Zaxis Acceleration and forward Airspeed Measurement for Garvey

  • Slides: 19
Download presentation
Z-axis Acceleration and forward Airspeed Measurement for Garvey P-12 A Mission

Z-axis Acceleration and forward Airspeed Measurement for Garvey P-12 A Mission

Contents o o o Garvey Spacecraft P 12 A System Objectives Requirements Design Constraints

Contents o o o Garvey Spacecraft P 12 A System Objectives Requirements Design Constraints Design n n n o C&DH Pitot-Static System Accelerometer subsystem EPS Schematics Software Architecture Risks and Mitigation 10/26/2020 2

Garvey Spacecraft P 12 A o o Garvey Spacecraft Corp. Expected to reach 10,

Garvey Spacecraft P 12 A o o Garvey Spacecraft Corp. Expected to reach 10, 000 feet 36 seconds of flight Reusable first stage 10/26/2020 3/83

Payload Integration o o XX participating universities RF emitting payloads in fairing Payload cylinder

Payload Integration o o XX participating universities RF emitting payloads in fairing Payload cylinder Payload shelves Side View 10/26/2020 faring 4/8

Objectives o o o Study Z-axis acceleration of the Garvey P-12 A flight Study

Objectives o o o Study Z-axis acceleration of the Garvey P-12 A flight Study airspeed of P-12 A flight Compare IMU data with direct airspeed information Testing Software libraries and hardware for future Kentucky Space Missions Practice design, development and testing processes 10/26/2020 5/8

Requirements o Main Requirements n n o Measure airspeed up to 500 MPH Measure

Requirements o Main Requirements n n o Measure airspeed up to 500 MPH Measure Z axis G forces up to 9 Gs Measure z-axis accelerations with a big margin for anomalies. 100 Hz sample rate Minimum Success Criteria n 10/26/2020 Successful recovery of airspeed and acceleration at 30 Hz sample rate 6/8

Design Constraints o o o Cost < $500 Time: Two week design, development and

Design Constraints o o o Cost < $500 Time: Two week design, development and testing Mass: 400 g Volume: 500 cc Staffing: 4 student team 10/26/2020 7/8

Design Overview o o o Solid-state Accelerometer on the Z-axis peak 9 G Pitot-static

Design Overview o o o Solid-state Accelerometer on the Z-axis peak 9 G Pitot-static system to measure airspeed (with differential pressure sensor) EPS: 9 V battery and 5 V and 3. 3 V regulators Ram air pressure tube Static air pressure tube 9 V Battery 5 V regulator Pitot-static Tube Differential Pressure Sensor Analog Channel 0 Analog Channel 1 3. 3 V regulator 10/26/2020 Microcontroller (MSP 430) SPI Interface Z-axis accelerometer SD Card 8/8

C&DH o MSP 430 Data logging Circuit n n n Low power 16 -bit

C&DH o MSP 430 Data logging Circuit n n n Low power 16 -bit microcontroller 8 channel 12 -bit Analog to Digital converter 2 Digital Communication ports (UART, SPI, I 2 C) Differential Pressure Sensor Z-axis accelerometer 10/26/2020 Analog Channel 0 Microcontroller (MSP 430) Analog Channel 1 SPI Interface SD Card

Pitot-Static Airspeed o Calculating Airspeed n Pitot-static equation: Source: NASA Glenn Research Center http:

Pitot-Static Airspeed o Calculating Airspeed n Pitot-static equation: Source: NASA Glenn Research Center http: //www. grc. nasa. gov/WWW/K-12/airplane/pitot. html 10/26/2020 10/8

Pitot-Static Subsystem o Pitot-tube airspeed sensor n n o Aircraft Spruce & Specialty Co.

Pitot-Static Subsystem o Pitot-tube airspeed sensor n n o Aircraft Spruce & Specialty Co. Pitot-Static tube (part number: #15144) To be mounted on the side of the rocket Pressure sensor n n n 500 MPH at 10, 000 feet would require 02. 17 PSI 15 PSI differential temperature compensate pressure sensor, with 0 -5 Volt output range. Using 0 to 2. 5 V analog to digital converter: o o 10/26/2020 o 12 bits over 0 to 7. 5 PSI effective range Maximum expected pressure: 2. 2 PSI. Sampling resolution: 0. 0018 PSI ~ 0. 2 mph 11/8

Accelerometer Subsystem n n n 2 -axis +/- 18 g accelerometer (ADXL 321) Regulated

Accelerometer Subsystem n n n 2 -axis +/- 18 g accelerometer (ADXL 321) Regulated 3. 3 Volt supply Using 0 to 2. 5 V analog to digital converter: o -18 to 14. 9 g effective range o 57 m. V/g sensor output o 12 bit Analog to Digital Converter: Sampling resolution: 0. 0107 g 10/26/2020 12/8

EPS o o o 5 Volt (LM 340 T) Voltage regulator to supply Pressure

EPS o o o 5 Volt (LM 340 T) Voltage regulator to supply Pressure sensor. 3. 3 Volt (LM 2937 ET) Voltage regulator for Accelerometer, MPS 430, SD Card. Energizer 9 V battery. 10/26/2020 13/8

Schematics – C&DH 10/26/2020 14/8

Schematics – C&DH 10/26/2020 14/8

Schematics - Sensors 10/26/2020 15/8

Schematics - Sensors 10/26/2020 15/8

Schematics - EPS 10/26/2020 16/8

Schematics - EPS 10/26/2020 16/8

Software Architecture o SW structure block diagram, A 2 D sample plan and schedule,

Software Architecture o SW structure block diagram, A 2 D sample plan and schedule, SD card libraries. Include a block diagram figure o max bandwidth to the SD. . 10/26/2020 17/8

Materials and Supplies Description Part number Price Quantity Supplier MSP 430 boards DEV-00047 $34

Materials and Supplies Description Part number Price Quantity Supplier MSP 430 boards DEV-00047 $34 1 Sparkfun SD card breakout boards BOB-00204 $18 1 Sparkfun 18 G accelerometer SEN-00848 $30 1 Sparkfun 7 Mhx oscillators X 188 -ND $4. 20 1 Digikey 5 V Regulators LM 340 T-5. 0 -ND $1. 74 1 Digikey 3. 3 V Regulators LM 2937 ET-3. 3 -ND $2. 05 1 Digikey Pressure Sensor 480 -1920 -ND $24 1 Digikey PC board V 2011 -ND $20 1 Digikey Pitot-tube #15144 $17. 75 1 Aircraft Spruce & Specialty Co. SD card sdsdb-2048 $6. 40 1 Amazon TOTAL 10/26/2020 $158. 14 18/8

Risks o o o Logistics of mounting Pitot-static tube on airframe. Tubing Surviving launch

Risks o o o Logistics of mounting Pitot-static tube on airframe. Tubing Surviving launch accelerations and vibrations Short turn-around and limited testing time. Recovery of SD card for data analysis RBF and triggering logging 19