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Line 253: − − == Budget == − − The overall Budget that the Pegasus team has is $4000. Currently our expenditure for our L3 rocket specifically, as predicted and as already purchased, stands at $3310. An extra $400 is expected to be spent on L1-L2 testing. The current budget break-down is as follows: − − {| − | '''Motor''' − |align="right"| $710 − |- − | '''Structural Components''' − |align="right"| − − |- − | Airframe − |align="right"| $200 − |- − | Nosecone − |align="right"| $120 − |- − | Fins − |align="right"| $80 − |- − | '''Recovery System''' − |align="right"| − − |- − | Parafoil − |align="right"| $1200 − |- − | Drogue − |align="right"| $66 − |- − | '''Backup Recovery System''' − |align="right"| − − |- − | Parachute − |align="right"| $324 − |- − | Recovery Accessories − |align="right"| $120 − |- − | '''Avionics''' − |align="right"| $490 − |- − | '''Reserve + Testing Expenses''' − |align="right"| $690 − |- − | − − |align="right"| $4000 − |} − + + +
no edit summary
The Pegasus team is designing a rocket with the goal of demonstrating the feasibility of controlled recovery from high-powered flight from over 10,000 ft through the use of a parafoil. The team is currently working on the design of an L3 rocket to be launched on March 19, 2016 as well as an L1 to be launched on February 6, 2016, the purpose of which is to test the どやって離す ejection of the parafoil from the airframe.
The Pegasus team is designing a rocket with the goal of demonstrating the feasibility of controlled recovery from high-powered flight from over 10,000 ft through the use of a parafoil. The team is currently working on the design of an L3 rocket to be launched on March 19, 2016 as well as an L1 to be launched on February 6, 2016, the purpose of which is to test the ejection of the parafoil from the airframe.
{{rocket-project
| header = Pegasus (ARES-2)
| img link = File:Pegasus_Flag.png
| launch details =
{{rocket-launch
|number=1
|launch class = L1
|launch date = February 20, 2016
|launch site = LUNAR
|next={{rocket-launch
|number=2
|launch class = L2
|launch date = Pending
|launch site = Pending
|next={{rocket-launch
|number=3
|launch class = L3
|launch date = Pending
|launch site = Pending
}}
}}
}}
| program = Project Daedalus
| last = Talos
| next = Charybdis
}}
= Team Summary =
= Team Summary =
Ian Gomez (Project Manager), Marie Johnson (Team lead), Austin Pineault (Structural Development and Mechanical Systems Integration), Andrew Milich (Avionics, Deployment, and Programming), John Dean (Avionics, Deployment, and Programming), Hannah Williams (Structural Development and Parafoil), Sruti Arulmani, Nate Simon (Parafoil and Aerodynamics). <br />
Ian Gomez (Project Manager), Marie Johnson (Team lead), Austin Pineault (Structural Development and Mechanical Systems Integration), Andrew Milich (Avionics, Deployment, and Programming), John Dean (Avionics, Deployment, and Programming), Hannah Williams (Structural Development and Parafoil), Nate Simon (Parafoil and Aerodynamics). <br />
= Launch Vehicle and Payload Summary =
= Launch Vehicle and Payload Summary =
The payload of this rocket is the active recovery system and its backup. The payload will be a parafoil deployed at apogee and controlled by two servos throughout descent.
The payload of this rocket is the active recovery system and its backup. The payload will be a parafoil deployed at apogee and controlled by two servos throughout descent.
= Launches and Tests =
== February 20 ==
'''Pegasus 1:''' This was the first test flight of the Pegasus rocket where a parafoil was used instead of a parachute to safely land the rocket. The main purposes of this launch were to:
# Test out our idea to store the parafoil under the nose cone
# Take a video of parafoil deployment on the rocket to try and find any unforseen problems with our current design, folding technique for the parafoil.
''Brief Rocket Design''
The rocket measures 7.5ft long with a 4" OD. It is made of two phenolic airframes connected by an internal phenolic coupler 7" long. The three fins are fiberglass with a trapezoidal design and the nosecone is an ogive shape 18" long made of polystyrene. We had the parafoil stored under the nosecone and had the attachment lines running along the outside, lightly taped to the rocket with white duct tape.[[File:Pegasus1Launch.JPG|thumb|frame|right|300px|Pegasus 1 launching off the rod at TCC on Feb 20,2016]] Inside we custom built an avionics bay to contain and protect our SPOT trackers from the heat of the motor ejection charge. We decided to make this launch an ultra basic one where instead of using an altimeter to set off the charge at specified height. The holes through which which the parafoil is attached is 5"towards the aft of the coupler in the lower airframe. A 10dof had originally been planned to have on the parafoil, but there was not enough time to attach and secure the 10dof prior to launch. Lastly, a mini U8 camera was mounted on the aft airframe just above the fins to take video of the parafoil deployment. Initially, two were planned to be used, but one was loaned to another team and was not returned in time for the launch.
The motor that was chosen for this launch was a DMS I280 from Aerotech. This was because it closely mimicked the speed off the rod and average thrust of our predicted final rocket motor. The I280 that was purchased included Magnesium in its propellant to create the sparkling flame trail behind the rocket.
''Results''
This launch successfully displayed that storing the parafoil underneath the nosecone is a very feasible option. There was no initial tangling of the lines over the parafoil, however a problem of the lines becoming twisted around each other was shown to be a serious concern for when control lines are invariably added to each 'flaperon' on the parafoil. The launch also demonstrated that we had correctly sized the parafoil to our rocket weight, and could even safely add weight, as the landing was extremely soft and the rocket experienced no damage upon touchdown.
= Vehicle Criteria =
= Vehicle Criteria =
== Propulsion System ==
== Propulsion System ==
The Cesaroni M1450 was chosen because it is commercially available, reloadable, complies with the Tripoli and California restrictions, keeps our rocket sub Mach-1, and should achieve a maximum height of 16,300 ft with the current mass estimates. Thus even if our mass budget increases, there will still be ample altitude to test the parafoil system.
The Cesaroni M1450 was chosen because it is commercially available, reloadable, complies with the Tripoli and California restrictions, keeps our rocket sub Mach-1, and should achieve a maximum height to a safe margin below the maximum ceiling. Thus even if our mass budget increases, there will still be ample altitude to test the parafoil system.
The M1450 has an average thrust of 1500 N, a total impulse of 10000 N-s, a specific impulse of 210 s, a burn time of 6.9 s, and a maximum velocity of 300 m/s (Mach 0.9).
The M1450 has an average thrust of 1500 N, a total impulse of 10000 N-s, a specific impulse of 210 s, and a burn time of 6.9 s.
=== Motor Performance ===
=== Flight Characteristics ===
With current mass budget considerations, the M1450 motor is projected to boost the rocket to a peak of roughly Mach 0.78 and an apogee of roughly 11000 ft after 27 s.
[[File:CM1450_Mass.png|image]]
[[File:Pegasus_Performance_Altitude_Speed.png|thumb|frame|center|1000px|Altitude and Mach variation throughout the flight]]
On liftoff, the acceleration of the rocket is projected to be roughly 10 g, increasing to a sustained 11.5 g. A maximum drag force of roughly 85 N is expected. Max-Q is expected to occur roughly 4 s into the flight.
[[File:Performance_Altitude_Speed.png|image]]<br />
[[File:Pegasus_Performance_Acceleration_Drag.png|thumb|frame|center|1000px|Acceleration and drag forces on the rocket during the motor firing]]
A nominal static stability ranging between 1.5 and 2.3 calibers is expected in the current configuration.
[[File:CM1450_S_Stabil.png|image]]
[[File:Pegasus_Performance_Mass_Stability.png|thumb|frame|center|1000px|Mass decrease and change in static stability during the motor firing]]
== Structural Design ==
== Structural Design ==
The forward airframe will be 6“ in diameter and 44” in length. It will house, from front to rear, the primary recovery system (parafoil), backup recovery system (parachute payload), and avionics bay.
The forward airframe will be 6“ in diameter and 44” in length. It will house, from front to rear, the primary recovery system (parafoil), backup recovery system (parachute payload), and avionics bay.
[[File:f_airframe.png|image]]<br />
[[File:Pegasus_Parafoil_Structural_Overview.png|thumb|frame|center|600px|Structural overview for parafoil storage in forward airframe]]
Each of these components will be separated by bulkheads; the foreward bulkhead is designed to protect the backup recovery system from the parafoil’s expulsion and will be mobile (supported on the aft side by blocks along the inner wall of the airframe) to allow backup system to exit the rocket, while the aft bulkhead is designed to protect the avionics and therefore will be stationary.
Each of these components will be separated by bulkheads; the foreward bulkhead is designed to protect the backup recovery system from the parafoil’s expulsion and will be mobile (supported on the aft side by blocks along the inner wall of the airframe) to allow backup system to exit the rocket, while the aft bulkhead is designed to protect the avionics and therefore will be stationary.
Telemetry is accomplished using two XBee 9B 900MHZ 250MW long range radio transmitters. Under line of sight conditions, these are expected to achieve a maximum range of 28 miles. We equipped both with 900 MHZ, low impedance, RP-SMA duck antennas.
Telemetry is accomplished using two XBee 9B 900MHZ 250MW long range radio transmitters. Under line of sight conditions, these are expected to achieve a maximum range of 28 miles. We equipped both with 900 MHZ, low impedance, RP-SMA duck antennas.
[[File:Avionics_Block_Diagram.png|thumb|300px|right|Avionics block diagram]]
[[File:Pegasus_Avionics_Block_Diagram.png|thumb|300px|right|Avionics block diagram]]
=== Avionics Teensy Pinout ===
=== Avionics Teensy Pinout ===
The in-flight tracking will use a XBee Pro module and an Adafruit GPS receiver with a ceramic antena.
The in-flight tracking will use a XBee Pro module and an Adafruit GPS receiver with a ceramic antena.
[[File:Avionics_XBee.png|80px|XBee Pro module]]
[[File:Pegasus_Avionics_XBee.png|80px]]
For the in-flight communication and redundant tracking, the rocket will rely on live communication via XBee transmitters and the use of a small SPOT GPS for precise location of the rocket.
For the in-flight communication and redundant tracking, the rocket will rely on live communication via XBee transmitters and the use of a small SPOT GPS for precise location of the rocket.
The parafoil is going to be stored directly behind the nosecone within the forward airframe. The majority of the attachment and support lines are going to be folded in with the parafoil with the four main lines leading out of the nosecone and down the outside of the airframe. These four lines are the two control and two load bearing lines respectively. Each of these four lines is to be inserted through its own slot in the foreward/aft airframes where it is attached to the inside of the rocket near the CG.
The parafoil is going to be stored directly behind the nosecone within the forward airframe. The majority of the attachment and support lines are going to be folded in with the parafoil with the four main lines leading out of the nosecone and down the outside of the airframe. These four lines are the two control and two load bearing lines respectively. Each of these four lines is to be inserted through its own slot in the foreward/aft airframes where it is attached to the inside of the rocket near the CG.
[[File:Pegasus_Parafoil_Storage.png|thumb|frame|center|400px|Bulkhead and backup separation design]]
=== Deployment ===
=== Deployment ===
* Other simple applications to monitor range or other basic parameters.
* Other simple applications to monitor range or other basic parameters.
[[File:Avionics_Ground_Station.png|800px|center]]
[[File:Pegasus_Avionics_Ground_Station.png|800px|center]]
=== Landing ===
=== Landing ===
Upon the need for the backup recovery system, a pyrodex ejection charge located behind the parachute will be ignited from a command given by the altimeter. This charge will force out the parachute, pushing the movable bulkhead out of the forward airframe with it. Since the shockcord is going to be traveling a large distance within the rocket, the shockcord will have a tennis ball around it to mitigate possible zippering of the rocket.
Upon the need for the backup recovery system, a pyrodex ejection charge located behind the parachute will be ignited from a command given by the altimeter. This charge will force out the parachute, pushing the movable bulkhead out of the forward airframe with it. Since the shockcord is going to be traveling a large distance within the rocket, the shockcord will have a tennis ball around it to mitigate possible zippering of the rocket.
[[File:Pegasus_Design_Bulkheads.png|thumb|frame|center|600px|Bulkhead and backup separation design]]
= Manufacturing and Assembly =
= Manufacturing and Assembly =
== Safety Hazards ==
== Safety Hazards ==
For this rocket using a parafoil recovery system creates most of the possible risks of having an unsuccessful flight. Our first risk is the parafoil not deploying properly. This could mean not emerging from the rocket, becoming tangled upon exit of the airframe, and becoming tangled in mid-air while opening. To mitigate the first issue, non-emergence, we are performing pre-launch date small scale tests to practice our system and amount of propellant needed to fully expel the parafoil. The second issue of becoming tangled upon exit we will also be performing small scale tests on prior to the full L3 rocket. This test will be performed again using a static run on the L3 to make sure we scaled it up properly. The final issue of becoming tangled while opening will also be examined through the small scale L1-L2 tests and should be mitigated depending on how the parafoil is folded and fit into the rocket airframe. The parafoil is also going to be contained in a freebag that will be pulled out by the drogue chute. This combination should also help prevent the other issues upon exit. In the event that all of this fails, the payload for the rocket is a parachute that is rigged to an altimeter. Upon too quick of a descent (aka parafoil mal-deployment) the parachute will deploy prematurely to slow the descent of the rocket to a safe speed of 20 <math>m/s</math>.
For this rocket using a parafoil recovery system creates most of the possible risks of having an unsuccessful flight. Our first risk is the parafoil not deploying properly. This could mean not emerging from the rocket, becoming tangled upon exit of the airframe, and becoming tangled in mid-air while opening. To mitigate the first issue, non-emergence, we are performing pre-launch date small scale tests to practice our system and amount of propellant needed to fully expel the parafoil. The second issue of becoming tangled upon exit we will also be performing small scale tests on prior to the full L3 rocket. This test will be performed again using a static run on the L3 to make sure we scaled it up properly. The final issue of becoming tangled while opening will also be examined through the small scale L1-L2 tests and should be mitigated depending on how the parafoil is folded and fit into the rocket airframe. The parafoil is also going to be contained in a freebag that will be pulled out by the drogue chute. This combination should also help prevent the other issues upon exit. In the event that all of this fails, the payload for the rocket is a parachute that is rigged to an altimeter. Upon too quick of a descent (aka parafoil mal-deployment) the parachute will deploy prematurely to slow the descent of the rocket to a safe speed of 20 m/s.
The second point of risk is when the rocket is descending while being controlled by the parafoil and the step motors. There is always a possibility of having strong winds above 10,000ft and gusts could cause major control issues for both the stepper motors and for the coded flight plan. Some fail-safes are put into place such as having overly robust stepper motors so that under larger-than-predicted forces the stepper motors will not fail. Another safe-guard are pre-written statements that are associated with the parachute. These safe-guards include too quick of a descent rate (parafoil failure), prolonged ascension after the rocket has reached apogee (in case of thermals or wind gusts forcing the parafoil upwards).
The second point of risk is when the rocket is descending while being controlled by the parafoil and the step motors. There is always a possibility of having strong winds above 10,000ft and gusts could cause major control issues for both the stepper motors and for the coded flight plan. Some fail-safes are put into place such as having overly robust stepper motors so that under larger-than-predicted forces the stepper motors will not fail. Another safe-guard are pre-written statements that are associated with the parachute. These safe-guards include too quick of a descent rate (parafoil failure), prolonged ascension after the rocket has reached apogee (in case of thermals or wind gusts forcing the parafoil upwards).
; March 19th:
; March 19th:
: L3 Launch
: L3 Launch
[[Category:Rockets]]
[[Category: Daedalus]]
[[Category: Rockets]]
[[Category: Documentation]]