before_revision: Marlet 3B The Martlet 3B was similar to the Martlet 3A but using steel casings and attempting to solve some of the 3A model's other problems. The casings survived , but the propellant failed at . This was solved for later rockets by filling the propellant cavity with liquid, but only after development of the 3B model had ended. Martlet 3E The Martlet 3E was a suborbital solid rocket designed to be fired from a smaller, 7-inch (180mm) cannon used in the HARP project. Its basic concept revolved around packaging the rocket grain in a case with elastic properties to transmit the lateral strain to the gun tube. The 3E model utilized a new technique of rocket grain construction  that consisted of laminating sheet double-base propellant grain under hydraulic pressure. Martlet 4 By July 1964, the Marlet 4 program pursued the development of an orbit capable multi-stage rocket system to be launched from the 16" Barbados gun. Two versions of full-scale orbital launch vehicle projectiles were proposed in the Martlet 4 series. The first was to have used three solid rocket motor stages and was planned to orbit approximately 50 pounds of payload. The second used liquid rocket motors and was planned to have orbited 200 pounds of payload. Both were about long and in diameter, weighing about at launch. However, no Martlet 4 vehicles were built; the project was halted before the design was completed. Martlet 4 Control Systems A guidance and control system was developed for the orbital mission by Aviation Electric Limited of Montreal under the direction of McGill-BRL-Harry Diamond Laboratory group. Infrared horizon sensors and sun sensors were included to calculate vehicle attitude. Information for on-board sensors was to be processed by the logic module  which provided commands to a cold gas thruster system which in turn adjusted the orientation of the vehicle . The components of the guidance and control assembly were integrated into a 6.25 inch diameter test projectile. Sun sensors, horizon sensors, telemetry packs, receiving/transmitting antenna, hydraulic systems, logic modules, and gas thruster attitude control systems were all test fired to approximately 10,000 g's.
after_revision: Marlet 3B The Martlet 3B was similar to the Martlet 3A but using steel casings and attempting to solve some of the 3A model's other problems. The casings survived , but the propellant failed at . This was solved for later rockets by filling the propellant cavity with liquid, but only after developing the 3B model had ended. Martlet 3E The Martlet 3E was a solid suborbital rocket designed to be fired from a smaller, 7-inch (180mm) cannon used in the HARP project. Its basic concept revolved around packaging the rocket grain in a case with elastic properties to transmit the lateral strain to the gun tube. The 3E model utilized a new rocket grain construction technique that consisted of laminating sheet double-base propellant grain under hydraulic pressure. Martlet 4 By July 1964, the Marlet 4 program pursued developing an orbit capable multi-stage rocket system to be launched from the 16" Barbados gun. Two versions of full-scale orbital launch vehicle projectiles were proposed in the Martlet 4 series. The first was to have used three solid rocket motor stages and was planned to orbit approximately 50 pounds of payload. The second used liquid rocket motors and was planned to have orbited 200 pounds of payload. Both were about long and in diameter, weighing about at launch. However, no Martlet 4 vehicles were built; the project was halted before the design was completed. Martlet 4 Control Systems A guidance and control system were developed for the orbital mission by Aviation Electric Limited of Montreal under the direction of McGill-BRL-Harry Diamond Laboratory group. Infrared horizon sensors and sun sensors were included in calculating vehicle attitude. Information for on-board sensors was to be processed by the logic module , which provided commands to a cold gas thruster system which in turn adjusted the vehicle's orientation . The components of the guidance and control assembly were integrated into a 6.25 -inch diameter test projectile. Sun sensors, horizon sensors, telemetry packs, receiving/transmitting antenna, hydraulic systems, logic modules, and gas thruster attitude control systems were all test-fired to approximately 10,000 g's.
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