9/21/2023 0 Comments Canopy jettison![]() ![]() In a hermetically sealed rocket case, such as the MK 109 Canopy Jettison Rocket System that is capable of surviving and operating as designed while installed Produce prototype plans to be developed under Phase II. Evaluation criteria are listed in the Description above. Perform an analysis of alternatives and demonstrate feasibility of Propellant grain and transmit the sensor data through a hermetically sealed Improve warfighter safety and reduce total ownership costs for energeticĭemonstrate potential alternatives for a sensor system to detect cracking in a TheĬapability of detecting propellant grain cracks in-situ and in real time will Surviving environmental exposures, documented in MIL-P-83126. System reliability, (4) 10-year ordnance service life, and (5) capability of ![]() Sealed rocket case (such as the MK 109 Canopy Jettison Rocket Motor), (3) Evaluation criteria will be: (1) crackĭetection capability, (2) data transmission capability through a hermetically The proposer must prototype andĭemonstrate the solution, before and after environmental conditioning, asĭescribed in MIL-P-83126. Possible with a maximum weight of 6 ounces. The total weight of the sensor system must be as light as Size of the sensor system should be kept to a minimum size but must not exceedĢ”x 3”x 0.08” thick. Grain and to assure system reliability (90% reliability at 90% confidence). Sensors may be required to ensure crack detection throughout the propellant Once a day and wirelessly downloaded every three months. Sensor system should record the installation date of the unit, temperature, andĭata dependent of method used for crack detection. Present as soon as they are detected, providing an alert (visual and/orĪuditory) to maintenance personnel, and maintaining data collected for downloadīy engineering staff at the completion of a 10-year ordnance service life. Seeks a sensor system capable of detecting the presence of cracks greater thanĢmm anywhere within the propellant grain, providing an indication if cracks are Transmit information through a hermetically sealed rocket motor case. Too large to fit within the available device’s envelope) and inability to The limitations of the previous designs included size (the design was There were limitations in capability, which prevented transition to fleet TheĪbility to detect a propellant grain crack was demonstrated in the past, but Provide wireless through-case data transmission, in situ rocket motor healthĪssessment, and appropriate miniaturization for CAD/PAD applications. The required work will employ innovative technologies to Of the propellant, causing an increase in the gas production that may result in Initiated, the cracks would result in an increase of the burning surface area (CADs) can develop cracks while installed onboard an aircraft. Used in Propellant Actuated Devices (PADs) and Cartridge Actuated Devices Through a hermetically sealed rocket motor case. TITLE: Propellant Grain Cracks Detection SystemĬapable of detecting cracks in a propellant grain and transmitting that data ![]()
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