1 COMMAND AND DATA HANDLING (C&DH)
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1 1 COMMAND AND DATA HANDLING (C&DH) 1.1 Requirements and Design Drivers Functional The command and data handling shall provide the capability to: Transfer information in digital or discrete representation from its source or to its destination within each spacecraft (e.g. via data bus, point to point lines) Exchange information in digital or discrete representation with the environment of each spacecraft (i.e. with the electrical and ground support equipment, the launcher, the ground segment, with the other two spacecraft in the constellation for telemetry possibly received over the InterSpacecraft Links) Process information in digital representation so as to meet the mission objectives (e.g. provide processing resources that support the execution of computer programs) Retain information in digital representation for allocated periods of time so as to meet the mission objectives (e.g. store telemetry data during communication interruptions or context data in auxiliary (mass) memory) Maintain and disseminate timing information on board Performances The commands to the micropropulsion system generated by the drag free and attitude control system (DFACS) shall be routed to the micropropulsion system with a maximum additional time delay of 10 ms (TBC). One LISA spacecraft bus shall have reliability consistent with a probability of success (Ps) of 95.3 percent or greater at the end of the required mission System Configuration During the CDF study, it has been requested to suppress the payload control computer from the payload of each spacecraft. This constitutes a (new) requirement, which can be formulated as follows: There should be only one computer equipment unit per spacecraft Design Drivers For this mission, the main criteria for the command and data handling design are: (Mass), volume and electrical power constraints Environmental conditions (e.g. temperature, ionizing radiations, vibrations or shocks) Performance objectives (time criticality, dependability) Telemetry and telecommand data rates and schedule of communication with the ground segment Commonalities of the requirements applicable to command and data handling down to the configuration item level of the spacecraft bus.
2 1.2 Assumptions and TradeOffs Assumptions It is assumed that: Each spacecraft generates 11 kbps in real time, in nominal science mode The telecommunication schedule is nominally 8 hours every 48 hours through one master spacecraft, or 8 hours every 96 hours if the downlink on one spacecraft fails TradeOffs Mass, volume and power consumptions can be traded against recurrence of configuration items (product category according to heritage, e.g. from LISA Pathfinder) 1.3 Baseline Design Various designs for command and data handling are possible. Aside from functional and performance requirements, the selection of a particular arrangement of the command and data handling is influenced by a number of criteria related to the lifecycle of the spacecraft. Those criteria include delineation of engineering interfaces, configuration management, manufacturing, integration, assembly and test. The architecture for command and data handling is intended to be common for all spacecraft items in the constellation. Figure 11 shows a block diagram of a command and data handling design. The command and data handling design is based on the use of: An onboard computer unit (OBC) A (serial) data bus system Pointtopoint links. The EEE configuration items in the command and data handling (i.e. bus lines, components, boards, units) are duplicated.
3 Avionics internal to the spacecraft bus ( 1 ) Avionics internal to the payload ( 2 ) To/from: ground segment RF link Data bus On board computer On board time (internal time source) Auxiliary (Mass) Memory Processing resources (CPU, main memory) TC decoder TM formatter Data bus Optical link (ISL) To/from: other spacecraft To/from: launcher, ( 3 ) ground support equipment, other spacecraft I/O Bilevels Serial data links Pulse commands Serial data links Figure 11: Command and data handling design block diagram NOTES: ( 1 ) includes AOCS sensors, TT&C, thermal control, electrical power control, propulsion and micropropulsion ( 2 ) includes optical, laser, phase measurement, GRS, diagnostics ( 3 ) during prelaunch, launch, and separation 1.4 List of Equipment OnBoard Computer (OBC) The onboard computer is the main equipment unit in the command and data handling. It is a critical item for the mission. It includes a power supply unit, a central processing unit and main memory, auxiliary (mass) data storage, TM/TC and external inputs / outputs controllers. All those elements are functionally partitioned (into modules) and encompassed in one physical enclosure (i.e. one box). It is recommended that the OBC implements internal redundancy of EEE parts to optimize mass and volume quantities. The central processing unit and main memory are essential resources to execute computer programs. Those are protected against single event effects (e.g. SEU). The instruction set of the central processing unit (CPU) is that of a reduced instruction set computer including floating point instructions. The instruction set architecture is recommended to conform to SPARC specification (e.g. ERC32, LEON series) so that to benefit from the legacy of computer programs and tools (i.e. development environment, software).
4 The OBC equipment unit for the LISA path finder mission implements an ERC32SC (i.e. TSC695F) central processing unit running with a nominal frequency of 22.5 MHz, with zero wait state (i.e. CPU instruction rate ~ 14 MIPS). Depending on the detailed design of the onboard computer, the computer programs for the operation of the payload and spacecraft bus may be executed in concurrency (i.e. with shared resources) or in parallel (i.e. with dedicated resources). If an instruction rate of 14 MIPS is not sufficient (for concurrent computing) then using a LEON2FT running at 80 MHz (~ 100 MIPS) is an option. The auxiliary (mass) data storage enables to store context data (e.g. system log upon anomaly detection stored into safeguard memory) as well a TM/TC data between contacts with the ground (stored into mass memory unit). The auxiliary data storage is based on solid state memory. The capacity of the auxiliary (mass) storage is driven by two main factors: the net data rate that needs to be stored, and the telecommunication schedule, which determines the frequency at which data will be downloaded to ground. From the assessment made in the spacecraft preliminary design description document, it is concluded that a storage capacity of 16Gbit (for each spacecraft) is sufficient to meet the mission requirements. This figure includes a margin that allows for growth in data rate, or, alternatively, provides significant flexibility in terms of communications schedule. The inputs/outputs controllers are devoted to acquisition and command distribution (either through data bus system or point to point lines) (e.g. for propulsion, AOCS, detection of separation). A section in the onboard computer supports acquisition (res. distribution) of high level telemetry (res. high level telecommands) without software intervention (e.g. using a pulse command distribution unit). Technical risk and costs can be reduced by using an equipment unit that is already qualified for use in conservative space environment conditions Data Bus System The data bus system provides the capability to transfer command and data within bounded time constraints using one physical media, reducing the total cable mass w.r.t. point to point lines. To ensure compatibility between equipment from various vendors and the OBC it is recommended that the data bus system conforms to a standard technology suitable for space application (e.g. MILSTD1553B or CAN). Technical risk and costs can be reduced by using the same data bus technology as in LISA path finder (i.e. MILSTD1553B) Point To Point Links The point to point links are used to support communication between two end points over a dedicated line (e.g. bilevel signals, pulse commands, high rate data flows). The data flows between the spacecraft bus and the payload include thrusters actuation It is recommended that the serial data links conform to a standard technology suitable for space application (e.g. ECSSEST5014 for discrete interfaces, SpaceWire for high data rate)
5 1.5 Budgets The budget in mass, power and dimensions for command and data handling is given in the data handling model document. This budget takes into account redundancy of EEE parts. Element 1 MASS [kg] Name Quantity Mass per Maturity Level quantity excl. margin 1 Onboard computer To be modified Click on button below to insert new unit Margin Total Mass incl. margin Element 2 Name MASS [kg] Quantity Mass per quantity excl. margin Maturity Level Total Mass incl. margin 1 Onboard computer To be modified Click on button below to insert new unit Table 11: Mass Budget Margin Element 1 DIMENSIONS [m] Name Quantity Shape Dim1 Dim2 Dim3 Length Width Height or D 1 Onboard computer Click on button below to insert new unit 1 Element 2 Name DIMENSIONS [m] Quantity Shape Dim1 Length Dim2 Width or D Dim3 Height 1 Onboard computer Click on button below to insert new unit 1 Table 12: Equipment dimensions Element 1 Name Quantity Ppeak 1 Onboard computer Click on button below to insert new unit
6 Element 2 Name Quantity Ppeak 1 Onboard computer Click on button below to insert new unit List of Acronyms Table 13: Power budget Acronym C&DH EEE I/O MIPS OBC SEU SPARC TC TM Definition Command and Data Handling Electronic, Electrical and Electromechanical Input/Output Million Instructions per Second Onboard computer Single Event Upset Scalable Processor Architecture Telecommand Telemetry 1.7 List of References None
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