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experience and resources to successfully complete demonstration of the spacecraft in a flight environment will be required. the proposed system is to be demonstrated in flight at altitudes typical of iss and space vehicles. it is expected that ground testing will establish a strong knowledge base for the integration of the analysis/ablation tools with the spacecraft simulator. the implementation of this capability will use a computer aided design (cad) system as well as data from the spaceflight vehicles on orbit. in-flight demonstration requires that the aircraft be modified or build for certification by an engineering group experienced in unmanned aircraft. the group will include aerospace designers, professional engineers, and flight instrumentation experts. the aircraft will be primarily composed of a fuselage and tail wing assemblies. the system will use an advanced software package in order to communicate with the capsule systems. the software is capable of interfacing with ground based sensors and the space vehicles in orbit. the hardware will consist of a flight control unit interface computer and the following flight critical sensors: (1) a flight data recorder, (2) a multimodal data capture system, (3) a spectrum analyzer, (4) a chemical vapor detector, (5) an electroglobal scope for anomaly detection, (6) a stroboscope, and (7) a flight simulator or other simulation systems with appropriate external environmental conditions.
the system must be capable of demonstrating a flight scenario to identify and quantify the stability, effects of harsh environments, maneuverability and retention of stability and function over time. additional test requirements include: (1) long endurance, (2) high altitude or trans-atmospheric flight, (3) configuration changes, (4) thermal protection, (5) stowage capability, (6) terrain avoidance, (7) impact protection, and (8) safety and reliability.
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