Document Type
Paper
Abstract
The purpose of this project is to design test systems for a Spaceport America Cup capable rocket. Specifically, to design a test system for the recovery systems and test system for the motor. The rocket must be capable of reaching an apogee of 10,000 feet and recovered using a dual deployment recovery system.
The motor test will be used to determine if the actual thrust from the selected motor will be sufficient to launch a rocket carrying an 8.8 pound payload to an apogee of 10,000 feet. Using a load cell and designed static launch stand, the team will be able to determine the actual thrust of the motor and calculate a trajectory for the rocket.
The recovery system test will be designed to mimic the atmospheric pressure across the flight of the rocket. This will allow the altimeters and dual deployment systems to be tested at an accurate replication of flight. Testing in this manor will insure against failure during actual launch.
Letter of Intent
The purpose of this project is to design test systems for a Spaceport America Cup capable rocket. Specifically, to design a test system for the recovery systems and test system for the motor. The rocket must be capable of reaching an apogee of 10,000 feet and recovered using a dual deployment recovery system.
The motor test will be used to determine if the actual thrust from the selected motor will be sufficient to launch a rocket carrying an 8.8 pound payload to an apogee of 10,000 feet. Using a load cell and designed static launch stand, the team will be able to determine the actual thrust of the motor and calculate a trajectory for the rocket.
The recovery system test will be designed to mimic the atmospheric pressure across the flight of the rocket. This will allow the altimeters and dual deployment systems to be tested at an accurate replication of flight. Testing in this manor will insure against failure during actual launch.
