Upload
others
View
0
Download
0
Embed Size (px)
Citation preview
MIT Rocket Team
USLI 2011
Flight Readiness Review Addendum
April 6, 2011
Project Valhalla
REPORT AUTHORS
Christian Valledor Project Manager
Andrew Wimmer Team Safety Officer, Tripoli Rocket Association Level 3
Ben Corbin EHS Representative
Ryan McLinko Launch Vehicle Lead
Eric Peters Recovery Lead
Ben Couchman Avionics Lead
TABLE OF CONTENTS
1 Introduction .............................................................................................................. 4
2 Reasoning ................................................................................................................ 4
3 Physical CHanges .................................................................................................... 5
4 Flight Results ........................................................................................................... 6
5 Drift Calculations ...................................................................................................... 7
6 List of Radio Frequencies Used ............................................................................... 7
7 Updated CAD Drawings ........................................................................................... 7
1 INTRODUCTION
After completion of the final full-scale test flight before submitting our final Flight
Readiness Review, it became clear to the team that it was necessary to rebuild the
lower section of the flight vehicle. This wish was presented to the review board during
the process of the FRR presentation to ensure the team would stay within full
compliance of the USLI rules. From this discussion it was decided that if the team were
to make a change on the scale that was discussed, it would be necessary to again test
fly the complete rocket to fall within the rules of the competition. With this resolve, the
team undertook the challenging task of fabricating a new lower rocket section, and
traveling to a launch.
The team has been successful in this regard, and we have completed both the fabrication and flight testing of the new section. In fulfillment of the requirements discussed in the FRR Presentation, the following document serves as a discussion of our reasoning, and the results of the flight testing. In completion of this testing and this documentation the team is confident in the newly fabricated section, and our modeling. We look forward to seeing you in the coming week.
2 REASONING
The first full-scale test of the rocket occurred on March 22nd, 2011. The test launch
configuration differed from the competition launch configuration in several ways. The
first major difference was that the UAV payload was only a scale model, which was
incapable of controlled flight, that closely matched the physical dimensions of the UAV
that will be used in the competition. This was to test the wing rotation mechanism and
ensure it could operate under the loads it will experience in flight.
The other major difference between the test flight configuration and the planned competition configuration was that no ballast was added to the rocket. In order for the rocket to meet and not exceed 5280 feet in altitude, 3.5 kg of ballast needed to be added. Without this ballast, the RockSim model showed that the rocket would achieve an altitude of approximately 7200 feet. Additionally, without the ballast, the static margin of the rocket was much higher than it was with the ballast. This extreme difference in static margin alone may have invalidated the results from the test flight to prove that the rocket could fly in the competition configuration, but this is only a small part of why an additional full-scale test flight was necessary. When the lower section of the rocket was manufactured, the phenolic tubing that was used as a tool for the carbon fiber molding was not long enough. As a result, one end was angled compared to the other. When the motor mount was installed, it was off-axis by approximately one inch. Since the lower section is 48 inches, this corresponds to an angular error of 1/48 radians, or 1.2 degrees. Initially, the team did not think this would be an issue; however, the test launch showed that this could not be ignored.
During the test flight, the rocket experienced coning, which can be seen in the contrail shown in Figure 1. Due to this coning, the rocket only achieved an altitude of 5600 feet; while this is still high enough to be disqualified from the USLI competition, it was nearly 1700 short of the altitude predicted by the simulations. Since the effect of coning could not be duplicated in the simulations, the model was invalidated for the configuration as it was flown, so it would not be acceptable for predicting the altitude of the rocket on launch day. This is the primary reason why the lower section of the rocket had to be rebuilt. However, other changes were discussed as well.
FIGURE 1. CONING SEEN DURING THE 3/22/11 TEST FLIGHT
After much discussion among team members and review of technical documents
describing dynamic instability, it was determined that the coning effects were caused
primarily by the misalignment of the motor. However, other comparisons with rockets
that experienced coning and other instabilities showed that the initial flight configuration
had fins that were surprisingly small. While the static margin of the rocket was still
positive (and intentionally close to 1), given the high length to diameter ratio, this put the
rocket at risk for problems with coning. As a result, the team decided to size the fins
such that the static margin was close to 3 in the ballasted flight configuration.
3 PHYSICAL CHANGES
The only section of the rocket that was rebuilt was the lower body tube and fins. When
the body tube was manufactured the second time, a longer section of phenolic tubing
was used as the molding tool. When the motor mount was installed, the distance from
the centerline was less than 0.1 inches, corresponding to an angular error of less than
1/10th of a degree.
The linear dimensions of the fins were increased by 15%, so that when the flight motor (L1115) was loaded, the rocket had a static margin of 3. Now, the rocket reached the target altitude with no winds if 2 kg of ballast was installed on the end of the rocket. The overstability of the rocket makes it more vulnerable to weathercocking; however, the effect of weathercocking is much more easily simulated and predicted than the effects of coning, so the model will be more accurate even if the final altitude is affected more by the launch rail exit velocity. Additionally, even though the rocket experienced coning during the test flight, it was not affected by weathercocking in light winds.
4 FLIGHT RESULTS
The team traveled to Pine Island, NY to launch at METRA’s launch on April 3. Due to
the short time frame to prepare for this flight, an L1115 was unavailable. An Aerotech
M1297 was purchased ahead of time and delivered by an onsite vendor. The motor was
flown in the Cesaroni motor case, with the proper modifications for it to operate
properly. METRA’s launches are “Indy” format, thus uncertified motors are allowed.
The rocket was flown in the flight configuration for Huntsville, with 2.0 kg of ballast, a
UAV and recovery in the configuration to be flown. The UAV was attached to a
parachute as METRA rules do not allow RC vehicles to be flown at their field. The
rocket was ballasted such that it would reach 1 mile on an L1115 in mild winds. The
expected altitude in the wind conditions on site was 5,700’. The main parachute was set
to deploy at 1,000’ with a backup at 700’, instead of the 2500’ for the Huntsville flight in
order to reduce drift on the smaller field with high winds. Half-gram backup charges
under the sabot were attached to both altimeters, and helped expedite the sabot exit,
although further analysis of the March 20th flight shows they were not in fact needed.
Launch occurred at 3:00pm after 2.5 hours of integration. Winds were upwards of 17
miles per hour, and the launch rail only provided 7 feet of guidance. With a liftoff mass
of 53.0 pounds, a thrust to weight ratio of 7.5:1 and given the winds, the rocket should
have been travelling sufficiently fast upon rail exit. The motor ignited promptly, and the
rocket left the launcher with severe weathercocking. The rocket reached 3725’
according to the MAWD and deployed the drogue parachute at apogee. At 1,000’, the
sabot and main parachute deployed as planned and the rocket landed a short while
later about 1000’ downwind of the launch pad. The UAV sustained minimal damage
from being dragged in the wind by its parachute until it reached a tree line where it
stopped.
Post-flight analysis of the ARTS data shows that the M1297 performed more like an
L1037, with only 4470 of the expected 5417 Ns total impulse, or about 88%. The initial
thrust was also much slower than expected, causing the rocket to exit the rail at only
about 40 feet per second. By taking the motor profile created by the ARTS and
importing it into RockSim, the flight can accurately be recreated. This low motor
performance explains the considerable weathercocking and much lower than expected
altitude. Discussions are ongoing with Aerotech to determine what the cause of the
motor performance failure was. However, it is worth noting that flying the motor in the
uncertified case has no effects on the internal components of the motor and would not
affect motor performance.
In summary, the test flight, as expected, showed that the modifications that were made
to the rocket post-FRR solved the coning issue and did not cause any other problems
with the rocket. The flight also proved a second time that the UAV and main parachute
deployment techniques are viable and reliable, despite their complexity.
5 DRIFT CALCULATIONS
An online tool provided by Essence’s Model Rocketry Reviews & Resources1 was used
to calculate the distances that the rocket will drift under various wind conditions. The
following parameters were used:
Max Altitude 5280 ft
Drogue Descent Rate 60 ft/s
Main Deployment Alt. 2500 ft
Main Descent Rate 21 ft/s
Calculations were performed for winds of 0.5 mph, 5 mph, 10 mph, and 15 mph. The respective drift distances can be seen in the table below.
Wind Speed Drift Distance
0.5 mph 121 ft
5 mph 1212 ft
10 mph 2425 ft
15 mph 3638 ft
The code for this calculator was copied and translated into MATLAB and can be found in Appendix A of this document.
6 LIST OF RADIO FREQUENCIES USED
A list of all radio transmission frequencies being used will be submitted by 5:00pm CST
on Monday, April 11, 2011.
7 UPDATED CAD DRAWINGS
1 http://archive.rocketreviews.com/tool_drift_rate.shtml
An updated drawings package can be found in Appendix B of this document.
APPENDIX A: MATLAB CODE FOR DRIFT CALCULATIONS
clear all close all clc
%% Initial conditions MaxAlt = 5280; % Maximum altitude of rocket (ft) DrogueDescent = 60; % Descent rate under drogue parachute (ft/s) DrogueAlt = 2500; % altitude at which the main parachute is deployed (ft) MainDescent = 21; % descent rate under main parachute (ft/s) WindSpeed = 5; % launch site wind speed (mph)
% set dual deployment parameter dual = true;
%% Calculations
if dual == false Drift = (MaxAlt / MainDescent) * (WindSpeed * 1.46666666628); DriftB0 = (MaxAlt / MainDescent) * (.5 * 1.46666666628); DriftB1 = (MaxAlt / MainDescent) * (2 * 1.46666666628); DriftB2 = (MaxAlt / MainDescent) * (5 * 1.46666666628); DriftB3 = (MaxAlt / MainDescent) * (10 * 1.46666666628); DriftB4 = (MaxAlt / MainDescent) * (15 * 1.46666666628); DriftB5 = (MaxAlt / MainDescent) * (21 * 1.46666666628); elseif dual == true Drift = (((MaxAlt - DrogueAlt) / DrogueDescent) *... (WindSpeed * 1.46666666628)) + ((DrogueAlt / MainDescent) * ... (WindSpeed * 1.46666666628)); DriftB0 = (((MaxAlt - DrogueAlt) / DrogueDescent) * ... (.5 * 1.46666666628)) + ((DrogueAlt / MainDescent) * ... (.5 * 1.46666666628)); DriftB1 = (((MaxAlt - DrogueAlt) / DrogueDescent) * ... (2 * 1.46666666628)) + ((DrogueAlt / MainDescent) * ... (2 * 1.46666666628)); DriftB2 = (((MaxAlt - DrogueAlt) / DrogueDescent) * ... (5 * 1.46666666628)) + ((DrogueAlt / MainDescent) * ... (5 * 1.46666666628)); DriftB3 = (((MaxAlt - DrogueAlt) / DrogueDescent) * ... (10 * 1.46666666628)) + ((DrogueAlt / MainDescent) * ... (10 * 1.46666666628)); DriftB4 = (((MaxAlt - DrogueAlt) / DrogueDescent) * ... (15 * 1.46666666628)) + ((DrogueAlt / MainDescent) * ... (15 * 1.46666666628)); DriftB5 = (((MaxAlt - DrogueAlt) / DrogueDescent) * ... (21 * 1.46666666628)) + ((DrogueAlt / MainDescent) * ... (21 * 1.46666666628)); end
%% Results
disp(horzcat('In calm air (<1 mph) the rocket will drift ',... num2str(DriftB0),' feet'))
disp(horzcat('In light air (1 - 3 mph) the rocket will drift ',... num2str(DriftB1),' feet')) disp(horzcat('In a light breeze (4 - 7 mph) the rocket will drift ',... num2str(DriftB2),' feet')) disp(horzcat('In a gentle breeze (8 - 12 mph) the rocket will drift ',... num2str(DriftB3),' feet')) disp(horzcat('In a moderate breeze (13 - 18 mph) the rocket will drift ',... num2str(DriftB4),' feet')) disp(horzcat('In a fresh breeze (19 - 24 mph) the rocket will drift ',... num2str(DriftB5),' feet'))
APPENDIX B: CAD DRAWINGS PACKAGE
1.89
BODY TUBE: SEGMENT1
FINISH: NONE
1
MATERIAL: LAMINATE AS SPEC'D BELOW
2
1
PLY # MATERIALTHICKNESS
(IN)ORIENTATION
(DEG)NOTES
1 CARBON FIBER 11 OZ WEAVE .023 0 TOOL SIDE
2 CARBON FIBER 11 OZ WEAVE .023 0
SHEET 1 OF 1
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2 1
1
THE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ON
APPLICATION
WITHOUT THE WRITTEN PERMISSION OF
REPRODUCTION IN PART OR AS A WHOLE
UNLESS OTHERWISE SPECIFIED:
THE MITRT PROGRAM. ANY
DRAWING IS THE SOLE PROPERTY OF
SCALE: NONE
THE INFORMATION CONTAINED IN THIS
THREE PLACE DECIMAL
WEIGHT:
INTERPRET GEOMETRIC
DO NOT SCALE DRAWING
NOTES:
0.02 MITRT_Standard
DWG. NO. REV
0.005
TOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE
B
DIMENSIONS ARE IN INCHES
TOLERANCES:FRACTIONAL 0.05
ANGULAR: MACH/BEND 0.1
ONE PLACE DECIMAL 0.1TWO PLACE DECIMAL
2 01
6.16
3
4X 6-32 CLEARANCE HOLE
0.250
1.1310.00
SolidWorks Student License Academic Use Only
PAYLOAD ACCESS DOOR
4
3
5.002X THRU0.144
6.0
6.5
0.63
SCALE: NONE SHEET 1 OF 1
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3
DO NOT SCALE DRAWING
MITRT_Standard 0.005
THE MITRT PROGRAM. ANY
THE INFORMATION CONTAINED IN THIS
1
REPRODUCTION IN PART OR AS A WHOLE
THE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSYWITHOUT THE WRITTEN PERMISSION OF
0.02
B
THREE PLACE DECIMAL
INTERPRET GEOMETRIC
NOTES:
2
DWG. NO.DRAWING IS THE SOLE PROPERTY OF REV
1
UNLESS OTHERWISE SPECIFIED:
SIZE
WEIGHT:
USED ON
APPLICATION
TOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
DIMENSIONS ARE IN INCHES
TOLERANCES:FRACTIONAL 0.05
ANGULAR: MACH/BEND 0.1
ONE PLACE DECIMAL 0.1TWO PLACE DECIMAL
2 01
5
1
1
PHENOLIC COUPLER
FINISH: NONE
MATERIAL: LAMINATE AS SPEC'D BELOW
BODY TUBE: SEGMENT2
2
3 DOUBLER REGION; DROPOFF IN AT LEAST .50"
PLY # MATERIALTHICKNESS (IN)
ORIENTATION (DEG)
NOTES
1 CARBON FIBER 11 OZ WEAVE .023 0 TOOL SIDE
2 CARBON FIBER 11 OZ WEAVE .023 0
6.16
SolidWorks Student License Academic Use Only
WEIGHT:
NOTES:
D
C
B
AA
B
C
D
12345678
8 7 6 5 4
MITRT_Standard
SHEET 1 OF 1
DRAWING IS THE SOLE PROPERTY OF
1
0.02
1
REPRODUCTION IN PART OR AS A WHOLE
THE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
WITHOUT THE WRITTEN PERMISSION OF
THE INFORMATION CONTAINED IN THIS SIZETHE MITRT PROGRAM. ANY
0.005
DWG. NO.
3
THREE PLACE DECIMAL
B
UNLESS OTHERWISE SPECIFIED:
DO NOT SCALE DRAWING
2
SCALE: NONE
TITLE:
REV
INTERPRET GEOMETRIC
NEXT ASSY USED ON
APPLICATION
TOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
DIMENSIONS ARE IN INCHES
TOLERANCES:FRACTIONAL 0.05
ANGULAR: MACH/BEND 0.1
ONE PLACE DECIMAL 0.1TWO PLACE DECIMAL
2 01
2
1
FIN LAMINATE
3
FINISH: NONE
NOTE THAT CARBON FIBER LAMINATEPLIES ONLY EXTEND IN THIS REGION
1
MATERIAL: LAMINATE AS SPEC'D BELOW
PLY # MATERIALTHICKNESS
(IN)ORIENTATION
(DEG)NOTES
1 CARBON FIBER 11 OZ WEAVE .015 0
2 MDF 3/16 0
3 CARBON FIBER 11 OZ WEAVE .015 0
3
10.95
7.35
1.60
14.52
11.50
1.44
0.85
0.31
SolidWorks Student License Academic Use Only
2.97 STK
3.08 STK
26.00
MOTOR TUBE
FINISH: NONE
MATERIAL: PHENOLIC TUBE
2
1
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2 1
THE INFORMATION CONTAINED IN THISDRAWING IS THE SOLE PROPERTY OFTHE MITRT PROGRAM. ANY REPRODUCTION IN PART OR AS A WHOLEWITHOUT THE WRITTEN PERMISSION OFTHE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ON
APPLICATION
DIMENSIONS ARE IN INCHESTOLERANCES:FRACTIONAL 0.05ANGULAR: MACH/BEND 0.1ONE PLACE DECIMAL 0.1TWO PLACE DECIMAL 0.02THREE PLACE DECIMAL 0.005
INTERPRET GEOMETRICTOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE
BDWG. NO. REV
WEIGHT: SCALE: NONE
UNLESS OTHERWISE SPECIFIED:
SHEET 1 OF 1
MITRT_Standard
DO NOT SCALE DRAWING
1
2
NOTES:
01
SolidWorks Student Edition. For Academic Use Only.
3
2.5
6.0 47.0 3.05
3 INTERIOR MOLDED TO SHAPEOF UAV
SABOT
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2 1
THE INFORMATION CONTAINED IN THISDRAWING IS THE SOLE PROPERTY OFTHE MITRT PROGRAM. ANY REPRODUCTION IN PART OR AS A WHOLEWITHOUT THE WRITTEN PERMISSION OFTHE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ON
APPLICATION
DIMENSIONS ARE IN INCHESTOLERANCES:FRACTIONAL 0.05ANGULAR: MACH/BEND 0.1ONE PLACE DECIMAL 0.1TWO PLACE DECIMAL 0.02THREE PLACE DECIMAL 0.005
INTERPRET GEOMETRICTOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE
BDWG. NO. REV
WEIGHT: SCALE: NONE
UNLESS OTHERWISE SPECIFIED:
SHEET 1 OF 1
MITRT_Standard
DO NOT SCALE DRAWING
1
2
NOTES:
1
2
MATERIAL: FOAM
FINISH: NONE
01
SolidWorks Student Edition. For Academic Use Only.
A
B
B
B
C
1.854X
THRU0.50
1.75
0.397 THRU
4X 1.000
0.170 THRU
NOTES:
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2 1
1
THE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ON
APPLICATION
WITHOUT THE WRITTEN PERMISSION OF
REPRODUCTION IN PART OR AS A WHOLE
UNLESS OTHERWISE SPECIFIED:
THE MITRT PROGRAM. ANY
DRAWING IS THE SOLE PROPERTY OF
SCALE: NONE
THE INFORMATION CONTAINED IN THIS
THREE PLACE DECIMAL
WEIGHT:
INTERPRET GEOMETRIC
DO NOT SCALE DRAWING
REV
0.02 MITRT_Standard
DWG. NO.
SHEET 1 OF 1
0.005
TOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE
B
DIMENSIONS ARE IN INCHES
TOLERANCES:
FRACTIONAL 0.05
ANGULAR: MACH/BEND 0.1
ONE PLACE DECIMAL 0.1
TWO PLACE DECIMAL
2 01P/L Support Bulkhead
FINISH: NONE
MATERIAL: NYLON
2
1
0.01 A CM B
CBAM0.02
0.01 M A B C
SECTION B-B
0.750
3.000.25R
3.08
2.83
0.625 1.000
SolidWorks Student License Academic Use Only
STK6.007
6.155 STK
DWG. NO.
FINISH: NONE D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2
NOTES:
REPRODUCTION IN PART OR AS A WHOLE
THE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ONWITHOUT THE WRITTEN PERMISSION OF
1
DO NOT SCALE DRAWING
INTERPRET GEOMETRIC
1
2
THREE PLACE DECIMAL
0.02
1THE MITRT PROGRAM. ANY
DRAWING IS THE SOLE PROPERTY OF
APPLICATION
TOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE
B
UNLESS OTHERWISE SPECIFIED:
REV
WEIGHT:
MATERIAL: PHENOLIC
SCALE: NONE SHEET 1 OF 1
THE INFORMATION CONTAINED IN THIS
MITRT_Standard 0.005
DIMENSIONS ARE IN INCHES
TOLERANCES:
FRACTIONAL 0.05
ANGULAR: MACH/BEND 0.1
ONE PLACE DECIMAL 0.1
TWO PLACE DECIMAL
2
01AVIONICS TUBE
.5 2.0
6.40
.40
SolidWorks Student License Academic Use Only
0.75
1.00
0.50
3.00
R0.125 MIN
REV
CUT FILE SERVES AS PROFILE MASTER
DEFAULT DIMENSIONS AND
D
C
B
AA
B
C
D
12345678
8 7 6 5
1
2
3
REPRODUCTION IN PART OR AS A WHOLE
THE MITRT PROGRAM IS PROHIBITED.
WITHOUT THE WRITTEN PERMISSION OF 2
NOTES:
MATERIAL: AL 6061-T6
0.02
4
1
THREE PLACE DECIMAL
DO NOT SCALE DRAWING
INTERPRET GEOMETRIC
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ON
APPLICATION
TOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
SIZE
B
TITLE:
DWG. NO.
WEIGHT:
3
SCALE: NONE
PROFILE DIMENSIONS ARE REFERENCE ONLY
FINISH: NONE
2
UNLESS OTHERWISE SPECIFIED:
SHEET 1 OF 1
1
MITRT_Standard
DRAWING IS THE SOLE PROPERTY OF
THE INFORMATION CONTAINED IN THIS
THE MITRT PROGRAM. ANY
0.005
DIMENSIONS ARE IN INCHES
TOLERANCES:
FRACTIONAL 0.05
ANGULAR: MACH/BEND 0.1
ONE PLACE DECIMAL 0.1
TWO PLACE DECIMAL
4 UNLESS OTHERWISE SPECIFIED, PROFILE TOLERANCES ARE SHEET
01 SolidWorks Student License Academic Use Only
DATENAME
MITRT_Standard
DO NOT SCALE DRAWING
NOTES:
D
C
B
AA
B
C
D
12345678
8 7
SCALE: NONE WEIGHT:
0.005
4 2 1
THE INFORMATION CONTAINED IN THIS
0.02
1
WITHOUT THE WRITTEN PERMISSION OF
3
DWG. NO.THE MITRT PROGRAM. ANY
INTERPRET GEOMETRIC
TITLE:
6
THREE PLACE DECIMAL
BDRAWING IS THE SOLE PROPERTY OF REVSIZE
5
SHEET 1 OF 2
COMMENTS:
UNLESS OTHERWISE SPECIFIED:
REPRODUCTION IN PART OR AS A WHOLE
THE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ON
APPLICATION
TOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
DIMENSIONS ARE IN INCHES
TOLERANCES:
FRACTIONAL 0.05
ANGULAR: MACH/BEND 0.1
ONE PLACE DECIMAL 0.1
TWO PLACE DECIMAL
2 01SABOT HARDPOINT
MATERIAL: ALUMINUM 6061-T6
FINISH: NONE2
1
RIGHT CONFIGURATION
0.193
6.000 0.39
6.130
0.196 THRU
4X
0.290 THRU
1.00
2.38
0.50
0.386
1.25
0.196 THRU
THRU
1.50
2.00
2X 1.25
2X
2X
R0.193
SolidWorks Student License Academic Use Only
LEFT, UPPER CONFIGURATION
WEIGHT: SHEET 2 OF 2
MITRT_Standard
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2 1
TITLE:
SIZE
SCALE: NONE
DWG. NO. REV
B 01
2.25
2X 0.196 THRU
0.1932.00 R
1.50
0.20 0.50
6.130
0.193
0.396.000
0.193
6.000
0.39
6.130
LEFT, LOWER CONFIGURATION
1.50
THRU
1.25
0.193
0.196
2.00
2.25
R0.386
0.50
THRU
2X
0.20
SolidWorks Student License Academic Use Only
0.031 STKA
3.00
R1.88
2X 2.38
2X R0.38
2X 0.170 THRU
B
C
RETENTION PLATE
UNLESS OTHERWISE SPECIFIED, PROFILE TOLERANCES ARE SHEETDEFAULT DIMENSIONS AND
4
PROFILE DIMENSIONS ARE REFERENCE ONLYCUT FILE SERVES AS PROFILE MASTER
3
FINISH: NONE
MATERIAL: STAINLESS STEEL
2
1
0.02 B C0.02 A B C
0.005 M B C
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2 1
THE INFORMATION CONTAINED IN THISDRAWING IS THE SOLE PROPERTY OFTHE MITRT PROGRAM. ANY REPRODUCTION IN PART OR AS A WHOLEWITHOUT THE WRITTEN PERMISSION OFTHE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ON
APPLICATION
DIMENSIONS ARE IN INCHESTOLERANCES:FRACTIONAL 0.05ANGULAR: MACH/BEND 0.1ONE PLACE DECIMAL 0.1TWO PLACE DECIMAL 0.02THREE PLACE DECIMAL 0.005
INTERPRET GEOMETRICTOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE
BDWG. NO. REV
WEIGHT: SCALE: NONE
UNLESS OTHERWISE SPECIFIED:
SHEET 1 OF 1
MITRT_Standard
DO NOT SCALE DRAWING
1
2
NOTES:
01
SolidWorks Student Edition. For Academic Use Only.
B
C
2X
3.755.00
1.25
6.00
2X .40.402X
4X R.25 MIN
2X
.144 THRU
A
.125 STK
B C0.02 A
0.02 B C
0.01 M A B C
SCALE: NONE
DEFAULT DIMENSIONS AND
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2
CUT FILE SERVES AS PROFILE MASTERPROFILE DIMENSIONS ARE REFERENCE ONLY
FINISH: NONE
REPRODUCTION IN PART OR AS A WHOLE
THE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ONWITHOUT THE WRITTEN PERMISSION OF
3
MATERIAL: POLYCARBONATE1
1
2
NOTES:
DRAWING IS THE SOLE PROPERTY OF
APPLICATION
TOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE
BREV
WEIGHT:
UNLESS OTHERWISE SPECIFIED:
DWG. NO.
SHEET 1 OF 1
THE INFORMATION CONTAINED IN THIS
MITRT_Standard 0.005
THE MITRT PROGRAM. ANY
0.02
THREE PLACE DECIMAL
INTERPRET GEOMETRIC
DO NOT SCALE DRAWING
1
2
DIMENSIONS ARE IN INCHES
TOLERANCES:
FRACTIONAL 0.05
ANGULAR: MACH/BEND 0.1
ONE PLACE DECIMAL 0.1
TWO PLACE DECIMAL
4 UNLESS OTHERWISE SPECIFIED, PROFILE TOLERANCES ARE SHEET
01 SolidWorks Student License Academic Use Only
SCALE: NONE
MATERIAL: AL 6061-T6
FINISH: NONE D
C
B
AA
B
C
D
12345678
8 7 6 5 4
NOTES:
INTERPRET GEOMETRIC
THREE PLACE DECIMAL
2
1
REPRODUCTION IN PART OR AS A WHOLE
THE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
WITHOUT THE WRITTEN PERMISSION OF
1
SHEET 1 OF 1
DRAWING IS THE SOLE PROPERTY OF
3
0.02
THE MITRT PROGRAM. ANY
0.005
1
DO NOT SCALE DRAWING
THE INFORMATION CONTAINED IN THIS
MITRT_Standard
NEXT ASSY USED ON
APPLICATION
TOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE DWG. NO. REV
BWEIGHT:
2
UNLESS OTHERWISE SPECIFIED:
DIMENSIONS ARE IN INCHES
TOLERANCES:
FRACTIONAL 0.05
ANGULAR: MACH/BEND 0.1
ONE PLACE DECIMAL 0.1
TWO PLACE DECIMAL
2
01BOTTOM AVIONICS PLATE
BA0.01 CM
0.01 M A B C
A
6.155
.10
.25 STK 6.007
B
C
1.00
1.85
.397 2X
2X
THRU
4x .144 THRU
SolidWorks Student License Academic Use Only
0.50 STKA
6.16
3.08
B
0.50 STKA
3.08
R3.08
4X 0.20
4X 2.39
B
CENTERING RINGS
UNLESS OTHERWISE SPECIFIED, PROFILE TOLERANCES ARE SHEETDEFAULT DIMENSIONS AND
4
PROFILE DIMENSIONS ARE REFERENCE ONLYCUT FILE SERVES AS PROFILE MASTER
3
FINISH: NONE
MATERIAL: PLYWOOD
2
1
SINGLE-MOTOR, SLOTTED CONFIGURATIONSINGLE-MOTOR, UNSLOTTED CONFIGURATION
0.02 B0.02 A B
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2 1
THE INFORMATION CONTAINED IN THISDRAWING IS THE SOLE PROPERTY OFTHE MITRT PROGRAM. ANY REPRODUCTION IN PART OR AS A WHOLEWITHOUT THE WRITTEN PERMISSION OFTHE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ON
APPLICATION
DIMENSIONS ARE IN INCHESTOLERANCES:FRACTIONAL 0.05ANGULAR: MACH/BEND 0.1ONE PLACE DECIMAL 0.1TWO PLACE DECIMAL 0.02THREE PLACE DECIMAL 0.005
INTERPRET GEOMETRICTOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE
BDWG. NO. REV
WEIGHT: SCALE: NONE
UNLESS OTHERWISE SPECIFIED:
SHEET 1 OF 1
MITRT_Standard
DO NOT SCALE DRAWING
1
2
NOTES:
01
SolidWorks Student Edition. For Academic Use Only.
6.273
6.155
0.19
0.38
A
2X 2.38
2X 0.219 THRUB
C
0.50A
6.155B
MOUNTING RINGS
UNLESS OTHERWISE SPECIFIED, PROFILE TOLERANCES ARE SHEETDEFAULT DIMENSIONS AND
4
PROFILE DIMENSIONS ARE REFERENCE ONLYCUT FILE SERVES AS PROFILE MASTER
3
FINISH: NONE
MATERIAL: PLYWOOD
2
1
PROPULSION BULKHEADREAR MOUNTING RING
0.02 B C0.02 A B C
0.005 M B C
D
C
B
AA
B
C
D
12345678
8 7 6 5 4 3 2 1
THE INFORMATION CONTAINED IN THISDRAWING IS THE SOLE PROPERTY OFTHE MITRT PROGRAM. ANY REPRODUCTION IN PART OR AS A WHOLEWITHOUT THE WRITTEN PERMISSION OFTHE MITRT PROGRAM IS PROHIBITED.
PROPRIETARY AND CONFIDENTIAL
NEXT ASSY USED ON
APPLICATION
DIMENSIONS ARE IN INCHESTOLERANCES:FRACTIONAL 0.05ANGULAR: MACH/BEND 0.1ONE PLACE DECIMAL 0.1TWO PLACE DECIMAL 0.02THREE PLACE DECIMAL 0.005
INTERPRET GEOMETRICTOLERANCING PER: ASME Y14.M-2009
MATERIAL
FINISH
DRAWN
CHECKED
ENG APPR.
MFG APPR.
Q.A.
COMMENTS:
DATENAME
TITLE:
SIZE
BDWG. NO. REV
WEIGHT: SCALE: NONE
UNLESS OTHERWISE SPECIFIED:
SHEET 1 OF 1
MITRT_Standard
DO NOT SCALE DRAWING
1
2
NOTES:
01
SolidWorks Student Edition. For Academic Use Only.