CLIN1_VADR_LSIRD_Template_EXAMPLE.pdf

PDF 239 KB Posted

Attached to
Venture-Class Acquisition of Dedicated and Rideshare (VADR) Launch Services Federal contract opportunity
Solicitation number
80KSC021R0034_On-Ramp_Issue01
Issued by
National Aeronautics and Space Administration Kennedy Space Center

About this file

This Launch Services Interface Requirements Document (LSIRD) template outlines the key spacecraft and mission parameters required for a CLIN 1 launch service. It defines the spacecraft's not-to-exceed and current best estimate masses, dimensions, separation plane interface, orbital insertion requirements, separation and tip-off requirements, launch period, structural and electrical interfaces to the launch vehicle including separation indicator loops, expected environments, ground processing facility requirements including fueling needs and hazards, and any additional mission-specific requirements. The related federal contract opportunity is a pre-solicitation for Venture-Class Acquisition of Dedicated and Rideshare Launch Services through the National Aeronautics and Space Administration Kennedy Space Center.

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Text version

Rev. A, Date

Note: This LSIRD template includes an example of the type of spacecraft requirements that may be included as part of an

RLSP for a CLIN 1 launch service.

[Mission Name] VADR Launch Services Interface Requirements Document (LSIRD)

1 INTRODUCTION AND SCOPE

This section summarizes the SC and mission.

2 SPACECRAFT MASS

2.1 Not to Exceed (NTE) Mass

The SC NTE mass is [XX.XX] kg.

2.2 Current Best Estimate (CBE) Mass

The SC CBE mass is [XX ± XX] kg. The SC CBE mass properties are shown in Table 1.

Table 1 - SV Current Best Estimate (CBE) Mass Properties

Description Axis CBE Uncertainty

Center of Gravity (mm)

X

Y

Z

Moments of Inertia (kgm2)

IXX

IYY

IZZ

3 SPACECRAFT VOLUME

This section defines the SC’s NTE dimensions and notes any excursions below the separation plane with dimensions.

• Provide SC figures with dimensions o Top and side views

4 MISSION DESIGN

This section defines the SC orbit and separation requirements. Includes any additional requirements such as (but not limited to) thermal roll, sun-angle restrictions, or ascent duration as necessary.

• Orbital insertion requirements

• Separation and tip-off requirements

• Launch period

Rev. A, Date

5 STRUCTURAL INTERFACES

• Define the SC to LV mechanical interface requirements

• Define the separation system requirements or design details if known

• Define the SC coordinate system and origin (this can be shown in section 3)

• Define the SC to LV interface plane (this can be shown in section 3)

6 ELECTRICAL INTERFACES

• Define the electrical interfaces o Number of pins needed in the IFD(s)

▪ Power circuits

▪ Data circuits

▪ SC separation indicator loops

7 ENVIRONMENTS

This section defines the environments the SC is designed to if they are known. After the contract is awarded, the LV specific environments will be defined in the ICD.

• Dynamic Environments o Vibration

▪ Random

▪ Sine o Acoustics o Shock

• EMC-RF

• Ground Operations Temperature and Humidity

• Contamination Control requirements above and beyond ISO Class 8

8 GROUND PROCESSING

8.1 Payload Processing Facility (PPF) Requirements

• PPF occupancy duration o Pre-integration SC standalone processing

• Fueling requirements (if any)

• Lifting, handling, or orientation requirements

• SC hazards

9 ADDITIONAL MISSION SPECIFIC REQUIREMENTS

This section defines any additional mission specific requirements..

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