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SERVIS : Space Environment Reliability Verification Integrated System

Outline

1. INTRODUCTION

The Space Environment Reliability Verification Integrated System (SERVIS) is being developed by the Japan Space Systems (former the Institute for Unmanned Space Experiment Free Flyer (USEF)) under the Ministry of Economy, Trade and Industry (METI). The purpose of the project is to establish a parts database, a parts evaluation guideline and an equipment design guideline to utilize commercial-off-the-shelf parts and technologies (COTS) under the space environment so that they can be utilized for space applications. The SERVIS project was started in 1999 and has been continuing. The first verification satellite (SERVIS-1) was already launched in October, 2003 and its two year on-orbit operation was successfully completed. The second verification satellite (SERVIS-2) was launched in June, 2010 and also completed its mission successfully in June, 2011. Then the SERVIS-3 was started in 2012.

This project has been established in order to strengthen technical and cost competitiveness of the Japanese space industry in the world market. In realizing this, the following considerations are taken into account.

Cost reduction of satellites and their equipment is an urgent issue. In order to realize this, introduction of COTS is necessary.
For realistic COTS application, low earth orbit (LEO) has been selected due to its reasonable radiation environment. And the orbit altitude for the verification satellites is selected about 1000 km.
In order to reduce total cost, programmatic cost reduction in addition to hardware cost is also important.
By achieving the above, it is expected to increase technical and cost competitiveness for LEO satellite buses and their equipment.

 

The entire project activity is comprised of four segments. They are;
Ground evaluation tests for various COTS, including radiation tolerance test,
Development and space verification of advanced experimental equipment with COTS,
Development of space verification satellites,
Development of design infrastructure called “Virtual Integration”.

2. Summary of SERVIS Satellites

The flown SERVIS satellite system summary is shown in Table 1. As payload, experimental equipment shown in Table 2 and 3 were onboard. Commercial Parts Test Unit (CPT) is also onboard in order to evaluate COTS parts performance precisely under on-orbit condition as shown in Table 4.

Table 1 System Summary of Two Verification Satellites

Item

SERVIS-1

SERVIS-2

Launch Date

Oct. 30, 2003

June 2, 2010

Launch Vehicle

ROCKOT

ROCKOT

Operational
Orbit

1000 km

1200 km

i= 99.5 deg.
SSO

i= 100.4 deg.
SSO

Mission
Duration

2 years

1 year

Satellite Mass

840 kg

740 kg

Dimensions

2.5 m(H) x 10.2 m(L)

Generated Power

More than 1300 W

Satellite Control

Centralized Control
by Integrated Satellite Controller

Attitude Control

3-axis Stabilization

Power Supply

50 V Floating Bus System

Data Handling

CCSDS Recommended Space
Packet Protocol

Communications

Telemetry:
USB(2 kbps), HSB(256 kbps)
Command: 4 kbps

Propulsion

Mono Propellant Hydrazine System,
Thruster: 1N

Satellite
Operation

USEF Space Operations Center
(USOC)

Ground Stations

JAXA Ground Network Stations

Resources for
Payload

Mass: >300 kg, Power: >500 W,
Date Rate: >2400 bps

 

Table 2 Experimental Equipment onboard of SERVIS-1

Equipment

Acronym

Vane-type Propellant Tank System

VTS

Integrated Navigation Unit

INU

Power Control & Distribution Unit

PCDS

Advanced Paddle Drive Mechanism

APDM

Advanced TT & C Transponder

ATTC

On Board Computer

OBC

Integrated Satellite Controller with Star Sensor

SIS

Lithium Ion (Co type) Battery System

LIB

Fiber Optic Gyro Inertial Reference Unit

FOIRU

 

Table 3 Experimental Equipment onboard of SERVIS-2

Equipment

Acronym

Lithium Ion (Mn type) Battery System
with Automotive Technology

LIBA

High Assurance Data Management System

ADMS

Fault Tolerant Computer with CRAFT System

CRAFT

Plug-and-Play Remote Terminal Unit

PPRTU

High Performance Data Compressor

HPDC

Advanced Positioning Experimental Module

APE

Advanced Satellite Structure Experimental Module

ASM

Magnetic Bearing Wheel

MBW

RF-MEMS Experiment Unit

MEMS

 

Table 4 COTS evaluated by Commercial Parts Test Unit (CPT)

SERVIS-1

SERVIS-2

SRAM

1Mbit, 4Mbit

4Mbit, 8Mbit

DRAM

128Mbit, 256Mbit

256Mbit, 512Mbit

SOI SRAM

256kbit, 0.35 µm rule

128kbit, 0.18 µm rule

Flash Memory

NOR type 32Mbit

NOR type 128Mbit

FPGA

SRAM type, EEPROM type

SRAM type, EEPROM type

3. SERVIS-1 Space Verification Results

SERVIS-1, which was an 840kg box type satellite with COTS payloads, was launched on October 30, 2003 aboard ROCKOT from Plesetsk Cosmodrome in Russia. SERVIS-1 was operated exactly for two years after the launch. During that period, all experimental payloads had been operated normally and all of them well cleared “extra success level” criteria of the verification test which was established prior to the launch.
Table 5 shows the frequency of single event upsets (SEU) observed for COTS components on orbit, in comparison with predicted frequency as a result of ground radiation tolerance test. As shown in the table, actual frequency of SEUs observed on orbit was less than predicted frequency using ground test results. The table also indicates that better match between ground test and orbit result was observed for proton than for heavy ion, thus proving the concept that proton has the dominant effect for SEU for low earth orbit.
Figure 1 shows examples of the proton and electron data measured by the Energetic Light Particle Spectrometer, which are plotted on a world map.

Table 5 Frequencies of Single Event Upsets (SEU) on COTS in SERVIS-1 Experimental Equipment and CPT

Equipment

Parts Type

SEU(times)

Predicted values
from heavy ion
irradiation test

Measured values
on orbit

OBC

32bit CPU

4.2 / day

0.16 / day

64M SDRAM

18 /day

0.005 / day

4M SRAM

18 /day

3.7 / day

SIS

32bit CPU

0.23 / day

0.08 / day

1M EEPROM

0 / day

0 / day

256M SDRAM

4.5 / day

0.3/ day

ATTC

16bit DAC

0.8 / day

0.06 / day

16bit ADC

1.0 / day

0.12 / day

PCDS

16bit CPU

2.3* / year

1.5 / year

CPT

1M SRAM

1.0 or 2.1* / day

0.79 / day

4M SRAM

3.4 or 6.6* / day

2.0 / day

128M SDRAM

2.6 or 0.2* / day

0.17 / day

256M SDRAM

3.6 or 0.5* / day

0.3 / day

*:Predicted values from proton irradiation ground test results

 

 

Figure 1 Proton and Electron data measured by SERVIS-1 Energetic Light Particle Spectrometer

4. TECHNICAL KNOWLEDGE BASES

4.1 Basic Concept

Technical knowledge bases are the ultimate product of SERVIS project. They are a group of documents to indicate the way to use COTS parts for space application through extensive ground evaluation test and orbit verification test. Those documents have been assembled and updated after the SERVIS-2 on-orbit verification test. They have been revised and maintained by incorporating the latest COTS.

4.2 COTS Database

The Commercial Off-the-Shelf parts and technologies database (COTS Database) contains the result of ground evaluation tests especially that of radiation tolerance test.
By this database, one can learn to what extent a certain COTS part can withstand to the space environment, thus to give the criteria in using that particular COTS for space application.
Considering the criticality of COTS information to be used for space application, the database has two-tier structure. Namely, the first tier contains limited information open to the public, while the second tier has more detailed and specific information.
The first tier database contains following information.
1) COTS ID number (assigned by USEF or Japan Space Systems)
2) General specification
3) Summary of radiation test
4) Summary of quality conformance test
Click here for the first database
Second tier and detailed database is restricted to the relevant personnel or organization only and contains following information.

1) Parts number
2) Name of manufacturer
3) Specification
4) Screening test condition and its result
5) Radiation test condition and its result
6) Quality conformance test and its result

In case potential users are interested in certain COTS parts by reviewing the first tier database, they can contact Japan Space Systems for more detailed information and would be able to contact with the parts manufacturer for detailed discussion.

4.3 COTS Evaluation Guideline

This guideline specifies test and evaluation method and criteria for COTS parts in order to apply them for space purposes. It contains following items.
– Characterization of COTS parts v.s. conventional hi-rel parts in general, and issues and necessary considerations of COTS usage for space application
– Description of ground tolerance test methods and criteria for space application
– Estimation method of accurate radiation environment at actual COTS location in the satellite equipment

4.4 Equipment Design Guideline

This guideline indicates various considerations which are required for engineers in order to use COTS parts and technologies for space equipment. It is intended that by following this guideline, space equipment with COTS would have sufficient quality and reliability performances for space use.
The guideline consists of two parts. Part I elaborates design criteria and necessary considerations to be followed. It is intended that it will serve as a design handbook which design engineers always keep on their desks for daily work. Part II explains example of experimental equipment aboard SERVIS satellites from the standpoint how COTS parts and technologies were applied in those equipment. It is intended to promote the understanding of COTS application for space use.

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