High Altitude Balloon Payload Research Articles

A Platform for Active Stabilization of High-Altitude Balloon Payloads

Abstract Weather balloon payloads are commonly used by atmospheric researchers and enthusiasts to gain insight about the upper atmosphere. Balloon payloads are often unstable during flight due to high wind speeds that are experienced in both the troposphere and the lower stratosphere. High Altitude Visual Orientation Control (HAVOC) is a platform of cold-gas thrusters designed to control the azimuth of high-altitude balloon payloads to counteract high wind conditions. HAVOC’s active control scheme uses valves that direct the flow of pressurized gas into two sets of nozzles that can generate torque in either a clockwise or counterclockwise direction. This counteracts the rotation induced by wind and other forces encountered during a high-altitude balloon flight. The HAVOC design is discussed including its methods of measuring and controlling balloon payload rotation. Data from preliminary flights are presented, demonstrating the system’s ability to reduce payload rotation to a user-defined ±40° s−1 for a duration of 1 h 49 min and to maintain a fixed payload azimuth within ±30° for 1 h. In addition, we present possible uses for the HAVOC system tailored to the type of user, including atmospheric researchers, videographers, and students.

High-Altitude Astrophotography and Investigating the Ionosphere: 2020 WSGC ELIJAH High-Altitude Balloon Payload

The objective of the 2020 WSGC Elijah High-Altitude Balloon Payload Team was to design a payload intended to collect data during the total solar eclipse taking place in April 2024. The COVID-19 pandemic posed unique challenges to the research team, primarily restricting their correspondence to remote meetings and preventing them from fabricating a payload to launch for flight testing. Ground-based experimentation was conducted to analyze the viability of each of the payload modules to be constructed and launched in a future research term. Two of the four designed experiments are elaborated on in this document: an astrophotography and luminance tracking system to image celestial objects and determine the visibility of deep-space objects, and a surveillance system to identify and measure variation in magnetic fields and solar radiation in the ionosphere.

2021 Elijah High-Altitude Balloon Payload

The 2021 WSGC Elijah High-Altitude Balloon Payload Team focused their projects on the upcoming 2024 solar eclipse. These included solar sensing, solar imaging, and the study of cosmic radiation. The solar sensing project involved collecting flight data such as altitude, temperature, and pressure. In addition to this data, quantitative UVA, UVB, light intensity, and solar energy values using various sensors and solar panels. Solar imaging utilized an action camera with solar, IR, and IR cut-off filters in conjunction with a 360-degree camera that captured the entire payload’s flight. The radiation shielding project focused on studying the effectiveness of low-density polyethylene as a radiation shielding material by comparing observations collected by shielded and unshielded Geiger counters. To observe radiation originating from nearby star systems, a particle detector consisting of a scintillator coupled to a silicon photomultiplier was constructed.

2019 Elijah High Altitude Balloon Payload: Electronic Failure at Altitude, Applications of Turbulence and Sonification of Data

The 2019 WSGC Elijah High-Altitude Balloon Payload Fellowship focused on 4 high-altitude phenomena: Modular Payload Design, Applications of Air Turbulence (power generation and visualization), Electronic Behavior at Altitude, and Sonification of Atmospheric Data. Modular payload design focused on user-accessibility by creating friction-reducing rings in-between insulation and the instrumentation capsule. Height-adjustable, modular shelving was also constructed. Turbulence and Electronics project both suffered data loss during flight. However, post-flight lab analysis showed the power generation apparatus produced 96J – 120J and turbulence visualization’s potential to assist in calculating Eddie dissipation rates. Additionally, Electronic Behavior observed corona discharges across large electrical gaps near-vacuum pressures. Sonification of Data used computer algorithms to transcribe data relationships into music. The intent was to allow users to perceive data relationships and patterns aurally.

2017 WSGC Elijah High-Altitude Balloon Payload

The 2017 WSGC Elijah High-Altitude Balloon Payload Fellowship focused on three different topics for high altitude research: Modular Payload Design, Balloon Dynamics, and Energy Harvesting. A modular payload system was created using advanced manufacturing methods, which improved assembly and field operation. Minor structural fracturing was observed upon recovery. All instrumentation recovered were functioning. Vertical flight dynamics of a high-altitude balloon were studied to create a model that was compared against experimental data. Predictions did not accurately replicate GPS altitude data, possibly due to incorrect internal-balloon pressure readings and underlying assumptions. Habitability of high-altitude environments were explored by monitoring insect analog in pressurized environment. A slow pressure leak induced insects into a comatose state. Radiation was detected visually with camera.Investigated energy generation from balloon kinematics. Flight data not obtained but flight simulation data produced average voltage = 0.0039 V and total energy = 245.13 J.

2017 Elijah High-Altitude Balloon Launch Team Summer Proceedings Report

The 2017 Wisconsin Space Grant Consortium Elijah High-Altitude Balloon Launch Team was comprised of one student from Lawrence University, two students from the Milwaukee School of Engineering, and one student from the University of Wisconsin – Fox Valley. This year, three members of the team had experience with high altitude balloon launches due to previous participation on either the Elijah Payload or Launch Team, or both. A training session was hosted by Dr. Farrow to familiarize or refresh the team with the physical setup of a launch train as well as how to run track predictions and how to read the jet stream charts. Launches were planned and carried out for the Elijah High-Altitude Balloon Payload Team. This launch was successful, reaching a peak altitude of over 115,000 ft (35 km) above mean sea level.

High Altitude Balloon Payload Design for Atmospheric Observations

In 2016, Microcontroller Research Group at Dept. of Electrical Engineering Universitas Muhammadiyah Yogykarta has designed and developed a payload for High Altitude Balloon. This payload has function measuring atmospheric parameter vertically and sending the data to ground station on earth using telemetry. The parameters measured are air pressure, temperature and relative humidity. Besides sending these parameters, payload also have mission monitoring real positions of payload using GPS, real time video transmission,regulary capturing and sending image from payload . This payload is tested on the annual Atmosphere Balloon Payload Competition (KOMBAT) 2016. This paper will describe the design payload, payload software algorithms and the results that have been obtained.

Waves and Magnetism in the Solar Atmosphere (WAMIS)

Comprehensive measurements of magnetic fields in the solar corona have a long history as an important scientific goal. Besides being crucial to understanding coronal structures and the Sun’s generation of space weather, direct measurements of their strength and direction are also crucial steps in understanding observed wave motions. In this regard, the remote sensing instrumentation used to make coronal magnetic field measurements is well suited to measuring the Doppler signature of waves in the solar structures. In this paper, we describe the design and scientific values of the Waves and Magnetism in the Solar Atmosphere (WAMIS) investigation. WAMIS, taking advantage of greatly improved infrared filters and detectors, forward models, advanced diagnostic tools and inversion codes, is a long-duration high-altitude balloon payload designed to obtain a breakthrough in the measurement of coronal magnetic fields and in advancing the understanding of the interaction of these fields with space plasmas. It consists of a 20 cm aperture coronagraph with a visible-IR spectro-polarimeter focal plane assembly. The balloon altitude would provide minimum sky background and atmospheric scattering at the wavelengths in which these observations are made. It would also enable continuous measurements of the strength and direction of coronal magnetic fields without interruptions from the day-night cycle and weather. These measurements will be made over a large field-of-view allowing one to distinguish the magnetic signatures of different coronal structures, and at the spatial and temporal resolutions required to address outstanding problems in coronal physics. Additionally, WAMIS could obtain near simultaneous observations of the electron scattered K-corona for context and to obtain the electron density. These comprehensive observations are not provided by any current single ground-based or space observatory. The fundamental advancements achieved by the near-space observations of WAMIS on coronal field would point the way for future ground based and orbital instrumentation.

2015 WSGC Elijah High-Altitude Balloon Payload Project Final Report

The purpose of this report is to discuss the research, development, and findings of several experiments performed on a high-altitude balloon payload platform. The team decided on the following five experiments to be performed during the flight: Oxygen Generation, Internal Heating, Speed of Sound Properties, Ozone Levels, and a new payload structure concept. The entire team was required to research and develop new skills to effectively design our experiments, including: Arduino programming, 3-D modeling/printing, soldering, launch equipment handling, and construction techniques. While the launch was successful, we did fall short of our overall goal in terms of data acquisition. The internship proved to be a rewarding introductory experience to real-world engineering. The project help us learn how to implement the entirety of the engineering process, using each person’s strengths to achieve an objective.

2015 Elijah High Altitude Balloon Launch Team Summer Proceedings Report

The 2015 Wisconsin Space Grant Consortium Elijah High Altitude Balloon Launch Team is comprised of three students from Milwaukee School of Engineering and one student from Ripon College. This year, all members of the team had experience with high altitude balloon launches due to previous participation on either the Elijah Payload or Launch Team, or both. Despite the previous experience, a training session was hosted by the 2014 Elijah Launch Team to familiarize the new team with the physical set up of a launch train as well as how to run track predictions and how to read the jet stream charts. Launches were planned for both Carthage College and the Elijah High Altitude Balloon Payload Team, but only the launch for the Payload Team came to fruition. This launch was successful, reaching a peak altitude of 31,021m.Â

2014 WSGC Elijah High-Altitude Balloon Payload Project

The purpose of this paper is to discuss the development and findings of the experiments performed on the high altitude balloon payload. After some bonding time in the beginning of the summer, the team got together and decided on the four following experiments: Atmospheric Electric Field, Breakdown Voltage, IR Imaging, and Solar Efficiency/Payload Spin. Subsequently, research and fabrication began which involved learning new skills such as Arduino programming, 3-D modeling, foam cutting, and more. The launch was successful, and the results retrieved were more or less what were expected. This internship opportunity proved to be an amazing learning experience for the team which will be valued for each of their future career experiences.

2013 Elijah High Altitude Balloon Payload Team

Over the past ten weeks, the payload team for the Elijah High Altitude Balloon Project has researched, designed, and constructed a scientific payload that would fly to the edges of space and gather data advancing the team’s knowledge of Earth sciences, aerospace sciences, and aerospace engineering. The payload packages consisted of a sensor suite, telemetry system, Geiger counter, and camera. The telemetry system was able to provide a live data feed that interacted with existing networks to record data acting as a proof of the concept that a similar system would be viable and even suggested for future teams. The sensor suite was designed to gather data that would provide tracking data and finalize the battery experiment. While the tracking sensors were unsuccessful the thermistors and voltmeter reported data that confirmed that the various electronic components onboard were kept within their operating temperatures and gave data on the battery performance inflight. The Geiger counter data that was gathered was not able to be directly correlated with an altitude, it was able to be correlated with time, and as all data points received were on the ascent of the balloon it is possible to state that there was a positive correlation between radiation levels and altitude. The camera system that was included in the payload was able to record the entirety of the two flights and provided imagery from the edge of space. A large amount of the project was also devoted to the development of a rugged and reusable capsule; this task was accomplished by the creation of a layered capsule wall that insulated the capsule and gained increased rigidity due to the geometry of the capsule and an internal rib cage that supported plates for the electronics.Â

THE WINCUBE SATTELITE PROJECT MANITOBA HIGH SCHOOL STUDENTS CONSTRUCTING AND LAUNCHING PICO-SATELLITE AND HIGH ALTITUDE BALLOON PAYLOADS

The WinCube Satellite Project is a cooperative effort among Manitoba high schools, the Manitoba Satellite Interest group (MSIG), the Faculty of Engineering at the University of Manitoba, Maples Collegiate Space Exploration Academy, the Manitoba Aerospace Human Resources Coordinating Committee and numerous aerospace industry partners. Through a mentorship program, Manitoba high school students will design, construct, and launch a pico-satellite with technical support provided by aerospace faculty and engineering students. Basic system design and construction experience for the high school students is provided by the construction and launch of high altitude balloon payloads. Students learn first hand about space mission design, telecommunications, programming, electrical and mechanical engineering.

Balloon-borne planetary atmospheric sounder tested in the terrestrial environment

A prototype high altitude balloon payload dedicated to measuring wind characteristics, pressure and temperature in terrestrial atmospheric environments was developed as part of a National Aeronautics and Space Administration (NASA) Workforce Development Educational Grant. The WindSat as it became known was one of 15 conceptual projects suggested by various NASA agencies with this specific concept suggested by the Jet Propulsion Laboratory (JPL). The WindSat project was designed, built, and tested by the University of Colorado at Colorado Springs (UCCS) Space Grant program to determine the feasibility of obtaining atmospheric weather in the upper and lower atmosphere for entry, descent, and landing of planetary missions. In the first phase of the project described in this paper, the payload was designed for and tested in the terrestrial environment of Earth. The prototype is similar to a radiosonde in function; however, the prototype logs data at a frequency of 1 Hz to determine relative gusts and also records values on both ascent and descent through the atmosphere. Some preliminary results from the first two test flights of WindSat are given in this paper.

Linear-quadratic-regulator pointing control system for a high-altitude balloon payload

A pointing control system design for the science package of a NASA high-altitude research balloon is described. The balloon assembly consists of a single helium balloon connected to a payload recovery parachute, payload gondola, and ballast hopper. Pointing of the scientific payload is accomplished via an arrangement of drive motors and a flywheel. Linear quadratic regulator (LQR) synthesis techniques are employed to produce the azimuth and elevation controller designs. The use of LQR synthesis is motivated by the azimuthal dynamic coupling encountered between the balloon and gondola. Two control devices are employed in azimuth, one of which is a decoupler motor and the other a flywheel. The decoupler motor is intended to isolate the gondola from the balloon such that the flywheel can be accelerated or decelerated about a steady-state angular velocity to provide precise azimuthal pointing. The multiple-input/multiple-output nature of the azimuth pointing problem is best handled in a matrix synthesis procedure such as LQR. The controller design methodology is explained, and a combination of time responses and singular value analyses are used to analytically evaluate the performance of the control system. 11 refs., 17 figs.