I have a RW AGM-58 where the aft end of the rocket weighs 8 lbs dry and the payload section forward weighs 4 lbs. I am concerned about drag separation after motor burnout, so I put 3 x 2-56 shear pins into the aft airframe/coupler connection point.
I am going to fly this with motor eject and chute releases, so I am not using electronics to control separation at this point. I am going to use motor eject. Because of the shear pins, I need to test ejection to make sure the ejection charge will shear the pins and separate the rocket properly. That is where I am not sure what to do. Testing ejection charges using canisters on an avionics bay is no problem. I am just not sure how to test motor eject.
Here is an idea I had, but I wanted to see what others that have done it before think.
My idea is to thread an igniter through the hole in the motor's forward closure, secure it in place, then fill the cavity with the calculated amount of BP, and seal it as if it were for a flight. Would lighting the igniter to ignite the BP simulate motor eject properly?
Thanks for any and all advice,
Steve
I am going to fly this with motor eject and chute releases, so I am not using electronics to control separation at this point. I am going to use motor eject. Because of the shear pins, I need to test ejection to make sure the ejection charge will shear the pins and separate the rocket properly. That is where I am not sure what to do. Testing ejection charges using canisters on an avionics bay is no problem. I am just not sure how to test motor eject.
Here is an idea I had, but I wanted to see what others that have done it before think.
My idea is to thread an igniter through the hole in the motor's forward closure, secure it in place, then fill the cavity with the calculated amount of BP, and seal it as if it were for a flight. Would lighting the igniter to ignite the BP simulate motor eject properly?
Thanks for any and all advice,
Steve