Midwest
Past Midwest Leads
The Midwest High Power Rocket competition is run by the NASA Space Grant Consortium and held in North Branch, MN. This competition presents unique design problems, leading to a variety of rocket configurations over the years.
The Midwest High Power Rocket competition is run by the NASA Space Grant Consortium and held in North Branch, MN. This competition presents unique design problems, leading to a variety of rocket configurations over the years.
This project was put on hold for our team in 2021 to further develop our special projects team to support other projects across the team.
Meet Our Rockets
Meet Our Rockets
2021 - Vanadium Mist
2021 - Vanadium Mist
During the Spring 2021 semester, the Minnesota Space Grant did not hold a high-powered rocketry competition. In order to keep the members busy and to help teach new members about high-powered rocketry, the Midwest Team decided to attempt to beat the Tripoli Rocketry Association Altitude Record using a single G class motor(8,796 ft.).
During the Spring 2021 semester, the Minnesota Space Grant did not hold a high-powered rocketry competition. In order to keep the members busy and to help teach new members about high-powered rocketry, the Midwest Team decided to attempt to beat the Tripoli Rocketry Association Altitude Record using a single G class motor(8,796 ft.).
The rocket, Vanadium Mist, had an attempted launch over the summer, but there was a failure with the rail guides and the rocket did not make it off the pad.
The rocket, Vanadium Mist, had an attempted launch over the summer, but there was a failure with the rail guides and the rocket did not make it off the pad.
2020 - Iridium Sandstorm
2020 - Iridium Sandstorm
Canceled
Canceled
This competition required teams to build a rocket that will conduct two flights - one to 2345 ft and one to 3456 ft. During ascent the rocket will try to minimize its roll rate to create a stable, easy to view video. After apogee the rocket will also capture video of each section as they separate, and then through the descent in order to verify good separation and aid in the diagnostics of any anomalies. After landing the rocket will take a 360 degree panorama photo from as high off the ground as possible..
This competition required teams to build a rocket that will conduct two flights - one to 2345 ft and one to 3456 ft. During ascent the rocket will try to minimize its roll rate to create a stable, easy to view video. After apogee the rocket will also capture video of each section as they separate, and then through the descent in order to verify good separation and aid in the diagnostics of any anomalies. After landing the rocket will take a 360 degree panorama photo from as high off the ground as possible..
The unique combination of challenges presented by this 2019-2020 competition pushed our planning capabilities to the limit, but by the time Spring Break arrived, the Midwest project team had developed a robust design for a rocket with a deploying landing device. Prototyping and testing of the device was well underway.
The unique combination of challenges presented by this 2019-2020 competition pushed our planning capabilities to the limit, but by the time Spring Break arrived, the Midwest project team had developed a robust design for a rocket with a deploying landing device. Prototyping and testing of the device was well underway.
Work Iridium Sandstorm was canceled due to University restrictions.
Work Iridium Sandstorm was canceled due to University restrictions.
To learn more about Iridium Sandstorm and its preliminary design, click here.
To learn more about Iridium Sandstorm and its preliminary design, click here.
2019 - Cesium Black
2019 - Cesium Black
The 2019 competition challenged teams to build an "efficient" supersonic rocket. The trick this year was to focus on transonic aerodynamics. The competition involved two flights, one on a prescribed motor set by the competition and one on a larger motor of the team's choice
The 2019 competition challenged teams to build an "efficient" supersonic rocket. The trick this year was to focus on transonic aerodynamics. The competition involved two flights, one on a prescribed motor set by the competition and one on a larger motor of the team's choice
On the first flight with the standard motor, the goal was simple: to reach the highest altitude possible. This called for a smooth, low drag profile. Cesium Black therefore used a a low-drag nosecone and a tailcone for this flight.
On the first flight with the standard motor, the goal was simple: to reach the highest altitude possible. This called for a smooth, low drag profile. Cesium Black therefore used a a low-drag nosecone and a tailcone for this flight.
On the second flight, the rocket was required to break the sound barrier while achieving the lowest altitude possible. We choose a very high-thrust short-burn motor to quickly accelerate the rocket to supersonic speeds. Teams were allowed to change the nosecone and the tailcone of the rocket between flights, so we removed the tailcone and used a very blunt high-drag nosecone for this flight. Cesium Black was very light so that she could rapidly decelerate to reduce apogee.
On the second flight, the rocket was required to break the sound barrier while achieving the lowest altitude possible. We choose a very high-thrust short-burn motor to quickly accelerate the rocket to supersonic speeds. Teams were allowed to change the nosecone and the tailcone of the rocket between flights, so we removed the tailcone and used a very blunt high-drag nosecone for this flight. Cesium Black was very light so that she could rapidly decelerate to reduce apogee.
This rocket won FIRST PLACE in the competition!
This rocket won FIRST PLACE in the competition!
2018 - Wolfram Green
2018 - Wolfram Green
In 2018, teams were challenged to design a roll control system for their rocket. First the rocket was to fly with the anti-roll system deactivated to demonstrate the rocket's natural roll rate. Second, the rocket would orient itself in a set of prescribed compass orientations.
In 2018, teams were challenged to design a roll control system for their rocket. First the rocket was to fly with the anti-roll system deactivated to demonstrate the rocket's natural roll rate. Second, the rocket would orient itself in a set of prescribed compass orientations.
The bonus challenge for this year included incorporating a radio communication system onto the rocket that could reprogram the orientation sequence while the rocket was still on the pad, and transmit data during ascent.
The bonus challenge for this year included incorporating a radio communication system onto the rocket that could reprogram the orientation sequence while the rocket was still on the pad, and transmit data during ascent.
Our team leveraged experience gained from developing a roll control system for our IREC rocket. Our system utilized four control surfaces located near the center of gravity of the rocket such that they would effectively control the roll of the rocket with minimal effect on pitch and yaw.
Our team leveraged experience gained from developing a roll control system for our IREC rocket. Our system utilized four control surfaces located near the center of gravity of the rocket such that they would effectively control the roll of the rocket with minimal effect on pitch and yaw.
The electrical hardware included a custom 4-card PCB stack with separate boards for power, sensors, CPU, and servo control. RTEMS served as the operating system. A robust state space controller capable of tracking a reference was used to command the fin angles.
The electrical hardware included a custom 4-card PCB stack with separate boards for power, sensors, CPU, and servo control. RTEMS served as the operating system. A robust state space controller capable of tracking a reference was used to command the fin angles.
At competition, exposed wires caused a short in the PCB stack, preventing successful operation. Wolfram was nonetheless flown and recovered nominally.
At competition, exposed wires caused a short in the PCB stack, preventing successful operation. Wolfram was nonetheless flown and recovered nominally.
2017 - Red Mercury
2017 - Red Mercury
The 2017 competition challenged teams to develop a rocket that could reach the same apogee on two motors that were "as different as possible." This requirement was evaluated as a function of the differences in the two motors' performance characteristics such as total impulse, thrust, and burn time.
The 2017 competition challenged teams to develop a rocket that could reach the same apogee on two motors that were "as different as possible." This requirement was evaluated as a function of the differences in the two motors' performance characteristics such as total impulse, thrust, and burn time.
Red Mercury achieved this goal with no moving parts. She was carefully designed such to have a low drag coefficient in the subsonic regime, but high drag in the supersonic regime. Being lightweight was also critical.
Red Mercury achieved this goal with no moving parts. She was carefully designed such to have a low drag coefficient in the subsonic regime, but high drag in the supersonic regime. Being lightweight was also critical.
This design allowed Red Mercury to fly to a high altitude on a relatively low-impulse slow-burning J90 motor because she maintained a low speed throughout the flight. She then flew on a punchy, high-impulse K2045 motor. On this flight the rocket experienced 100 G's and hit Mach 1.6 in less than a second, but quickly decelerated due to high supersonic drag.
This design allowed Red Mercury to fly to a high altitude on a relatively low-impulse slow-burning J90 motor because she maintained a low speed throughout the flight. She then flew on a punchy, high-impulse K2045 motor. On this flight the rocket experienced 100 G's and hit Mach 1.6 in less than a second, but quickly decelerated due to high supersonic drag.
This rocket won SECOND PLACE in the overall competition and FIRST PLACE in the flight score.
This rocket won SECOND PLACE in the overall competition and FIRST PLACE in the flight score.
2016 - Blue Steel
2016 - Blue Steel
In 2016 the design goal was to fly twice on the same motor and reach two different altitudes that were as different as possible. However, the air-braking system used to achieve this had to be deployable.
In 2016 the design goal was to fly twice on the same motor and reach two different altitudes that were as different as possible. However, the air-braking system used to achieve this had to be deployable.
Our design used four air intakes near the base of the rocket that could be opened or closed by a rotating piece that either uncovered or covered the holes, depending on its position. This created a very simple and reliable system that performed well in the competition environment.
Our design used four air intakes near the base of the rocket that could be opened or closed by a rotating piece that either uncovered or covered the holes, depending on its position. This created a very simple and reliable system that performed well in the competition environment.