P07105: Project METEOR - Steel Rocket January 19, 2007 1 Project METEOR Design and Optimization of a...
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Transcript of P07105: Project METEOR - Steel Rocket January 19, 2007 1 Project METEOR Design and Optimization of a...
January 19, 20071
P07105: Project METEOR - Steel Rocket
Project METEOR
Design and Optimization of a Small Scale Rocket for Pico-Satellite Launching
Team Members:Ray MulatoJoe D’AmatoJoel BaillargeonKent EtienneGuion LucasRyan Kuhns
January 19, 20072
P07105: Project METEOR - Steel Rocket
Project Overview
Projected Flight Pattern
EARTH
BALLOON-PLATFORM-
ROCKET-SATELLITE
LAUNCH
~30
km
ROCKET-SATELLITE
LAUNCH
ROCKET-SATELLITE
LAUNCH
SATELLITE IN LOWEARTH ORBIT
SATELLITE IN LOWEARTH ORBIT
~16
0 k
m
LAUNCH PLATFORMLANDS W/ PARACHUTE
AND IS RECOVERED,REFURBISHED AND
REUSED
10-50 km10-70 km
BALLOON-PLATFORM-ROCKET-SATELLITE REACH ROCKETLAUNCH ALTITUDE AFTER
~1HOUR
PLATFORMSTABILIZATIONAND ROCKET-
SATELLITEORIENTATION
PLATFORMSTABILIZATIONAND ROCKET-
SATELLITEORIENTATION
Fig. 2. Typical Mission Profile
January 19, 20073
P07105: Project METEOR - Steel Rocket
Hybrid Rocket
• Classified as utilizing a liquid oxidizer and solid propellant to achieve thrust
– Current Oxidizer: Nitrous Oxide (NOX)
– Current Propellant: Hydroxyl Terminated Poly-Butadiene (HTPB)
– Possible Propellant: Poly-Methyl Methacrylate (PMMA )
Project Overview
January 19, 20074
P07105: Project METEOR - Steel Rocket
Injector Plate
Garolite Pre & Post Combustion Chambers
2-D Nozzle
Hydroxyl-Terminated Polybutadiene (HTPB) Fuel Grain
Chamber WallSnap Ring
Current Test Chamber Setup
January 19, 20075
P07105: Project METEOR - Steel Rocket
• Theoretical Isp for HTPB & NOX 320 s
• Properties– Efficiency of propulsion system– Ratio of thrust to weight– Change in momentum per unit mass of propellant – Affected by combustion temp, chamber pressure, exit pressure, and
mass flow rate
gm
FI sp
0g
vI esp
Project Deliverable – Specific Impulse
January 19, 20076
P07105: Project METEOR - Steel Rocket
• Optimization of:– Nozzle Geometry– Fuel Grain
• Material• Geometry
– Oxidizer Flow Rate – Ignition System
• Data Acquisition– Temperature– Pressure– Thrust
Specific Impulse of 220 s
Project Objectives
January 19, 20077
P07105: Project METEOR - Steel Rocket
From Guidance Team for controlled flight to 90 km:mfuel = 10kg;
mdot = 0.2kg/s;
tburn = 50 s; T = 445 N (100 lb)
Specification Number
Design SpecificationUnit of
MeasureMarginal
ValueIdeal Value
1 Specific Impulse sec 227 300
2 Oxidizer/Fuel Ratio - 5 8
3 Thrust N 445 500
4 Burn Time sec 50 60
5 Overall Mass Flow Rate kg/s 0.2 0.17
6 Mass of Fuel Grain kg 1.6 1.1
7 Mass of Oxidizer kg 8 8.75
Project Specifications
January 19, 20078
P07105: Project METEOR - Steel Rocket
Testing Purpose
• Testing took place December 9th & 10th, 2006
• Vary Nozzle Geometry to see the effects on thrust
• Conceivably measure mass flow rate of system– Weigh nitrous oxide tank and fuel grains prior and after each test– Come up with approximate O/F ratios
• Introduce Team to current design
January 19, 20079
P07105: Project METEOR - Steel Rocket
Results
January 19, 200710
P07105: Project METEOR - Steel Rocket
Testing 11 Degree Half Angle
January 19, 200711
P07105: Project METEOR - Steel Rocket
Testing 11 Degree Half Angle
Pressure
-100.0000
0.0000
100.0000
200.0000
300.0000
400.0000
500.0000
600.0000
0.0000 5.0000 10.0000 15.0000
Time (s)
Pre
ssu
re (
psi
)
Tank
Pre-Comb
Pre-Inj
Thrust
0.0000
10.0000
20.0000
30.0000
40.0000
50.0000
60.0000
70.0000
80.0000
90.0000
0.0000 2.0000 4.0000 6.0000 8.0000 10.0000 12.0000 14.0000 16.0000
Time (s)
Th
rust
(lb
)
January 19, 200712
P07105: Project METEOR - Steel Rocket
September 16th, 2006 Test
0 2 4 6 8 10 120
100
200
300
400
500
600
700
800
Time(s)
Pre
ssur
e (p
si)
Pressure
0 2 4 6 8 10 120
10
20
30
40
50
60
70
80
90
100
Time (s)
Thr
ust
Thrust
January 19, 200713
P07105: Project METEOR - Steel Rocket
First Testing – December 2006
• Observations– Overall system setup– Ignition system can be inconsistent in terms
of time– Oxidizer tank temperature varied
considerably from test to test– Teflon tape in feed system was tedious and
led to increased time between tests– Brass fittings can be cross-threaded and/or
broken easily– Noticeable inaccuracies in current mass flow
rate measurement– Power supply was convoluted– 8 Degree Half Angle Nozzle design gave the
best thrust results– Nitrogen tank regulator was damaged,
consistently leaks, had to develop a work around for it
• Conclusions– Began to reduce time between tests– Steady voltage and current supply is needed
to minimize ignition time– A method of controlling internal tank
temperature is needed to remove guesswork– Stainless steel can be used in place of brass
and teflon combination– Stainless steel fittings in oxidizer feed system
should be used– Means of gathering reliable mass flow is
crucial – Coriolis flow meter or volumetric flow meter in combination with other values
– A generator might be a better means of running the operation
– Difficult to draw definite conclusion from this, as multiple variables play a role in thrust
– Need to order a more robust regulator
January 19, 200714
P07105: Project METEOR - Steel Rocket
Feed System Equipment
• Goals of adding additional feed system equipment:– Acquire a reliable value for mass flowrate in order to calculate a number of
parameters• Regression rate• Test Chamber Pressure• Oxidizer-Fuel Ratio• Oxidizer Mass Velocity
– Feedback Pressure Regulator• Constant supply pressure leads to overall experimental control• Capability to vary supply pressure
– Optimization of nozzle for a supply pressure– Gas Tank Heating Blanket
• Allows for a controlled internal tank temperature– Temperature control leads to internal pressure control
January 19, 200715
P07105: Project METEOR - Steel Rocket
• Longer, wider chamber for longer burn and increased thrust
• Injector plate – redesign hole pattern and sizing in order to increase burn efficiency and completeness
• Use of Polymethyl Methylacrylate (PMMA) as a solid fuel in place of HTPB – possibly higher thrust
• Redesign of Pre and Post combustion chambers to minimize viscous losses inside the chamber
• Redesign of nozzle to take advantage of expansion of hot gas inside the diverging section of the nozzle rather than behind it
• Redesign of fuel grain to optimize regression rate and thrust (increase surface area exposed to flame)
Possible Test Chamber Improvements
January 19, 200716
P07105: Project METEOR - Steel Rocket
N2
N2O
2
4 25
22
21
14
26
2
1
22
6
3
6
2
22 25
6 3
7
6
6
6
12
15
10
15
14 28
8 26
2
26
2
11
2 18
2
19
2
17 17 17
16
23
1
4
26
2 20
19
18
9
2 22 25
14 6
Injector
Combustion Chamber
24
5
16
Lexan Frame
Hybrid Rocket Feed System
Current Feed System
January 19, 200717
P07105: Project METEOR - Steel Rocket
• Control of Oxidizer (N2O) Pressure via tank as well as before injector – installation of a feedback regulator
• Use of Stainless Steel in place of Brass in Nitrous Oxide feed system due to N2O effect on brass components (shorter life, corrosion of surfaces)
• Use of a tank “stand” to hold oxidizer tank inverted as well as to measure weights (for the current round of testing)
Possible Feed System Improvements
January 19, 200718
P07105: Project METEOR - Steel Rocket
N2
N2O
2
4 25
22
21
14
26
2
1
22
6
3
6
2
22 25
6 3
7
6
6
6
12
15
10
15
14 28
8 26
2
26
2
11
2 18
2
19
2
17 17 17
16
23
1
4
26
2 20
19
18
9
2 22 25
14
6
Injector
Combustion Chamber
24
5
16
Steel Baseplate
Hybrid Rocket Feed System
299999999
30
Highlighted areas show where changes are being made
Proposed Changes to Feed System
January 19, 200719
P07105: Project METEOR - Steel Rocket
Feed System Equipment
Test Chamber
Pressure Transducer
Tee Fitting
Mass Flowrate Meter
Backflow Pressure Regulator
Inline Flow Filter
January 19, 200720
P07105: Project METEOR - Steel Rocket
Design of Experiments
• Factorial Method vs. One Variable at a Time– Factorial method able to achieve comparable results
with fewer tests– Factorial method able to correlate relationships
between factors being tested
Factor A
Fac
tor
B
Low High
High
3
6
2
1
4
5
Factor A
Fac
tor
B
Low High
High
2
4
1
3
O.V.A.T. Factorial
January 19, 200721
P07105: Project METEOR - Steel Rocket
Design of Experiments
• NOX Pressure (Pre-Inj.)• Length of Fuel Grain• Post-Combustion Chamber• Nozzle• Injector Plate• Fuel Grain Additive
• Fuel Grain Geometery
• 3 levels (∆ of 50 psi.)• 2 levels (11” – 18”)• 4 levels (1.5” - 3.0”; ∆ 0.5”)• 2 levels• 2 levels (4 holes/ 9 holes)• 2 levels (Alum. Pwdr/ Non-Alum.
Pwdr)• 3 levels (Star, Circle, Cross)
Independent Test Variables Levels
January 19, 200722
P07105: Project METEOR - Steel Rocket
Design of Experiments
• Reasons for choosing these variables:– Short lead time for testing– See how pressure, and (L/D) ratio of the fuel grain effects thrust– No prior knowledge of injector plate design– Combustion chamber wasn’t chosen due to the additional changes to the system
needed to accommodate that test.
• NOX Pressure (Pre-Inj.)• Length of Fuel Grain• Injector Plate
Variables In Next Test
• 3 levels (∆ of 50 psi.)• 2 levels (11” – 18”)• 2 levels (4 holes/ 9 holes)
Levels
January 19, 200723
P07105: Project METEOR - Steel Rocket
Senior Design I Project Plan