KCRSXTypeS
Newbie
Ok ladies and gentlemen, here is the deal. My name is Devon, I am a 5th year senior at the University of Kansas. For my senior design class we are to design an aircraft for an AIAA competition which would qualify as an LSA and meet the specs. Seeing as how I am :der: I decided to go with a gyroplane just to stand out from among my peers who are doing typical puller style airplanes. The problem is I have almost no aerodynamic, structure, analysis, or design experience when it comes to rotor craft and the knowledge base around the school is limited. I am using Frankenstein techniques to design this aircraft based around airplane design and am running into trouble. What I am looking for is all the help I can get basically.
What I would like is, since I didn't see a sticky at the top here, all the things to REALLY consider when designing a gyroplane. What are the fundamentals to watch out for, how do I choose a rotor airfoil, how do I decide where to place the CG, what engine should I use, what kind of prerotator. These are just SOME of the things that I am looking for. If anyone has an article or something that could point me in the right direction that would be a big help as well. As a note, I do not actually have to build this thing, just design it. It has to meet the following specs. Please also let me know if you foresee anything below being a problem to attain.
Seating: Two
Cargo/baggage bay volume: > 12 ft3
Fuel Capacity: >26 US gallons
Useful load (people, cargo, fuel): >550 lbs
Take-off Performance @ Max weight, standard day, sea level conditions:
Ground Roll: < 250’
Take-off over 50’: < 550’
Landing roll: < 300’
Landing over 50’: < 650’
Dash Speed: < 120 knots
Maximum Cruise speed: > 113 knots (at best altitude and continuous cruise power)
Maximum Range at max cruise speed: 400 n.m. (accounting for take-off, climb fuel burn, plus 30 minute additional reserve at most economical cruise power setting).
Airplane shall be rugged for operations out of unimproved landing strips, reliable and easily repaired. The airplane shall be easily parked in a standard 40’ wide ‘T’ hangar.
Pilot visibility shall be very good.
Center of gravity loadability shall be sufficient for flights with:
· Full fuel and one 130 lb pilot, no cargo;
· Full fuel, two 200 lb people, no cargo; and,
· Two 170 lb people, 90 lbs cargo, and at least 20 gallons fuel.
Optional capability to utilize high flotation tires (with decrease in maximum cruise speed permitted) shall be provided for.
Instrumentation will be typical of that allowed for LSA class airplanes (basic VFR). Minimum installation of a single VHF Communication radio, and an installed GPS.
The airplane shall in all matters be compliant with Light Sport Aircraft ASTM standards (ASTM 2245), per FAA rules outlining LSA class aircraft.
Operating costs, specifically fuel costs and maintenance (routine scheduled, non-routine, overhauls, etc.), shall be demonstrated to be typical, or below average, for the LSA class of aircraft.
Airplane acquisition cost shall be commensurate with other LSA class aircraft. Production runs of 100 and 500 units shall be assessed.
What I would like is, since I didn't see a sticky at the top here, all the things to REALLY consider when designing a gyroplane. What are the fundamentals to watch out for, how do I choose a rotor airfoil, how do I decide where to place the CG, what engine should I use, what kind of prerotator. These are just SOME of the things that I am looking for. If anyone has an article or something that could point me in the right direction that would be a big help as well. As a note, I do not actually have to build this thing, just design it. It has to meet the following specs. Please also let me know if you foresee anything below being a problem to attain.
Seating: Two
Cargo/baggage bay volume: > 12 ft3
Fuel Capacity: >26 US gallons
Useful load (people, cargo, fuel): >550 lbs
Take-off Performance @ Max weight, standard day, sea level conditions:
Ground Roll: < 250’
Take-off over 50’: < 550’
Landing roll: < 300’
Landing over 50’: < 650’
Dash Speed: < 120 knots
Maximum Cruise speed: > 113 knots (at best altitude and continuous cruise power)
Maximum Range at max cruise speed: 400 n.m. (accounting for take-off, climb fuel burn, plus 30 minute additional reserve at most economical cruise power setting).
Airplane shall be rugged for operations out of unimproved landing strips, reliable and easily repaired. The airplane shall be easily parked in a standard 40’ wide ‘T’ hangar.
Pilot visibility shall be very good.
Center of gravity loadability shall be sufficient for flights with:
· Full fuel and one 130 lb pilot, no cargo;
· Full fuel, two 200 lb people, no cargo; and,
· Two 170 lb people, 90 lbs cargo, and at least 20 gallons fuel.
Optional capability to utilize high flotation tires (with decrease in maximum cruise speed permitted) shall be provided for.
Instrumentation will be typical of that allowed for LSA class airplanes (basic VFR). Minimum installation of a single VHF Communication radio, and an installed GPS.
The airplane shall in all matters be compliant with Light Sport Aircraft ASTM standards (ASTM 2245), per FAA rules outlining LSA class aircraft.
Operating costs, specifically fuel costs and maintenance (routine scheduled, non-routine, overhauls, etc.), shall be demonstrated to be typical, or below average, for the LSA class of aircraft.
Airplane acquisition cost shall be commensurate with other LSA class aircraft. Production runs of 100 and 500 units shall be assessed.