CINEMA Mission Readiness Review 2011-11-181. 2 Project Overview Cubesat for Ions Neutrals Electrons...

CINEMAMission Readiness Review

2011-11-18 1

2011-11-18 2

Project Overview• Cubesat for Ions Neutrals

Electrons and MAgnetic fields

• CINEMA is based on ~8 minutes of data from the STEREO-STE commissioning in Nov. 2006 which unexpectedly saw Energetic Neutral Atoms from the Earth’s ring current– The most sensitive

measurement ever in this energy range, but it was completely by chance

FOV rotates at few RPMTo build up Local Time ENAimage Size of STEIN FOV

Integration

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Project Overview• Supra-Thermal Electrons Ions and

Neutrals (STEIN)– Electrons and ions from ~4keV-

200keV– Energetic Neutrals clearly identified

below ~30keV at max deflection voltage

– Uses 4kV of electrostatic deflection in front of a 32 pixel thin window Si detector

– Mechanical attenuator allows for expanded dynamic range

• MAGnetometer from Imperial College (MAGIC)– Magnetoresistive with ~10nT

resolution– On a 1m rigid boom, sensor is ~10

grams– Provides input to the ACS system and

makes science measurements at 8Hz

Edgepixels

• Current State vs. ELaNa Launch Initiative Objectiveso CINEMA’s scientific objectives have not changed since the

initial proposal to the ELaNa

• Identify any de-scope of mission objectiveso There has not been any de-scope of CINEMA’s scientific

objectives.

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Mission Objectives

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Organization Chart

Project ManagerT. Immel

Principal Investigator R. Lin

Project ScientistJ. Sample

Lead Mechanical Eng.D. Glaser

Systems EngineerJ. Kim

CS Student Group

EE Student Group

ACS System Lead Y.T. Mao

ME Student Group

STEIN Instrument LeadS. McBride

MAGIC Instrument Lead

P. Brown

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ScheduleNovember

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ScheduleDecember

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ScheduleJanuary

• Pre-P-POD Integration Operations– CINEMA will be delivered to Cal Poly with all functional

testing complete– No further testing will be conducted prior to integration upon

delivery

• Post-P-POD Integration– Battery is to be charged whenever possible

• Equipment:– USB A (Female) to USB B (Male) Cable– GSEOS Laptop

• Time Duration:– 14 Hours (to ensure full charge)

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CubeSat-to-P-POD Integration Plan

• 3.1.1 CubeSat Design:– “The CubeSats shall be self-contained, and provide their own power,

sequencing, and wiring.”

• 3.1.2 Pressure Vessels:– “The CubeSat shall not contain pressurized vessels.”

• 3.1.3 Propulsion Systems:– “The CubeSat shall not contain propulsion systems.”

• 3.1.4 Radioactive Material:– “The CubeSat shall not contain radioactive material.”

• 3.1.5 Explosive Devices:– “The CubeSat shall not contain explosive devices.”

o CINEMA satisfies these requirements as described in its PI Compliance Memo

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CubeSat-to-P-POD Interface Compliance

• 3.1.6 Range Safety– “CubeSats hazardous material shall conform to AFSPCMAN

91‐710, Range Safety User Requirements Manual Volume 3 – Launch Vehicles, Payloads, and Ground Support Systems Requirements”

o CINEMA has complied with all of APIC’s Safety Information requests.

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• 3.2.1 CubeSat Static Envelope Definitions– “The CubeSat shall have the physical dimensions according to

the appropriate figure in Section 6.”

o CINEMA has satisfied the CAC performed by Cal Poly on October 20, 2011.

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• 3.2.3 Reference Coordinates– “The CubeSat shall have reference coordinates according to

the appropriate figure in Section 6.”

o CINEMA has reference coordinates according to the appropriate figure in Section 6.

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-X

+Y -Z

+Y

+Y

-X

-X

-Z

CINEMA

• 3.2.3.2 P-POD Reference Coordinates– “The P-POD shall use the coordinate system as defined in

Figure 1. The origin of the P-POD coordinate system is centered on the back panel. Once fully integrated into the P-POD, the CubeSat and P-POD coordinate system are the same.”

o CINEMA will be rotated 180° around the Z-Axis such

that the Mag Boom will face the +Y side of the

P-POD as requested.

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• 3.2.5 CubeSat Mechanical Deployment– “Exterior CubeSat components shall not contact the interior

surface of the P-POD, in addition to the designated CubeSat rails, in any way that would cause resistance upon deployment.”

o CINEMA has satisfied the CAC performed by Cal Poly on October 20, 2011.

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• 3.2.5.1 CubeSat Deployables Constraint– “All CubeSat deployables shall be constrained by the CubeSat

and not use the P-POD to constrain deployables.”

o CINEMA has two deployables:1. A magnetometer boom

o Contrained in its stowed state by a TiNi Aerospace P5 Pinpuller

2. A pair of UHF antennaso Constrained in their stowed positions by a pair of spring-loaded

latches

o CINEMA has submitted all requested information to APIC.

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• 3.2.5.2 CubeSat Deployable Time Delay– “All deployables, such as booms, antennas, and solar panels,

shall not be deployed until 30 minutes after ejection from the P-POD.”

o Once CINEMA’s deployment switch is disengaged:o Flight Software initializes and checks battery state

o If CINEMA successfully ejected from the P-POD:o Solar panels have currento Battery charging and at 6.9V

o FSW then initializes a timer upon deployment to count down 30 minutes until deployment of peripherals

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• 3.2.6 CubeSat Rail Material– “The CubeSat rails and standoffs which contact the P-POD

interior surfaces shall be hard anodized aluminum. The P-POD rails are also hard anodized with Teflon impregnation to reduce friction.”

o The CINEMA chassis rails will be Hard Black Anodized .0005 inches thick, per MIL-A-8625, TYPE 3 CLASS 2.o CINEMA has submitted a LSP Materials List document to Cal

Poly

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• 3.2.8 CubeSat Venting– “The CubeSat shall be designed to accommodate ascent

venting per ventable volume/area <2000 inches in accordance with JPL D-26086, Revision D, Environmental Requirements Document (ERD).”

o The ratio of the vent area in the CINEMA chassis to the internal volume of the chassis is approximately 1:34, not taking into account the displaced volume of the components inside the chassis.o The actual venting ratio is estimated to be between 1:20 and

1:30.

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• 3.2.9 CubeSat Material Selection– “CubeSat Materials shall be selected in accordance with

NASA-Technical-STD-6016 (Section 4.2), Standard Materials and Processes Requirements for Spacecraft.”

o All of the materials used in the CINEMA CubeSat meet NASA requirements for spacecraft.o CINEMA has submitted a LSP Materials List document to Cal

Poly

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• 3.2.10 CubeSat Orbital Debris– “CubeSat mission design and hardware shall be in accordance

with NPR 8715.6A, NASA Procedural Requirements for Limiting Orbital Debris.”

o CINEMA has submitted an ODAR to Cal Poly.

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• 3.3.1 CubeSat Power State– “The CubeSat power system shall be at a power off state to prevent CubeSats from

activating any powered functions while integrated in the P-POD from the time of delivery to LV through on-orbit deployment. CubeSat powered functions include the variety of subsystems such as Command and Data Handling (C&DH), RF Communications, Attitude Determination and Control (ADC), deployable mechanism actuations. CubeSat power system includes all battery assemblies and solar cells.”

• 3.3.1.1 CubeSat Deployment Switch Function– “In the actuated state, the CubeSat deployment switch shall electrically disconnect

the power system from the powered functions.”

o Testing has been done on a development system where the flight power supply and battery were hooked up to a deployment and RBF switch

o With the deployment switch actuated, the main power rails on the satellite (3.3V, 5V) were inactive. Further testing on a flight-like setup of the avionics showed the same results.

o Documentation In Progress

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• 3.3.1.2 CubeSat Deployment Switch Location– “The CubeSat shall have, at a minimum, one deployment

switch on a rail standoff, per Figure 2.”

o CINEMA has a single deployment switch located on a rail standoff (Option B).

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• 3.3.1.3 CubeSat Deployment Switch Actuated State– “The deployment switch shall be in the actuated state at all

times while integrated in the P-POD. In the actuated state, the CubeSat deployment switch will be at or below the level of the standoff.”

o CINEMA’s deployment switch is in actuated when integrated into the P-POD, since it is at the level of the standoff.

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NOT ACTUATED ACTUATED

ACTUATED

Deployment Switch

Deployment Switch Plunger

• 3.3.1.4 CubeSat Deployment Switch Chatter– “If the CubeSat deployment switch toggles from the actuated

state and back, the transmission and deployable timers shall reset.”

o When deployment switch is actuated, the processor’s main counter resets to the beginning, where it initializes the timers to reset state.

o Test Procedure/Documentation In Progress

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• 3.3.4 CubeSat Battery Protection– “CubeSats shall incorporate battery circuit protection for

charging/discharging to avoid unbalanced cell conditions.”

o The Clyde Space EPS controls power from the Battery.o Includes discharging protection and overcurrent protection.

o We have performed testing on its discharging and overcurrent protection properties and confirmed that it will not result in unbalanced cell conditions.

o Documentation: CPD 7001 – EPS Testing Section 1.2, 2.3, 2.4.

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• 3.3.5 CubeSat Transmission Exclusions– “The CubeSat shall not generate or transmit any signal from

the time of integration into the PPOD through 45 minutes after on-orbit deployment from the P-POD. However, the CubeSat can be powered on following deployment from the P-POD.”

o Testing and Implementation in a development system of a software feature to delay any transmission until at least 45 minutes after deployment:o This software will be identical to the flight model


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• 3.3.6 CubeSat RF Inhibits– “The CubeSats shall be designed to meet at least one of the

following requirements to prohibit inadvertent RF transmission.”

o The CubeSat will not transmit signals until both of the following are satisfied:o Software detects that its solar panels are producing powero Software sees that 45 minutes have elapsed since deployment

o Sep. switch diagram showing inhibits and TX survey submitted


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• 3.4.3 CubeSat Structural Survivability– “CubeSats shall be structurally adequate to survive the

dynamic qualification and acceptance testing.”

o CINEMA passed a confidence vibe performed October 24 to 26, 2011o Complete information is available in the CPD 10002 –

Vibration Test #1/3 document.

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• 3.4.4 Random Vibration– “Each cubesat shall test, in each axis, the predicted random

vibration levels at the P-POD to NPSCuL mechanical interface. These levels and tolerances are defined in Section 8.”

o CINEMA is scheduled to undergo a random vibration test at the Naval Postgraduate School during the week of December 5-9, 2011o CINEMA will be inside P-POD #6 of the NPSCUL.

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P-POD #X Y Z

Actual Envelope Actual Envelope Actual Envelope

6 18.830 23.15 11.69 15.29 8.91 10.29

• 3.4.6 Thermal Vacuum Bakeout– “CubeSats shall perform a thermal vacuum bakeout at a high

vacuum level (minimum 1x10-4 Torr).”

o CINEMA is scheduled to undergo Thermal Vacuum bakeout at the UC Berkeley Space Sciences Laboratory during the week of January 12-16, 2012.

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• 3.4.6.1 Thermal Vacuum Bakeout Profile– “The CubeSat shall test to one of the two bakeout profiles

outlined in Table 3 and Figure 3, with a temperature ramp rate of no greater than 5°C per minute.”

o CINEMA will be tested to Profile 1.

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• Subsystem Status Reports– Mechanical (Complete):

• No Plans for Retrofitting– Electrical (In Progress):

• STEIN Rework and Testing– Software (In Progress):

• Functional Testing (Communications, ACS, Deployment)

• CubeSat to P-POD Integration Status– CAC Complete– Confidence Vibe Complete– Environment Tests for Flight Unit Scheduled– CINEMA has complied with all APIC information requests

concerning risk assessment

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CubeSat Flight Readiness

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CONOPS Plan

• Safe mode• All instruments unavailable.

• Science mode• All instruments (except boom and an-

tenna actuators and torque coils) available.

• ACS mode• STEIN instruments not available and

MAGIC operation mode is switched to ACS mode.

• Torque coils are available.• Engineering mode

• All instruments are available.• OBC, EPS, BATT, RX and Sun Sensors

are always turned on.

HSK STE TX STE MAG STE TX STE


STE TX STE MAG STE TX STE

CMD STE TX STE MAG STE TX STE





Operation Modes

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CONOPS Plan

• Launch – Launch and separation from the launch vehicle

• Startup– Power-on, initializes FSW, deploys UHF Antenna, waits for contact from

Ground Station

• Stabilization– Contacts Ground Station, deploys the boom, calibrates the MAGIC, ACS

acquisition mode, ACS precession mode

• Scientific Operation– Download mode, Observation mode, ACS mode, Safe mode, Fault recovery

• Mission Termination

Operation Scenario

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CONOPS Plan

• Separation from the launch vehicle– CINEMA is ejected from P-POD

• Acquisition of orbit parameters– Ground Station obtains orbit parameters of spacecraft from the

Launch Service Provider and estimates the position of the spacecraft.

1.0 Launch Process

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CONOPS Plan

• Power on– Spacecraft is powered on immediately after separation when

deployment switch disengages

• Initialization FSW– Spacecraft enters Initialization Process for each FSW module– Default Operation Mode is Safe Mode. – As shown in the Enable Table; all instruments turned off

except OBC, EPS, BATT, Sun Sensors & UHF Receiver. – Checks System Status (i.e. Charging Condition)

2.0 Startup Process

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CONOPS Plan

• Deploy UHF Antenna & MAG Boom– After Initialization, FSW checks the status of the Battery & Solar Array to

confirm separation from P-POD– If FSW decides that spacecraft is successfully separated, then the

countdown for the 30 min timer begins– Once 30 min on the timer has elapsed, deployables are deployed.– FSW enters into Engineering Mode and powers only the IIB with LVPS

and MAGIC on via ‘InstOn’ pin. • Calibrate MAGIC

– Using an Internal Rotation Matrix, MAGIC is calibrated for use in ACS mode.

2.0 Startup Process

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CONOPS Plan3.0 Stabilization Process

• ACS to Detumble– CINEMA is de-tumbled to maintain 4 RPM– This process is entered automatically or via Ground Station Command

• ACS to Precess to Sun-Normal– Maintain spin rate of 4 RPM– Precess to sun normal spinner– This process is entered automatically or via Ground Station Command

• Generate the Beacon Signal– Transmission of beacon signal is enabled 45 min after separation from P-POD– The beacon signal includes the recent housekeeping– Default period: 30 sec ON, 4 min 30 sec OFF

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CONOPS Plan3.0 Stabilization Process

• Contact the ground station– Once Ground Station receives beacon signal, beacon is turned off by

Ground Station command– FSW is in engineering mode. – Ground Station checks Housekeeping & send commands to enable ACS &

payloads

• Attitude Control to precess to ecliptic normal– With ACS ephemeris table from Ground Station, CINEMA precesses to an

Eliptical-Normal Orbit via FSW– Once Precession is finished, FSW enters into previous operating mode

automatically.

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CONOPS Plan4.0 Science Operations

• Safe Mode (Default mode)– Pending Ground Station Commands– All instruments are turned off except OBC, EPS, Sun Sensor & UHF

receiver– If Battery Status is at a low charge state, FSW enters into this mode

• Observation mode– FSW enters into Normal (Science) Mode, described by Enable Table– CINEMA observes ENA & Mag. fields via STEIN & MAGIC– Payloads are scheduled for observation by ‘Delayed Commands

(Timestamp + Command)’. – When Payloads are not used, the instruments for STEIN are turned OFF

& MAGIC enters into ACS mode for power-saving

• Download mode– Used to transmit telemetry from the SD card to Ground Station– During this process, Operation Mode is Download Mode

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CONOPS PlanContact Sequence Flow

• ACS Mode– Ground Station obtains Attitude Status from Housekeeping– Ground Station generates Ephemeris Table including

Magnetic Field data in orbit– FSW controls Attitude using Ephemeris Table to precess to

Ecliptic-Normal

• Fault Recovery– If any errors occur, then FSW enters into Safe Mode or the

Processor is reset by the WatchDogTimer– FSW conducts error detection and recovery– If the error cannot be resolved, CINEMA waits for Ground

Station commands in Safe Mode or the mission is terminated

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• Ground System Status– S-Band to Ground Station: Complete– UHF Ground Station: In Progress

• Parts acquired• Integration to UCB/SSL MOC: In Progress

• Flight Operations System: In Progress• NTIA Licensing:

– Spectrum Certification: Complete– Frequency Assignment: In Progress

• Spacecraft End-of-Life Plan: In Progress• Satellite Tracking & Communications Link: In Progress

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CONOPS Plan

CINEMA Mission Readiness Review 2011-11-181. 2 Project Overview Cubesat for Ions Neutrals Electrons...

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