Annex 1 - TROPICS LSIRD.pdf

Time-Resolved Observations of Precipitation structure and storm Intensity with a

Constellation of Smallsats

(TROPICS)

Launch Service Interface Requirements Document (LSIRD)

[Rev.]

TROPICS Attachment 01 – Annex 1 – LSIRD 80KSC020R0036

DOCUMENT CHANGE LOG

Date Pages Affected Reason for Change Version/Revision

TABLE OF CONTENTS

1 INTRODUCTION & SCOPE 5

1.1 DOCUMENT PURPOSE 6

1.2 DOCUMENT OBJECTIVES 6

2 DOCUMENTS 6

2.1 APPLICABLE DOCUMENTS 6

2.2 REFERENCE DOCUMENTS 6

3 INTERFACE REQUIREMENTS 8

3.1 MECHANICAL INTERFACES 8

3.1.1 Structural Interfaces 8

3.1.2 Structural Loads 12

3.1.3 Mass Properties 12

3.2 ELECTRICAL INTERFACES 13

3.2.1 Airborne Interfaces 13

3.2.2 Lightning Suppression 16

3.2.3 GSE Interfaces 16

3.3 ENVIRONMENTAL INTERFACES 16

3.3.1 Thermal Interfaces 16

3.3.2 Purge 17

3.3.3 Payload Fairing Internal Pressure 17

3.3.4 Dynamic Environments 17

3.3.5 Electromagnetic Compatibility 19

3.4 MISSION DESIGN 20

3.4.1 Orbit Insertion Requirements 20

3.4.2 Thermal Roll 21

3.4.3 Sun Angle Constraints 21

3.4.4 LV Ascent Duration Requirement 21

3.4.5 Launch Period/Windows 21

3.4.6 S/C Events from T-0 through several minutes after separation 21

3.4.7 Separation Requirements 21

3.4.8 Post Separation Requirements 22

3.4.9 Acquisition Assistance 22

3.5 GROUND PROCESSING REQUIREMENTS 22

3.5.1 SV Ground Handling 22

3.5.2 Spacecraft Hazards 22

Figure 2: Stowed configuration

1.1 DOCUMENT PURPOSE

This document defines the TROPICS to LV interface/integration requirements and constraints necessary to assure technical compatibility and to contribute to mission success.

1.2 DOCUMENT OBJECTIVES

1. To provide a definition of the TROPICS to LV integration and interface requirements as necessary to permit their design and implementation.

2. To identify facility and mission operations support requirements.

2 DOCUMENTS

2.1 APPLICABLE DOCUMENTS

MIL-STD-461F Requirements for the control of Electromagnetic Interference Characteristics of Subsystem and Equipment, 1999-8-20

IEST-STD-CC1246 Product Cleanliness Levels and Contamination Control Program

2.2 REFERENCE DOCUMENTS

ISO 14644-1 Classification for Air Cleanliness

PSC 2002337E Canisterized Satellite Dispenser (CSD) Data Sheet

PSC 3000257B

Canisterized Satellite Dispenser (CSD) Operating and Integration Procedure

SW-150-1000-190-7575 Shockwave Isolator Assembly ICD

TRPCS-ICD-003 TROPICS Space Vehicle to Ground Station ICD

3 INTERFACE REQUIREMENTS

This section establishes the launch services (LS) interface design requirements for TROPICS.

The TROPICS design is finalized and this section reflects requirements levied on the space vehicle design and identifies launch vehicle and processing interface requirements known to date.

3.1 MECHANICAL INTERFACES

3.1.1 Structural Interfaces

a) The LV shall deploy six TROPICS SVs, each from the Canisterized Satellite Dispenser (CSD) launch dispenser, as depicted in Figure 3.

Figure 3: Launch Dispenser and Isolation System for the TROPICS Space Vehicles

Figure 4: TROPICS Space Vehicle Stowed in the CSD

LV Interface Figure 5 details the isolator bolt locations for mounting to the LV. All dimensions are in mm.

a) The LV shall provide an interface compatible with the CSD/isolator bolt pattern as shown in Figure 5 for mounting to the LV using #10/32 tapped holes or inserts. A maximum true position tolerance on the LV adapter plate tapped holes is 0.010” (0.25 mm).

b) The LV shall install the 6 Moog Shockwave isolators onto the interface plate.

c) The LV shall install the CSD onto the isolators with TROPICS provided 10/32 x ¾” fasteners. (NAS1351N3-12)

Figure 5: CSD, Isolator, and LV Interface Bolt Pattern

CSD Coordinate System The CSD coordinate system is a right hand Cartesian coordinate system with the origin located as indicated in Figure 6. The +Y-axis is at the intersection between the dispenser backplane and the bottom plane; the +Z-axis points in the direction of the deployment velocity vector of the SV;

and the +X-axis points in the direction given by the right hand coordinate system.

Figure 6: CSD Coordinate System

SV Figures The physical dimensions of the TROPICS SV, loaded into its CSD and mated to its isolation system, are shown in Figure 7. All dimensions in mm.

Figure 7: Physical Dimensions of SV, Loaded into Dispenser, on Isolators

The CSD door is fully open at 91.5 degrees as shown in Figure 8.

Figure 8: Physical Dimensions of SV, Loaded into Dispenser, on Isolators

IC

Continuous Current Draw from Door Initiator (5)

A .10 1.5

T Time to Initiate (Open Door) (5)

-45 to +90 degree C, <10e-5 torr s .010 .050

RS

Switch Terminal Resistance

Door and occupancy switches, closed circuit, includes internal CSD wiring, - 45 to +90 degree C ohm .046 .107

ISR

Current Capacity of Switch, Resistive

28 Vdc, <10e-5 torr, door and occupancy switches

A - 2.5

ISI

Current Capacity of Switch, Inductive

28 Vdc, <10e-5 torr, door and occupancy switches

A - 1.5

PT

Payload Travel Required for Occupancy Switch Change State

+Z travel from launch position in [mm] 13.2 [335]

DP

Door Position for Door Switch Change of State

Angle (0 deg is closed) deg .3 2.0

Figure 9: CSD Electrical Schematic

Figure 10: Launch Vehicle Electrical Interface

Figure 11: Representative Initiation Electrical Profile

3.2.2 Lightning Suppression

TROPICS does not require lightning suppression.

3.2.3 GSE Interfaces

Electrical Connectors at the EGSE Room/Umbilical Interface N/A

3.3 ENVIRONMENTAL INTERFACES

3.3.1 Thermal Interfaces

Ground Operations Temperature, Humidity, and Contamination Control

a) The LVC shall maintain the temperature, humidity, and air cleanliness values given in

Table 4.

b) The LVC shall provide contamination control to meet TROPICS requests per Table 4.

c) The PLF and LV surfaces to which TROPICS is exposed to shall be cleaned, inspected, and maintained to be free of visible particles with the naked eye (corrected to 20/20 vision), with a 100-125 ft-candle light at a distance of 6 to 18 inches consistent with VCHS levels per IEST-STD-CC1246E.

Table 4: Spacecraft Gas/Thermal Conditioning Requirements

3.4.8 Post Separation Requirements

The LV shall perform a CCAM maneuver to ensure no recontact with the SVs.

3.4.9 Acquisition Assistance

The LV shall provide LSP and MIT LL with an Orbital Parameter Message (OPM) for the LV orbit state at each separation event within 30 minutes.

3.5 GROUND PROCESSING REQUIREMENTS

3.5.1 SV Ground Handling

Facility Requirements (PAD / Launch Site) N/A

Spacecraft Handling during Ground Processing The LSC shall provide the TROPICS team with a maximum of 5 days of non-hazardous standalone processing in their cleanroom work area at the integration facility for each launch campaign. At the end of this time, the TROPICS SVs will be ready for integration to their associated element of the Integrated LV Payload Stack.

3.5.2 Spacecraft Hazards

N/A

Appendix A – Common Acronyms and Abbreviations

ADCS Attitude Determination & Control System C Celsius CCAM Collision and Contamination Avoidance Maneuver CG Center of Gravity CSD Canisterized Satellite Dispenser deg Degree ECS Environmental Control System EGSE Electrical Ground Support Equipment F Fahrenheit ft Foot GEVS General Environmental Verification Standard GN2 Gaseous Nitrogen GSE Ground Support Equipment HEPA High-Efficiency Particulate Air hr Hour Hz Hertz ICD Interface Control Document I/F Interface IFD In-Flight Disconnect in Inch IRD Interface Requirements Document ISO International Standards Organization kbps Kilobits per Second km Kilometer KSC John F. Kennedy Space Center l Liter lb Pound LRD Launch Readiness Date LS Launch Services LSIRD Launch Services Interface Requirements Document LSP Launch Services Program LSTO Launch Services Task Order LV Launch Vehicle LVC NASA Launch Vehicle Contractor m Meter MGSE Mechanical Ground Support Equipment MIT Mission Integration Team MIT LL MIT Lincoln Laboratory MLT Mean Local Time mm millimeter MPE Maximum Predicted Environment NASA National Aeronautics and Space Administration NLS NASA Launch Services NLT No Later Than NRZ-L Non-Return to Zero – Phase L

NTE Not to Exceed NVR Non-Volatile Residue OPM Orbital Parameters Message PAC Percent Area Coverage PAF Payload Attach Fitting PLA Payload Adapter PLF Payload Fairing PSC Planetary Systems Corporation Psia Pounds Per Square Inch Absolute Psig Pounds Per Square Inch Gauge PPF Payload Processing Facility PTC Passive Thermal Control RAAN Right ascension of the ascending node RF Radio Frequency RLSP Request for Launch Services Proposal SV Space Vehicle or Spacecraft SVC Space Vehicle Contractor SCFH Standard Cubic Foot Per Hour SCFM Standard Cubic Foot Per Minute SI Systeme International d'Unites SOW Statement of Work SRS Shock Response Spectrum SSF Spacecraft Structural Frame TML Total Mass Loss TOD True of Date

TROPICS Time-Resolved Observations of Precipitation structure and storm Intensity with a Constellation of Smallsats

VDC Volts – Direct Current