Project Description

High Power, Amateur Rocketry

When Project LARSS started, we needed to come up with a concept for our senior design project. As most of the team are members of the Saint Louis University Rocket Propulsion Lab (SLURPL), we knew from the beginning that we wanted our senior design project to benefit the club. SLURPL builds high power, amateur rockets for an annual intercollegiate competition in New Mexico. In 2018, SLURPL planned to deploy a R/C drone from one of their rockets mid-flight. This project was ultimately scrapped before completion due to safety concerns over lack of control of the rocket’s orientation when trying to deploy the payload. Last year’s senior design group, Project Centurion, broke ground for SLURPL by developing the first two-stage rocket in the history of the club. Unfortunately, when Centurion launched, the second stage was never recovered. One possible cause is due to a lack of proper orientation of the rocket when the two stages separated. So, our senior design team decided to build a system that would solve these problems: a Low Altitude Rocket Stability System that would be able to guarantee the proper orientation of a rocket. This could be applied to a two-stage rocket or a rocket with a deployable payload. We opted for a low-altitude system because this system will serve as a proof-of-concept, something that SLURPL can build off of as it climbs to new heights.

Control/Canard System

The LARSS control system consists of 4 servo actuated canards positioned in the upper air frame. The canards are 3D printed delta wings with a NACA 0015 cross section. The control system also contains a LSM9DS1 functioning as the main IMU. A ADXL377 200G accelerometer to serve as a means of lift off an touch down detection. A MPL3115A2 to serve as an additional point for altitude, lift off, and touch down data. As well as, a Teensy 3.5 micro-controller bring the system together and accurately record all of the flight data.

Requirements

Risk Mitigation

G, J, and C are of little to no concern as they are either easily mitigated or have little consequence to the progression of flight testing Adiona. Value A was emphasised in the design from the initial design, and thus has not been a significant concern since the beginning. When determining the components for Adiona, this was the first consideration. Value B, was well managed by our internal Gantt schedule. Ample room for construction and getting an early start on critical elements, such as winding our booster tube in December was completed. Unfortunately our schedule has since increased dramatically due to COVID-19. At this point, there is limited options available to us.

H & F are both catastrophic in their impact. Neither can be undone and both have the capability to destroy Adiona completely. Both are mitigated by testing. A static fire of the motor and altimeter testing along with separation charge testing for F & H respectively will drastically reduce the likelyhood of these risks from happening.

The final and most haunting items are D, I, and E. Each shares a corner or border with a red square, indicating a serious cause for concern. D & E are both parachute failures. In order to mitigate both, appropriate wight sizing was done, separation testing will be performed, and redundant black powder separation charges will be onboard. Leaving I, the loss of a canard mid-flight. Earning the position 3,3 in the risk matrix it is quite possible to happen and if not taken care of could cripple the test flights. In order to reduce the possibility of it sheering off the canard mount and canards will be built out of nylon carbon fiber which is strong enough to withstand extreme forces. In the event teh canard breaks while impacting the ground, the canards are easily removable and ample spares are available to swap on.