Requirements Capture Example in VS .NET

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11.4.3 Requirements Capture Example
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The example given in Figure 11.5 shows a functional mapping process which identi es the elements or threads necessary to implement a fuel jettison function. Two main functional subsystems are involved: the fuel quantity measurement function and the fuel management function. Note that this technique
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Fuel Jettison Valves (2) 'Open' Fuel Dump Valves (2) 'Open'
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Fuel Jettison Select Min Fuel Quantity Set Isolation Valves (2) Select Isolation Valves (2) 'Open' Fuel Management Function
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Power C Power D Fuel Quantity Left Tank Probes (20) Centre Tank Probes (12) Right Tank Probes (20)
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Fuel Quantity Function
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Fuel Dump Valves (2) 'Open' Fuel Dump Valves (2) Select Power A
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Fuel Transfer Valves (4) Select Fuel Transfer Valves (4) 'Open/Closed'
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Power B
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merely identi es the data threads which are necessary to perform the system function. No attempt is made at this stage to ascribe particular functions to particular hardware or software entities. Neither is any attempt made to determine whether signals are hard-wired or whether they may be transmitted as multiplexed data as part of an aircraft system data bus network. The system requirements from the ight crew perspective are: The ight crew need to jettison excess fuel in an emergency situation in order that the aircraft may land under the maximum landing weight The ight crew wish to be able to jettison down to a preselected fuel quantity The crew wish to be given indications that fuel jettison is underway The information threads associated with the ight crew requirements are shown in the upper centre portion of the diagram. It may be seen that although the system requirements are relatively simple when stated from the ight crew viewpoint, many other subsystem information strands have to be considered to achieve a cogent system design: Fuel Quantity Function The fuel quantity function measures the aircraft fuel quantity by sensing fuel in the aircraft fuel tanks; in this example a total of 52 probes are required to measure the fuel held in three tanks. The fuel quantity calculations measure the amount of fuel which the aircraft has onboard taking account of fuel density and temperature. It is usual in this system, as in many others, to have dual power supply inputs to the fuel quantity function to assure availability
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in the event of an aircraft electrical system busbar failure. Finally, when the calculations have been completed they are passed to the ight deck where the aircraft fuel quantity is available for display to the ight crew. Fuel quantity is also relayed to the fuel management function so that in the event of fuel jettison, the amount of fuel onboard may be compared with the preset jettison value. The fuel quantity function interfaces to: The The The The fuel quantity system measurement probes and sensors ight deck multi-function displays fuel management system aircraft electrical system
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Fuel Management Function The fuel management function accepts information regarding the aircraft fuel state from the fuel quantity function. The ight crew inputs a Fuel Jettison Select command and the minimum fuel quantity which the crew wishes to have available at the end of fuel jettison. The fuel management function accepts ight crew commands for the fuel transfer valves [4], fuel dump (jettison) valves [2], and fuel isolation valves [2]. It also provides Open / Closed status information on the fuel system valves to the ight crew. As before two separate power inputs are received from the aircraft electrical system. The fuel management function interfaces with: The The The The fuel system valves ight deck displays multi-function displays and overhead panel fuel quantity function aircraft electrical system
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This example shows how a relatively simple function interfaces to various aircraft systems and underlines some of the dif culties which exist in correctly capturing system requirements in a modern integrated aircraft system.
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11.5 Fault Tree Analysis (FTA)
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The Fault Tree Analysis (FTA) is one of the tools described in SAE document ARP 4761 [1]. This analysis technique uses probability to assess whether a particular system con guration or architecture will meet the mandated requirements. For example, assume that the total loss of aircraft electrical power onboard an aircraft has catastrophic failure consequences as identi ed by the Functional Hazard Analysis see Figure 11.2 and Table 11.1 above. Then the safety objective quantitative requirement established by FAR/JAR25.1309 and as ampli ed in ARP 4754 will be such that this event cannot occur with a probability of greater than 1 10 9 per ight hour (or once per 1000 million ight hours). The ability of a system design to meet these requirements is established by a FTA which uses the following probability techniques.
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Fault Tree Analysis (FTA)
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In the example it is assumed: That the aircraft has two independent electrical power generation systems, the main components of which are the generator and the Generator Control Unit (GCU) which governs voltage regulation and system protection The aircraft has an independent emergency system such as a Ram Air Turbine (RAT) That the failure rates of these components may be established and agreed due to the availability of in-service component reliability data or sound engineering rationale which will provide a gure acceptable to the certi cation authorities The FTA analysis very much simpli ed for this example is shown in Figure 11.6.
Target Figure > 1 10 9 Analysis shows: Probability of Total Loss 10 = 4.9 10 which = 0.49 10 9 which meets target Probability of Total Power Loss
4.9 10 10
4.9 10 7