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-RFP

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

TROPICS Attachment O 1 - Annex 1 - LSIRD 80KSC020R0036-RFP

3.1.1.4 SV Access Requirements

TROPICS SVs do not require access after integration to the launch vehicle.

3.1.2 Structural Loads

3.1.2.1 Stiffness (SV Frequency)

The TROPICS SV, dispenser, and isolation system will have a first natural frequency greater than 30 Hz.

The prima1y modes of the SV in the dispenser will be over 100 Hz, and thus not excited by low frequency sinusoidal vibration.

3.1.3 Mass Properties

3.1.3.1 Mass

Table 1 presents the mass prope1ties of the TROPICS SV, loaded into its CSD and mated to its isolation system. Center of mass values are given in the CSD Coordinate System. Moment of inertia values are given about the center of mass and aligned with the CSD Coordinate System.

Table 1: Mass Properties of Integrated TROPICS SV, CSD. and Isolation System

Description Axis<1 > Mass property Uncertainty

Mass (kg) - 9.14 kg +/-0.2 kg

X 0mm +/-10 mm Center of y 70.3 mm +/-10 mm Gravity (mm)

190.4 mm +/-20 mm lxx 0.140 kgm2 +/-30% Moments of lyy 0.134 kgm2 +/-30% Inertia (kgm2) lzz 0.035 kgm2 +/- 30%

Table 2: Mass Properties of TROPICS SV

Description Axis<1 > Mass property Uncertainty

Mass (kg) - 5.34 kg +/- 0.1 kg

X 0mm +/- 10 mm Center of y 81.6 mm +/- 10 mm Gravity (mm)<1

182.7 mm +/- 20 mm lxx 0.056 kgm2 +/- 30% Moments of lyy 0.055 kgm2 +/- 30% Inertia (kgm2)<2> lzz 0.010 kgm2 +/- 30%

Notes: (1) Center of Gravity is in CSD coordinate system

(2) Moments of Inertia is in CSD coordinate system, about SV Center of Gravity

3.2 ELECTRICAL INTERFACES

3.2.1 Airborne Interfaces

3.2.1.1 Electrical Connectors

a) The L VC shall provide a cable utilizing a DB9 connector for each CSD to be used for deployment and L V separation sense.

b) The LVC shall provide a grounding strap for each CSD.

c) The L V shall provide primaiy and redundant discrete commands to initiate door opening, shown below in Table 3 and Figure 9. Figure 10 and 11 provide additional infonnation on the electrical interface and initiation profile.

Table 3: Electrical Connector Requirements

Symbol Parameter Conditions Units Min Max

Voltage Provided Power to pins 1 & 2, Vdc 22 34 V from Launch Vehicle return from pins 3 & to Open Door 4

Winding Resistance -45 to +90 degree C , ohm 7.4 13 Rm of Door Initiator ( 3) includes internal

CSD wiring

Lrn Inductance of Door At terminals mH .452 Initiator

IP

Peak Current Draw <0.005 sec A 1.7 4.9 from Door Initiator ( 4)

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

3.3.4.1 Acoustics

Acoustical environments are bound by random vibration for the spacecraft.

3.3.4.2 Vibration

3.3.4.2.1 Random Vibration

The LVC shall meet the random vibration environment at the LV side of the TROPICS isolators, as defined in Table 6 and provide the P95/50 maximum predicted environment for the proposed L V configuration.

Table 6: Random Vibration Environment

Frequency (Hz) PSD (g2/Hz)

20 0.013

20-50 +6 d.B/oct

50-800 0.08

800-2000 -6 d.B/oct

2000 0.013 gRMS 10.0

Duration 1 min/axis

3.3.4.3 Shock

The L V shall comply with maximum expected shock levels induced by any L V event as shown in Table 7 and Figure 12 at the LV side of the TROPICS isolators.

Table 7: LV Shock Environment

Shock Environment Values at Pavload Interface

Hz SRS (a-oeakl

100 50

1000 1000

5000 3000

10000 3000

Shock Environment at Payload Interface fl) fl)

10000

Frequency (Hz)

....,_Suggested Design Envelope

Figure 12: Shock Environment

3.3.5 Electromagnetic Compatibility

3.3.5.1 EMI Safety Margin

t....---i----

10000

a) Electromagnetic Interference (EMI) emissions and susceptibility of the SV and the L V shall be individually controlled to ensure Electrnmagnetic Compatibility (EMC) of the integrated SV /L V system.

b) The EMC for the TROPICS and LV systems shall be a minimum of 20 dB EMI Safety Margin (EMISM) versus a de no-fire threshold for ordnance circuits and a minimum of 6 dB EMISM for non-ordnance circuits that are deemed safety or mission critical.

3.3.5.2 TROPICS RF Susceptibility

TROPICS SV will demonstrnte system level compatibility compliance in accordance to the Radiated Susceptibility levels shown in Table 8.

a) The L VC shall request the masking or attenuation of the Range-controlled RF sources to the susceptibility levels identified in Table 8 during encapsulated SV transpo1i, encapsulated SV at the launch complex, and during ascent to maintain EMISM identified in paragraph 3.3.5.1 b.

TROPICS Attachment O 1 Annex 1 LSIRD 80KSC020R0036-RFP

Table 8: SV Radiated Susceptibility

E-Field Limit (V/m) Notes Frequency Range

Including 6dB of Margin

10 kHz 18 GHz 20 V/m Range Somces

b) The LVC shall not exceed the Spacecraft damage levels as defined in Table 9.

Table 9: TROPICS Damage Levels

Frequency Range TROPICS Component Damage Level

2.025 - 2.11 GHz S Band Radio Damage level: -20 dBm Antenna Factor: ~3 dB

1.2276 GHz(+/- 40 MHz) GPS Receiver

Damage level: 0 dBm Antenna Factor: -3 dB

1.57542 GHz(+/- 40 MHz) GPS Receiver

Damage level: 0 dBm Antenna Factor: -3 dB

3.3.5.3 SV Radiated Emissions

TROPICS SVs will be powered off from installation through deployment.

The SV system level test will include radiated emissions testing in accordance to MIL-STD- 461 G (RE-102) and L V susceptibilities lower than those limits.

a) L VC shall identify and coordinate with the SC the testing of any frequency band below MIL-STD-461 G (RE-102) to protect the L V RF receivers or any other susceptible L V electrical component.

3.4 MISSION DESIGN

3.4.1 Orbit Insertion Requirements

a) The LVC shall place six TROPICS SVs with mass prope1ties as defined in Table 2 in a constellation fonnation as described in the Table 10 below.

b) The LVC shall place all of the SVs into their operational orbit within 120 days (first inse1tion to final insertion). Each parameter is defined at separation in Trne-of-Date coordinates. Altitudes assume a spherical Eaith with a 6378.137 km radius.

Table 10: Target Orbital Parameters at Payload Separation

Plane 1 Plane 2 Plane 3

Number of SVs 2 2 2

Target Apogee (3cr) 550 (+/-50) km 550 (+/-50) km 550 (+/-50) km

Target Perigee (3cr) 550 (+/ 50) km 550 (+/ 50) km 550 (+/ 50) km

Target Inclination (3cr) 30 (+/-3) deg 30 (+/-3) deg 30 (+/-3) deg

Target RAAN (3cr) N1 (+/-1) deg N+120 (+/-10) deg N+240 (+/-10) deg

Note 1: Any initial RAAN may be selected, with a required vehicle performance accuracy of +/-1 degree.

3.4.2 Thermal Roll

NIA

3.4.3 Sun Angle Constraints

NIA

3.4.4 LV Ascent Duration Requirement

NIA

3.4.5 Launch Period/Windows

TROPICS SVs can launch any day of the year.

3.4.6 SIC Events from T-0 through several minutes after separation

The TROPICS SVs perfo1m post-launch mechanical deployments (commanded, passive, or othe1wise) immediately after spacecraft separation from the dispenser.

The TROPICS SV begin attitude adjustments after separation.

The TROPICS SV will not perfonn any propulsive orbit adjustments.

The TROPICS SV will not transmit less than 30 minutes after deployment.

3.4. 7 Separation Requirements

a) The LVC shall deploy each pair of TROPICS SVs in opposite directions, one along the velocity vector (+V) and the other along the anti-velocity vector (-V).

b) The L V upper stage pointing accuracy just prior to each SV separation command shall be ± 10 degrees.

c) The L V upper stage body rates just prior to separation command shall be ± 1. 5 degrees/sec in each axis.

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 no later than 60 minutes after each separation event.

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