0) 500 (+100/-0) 98.7 (±10) 1.3 1.3 Mar-20 TBD LSC Cube 56 3U 400 (±100) 400 (±100) 80 (+10/-2.2) 4 4 May-20 TBD LSC Cube 57 1.5U 450 (±50) 450 (±50) 96 (+14/-26) 1.8 1.8 Feb-20 Railed LSC Cube 58 1.5U 450 (±50) 450 (±50) 96 (+14/-26) 1.8 1.8 Feb-20 Railed LSC

Table 3-6: STP-S28 Complement 6 Payload Suite

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Complement 6 SVs Dispenser / Separation System

Name Form Factor Apogee (km) Perigee (km) Inclination

(deg)

Estimated SV Mass

(kg)

Estimated Dispenser Mass (kg)

Total Known

Estimated Mass (kg)

Ready Date

Designed Type / Model

Provided By

> ESPA 3 > ESPA 590 590 28.5 350 350 Jan-20 TBD LSC

Table 3-7: STP-S28 Complement 7 Payload Suite

Complement 7 SVs Dispenser / Separation System

Name Form Factor Apogee (km) Perigee (km) Inclination

(deg)

Estimated SV Mass

(kg)

Estimated Dispenser Mass (kg)

Total Known

Estimated Mass (kg)

Ready Date

Designed Type / Model

Provided By

Cube 53 3U 1200 (+100/-

400) 500 (+125/-25) 63.4 (+60/-5) 3.95 3.95 Mar-21 Railed LSC

Note: Eccentricity goal for Cube 53 is 0.0485.

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3.4 PAYLOAD INTERFACE (FOPR VOL II, SUBFACTOR 2: ELEMENT 2)

3.4.1 MECHANICAL INTERFACE

[Enhancement SLPRD E9-001] As defined in Tables 3-1 through 3-7, the LV(s) shall provide separation systems for the STP-S28 non-cubesat Complement 1 and additional Complement(s) SVs proposed, that impart separation velocity adequate to prevent re-contact between the SV and LV, with combined tip-off rates of less than 2 deg/sec (including separation system tip-off, vehicle rates, and CG alignment) about each axis. (MRD 010) [Enhancement SLPRD E9-001] As defined in Tables 3-1 through 3-7, the LV(s) shall provide containerized deployers for the STP-S28 cubesat Complement 1 and additional Complement(s) SVs proposed, that impart a separation velocity adequate to prevent re-contact between the SV and LV, with combined tip-off rates of less than 2 deg/sec (including separation system tip-off, vehicle rates, and CG alignment) about each axis. (MRD 011) The launch solution shall define and comply with the STP-S28 SVs and containerized deployers mass properties in the SV-LV ICD. (MRD 012)

3.4.2 ELECTRICAL INTERFACE

STP-S28 has no mission-unique requirements pertaining to the electrical interface.

3.4.3 ENVIRONMENTS

3.4.3.1 Dynamics - STP-S28 has no mission-unique dynamics environments requirements.

3.4.3.2 Thermal (Temperature and Humidity) - [Enhancement SLIS E1-001 to E1-005] The launch solution shall provide conditioned air to the SVs after encapsulation through launch to maintain temperature and humidity requirements described in the SLIS.

(MRD 013)

3.4.3.3 Contamination - STP-S28 has no mission-unique contamination requirements.

3.4.3.4 Radio Frequency (RF) / Electromagnetic Interference (EMI) / Electromagnetic Compatibility (EMC) - STP-S28 has no mission-unique requirements pertaining to EMI radiated and conducted emissions.

Specific limitations imposed on the SVs are TBS by the LSC and will be documented in the SV-LV ICD.

The LV(s) shall be compatible with SVs transmitter turn-on TBS seconds after each SV separation, to be documented in the SV-LV ICD. (MRD 014)

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3.4.3.5 Nitrogen Purge - [Enhancement SLIS E2-001, E2-002] The launch solution shall include a continuous clean dry gaseous nitrogen (GN2) purge to SV(s), as specified in Tables 3- 1 through 3-7, inside the PLF throughout processing until liftoff. (MRD 015)

3.4.3.6 Air Quality – [Enhancement SLIS E6-003 to E6-007] The launch solution shall include contamination control enhancement (CCE) air quality. (MRD 016)

3.5 SAFETY

STP-S28 has no mission-unique safety requirements.

3.6 TELEMETRY AND INSTRUMENTATION

STP-S28 has no mission-unique telemetry requirements.

3.7 FACILITIES

The launch solution shall include all support equipment required to process, integrate, handle, check-out, and launch the LV(s). (MRD 017) The launch solution shall provide the launch facilities for the LV(s). (MRD 018) The launch solution shall provide the STP-S28 SVs Payload Processing Facility (PPF) and SV/LV integration and encapsulation facility. (MRD 019)

3.8 SECURITY

Some of the STP-S28 SVs are being provided by international mission partners requiring a Technical Assistance Agreement (TAA) defined by ITAR regulations, and some of the SVs are classified at the TBD level. The launch solution shall include appropriately obtained TAAs and appropriately cleared personnel to support integration and encapsulation of the IPS(s) at the TBD classification level at the PPF. (MRD 020) For STP-S28 SVs needing secure storage prior to LV integration, the launch solution shall provide adequate storage at the TBD classification level or provide 24/7 access for security oversight of the SV prior to and after integration with the LV. (MRD 021) The launch solution shall provide the necessary security provisions at the TBD classification level whenever post-encapsulation access inside the fairing to the SVs is needed. (MRD 022) Additional security guidance will be provided as required.

3.9 DOCUMENTATION TRANSFER

STP will establish and manage a STP-S28 Virtual Distributed Library (VDL) for the transfer and sharing of mission documents with mission partners. The launch solution shall allow and support for the transfer and sharing of documents with STP-S28 mission partners using VDL and shall provide contact information of LSC personnel requiring VDL access to the STP point of contact.

(MRD 023)

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4.0 ACRONYMS AND ABBREVIATIONS LIST

ACA Associate Contractor Agreement AS&D Arctic Slope Regional Corporation Space and Defense ASRC Arctic Slope Regional Corporation ASTM American Society for Testing and Materials C Celsius C/CAM Collision/Contamination Avoidance Maneuver CCE Contamination Control Enhancement CG Center of Gravity CDRL Contract Data Requirements List deg Degree DoD Department of Defense EELV Evolved Expendable Launch Vehicle EGSE Electrical Ground Support Equipment EMI Electromagnetic Interference EMC Electromagnetic Compatibility F Fahrenheit FCTIE Flight Command and Telemetry Interface Enhancement ft2 Square Feet FTS Flight Termination System g Acceleration of Gravity GEVS General Environmental Verification Standard GFP Government Furnished Property GN2 Gaseous Nitrogen GPS Global Positioning System GSE Ground Support Equipment GTO Geosynchronous Transfer Orbit Hz Hertz IAI Integrity Applications, Inc.

ICD Interface Control Document ILC Initial Launch Capability IPS Integrated Payload Stack

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ISO International Organization for Standardization ITAR International Traffic in Arms Regulations IV&V Independent Verification and Validation Kbps Kilobits Per Second kg Kilogram km Kilometers LV Launch Vehicle LSC Launch Services Contractor m Meters m2 Square Meters MA Mission Assurance MAC Mission Assurance Contractor Mbps Megabits Per Second MDR Mission Design Review MHz Megahertz mm Millimeters mm2 Square Millimeters MM Mission Manager MRD Mission Requirements Document N/A Not Applicable NASA National Aeronautics and Space Administration NDA Non-Disclosure Agreement NET No Earlier Than OSP-4 Orbital Services Program-4 PL Payload PLF Payload Fairing PPF Payload Processing Facility P-POD Poly Picosatellite Orbital Deployer PR Pedigree Review PSC Planetary Systems Corporation PSR Pre-Ship Review PWS Performance-based Work Statement RF Radio Frequency

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RSLP Rocket Systems Launch Program RUG Rideshare User’s Guide sec Second SLIS Small Launch Interface Specification SLPRD Small Launch Performance Requirements Document SMC Space and Missile Systems Center SMC/ADS SMC Advanced Systems and Development Directorate, Space

Demonstrations Division SMC/LE SMC Launch Systems Enterprise Directorate SMC/LEX SMC/LE Small Launch and Targets Division SRR Service Requirements Review STP Space Test Program SV Space Vehicle SVC Space Vehicle Contractor SVPO Space Vehicle Program Office TAA Technical Assistance Agreement TBD To Be Determined TBP To Be Proposed TBS To Be Supplied TDRSS Tracking and Data Relay Satellite System UDS Universal Documentation System VDL Virtual Distributed Library W Watts

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5.0 REFERENCES

OSP-4 PWS

RSLP SLIS

RSLP SLPRD

EELV Rideshare User’s Guide (RUG), May 2016 Other reference documents are listed in the OSP-4 PWS

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6.0 MRD REQUIREMENTS LIST

MRD

Requirement Number

Short Description MRD Section

SLPRD / SLIS

Requirement

Number

OSP-4

PWS

Section

CWBS

001 Primary or Dedicated Launches 2.4 N/A 2.1.7 002 First ILC 2.4.2 N/A Annex 2 003 ILC NET SV Ready Date 2.4.2 N/A N/A 004 Time Between Launches 2.4.2 N/A N/A 005 Payload Manifest Complement

3.1 N/A 2.1.4.10.2, 2.1.7.1

006 Payload Manifest Additional Complements

3.1 N/A 2.1.4.10.2, 2.1.7.1

007 Mass-to-Orbit Complement 1 3.2 SLPRD Section 3.3 N/A 008 Mass-to-Orbit Additional

Complements

3.2 SLPRD Section 3.3 N/A

009 Increased Insertion Orbit Accuracy

3.2 SLPRD Section 4.1 N/A

010 LSC-Provided Separation Systems

3.4.1 SLPRD Section 4.9 N/A

011 LSC-Provided Containerized Deployers

3.4.1 SLPRD Section 4.9 N/A

012 Mass Properties in SV-LV ICD 3.4.1 N/A N/A 013 Conditioned Air Enhancement 3.4.3.2 SLIS Section 4.1 N/A 014 Compatibility with SV

Transmitters after Separation

3.4.3.4 N/A N/A

015 Nitrogen Purge Enhancement 3.4.3.5 SLIS Section 4.2 N/A 016 CCE Enhancement – Air Quality 3.4.3.6 SLIS Section 4.6.2 N/A 017 LV Support Equipment 3.7 N/A 2.1.4.5 018 LV Launch Facility 3.7 N/A 2.1.4.5 019 SV PPF and Integration and

Encapsulation Facility

3.7 N/A 2.1.4.5

020 SV Classification Level at PPF 3.8 N/A 2.1.4.9 021 SV Secure Storage 3.8 N/A 2.1.4.9 022 SV Classification Level Post-

Encapsulation

3.8 N/A 2.1.4.9

023 Documentation Transfer 3.9 N/A N/A