I have posted on here a few times before about an independent student project I am working on, a 38mm minimum diameter experimental rocket named Icarus I.
I have recruited a few local rocket enthusiasts, with a wide range of backgrounds, into a small team to help with this project. We are calling ourselves "Team Icarus", and I thought we'd document the build here on TRF. We are open to suggestions and criticism, so if you see anything we could be doing better or more efficiently let us know.
The design as it stands right now has the most aerodynamic fin configuration we can manage while maintaining healthy margins for stability. Several of the team members have experience with very tightly packed fuselages on R/C sailplanes, so we are hoping to keep things pretty compact. The current configuration sims to 13,686', with a top speed of Mach 1.58 in RASAero.
To find the minimum fin size, we used RASAero to find the configuration with the lowest drag that kept the CP in front of the CG at the maximum design parameters. The maximum design angle of attack, 15 degrees, would be experienced while leaving the rail on a day with ~25 mph winds. The barrowman stability method is known to be quite reliable at this speed, so the fins were sized to keep the CP about 1/4" behind the CG at this angle. To verify stability at speed, we ensured that the 0-4 degree CP remained at least one and a half calibers behind the CG up to mach 2.5. The final result left the CP 1.98 calibers behind the CG at zero degrees AoA, which was about what you would expect.
We ended up settling on a smaller tip chord than the clipped delta that I often see cited as being the lowest drag option. When I started running iterations on different fin designs, I originally kept the root-to-tip ratio around 2 to reduce induced drag losses. However, the increased sweep and aspect ratio from the reduced tip size more than makes up for any induced drag losses due to the extreme taper ratio. The trailing edge is swept back as much as we dared without fearing increased flutter or broken fins.
The body material of choice for this rocket is Blue Tube, as it offers a nice balance between performance and budget. We are looking to build some molds for custom carbon parts for future rockets, but want to keep construction more simple until we have more experience with rockets in this performance class. The fins will either be cut from carbon sheet or canvas phenolic (we are undecided), and glassed on. They will be coupled with a FWFG 4:1 ogive nosecone. A Von Karman or conical nosecone would be the more aerodynamic choice, but some of the team members had a strong aesthetic preference for the classic profile of the ogive. The simmed altitude difference was small, so we went with the ogive.
Given the launch altitude of this rocket, dual deploy and electronic tracking are pretty much mandatory. Both will be first-time experiences for us.
Greg from BigRedBee has generously agreed to donate a BeeLine GPS for use on this project, which will be a huge asset. We owe him a big thanks. I just passed my Ham Radio Technician test yesterday, so we can utilize the 70 cm unit. We plan to use a small handheld transceiver in conjunction with APRSDroid for the groundstation.
We are seeking an accelerometer-based altimeter unit, but will likely have to fall back on a simple stratologger for deployment. For main recovery, we have a 52" ripstop parachute, and a mylar streamer for the "drogue". What are everyone's thoughts on using the streamer vs simply going drogueless?
On the subject of the powerplant, this rocket will feature a research motor using commercially-produced 38/740 snap ring hardware with a graphite nozzle. The grain configuration of this motor was designed in tandem with the rocket itself to optimize the motor-rocket system. This process gives a little extra performance, but more importantly for me as a student it offers a valuable design exercise. The current configuration uses five BATES grains and is projected to produce an average thrust of 517 N.
Thanks for looking, we should be updating soon as we begin the actual build.
EDIT: This design is still somewhat fluid. At the time of this edit, the team has seen further growth in its member base, and the most updated fin and body design can be seen on post 16
I have recruited a few local rocket enthusiasts, with a wide range of backgrounds, into a small team to help with this project. We are calling ourselves "Team Icarus", and I thought we'd document the build here on TRF. We are open to suggestions and criticism, so if you see anything we could be doing better or more efficiently let us know.
The design as it stands right now has the most aerodynamic fin configuration we can manage while maintaining healthy margins for stability. Several of the team members have experience with very tightly packed fuselages on R/C sailplanes, so we are hoping to keep things pretty compact. The current configuration sims to 13,686', with a top speed of Mach 1.58 in RASAero.
To find the minimum fin size, we used RASAero to find the configuration with the lowest drag that kept the CP in front of the CG at the maximum design parameters. The maximum design angle of attack, 15 degrees, would be experienced while leaving the rail on a day with ~25 mph winds. The barrowman stability method is known to be quite reliable at this speed, so the fins were sized to keep the CP about 1/4" behind the CG at this angle. To verify stability at speed, we ensured that the 0-4 degree CP remained at least one and a half calibers behind the CG up to mach 2.5. The final result left the CP 1.98 calibers behind the CG at zero degrees AoA, which was about what you would expect.
We ended up settling on a smaller tip chord than the clipped delta that I often see cited as being the lowest drag option. When I started running iterations on different fin designs, I originally kept the root-to-tip ratio around 2 to reduce induced drag losses. However, the increased sweep and aspect ratio from the reduced tip size more than makes up for any induced drag losses due to the extreme taper ratio. The trailing edge is swept back as much as we dared without fearing increased flutter or broken fins.
The body material of choice for this rocket is Blue Tube, as it offers a nice balance between performance and budget. We are looking to build some molds for custom carbon parts for future rockets, but want to keep construction more simple until we have more experience with rockets in this performance class. The fins will either be cut from carbon sheet or canvas phenolic (we are undecided), and glassed on. They will be coupled with a FWFG 4:1 ogive nosecone. A Von Karman or conical nosecone would be the more aerodynamic choice, but some of the team members had a strong aesthetic preference for the classic profile of the ogive. The simmed altitude difference was small, so we went with the ogive.
Given the launch altitude of this rocket, dual deploy and electronic tracking are pretty much mandatory. Both will be first-time experiences for us.
Greg from BigRedBee has generously agreed to donate a BeeLine GPS for use on this project, which will be a huge asset. We owe him a big thanks. I just passed my Ham Radio Technician test yesterday, so we can utilize the 70 cm unit. We plan to use a small handheld transceiver in conjunction with APRSDroid for the groundstation.
We are seeking an accelerometer-based altimeter unit, but will likely have to fall back on a simple stratologger for deployment. For main recovery, we have a 52" ripstop parachute, and a mylar streamer for the "drogue". What are everyone's thoughts on using the streamer vs simply going drogueless?
On the subject of the powerplant, this rocket will feature a research motor using commercially-produced 38/740 snap ring hardware with a graphite nozzle. The grain configuration of this motor was designed in tandem with the rocket itself to optimize the motor-rocket system. This process gives a little extra performance, but more importantly for me as a student it offers a valuable design exercise. The current configuration uses five BATES grains and is projected to produce an average thrust of 517 N.
Thanks for looking, we should be updating soon as we begin the actual build.
EDIT: This design is still somewhat fluid. At the time of this edit, the team has seen further growth in its member base, and the most updated fin and body design can be seen on post 16
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