NUSPACE. Northeastern University Scientific Payloads: AtmosphericMeasurement and Controlled-Descent Experiment. Flight Readiness Review

Transcription

1 NUSPACE Northeastern University Scientific Payloads: AtmosphericMeasurement and Controlled-Descent Experiment Flight Readiness Review

2 Final CDLE Design

3

4

5 ATMOS Design and Dimensions ATMOS Components situated on a 5.5 x 4.25 vertical sled Component on wall Width Length Height Area (x2) Raspberry Pi in (5.588 cm) 3.35 in (8.509 cm) 0.66 in (1.68 cm) in2 (95.1 cm2) Arduino Mega 2.1 in (5.334 cm) 4.25 in ( cm) in2 (57.58 cm2) 9 Volt battery 1 in (2.54 cm) 1.9 in 0.6 in (4.826 cm) (1.524 cm) (x2) Power pack 3.6 in (9.144 cm) 1 in (2.54 cm) 1 in (2.54 cm) 1.9 in2 (12.3 cm2) 7.2 in2 (46.45 cm2)

6 FINAL LAUNCH VEHICLE

7 Launch Vehicle Specifications Vehicle Dimensions Length: 120 in. Diameter: 7.5 in. Materials Fins: G10 Fiberglass Nose cone: Polypropylene Launch Vehicle body: Blue tube Motor Recovery System: Carbon fiber Thrust-to-weight ratio: 9.08 Rail Exit velocity: 68 ft/s

8 Launch Vehicle Features Section Mass (kg) Mass (lb) Nose Cone Motor Section + Sheath The CDLE

9 Motor Selection Manufacturer Cesaroni Technologies Name L1115 Diameter 2.95 in (75 mm) Average Thrust N Maximum Thrust N Total Impulse Ns Burn Time 4.5 s Predicted Apogee: 5,432 feet Rationale: Most viable L2 motor to reach target altitude Armed Launch Vehicle Weight: 42.2 lb

10 Rocket Flight Stability The stability margin of the final competition launch vehicle is 2.16 calibers Center of gravity (CG) is located at in from the nose cone Center of pressure (CP) is located at in from the nose cone

11 Parachute Sizes and Decent Rates Section Parachute Size Shock Cord Length Terminal Velocity ft/s Nose Cone 36 in 20 ft 15.7 Sheath Motor Section 18 in (2) 20 ft (for each) 45.6 Motor Section + Sheath 72 in 40 ft 15.0 The CDLE (emergency parachute) 48 in 20 ft 21.0

12 Kinetic Energy and Projected Drifts Section Kinetic Energy Projected Drift (5, 10, 15, 20 mph wind) Nose Cone 12.3 ft-lbs ft ft ft ft Sheath 4.7 ft-lbs Motor Section ftlbs Motor Section + Sheath 65.1 ft-lbs ft ft ft ft The CDLE (emergency parachute) 71.6 ft-lbs ft ft ft ft

13 Test Plans and Procedures Tests of all electronic bays Static Piston Tests Arm Deployment Tests Quadcopter Flight Test

14 Recovery System Tests Motor Section Drogue Deployment Setup and Ejection Test

15 Full Scale Launch Results Apogee at 2933 feet Successful separations of all sections Predicted apogee at 2943 feet All charges energized at programmed altitudes Successful deployment of nose cone, mock CDLE, and drogue parachutes Main parachute deployed, did not completely unfurl All sections successfully recovered with minor damage to the motor section All sections landed within a half mile from the launch rail

16 Payload Integration Quadcopter is folded within the sheath section of the rocket The ATMOS payload is within the base of the CDLE

17 Interfacing with the Ground Systems Internal serial data connections PWM to motors Pixhawk to Radio Pixhawk to GPS MSP430 (auxiliary electronics) to Pixhawk (UART) Altimeter to MSP430 (auxiliary electronics) (I2C) From Pixhawk RFD 900 plus radio (915 MHz, 1W max) Ground link

18 Summary of Requirements Verified (LV) Requirement Verification The launch vehicle shall be designed to be recoverable and reusable. The vehicle can then be put back together for a relaunch by putting in new nylon shear screws on the parts of the rocket that separate and by repacking the parachutes, wadding and black powder. During the full scale launch the nose cone parachute and aft motor section parachutes ejected properly. The main parachute, due to improper folding, opened partially thus one of the electronic bays sustained damage. The vehicle shall deliver the payload to an apogee altitude of 5,280 feet above ground level (AGL). This was verified through tests of the apogee using the OpenRocket simulation software. This software predicts the apogee at 5,432 feet with all of the components and the L1115 motor; however, there is additional weight due to the epoxy within the sections will make the rocket s apogee be lower than the predicted height.

19 Summary of Requirements Verified (LV) The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant. The team is using a Ceseroni Technology L1115 Motor which is an approved and certified motor. It is a commercially available motor that uses APCP. This is verified through inspection of documents describing the motor. On the data sheet about this particular motor, it was described to follow these qualifications. The vehicle shall carry one commercially available, barometric altimeter for recording the official altitude used in the competition scoring. The rocket holds multiple StratoLoggers which are commercially available, barometric altimeters. Any of these could be chosen as the altimeter recording the altitude score. This was verified during tests of the subscale rockets and the full-scale rocket. These StratoLoggers each are able to collect readings based on the atmospheric pressure which was proved during these tests when they each outputted similar apogees depending on their placement within the rocket.

20 Summary of Requirements Verified (CDLE) Requirement Verification The CDLE will deploy at apogee Tested during Full scale test. A mock the CDLE with the same weight was released from the rocket at apogee using the piston system. The CDLE will transmit live flight data to ground A ground test was enacted to ensure that communications working for long distances and during flight. Initial tests with software allowed for proper transmission of GPS, altitude, and velocity data. Arms will lock into position after deployment Using a one way bearing will ensure that the arms lock into position. Ground tests were performed to verify that the arms deploy with enough force to lock. Arms locked after deployment in arm deployment prototype.

21 Summary of Requirements Verified (ATMOS) Requirement Verification Pressure Readings will be taken every ten seconds during descent and then once every minute after landing Sensor tested on the ground to verify that measurements are taken at the proper time increments. Pressure readings will be compared to accepted pressure vs altitude data. At least two pictures during descent and three after landing Images were taken using the Raspberry Pi and taken at specific intervals. This was successfully tested during a software simulation. Store Data onboard Verify data is on SD card in an easily read format. A data logging system that allows for easy postprocessing using tools such as MATLAB was created for this purpose.

22 Questions?