Flight Manual

Nationwide Eclipse Ballooning Project

Arizona / NASA Space Grant Consortium

Embry-Riddle Aeronautical University Prescott, AZ

Eclipse Project Flight Manual 1

TABLE OF CONTENTS 1.0 INTRODUCTION 2

2.0 SYSTEMS DESCRIPTION 3

2.2 ASU Scientific Payload 10

2.3 Auxiliary Payloads 11

2.4 Ground Station 12

3.0 PAYLOAD OPERATION 13

3.1 Digital Video Payload 14

3.2 Digital Image Payload 20

3.3 Iridium Tracking Payload 21

3.4 Cut Down Payload 23

3.5 Battery Charging 24

4.0 GROUND STATION OPERATION 26

5.0 FLIGHT OPERATION CHECKLIST 31

5.1 Pre-Flight Checklist 31

5.2 Launch Site Checklist 34

5.3 Ground Station Checklist 37

6.0 TROUBLESHOOTING 38

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Eclipse Project Flight Manual 2

1.0 INTRODUCTION

This project is part of NASA’s Nationwide Eclipse Ballooning Project, led by Montana State University (MSU) and supported by over fifty student teams across the U.S. The primary mission is to provide NASA a live video streaming source of the moon’s shadow crossing the earth from a high-altitude balloon during the total eclipse of the sun on August 21, 2017. The secondary mission is to provide students with the opportunity to develop and fly balloon-based scientific instruments to observe effects of the eclipse.

The team is supported by Arizona / NASA Space Grant Consortium (AZSGC), which consists of students and faculty from Embry-Riddle Aeronautical University (ERAU), Prescott and Arizona State University (ASU), Tempe. ERAU works with the primary mission payloads and the ground station and ASU is responsible for a scientific payload.

The purpose of this document is to provide information about the components and usage of the payloads which will be used to carry out the project’s mission. Broadly, the project entails two systems: flight (i.e., payloads) and ground station. Descriptions of the payloads and ground station can be found in Section 2.0: Systems Description .

Detailed operation of the payloads are found in Section 3.0: Payload Operation and for the ground station in Section 4.0: Ground Station Operation . These sections are designed to give the reader an understanding of how to use each component of the system.

The flight procedure is outlined in Section 5.0: Flight Operation Checklist and serves as a checklist for pre-launch, launch, and flight. Section 6.0: Troubleshooting is provided for common error resolutions. This document was compiled by Michael Fusco, Student Intern, AZSGC; Steven Buck, Student Intern, AZSGC; and Jack Crabtree, Arizona Space Grant ASCEND Eclipse Project Manager.

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2.0 SYSTEMS DESCRIPTION The payload and ground station descriptions come from Arizona ASCEND Solar Eclipse Payloads Description by Jack Crabtree (Crabtree, 2017). Note that the original payloads were designed by Montana State University for the Nationwide Eclipse Ballooning Project, but the teams were encouraged to make improvements and/or design changes.

2.1 Primary Payloads The Primary Mission Payloads were initially constructed during a NASA sponsored Eclipse Balloon Project Workshop held at Montana State University in August of 2016. Students from Arizona State University (ASU) and Embry-Riddle Aeronautical University (ERAU) participated in the workshop with groups of students from 42 other schools to construct a common baseline set of payload modules and ground station. Since the workshop, ERAU students have been updating and improving the baseline designs to enhance the performance of the equipment. Extensive hardware and software changes to the video and image modules have been made and tested. The primary payloads consist of the following:

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2.1.1 Digital Video Payload

To fulfil the primary mission of the project, a live streaming video system is being flown. This consists of a Raspberry Pi microcomputer and PI Camera aimed at the horizon that generates live video. A 5.8 GHz Wi-Fi transceiver running about 0.5 Watts transmits the video to the ground station using a medium gain antenna. To dampen the spin of the Video Module, a system of four wooden rods about 3 feet in length with Styrofoam balls at their ends are used. This payload weighs about 1.8 kg (4 pounds).

The payload, labelled with its components, is shown in Figure 2.1: Digital Video Payload External and Figure 2.2: Digital Video Payload Internal .

Figure 2.1: Digital Video Payload External

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Figure 2.1: Digital Video Payload External shows the horizontal, front view of the payload. Call-out 1 indicates the carbon fiber rod that is used to tie the payload to the main string; call-out 2 indicates the Pi camera used to capture video; and call-out 3 indicates the L-Com antenna use to transmit the video.

Figure 2.2: Digital Video Payload Internal

Figure 2.2: Digital Video Payload Internal shows the open, top view of the payload. Call-out 1 indicates the housing for the Raspberry Pi 3 microcomputer; call-out 2 indicates the lippo battery for the payload power source; call-out 3 indicates the DC to DC power converter in series with the Pi and the battery; and call-out 4 indicates the Ubiquiti 5AC 5.8 GHz Wi-Fi transceiver.

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2.1.2 Digital Image Payload In addition to the live video, this payload takes periodic still pictures of the earth and transmits them to the ground station. Similar to the video payload, the pictures are generated by a PI Camera and a Raspberry PI. The camera alternates aiming at the ground and at the horizon. A 2.4 GHz Wi-Fi transceiver running about 0.5 Watts transmits the pictures to the ground station using a medium gain antenna. This payload weighs about 1.8 kg (4 lbs).

The payload, labelled with its components, is shown in Figure 2.3: Digital Image Payload External and Figure 2.4: Digital Image Payload Internal .

Figure 2.3: Digital Image Payload External

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Figure 2.3: Digital Image Payload External shows the horizontal view of the payload. Similar to the Digital Video Payload, the Digital Image Payload has a carbon fiber rod to attachment and and L-com antenna, indicated by call-outs 1 and 2, respectively. The image payload takes still images in two positions with the camera indicated by call-out 3. The figure shows the image in the horizontal position.

2.4: Digital Image Payload Internal

Figure 2.4: Digital Image Payload Internal shows the open, top view of the payload. The camera sits in a housing, indicated by call-out 1, and controlled by a servo motor, indicated by call-out 2. The servo alternates the camera between the down and horizontal views. Call-out 3 indicates the Pi 3 housing, and call-out 4 indicates the Ubiquiti M2 2.4 GHz Wi-Fi transceiver.

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2.1.3 Iridium Tracking Payload

To facilitate tracking by the ground station and the FAA, a GPS receiver generates balloon position data. This is transmitted to the ground by the Iridium satellite communications system. This data along with data from all the participating teams is collected on a common server and made available to the FAA and the AZ ASCEND ground station via the internet. The Iridium system also provides a channel to the balloon that passes a possible payload cut-down command to the Cut-down module. This payload weighs about 820 g (1.8 lbs). The Iridium system is shown in Figure 2.5: Iridium Tracking System :

Figure 2.5: Iridium Tracking System

(Source: Montana State University, 2017)

In Figure 2.5: Iridium Tracking System , call-out 1 shows the Iridium’s NAL antennae, call-out 2 shows the X-bee antenna used to communicate with the cutdown payload, call-out 3 indicates the MSU-built OCCAMS microcontroller, and call-out 4 indicated the Iridium modem.

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2.1.4 Cut-down Payload

FAA regulations require a means to terminate the flight in case of an emergency. If necessary a command will be sent via the Iridium communication system to the Iridium Tracking module and then relayed via a low power 2.4 GHz transceiver to the Cut-down module. Here, a rotating circular blade will be activated to sever the cord between the parachute and the balloon. It is not anticipated this function will be used. This payload weighs about 270 g (0.6 lbs). The system is shown in Figure 2.6: Cutdown Payload System .

Figure 2.6: Cutdown Payload System The Cut Down Payload also uses an X-bee antenna and OCCAMS microcontroller. The OCCAMS attaches to a servo which rotates a blade, shown as call-out 1, when activated by the Iridium Tracking Payload.

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2.2 ASU Scientific Payload The goal of the ASU Experimental Payload goal is to measure how the solar eclipse will induce changes in the atmosphere in terms of light levels, air temperature, humidity, atmospheric pressure, and wind currents. In addition to measuring heat changes in the atmosphere, a long wave infrared and visible camera will be used to visually observe how the path of totality changes the temperature on the ground. To provide better context for sensor data, a ground weather station will be used as a reference to compare to the payload sensor array, as well as an orientation sensor will be used for determining payload orientation with respect to the eclipse. This payload weighs about 1.8 kg (4 lbs). Following are the sensors implemented for this payload:

● 3 axis accelerometer measuring payload acceleration

● 3 axis gyroscope measuring spin in degrees per second

● 3 axis compass measuring the magnetic field in micro Teslas

● Accelerometer, gyro, and compass are combined to calculate 3D orientation, roll, pitch, and heading.

● Humidity sensor measuring temperature, humidity, used to calculate how hot the humidity makes it "feel" to a human touch.

● Wide range thermocouple temperature sensor capable of extreme cold

temperature measurement for the outside.

● Internal temperature sensor for measuring payload insulation failure or electronics getting too cold or hot.

● FLIR Duo infrared and visible camera for imaging and measuring

temperature dynamic temperature changes as the moon's shadow passes over the Glendo region.

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2.3 Auxiliary Payloads The following payloads will also be flown:

● ERAU 360 Degree Camera Payload : A Kodak PIXPRO 360 degree camera will fly on one of the AZ ASCEND! Balloons. This will provide a recorded view of the earth horizon to horizon throughout the flight. To minimize spin, stabilization rods with Styrofoam balls will be incorporated on this payload. To further enhance the recorded video University of Arizona students will “de-spin” the video utilizing MATLAB video utility software. Processing of the video will be done post-flight. Students from ERAU are responsible for this payload.

● Outreach Payload : The Arizona ASCEND! Team will also fly an outreach

payload from the Department of Physics and Astronomy of the University of Central Arkansas. This payload will measure pressure, temperature, and light intensity as well as GPS position including latitude, longitude and altitude in addition to taking photos. The payload will be contained in an 8in X 8in X 8in foam carton and have a mass of 700 grams (1.54 pounds).

● APRS Tracking beacons : To provide redundant tracking information for

the ground stations, four tracking beacons, two on each balloon, will accompany the flight. Redundancy is desired to counter anticipated internet congestion during the eclipse. These consist of GPS receivers, modems, and transmitters operating in the VHF amateur radio band. The signals will be used to provide pointing data for the ground station as well as position data for our chase teams to recover the payloads after the flight.

● Mode-C Transponder : In addition to using the Iridium tracking system on

one balloon, the second balloon will carry a Mode-C transponder to provide FAA with position data for safety.

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2.4 Ground Station

The Arizona ASCEND! team will use a portable ground station to track and receive the mission data from the high altitude balloons. The ground station will include the following:

● Space Grant Tracker : This component of the ground station will have a

5.8 GHz microwave high gain dish antenna and a transceiver to receive the video signal. It will automatically track the air-borne video payload using the Iridium and APRS GPS beacons. This part of the ground station was student built at the Montana State U. workshop and is common to all the eclipse teams.

● ANSR tracker : Due to the weight of the required 2.4 GHz high gain dish

antenna, a second tracking system will be implemented. This system will use the APRS signals to maintain pointing on the balloon payloads. This tracker system was assembled by ANSR members.

● Hughes Satellite Internet Terminal : To guarantee adequate internet service

in a very congested period during the eclipse, a stand-alone portable satellite internet terminal will be utilized. This terminal uses the new Hughes Internet Satellite system and will provide the bandwidth for streaming live video to the NASA and public viewers.

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