Rocket Payload Research Articles

A High Spectral Resolution Study of the Soft X-Ray Background with the X-Ray Quantum Calorimeter

Abstract We present here a combined analysis of four high spectral resolution observations of the Diffuse X-ray Background, made using the University of Wisconsin-Madison/Goddard Space Flight Center X-ray Quantum Calorimeter sounding rocket payload. The observed spectra support the existence of a ∼0.1 keV Local Hot Bubble and a ∼0.2 keV Hot Halo, with discrepancies between repeated observations compatible with expected contributions of time-variable emission from Solar Wind Charge Exchange. An additional component of ∼0.9 keV emission observed only at low galactic latitudes can be consistently explained by unresolved dwarf M stars.

Grating Alignment for the Water Recovery X-Ray Rocket (WRXR)

High-resolution, high-throughput soft X-ray spectroscopy using reflection gratings has the potential to unlock answers to many of the questions about the high-energy Universe. To enable missions to use this technology in the future, the ability to precisely align reflection gratings needs to be demonstrated. The Water Recovery X-ray Rocket (WRXR), a soft X-ray spectrometer that successfully launched in April 2018 from the Kwajalein Atoll, required co-aligned X-ray reflection gratings. WRXR was designed to produce a moderate-resolution spectrum of the Vela supernova remnant over a large field-of-view. The grating module was manufactured, integrated onto the rocket payload, passed environmental testing and was successfully launched and recovered. This paper describes the grating and mirror alignment methodologies for WRXR, and their inherent systematic uncertainties. Improvements to the alignment method that are required to meet the tighter alignment tolerances of future X-ray spectrometers are also discussed.

ZERODUR® based optical systems for quantum gas experiments in space

Numerous quantum technologies make use of a microgravity environment e.g. in space. Operating in this extreme environment makes high demands on the experiment and especially the laser system regarding miniaturization and power consumption as well as mechanical and thermal stability. In our systems, optical modules consisting of ZERODUR® based optical benches with free-space optics are combined with fiber components. Suitability of the technology has been demonstrated in the successful sounding rocket missions FOKUS, KALEXUS and MAIUS-1. Here, we report on our toolkit for stable optical benches including mounts, fixed and adjustable mirrors as well as polarization maintaining fiber collimators and couplers made from ZERODUR®. As an example, we present the optical modules for the scientific rocket payload of MAIUS-2, a quantum gas experiment performing dual-species atom interferometry with Bose-Einstein condensates. The modules are used on the one hand to stabilize the laser frequencies and on the other hand to distribute, overlap and switch the laser beams. This includes the overlap and joint fiber coupling of beams at 767 nm and 780 nm in the same polarization state to cool and manipulate atoms of both species simultaneously. Future projects include the development of a platform for experiments with cold atoms onboard the International Space Station. The laser system again involves ZERODUR® based optical benches in conjunction with fiber optical components. The experiment is planned as multi-user facility and currently in the design phase. The next step is to build the training, test and flight hardware.

Developing Picosatellite Flight Software

We present a decision path for creating flight software for linux-based university-class picosatellites. We favor languages and frameworks that support modularity and strong exception handling, and add that languages enabling fewer lines of code are easier to validate. Heritage and use of existing frameworks are useful but human factors-- that are often team dependent-- are more crucial for undergraduate teams. Additionally, picosatellites can benefit from “pico Agile” development methods so as to maximize time available for testing. We include case studies including core Flight Software (cFS), our C-based TrapSat sounding rocket payload, and our Python-based Cactus-1 CubeSat.

Separation Behavior Evaluation of Notched Bolt for Rocket Payload Fairing Separation System

Separation Behavior Evaluation of Notched Bolt for Rocket Payload Fairing Separation System

Remote Sensing Systems At The Rocket's Payload Test

Aviation technology and space is one of the leading technology for developed countries, especially in the form of rocket technology and payload. Countries that are capable of mastering these technologies will be respected by countries all over the world. Indonesia as the island nation and the State's large and extensive maritime already should have independence in the mastery of the technology of the rocket and payload. Therefore, continuous efforts are required to achieve independence, including through enhancing aviation technology and space technology, particularly at early stages the rocket and payload. Remote Sensing Systems At the rocket's Payload was Test remote monitoring system image capture and the attitude of the launch payload through the computer screen (display) continuously (real-time) data obtained from sensors that are mounted on the rocket's payload. 3D point (x, y, z) must be expressed as a graph visualization perspective drawings of rockets with the appropriate direction. The radar conducted computer GS (Ground Segment) or Ground Control Station (GCS). The result of the attitude of the Rocket Test launch Payloads have been able to do the communication data transmission of images and data for 3D (x, y, and z) in real-time to the Ground segment. Wireless communication uses radio telemetry frequency 433 MHz, power of 100 mW, the distance range obtained in this study a maximum of 1000 meter in conditions in the air and without obstruction.

ANALISA KONSUMSI DAYA SISTEM PELACAKAN POSISI MUATAN ROKET BERBASIS ARDUINO

This study examines the power consumption of the Arduino-based rocket payload position tracking system. The system device consists of Arduino Mega 2560, Sensor Compass, Barometer Sensor, GPS (Global Positioning System) Sensor, LCD (Liquid Crystal Display) character, Xbee-Pro 900HP, and two servo motors. Testing is done using a Digital Watt Meter tool that is able to read the voltage, current, and power used in the system. Test method by observing digital watt meter when the system runs tracking the rocket payload. Data retrieval interval is once every 10 minutes for 1 hour and calculates usage time, until the battery reaches the maximum usage limit. This research has been carried out successfully. When test performs on interval of 1 hour, the power usage by the system is 0.470 Ah until the battery voltage reaches 11.8 volts and the average power reaches 5.56 watts. Usage time of a Li-Po 1300 mAh battery is 3 hours 56 minutes until the battery voltage reaches 10.08 volts.

Blind technique for point spread function equalization with application to the Multi-Order Solar Extreme Ultraviolet Spectrograph

When combining remote sensing data from multiple instruments or multiple imaging channels, differences in point spread function (PSF) can lead to systematic error. If the PSFs are not well known, then it is difficult to determine which differences in the image data are meaningful for the object being observed and which are artifacts of PSF. Direct PSF measurements can be problematic. For example, in a sounding rocket payload, launch vibrations and acceleration, subsequent operations in micro gravity, and the impact on return to Earth may all affect PSFs. We have developed a blind method to equalize the PSFs of three distinct instrument channels, as found in the Multi-Order Solar Extreme Ultraviolet Spectrograph (MOSES). To validate our technique, we generate three synthetic images with three different PSFs, with some spectrally interesting features. Thence, we demonstrate the successful removal of PSF-induced artifacts is possible, with the genuine spectral features left intact. We also perform blind PSF equalizations on three copies of the same solar image, but with differing PSFs, after applying independent noise to each. The results accurately reproduce corrections performed in the absence of noise, with full knowledge of the PSFs. Finally, we apply PSF equalization to solar images obtained in the 2006 MOSES flight and demonstrate the removal of artifacts.

Multi-Parameter Wireless Monitoring and Telecommand of a Rocket Payload: Design and Implementation

A rocket system generally consists of two parts, the rocket motor and the payload. The payload system is built of several sensors such as accelerometer, gyroscope, magnetometer, and also a surveillance camera. These sensors are used to monitor the rocket in a three-dimensional axis which determine its attitude. Additionally, the payload must be able to perform image capturing in a certain distance using telecommand. This article is intended to describe the design and also the implementation of a rocket payload which has attitude monitoring and telecommand ability from the ground control station using a long-range wireless module Digi XBee Pro 900 HP.

Wavefront sensing in space: flight demonstration II of the PICTURE sounding rocket payload

A NASA sounding rocket for high-contrast imaging with a visible nulling coronagraph, the PICTURE payload, has made two suborbital attempts to observe the warm dust disk inferred around Epsilon Eridani. The first flight in 2011 demonstrated a 5 milliarcsecond fine pointing system in space. The reduced flight data from the second launch, on 25 November 2015, presented herein, demonstrate active sensing of wavefront phase in space. Despite several anomalies in flight, post-facto reduction phase stepping interferometer data provides insight into the wavefront sensing precision and the system stability for a portion of the pupil. These measurements show the actuation of a 32$\times$32-actuator microelectromechanical system deformable mirror. The wavefront sensor reached a median precision of 1.4 nanometers per pixel, with 95% of samples between 0.8 and 12.0 nanometers per pixel. The median system stability, including telescope and coronagraph wavefront errors other than tip, tilt, and piston, was 3.6 nanometers per pixel, with 95% of samples between 1.2 and 23.7 nanometers per pixel.

X-ray verification of an optically aligned off-plane grating module.

Off-plane x-ray reflection gratings are theoretically capable of achieving high resolution and high diffraction efficiencies over the soft x-ray bandpass, making them an ideal technology to implement on upcoming x-ray spectroscopy missions. To achieve high effective area, these gratings must be aligned into grating modules. X-ray testing was performed on an aligned grating module to assess the current optical alignment methods. Results indicate that the grating module achieved the desired alignment for an upcoming x-ray spectroscopy suborbital rocket payload with modest effective area and resolving power. These tests have also outlined a pathway towards achieving the stricter alignment tolerances of future x-ray spectrometer payloads, which require improvements in alignment metrology, grating fabrication, and testing techniques.

Predicting Electron Population Characteristics in 2‐D Using Multispectral Ground‐Based Imaging

AbstractGround‐based imaging and in situ sounding rocket data are compared to electron transport modeling for an active inverted‐V type auroral event. The Ground‐to‐Rocket Electrodynamics‐Electrons Correlative Experiment (GREECE) mission successfully launched from Poker Flat, Alaska, on 3 March 2014 at 11:09:50 UT and reached an apogee of approximately 335 km over the aurora. Multiple ground‐based electron‐multiplying charge‐coupled device (EMCCD) imagers were positioned at Venetie, Alaska, and aimed toward magnetic zenith. The imagers observed the intensity of different auroral emission lines (427.8, 557.7, and 844.6 nm) at the magnetic foot point of the rocket payload. Emission line intensity data are correlated with electron characteristics measured by the GREECE onboard electron spectrometer. A modified version of the GLobal airglOW (GLOW) model is used to estimate precipitating electron characteristics based on optical emissions. GLOW predicted the electron population characteristics with 20% error given the observed spectral intensities within 10° of magnetic zenith. Predictions are within 30% of the actual values within 20° of magnetic zenith for inverted‐V‐type aurora. Therefore, it is argued that this technique can be used, at least in certain types of aurora, such as the inverted‐V type presented here, to derive 2‐D maps of electron characteristics. These can then be used to further derive 2‐D maps of ionospheric parameters as a function of time, based solely on multispectral optical imaging data.

Model of Segmentation of Rocket Fairings Due to the Action of a Cumulative Charge

Safe separation of the rocket payload fairing is one of the most important factors that affect the success of a flight mission. In recent years, composite materials instead of aluminum alloys are widely used in rocketry. Such materials must satisfy a number of requirements that include the certainty of a local failure due to the action of a cumulative charge of the given power. To analyze this process numerical research is an advisable approach. The model of a composite rocket fairing separating due to the action of a cumulative charge has been developed. The properties of the composite material have been modeled based on the averaged characteristics obtained experimentally. The cumulative charge has been modeled by impulse loading having parameters adequate to the charge type. The time of action of the impulse, maximum pressure and width of the loading area are determined from the charge properties and geometry. The rocket fairing is considered as a composite shell composed of conical and cylindrical parts. A technique for 3D numerical analysis of the dynamic strength and structural failure has been developed. The mathematical model of the structure deformation and failure takes into account the dynamical properties of the material. The maximum plastic deformation is used as a failure criterion. The results of numerical simulation for the typical rocket payload fairing are presented.

Experimental research of thermal loading of the rocket payload fairing element during the atmospheric phase of the descent trajectory

The thermal loading physical simulation in the experimental wind tunnel on the design element of the payload fairing made of carbon fiber was done. The experimental study is given in the speed range below 70 m/s, which corresponds to the interval of heights of the descent trajectory of the payload fairing half below 10 km. The values of heat transfer coefficient are obtained. The analysis of the results is carried out.

Graphic Monitoring on Test of Rocket Launch Payload

Aviation technology and space is one of the leading technology for developed countries, especially in the form of rocket technology and charge. The countries that are capable of mastering these technologies will be respected by countries all over the world. Indonesia as the island nation with large and extensive maritime should have independence in the mastery of the technology of the rocket and payload. Therefore, continuous efforts are required to achieve independence, including through enhancing the sense of love of aviation technology and space technology, particularly at early stages the rocket and payload. Graphic Monitoring Test Rocket Launch Payload Attitude is the attitude of remote monitoring launch vehicle through the computer screen (display) continuously (real-time) data obtained from sensors-sensors that are mounted on the rocket's payload. 3D point (x, y, z) must be expressed as a graph visualization perspective drawings of rockets with the appropriate direction. The radar conducted computer GS (Ground Segment) or Ground Control Station (GCS. The result of the attitude of the Rocket Test launch Payloads have been able to communicate with the 3D data sending (x, y, and z) in real-time to the Ground segment. Wireless communication uses radio telemetry frequency 433 MHz, power of 100 mW, the distance range obtained in this study a maximum of 500 Meters in the air, without a hitch.

Temporal 3D refined simulation of SF6 release in the ionosphere

A number of significantstudies have been dedicated to SF6 releases. However, given the complicated nature, the simulations provided at the design phases are still not consistent with those diagnosed in experiments. It is mainly because the actual conditions of experiments have not been fully introduced in the state-of-art models. A temporal 3D refined simulation model of SF6 release by a rocket payload is proposed in this paper. It first considers the release status (rocket attitude, velocity, etc.), release process (duration, injection velocity, the flux of the chemical release, etc.) and ambient neutral wind. This model is better than existing ones; the latter can only deal with release from a point source. The time-dependent drift of the released cloud, driven by the velocities of the rocket inertia and neutral wind, are calculated accurately. The non-uniform spherical structure of the electron density hole driven by the lasting release along the trajectory and the injection velocity are also described. The release flow field is calculated by using a new microcell method. The temporal 3D refined model proposed could be useful for improving the diagnosis and also helpful for the theory on chemical releases.

An Observation of Very Low Frequency (VLF) Electromagnetic Waves Generated by Lightning Strikes via RockSat-X

In an attempt to observe how very low frequency (VLF) signals from lightning discharges vary as a function of altitude, a sounding rocket payload was built and launched via the Colorado Space Grant Consortium’s RockSat-X program. The main components of the payload consisted of three magnetic field antennas, two pairs of electric field plate antennas, an amplification and filtration circuit board, and two microSD cards interfaced with high performance multi-core microcontrollers for data storage. Despite a flight anomaly preventing the retrieval of the stored data, low resolution telemetry data from flight shows the expected presence power line interference.

RockOn Workshop

RockOn is a sounding rocket payload building workshop organized by the Colorado Space Grant Consortium, Virginia Space Grant Consortium, and the National Aeronautics and Space Administration's Wallops Flight Facility (WFF). Participants spend a week at WFF building, testing, and integrating a predesigned payload from a kit and see it launched at the end of the week. We attended the workshop with the support of the Wisconsin Space Grant Consortium and report our experience here. We recommend this program to others and plan to participate in the next level of the program, RockSat-C, this year.

Analysis of nozzle geometry effect on supersonic jet noise using Schlieren

Strong acoustic waves emitted from rocket plume might damage to rocket payloads because rocket payloads consist of fragile structure. Therefore, it is important to predict acoustic directivity and reduce its intensity level. In this study, we conduct experiments of supersonic jet flows and investigate an influence of the nozzle geometry on acoustic waves by means of Schlieren method and microphone measurement. Three different nozzles are examined: a conical nozzle, a convergent-divergent nozzle (referred as C-D nozzle), and a tab-C-D nozzle. Tabs are equipped in the nozzle inside and turbulence is generated in the tab-C-D nozzle case. The Schlieren visualization shows that the strong shock trains are observed in the potential core of the jet for the conical nozzle case, while the shock waves are relatively weak since the nozzles are in the nearly ideal expanded condition in the C-D nozzle and tab-C-D cases. The distribution of near field OASPL (over all sound pressure level) obtained by microphone measurement shows strong directivity in the downstream direction for all the cases. This directivity seems to be the Mach wave radiation. Moreover, conical nozzle cases have strong acoustic intensity level caused by shock associated noise.

CHISL: the combined high-resolution and imaging spectrograph for the LUVOIR surveyor

NASA is currently carrying out science and technical studies to identify its next astronomy flagship mission, slated to begin development in the 2020s. It has become clear that a Large Ultraviolet/Optical/IR (LUVOIR) surveyor mission ( d primary ≈12 m , Δλ≈1000 Å , 2 μ m spectroscopic bandpass) can carry out the largest number of NASA’s exoplanet and astrophysics science goals over the coming decades. The science grasp of an LUVOIR surveyor is broad, ranging from the direct detection of potential biomarkers on rocky planets to the flow of matter into and out of galaxies and the history of star-formation across cosmic time. There are technical challenges for several aspects of the LUVOIR surveyor concept, including component level technology readiness maturation and science instrument concepts for a broadly capable ultraviolet spectrograph. We present the scientific motivation for, and a preliminary design of, a multiplexed ultraviolet spectrograph to support both the exoplanet and astrophysics goals of the LUVOIR surveyor mission concept, the combined high-resolution and imaging spectrograph for the LUVOIR surveyor (CHISL). CHISL includes a high-resolution ( R ≈120,000 ; 1000 to 1700 Å) point-source spectroscopy channel and a medium-resolution ( R ≥ 14,000 from 1000 to 2000 Å in a single observation and R ∼ 24,000 to 35,000 in multiple grating settings) imaging spectroscopy channel. CHISL addresses topics ranging from characterizing the composition and structure of planet-forming disks to the feedback of matter between galaxies and the intergalactic medium. We present the CHISL concept, a small sample of representative science cases, and the primary technological hurdles. Technical challenges include high-efficiency ultraviolet coatings and high-quantum efficiency, large-format, photon counting detectors. We are actively engaged in laboratory and flight characterization efforts for all of these enabling technologies as components on sounding rocket payloads under development at the University of Colorado. We describe two payloads that are designed to be pathfinder instruments for the high-resolution (CHESS) and imaging spectroscopy (SISTINE) arms of CHISL. We are carrying out this instrument design, characterization, and flight-testing today to support the new start of an LUVOIR surveyor mission in the next decade.