Artemis II launch April 1, 2026

2SLS Secondary Payloads: Quick Reference Guide

1 Purpose and Scope

This document provides a payload developer-facing reference for organizations developing CubeSat-class secondary payloads for SLS missions. It is meant to function as one-stop reference: a payload team should be able to read it and understand the design posture, verification mindset, and documentation expected for successful integration.

Figure 1-1. CubeSats deploying from ICPS (top left) after Orion (bottom right) separation during Artemis II. Image courtesy of s2a systems.

What this document does:

What this document does not do:

• Describes the SLS secondary payload integration concept at the program level

• Explains generic mechanical, electrical, environmental, and operational requirements

• Gives basic flight environments

• It does not replace requirements documentation, controlled drawings, or approved procedures

• It does not authorize launch or close safety hazards

• It does not publish every mission-specific environment, timeline, or clearance value

• It does not supersede regulatory, spectrum, export control, planetary protection, or debris obligations

3SLS Secondary Payloads: Quick Reference Guide

2 Artemis Secondary Payload System Overview

2.1 NASA-Provided Hardware

2.2 Why SLS Payloads Are Different

On SLS missions, secondary payloads are accommodated in dispensers mounted in the Orion Stage Adapter (OSA). The OSA can accommodate 6U and 12U CubeSats.

Payloads are deployed after Orion separation using spring-ejected dispensers managed by the secondary payload deployment avionics.

Artemis mission profiles will differ and can include deployment in LEO, HEO, and/or heliocentric orbit.

Figure 2-1. The dispensers are shown, nested in the Orion Stage Adapter for Artemis I.

NASA provides the following items:

• Flight dispenser

• Engineering Development Unit dispenser for fit check (As requested and available)

• Flight separation connectors and associated mounting hardware

— Information on this connector can be found in section 5.1

• Pre-Screened battery cells from NASA’s Strategic Reserve (As Requested)

• Requirements for SLS payloads are developed with consideration for crewed missions.

• They may encounter longer dormant periods between integration and deployment

• They remain subordinate to the primary mission timeline and crewed-mission priorities

4SLS Secondary Payloads: Quick Reference Guide

Figure 2-2. Artemis II Astronaut Christina Koch in front of a Secondary Payload Bracket on the OSA.

5SLS Secondary Payloads: Quick Reference Guide

2.3 SLS Payload Constraints

The following table provides a high-level overview of what type of interfaces and requirements a payload can expect during an SLS mission.

Table 2-1. Overview of Payload Accommodation

Baseline Rocket Lab CSD-class Dispenser

After handover to NASA and integration of payload, there will be no access (physical or electrical) aside from NASA personnel performing battery charging, if required.

https://rocketlabcorp.com/assets/Uploads/PSC/Rocket%20Lab%20PSC%20-%202002367F%20Payload%20Spec%20for%203U%206U%2012U.pdf

6SLS Secondary Payloads: Quick Reference Guide

3 Programmatic Interface and Data Exchange

Figure 3-1. Payload team just prior to handoff of their hardware to NASA.

3.1 Secondary Payload Integration Milestones

These milestones may occur concurrently but are generally executed in this order.

• Payload onboarding and baseline requirements

• Safety reviews and submittals

• Environmental test/verification campaign

• Flight unit delivery, processing and closeout

• Launch and deployment

7SLS Secondary Payloads: Quick Reference Guide

Table 4-1. Artemis Protected Frequencies

4 Radio Frequency Compatibility

Payloads must prove that their RF architecture does not interfere with the RF systems on the ground, in the SLS/Orion, or in the various other systems they may come in contact with as part of the Artemis missions.

Figure 4-1. Electric Field Strength Limits

8SLS Secondary Payloads: Quick Reference Guide

5 Environmental Testing

Payloads are required to perform Random Vibe and Quasi-Static Loads testing. All other environments are provided for reference in Chapter 6. If preferred, Qualification/Acceptance criteria can be provided.

Values given refer to the coordinate system shown below. This is test criteria that includes a factor of safety.

Sine burst must be conducted using an oscillating wave form that is ≤1/3 of the payload’s lowest natural frequency when hard mounted to the vibration table.

*Levels account for isolator effects and should be applied at the dispenser chassis mounting interface.

Table 5-1. Static Load Profiles

Figure 5-1. Notional Random Vibe Test Levels and Duration

9SLS Secondary Payloads: Quick Reference Guide

6 Other Environments

6.1 Deployment Speed and Tipoff

The following environments are provided for reference only.

SPLs could experience rotation rates, also known as tip-off rates, when deployed from either a 6U or 12U dispenser at < 10 deg/sec per axis after the payload is fully ejected.

Figure 6-1. Deployment Speed

10SLS Secondary Payloads: Quick Reference Guide

Figure 6-2. Axis Definition for Natural Frequency Coupling

6.2 Natural Frequency Coupling

Payload developers should ensure that the lowest frequency in the lateral axis be above 90 Hz, in the normal axis to be above 46 Hz, and in the long axis to be above 50 Hz to avoid interaction with launch vehicle dynamics. These frequencies are calculated with the spacecraft assemblies constrained to ground at tab interface with the CSD. Violation of the criteria above should be addressed by detailed evaluation of the hardware for payload frequencies that do couple with the vehicle assembly isolation system.

11SLS Secondary Payloads: Quick Reference Guide

6.3 Acoustic Environment

Table 6-1. Acoustic Environments

12SLS Secondary Payloads: Quick Reference Guide

6.4 Shock Environments

6.5 Depressurization Environment

Table 6-2. 95/50 Shock Environments for All Shock Events at SPL-Dispenser Interface (Q=10)

Figure 6-3. Depressurization Environment during Ascent

13SLS Secondary Payloads: Quick Reference Guide

Table 6-3. Tabulated Depressurization Environment

14SLS Secondary Payloads: Quick Reference Guide

6.6.2 Pad-to-Orbit Environment

Table 6-5. Dispenser Interface Temperature from Pad to Orbit

6.6 Thermal and Humidity Environments

There are two primary thermal environments the payload will experience, the on-the-ground environment in the VAB, and the pad-to-orbit environment during rollout and launch.

6.6.1 VAB Environment

Table 6-4. VAB Environmental Conditions

6.7 Electromagnetic Environment (EME)

There are two primary EMEs the payload will experience, on-the-ground through ascent, and on-orbit.

6.7.1 Launch RF EME

Figure 6-4. Launch RF EME (Peak Environment)

15SLS Secondary Payloads: Quick Reference Guide

Table 6-6. Launch RF EME (Peak Environment)

16SLS Secondary Payloads: Quick Reference Guide

6.7.2 On-Orbit RF EME

Figure 6-5. On-Orbit RF EME (Peak Environment)

Table 6-7. Tabulated On-Orbit RF EME (Peak Environment)

17SLS Secondary Payloads: Quick Reference Guide

18SLS Secondary Payloads: Quick Reference Guide

This page intentionally left blank.