Flight Payload Research Articles

The ground calibration of the HERMES-Pathfinder payload flight models

The ground calibration of the HERMES-Pathfinder payload flight models

A fiber-optic distributed temperature sensor for continuous in situ profiling up to 2 km beneath constant-altitude scientific balloons

Abstract. A novel fiber-optic distributed temperature sensing instrument, the Fiber-optic Laser Operated Atmospheric Temperature Sensor (FLOATS), was developed for continuous in situ profiling of the atmosphere up to 2 km below constant-altitude scientific balloons. The temperature-sensing system uses a suspended fiber-optic cable and temperature-dependent scattering of pulsed laser light in the Raman regime to retrieve continuous 3 m vertical-resolution profiles at a minimum sampling period of 20 s. FLOATS was designed for operation aboard drifting super-pressure balloons in the tropical tropopause layer at altitudes around 18 km as part of the Stratéole 2 campaign. A short test flight of the system was conducted from Laramie, Wyoming, in January 2021 to check the optical, electrical, and mechanical systems at altitude and to validate a four-reference temperature calibration procedure with a fiber-optic deployment length of 1170 m. During the 4 h flight aboard a vented balloon, FLOATS retrieved temperature profiles during ascent and while at a float altitude of about 19 km. The FLOATS retrievals provided differences of less than 1.0 ∘C compared to a commercial radiosonde aboard the flight payload during ascent. At float altitude, a comparison of optical length and GPS position at the bottom of the fiber-optic revealed little to no curvature in the fiber-optic cable, suggesting that the position of any distributed temperature measurement can be effectively modeled. Comparisons of the distributed temperature retrievals to the reference temperature sensors show strong agreement with root-mean-square-error values less than 0.4 ∘C. The instrument also demonstrated good agreement with nearby meteorological observations and COSMIC-2 satellite profiles. Observations of temperature and wind perturbations compared to the nearby radiosounding profiles provide evidence of inertial gravity wave activity during the test flight. Spectral analysis of the observed temperature perturbations shows that FLOATS is an effective and pioneering tool for the investigation of small-scale gravity waves in the upper troposphere and lower stratosphere.

A Novel Mini Jet Engine Powered Unmanned Aerial Vehicle: Modeling and Control

Significant progress has been made in recent years on personal air vehicles (PAVs), which offer independent and autonomous urban transportation. On-demand parcel delivery drones and heavy-lift drones are gaining serious attention. Although various designs for these systems have been put forward, they still have not reached sufficient maturity. The current systems provide somehow satisfactory operation, but many of these systems are limited in payload capacity and flight duration, and not suitable for future operations. In this paper, we propose a novel thrust system that uses multiple mini jet engines. Unlike electric motors, the jet engine thrust cannot vary rapidly. This led us to design and develop a thrust vectoring system for each jet engine. This proposed system has the potential to enable drones to carry more payload and achieve longer flight times. This paper discusses the design and modeling of the system as well as the stabilization algorithms that satisfactorily stabilize the proposed system. We presented that due to motor lag, thrust variations cannot stabilize the vehicle. We showed that the use of a thrust vectoring mechanism with LQR-based controller can overcome the effects of motor lag and stabilize the vehicle, successfully.

Research Progress of Space Mice Flight Payload

Rodents represent one of the most important animal models in space biology experiments. Compared to other animals, the mice could better adapt to weightless conditions in space. Consequently, more and more researchers focus on the study of space mice flight payload. In the capsule, the mice would undergo a series of magical changes in the physiological behavior, the bone, and the nervous system. The experiments have shown that the research about these changes might contribute to the diagnostic of astronauts health, such as muscle atrophy. It is reported that many space mice experiments have been carried out abroad. However, China has not yet had sufficient research in this field. In order to address the problem, a large number of relevant literature were surveyed in this work. The development of various mice flight payloads and the content of the experiment were summarized in this paper. The specific contents are as follows. Firstly, the technology of mice culture on the ground was introduced, which gives a reference for the design of the flight payload. Then, five kinds of existing flight payloads abroad were discussed. Finally, the proposal for the development of domestic mice flight payload was proposed.

Design, fabrication, and characterization of a multimodal hybrid aerial underwater vehicle

Hybrid aerial underwater vehicle is a novelty able to fly and swim, which is extensively suitable for missions like water sampling, observing semi-submerged structure, and underwater exploration, etc. Motivated by the efficiency of fixed-wing unmanned aerial vehicles (UAVs) and underwater gliders in their own specific environments and the maneuverability of rotary-wing UAVs, this paper presents an improved design of a multimodal HAUV capable of level and vertical flight, hovering, and underwater glide. Specially, to balance flight payload and weight under water, an innovative configuration is proposed, which includes a newly developed lightweight pneumatic buoyancy system and excludes the linear actuator commonly used for pitch control of gliders. Moreover, motor arms can fold for better hydrodynamics. All these tradeoffs demand an adequate match between the fuselage aerodynamics and propulsion property, and special management of buoyancy and weight to guarantee predicted performances. Therefore, key design principles are proposed and elaborated. Based on the principles, a prototype, named Nezha III, was fabricated and tested. The prototype’s performance characterization in the regions of underwater, flight, and water/air transition are presented. The results demonstrate the desired performance of the prototype under different modes, and notably prove its outstanding capability of diving to 50 m depth.

Flight Performance Analysis of the Samad Attack Drones Operated by Houthi Armed Forces

In recent years, there has been a large increase in the use of uncrewed attack aircraft, or attack drones, in the Yemen conflict. At the same time, the flight endurance and payload capabilities of these uncrewed aerial vehicles seem to have increased significantly. This article presents a flight performance analysis of the Samad aircraft family operated by Ansar Allah, the Houthi rebel movement. The analysis is based on information available in the public domain and accounts for modeling uncertainties, and terrain under weather conditions typical for Yemen and Saudi Arabia. With only limited data available in the form of images, the analysis method assesses the flight performance of fixed-wing attack aircraft with high aspect ratio wings and powered by piston engines and propellers. Results demonstrate that it is highly unlikely that the Samad-2 version could reach strategic locations in Saudi Arabia when launched from Houthi-controlled territory. The analysis shows that Samad-3, however, can achieve a flight range in excess of 1800 km, bringing Riyadh and oil installations near the Persian Gulf into reach. The results of the study can be used to predict the locations from which the Samad UAV can be deployed in an attack. Furthermore, it gives insight into the increasing threat of this type of UAV when employed by non-state actors. The methods and tools developed in this study can be used to analyze the capabilities of other UAV with similar configurations.

Modal Propellant Gauging in Microgravity

Since 2008, the Modal Propellant Gauging (MPG) team, consisting of multidisciplinary undergraduate researchers from Carthage College, has been developing and testing a fuel gauging system for use in microgravity environments. Using Experimental Modal Analysis (EMA) techniques, the goal of the MPG project is to develop a flight ready technology that gauges fuel in microgravity environments by correlating the modal response of a 1-g equilibrium surface to the microgravity surface response at the same fluid fill level. The technology has been tested aboard parabolic flights via a manned parabolic flight payload. The payload consists of two propellant tanks and is designed to measure the modal response of each propellant tank to an injected white noise signal via PZT sensors. Flight data shows that the MPG method can measure fuel with greater than or equal to 1% resolution at and below 50% fill levels. Under funding from the Wisconsin Space Grant Consortium during the summer of 2018 and 2019, the MPG team made improvements to the Blue Origin New Shepard research flight payload which saw flight on the New Shepard vehicle in January of 2019 and is manifested to fly again in December of 2019.

Optimization of Shaker Locations for Multiple Shaker Environmental Testing

For flight payloads or systems in free flight, Impedance Matched Multi-Axis Testing (IMMAT) can provide an accurate laboratory reproduction of the flight vibration environment at multiple response locations. IMMAT is performed by controlling multiple shakers attached to the system of interest, usually through slender rods so that the shakers impart negligible moments or shear forces at the attachment. The attachment usually requires that the shakers not physically support the system. Thus, IMMAT is different from other multi-degree of freedom testing where shakers for slip tables or with vertical bearings drastically change the impedance by their rigid attachment to the system or payload. Consequently, IMMAT shakers are generally smaller than used for traditional testing. In the laboratory IMMAT test, bungee cords can support the system to simulate free flight. For a system that is a flight payload, bungee cords can support a portion of the next level of assembly (such as a rack or rail) with the attached payload to greatly improve the laboratory reproduction of the payload environment with the approximate attachment impedance. Engineering judgment has historically been the basis for IMMAT test planning but provides no pre-test metrics to show whether the test setup can meet the desired requirements. For successful test planning, engineers need tools to optimize the number and location of shakers and predict the requirements for the shakers and amplifiers. Electrodynamic shakers and amplifiers have physical limitations such as maximum available amplifier current, voltage or power and shaker force or stroke. If shakers and amplifiers can barely meet required levels with a well-designed IMMAT test, improper shaker placement can cause exceedance of the limitations and failure of the test to meet required levels. We present a tool to optimize the number and locations of shakers with an objective function that performs a least square fit of the flight cross spectral density matrix while minimizing requirements on the amplifiers or shakers. In this work, an optimized IMMAT test with four shakers attached to a test article closely reproduces the vibration environment generated by a field acoustic test. The optimization is based on a model. The model consists of a modal model (derived from a finite element model) of the test article coupled to a simple calibrated electro-mechanical model of the shakers. The optimization selects shaker locations to minimize the required amplifier output voltage, but one can minimize shaker force, current, control error or some combination with appropriate physical limits.

Modal Propellant Gauging - Blue Origin Payload

Since 2008, the Modal Propellant Gauging (MPG) team, consisting of multidisciplinary undergraduate researchers from Carthage College, has been developing and testing a fuel gauging system for use in microgravity environments. Using experimental modal analysis (EMA) techniques, the goal of the MPG project is to develop a flight ready technology that gauges fuel in microgravity environments by correlating the modal response of a 1-g equilibrium surface to the microgravity surface response at the same fluid fill level. The technology has been tested aboard parabolic flights via a manned parabolic flight payload. The payload consists of two propellant tanks and is designed to measure the modal response of each propellant tank to an injected white noise signal via piezoelectric sensors. Flight data shows that the MPG method can measure fuel with greater than or equal to 1% resolution at and below 50% fill levels. Under funding from the Wisconsin Space Grant Consortium during the summer of 2018, the MPG team made improvements to the Blue Origin New Shepard research flight rig which is manifested to fly in the second half of 2018.

InSight Mars Lander Robotics Instrument Deployment System

The InSight Mars Lander is equipped with an Instrument Deployment System (IDS) and science payload with accompanying auxiliary peripherals mounted on the Lander. The InSight science payload includes a seismometer (SEIS) and Wind and Thermal Shield (WTS), heat flow probe (Heat Flow and Physical Properties Package, HP3) and a precision tracking system (RISE) to measure the size and state of the core, mantle and crust of Mars. The InSight flight system is a close copy of the Mars Phoenix Lander and comprises a Lander, cruise stage, heatshield and backshell. The IDS comprises an Instrument Deployment Arm (IDA), scoop, five finger “claw” grapple, motor controller, arm-mounted Instrument Deployment Camera (IDC), lander-mounted Instrument Context Camera (ICC), and control software. IDS is responsible for the first precision robotic instrument placement and release of SEIS and HP3 on a planetary surface that will enable scientists to perform the first comprehensive surface-based geophysical investigation of Mars’ interior structure. This paper describes the design and operations of the Instrument Deployment Systems (IDS), a critical subsystem of the InSight Mars Lander necessary to achieve the primary scientific goals of the mission including robotic arm geology and physical properties (soil mechanics) investigations at the Landing site. In addition, we present test results of flight IDS Verification and Validation activities including thermal characterization and InSight 2017 Assembly, Test, and Launch Operations (ATLO), Deployment Scenario Test at Lockheed Martin, Denver, where all the flight payloads were successfully deployed with a balloon gravity offload fixture to compensate for Mars to Earth gravity.

Adaptive Control for Quadrotor UAVs Considering Time Delay: Study with Flight Payload

Adaptive Control for Quadrotor UAVs Considering Time Delay: Study with Flight Payload

Modal Propellant Gauging

Since 2011, the Modal Propellant Gauging (MPG) team, consisting of multidisciplinary undergraduate researchers from Carthage College, has been developing and testing a fuel gauging system for use in microgravity environments. Using experimental modal analysis (EMA) techniques, the goal of the MPG project is to develop a flight ready technology that gauges fuel in microgravity environments by correlating the modal response of a 1-g equilibrium surface to the microgravity surface response at the same fluid fill level. The technology has been tested aboard parabolic flights via a manned parabolic flight payload. The payload consists of two propellant tanks and is designed to measure the modal response of each propellant tank to an injected white noise signal via piezoelectric sensors. Flight data shows that the MPG method can measure fuel with greater than or equal to 1% resolution at and below 50% fill levels. Under funding from the Wisconsin Space Grant Consortium during the summer of 2017, the MPG team made improvements to the parabolic flight payload in addition to designing a new payload for use aboard a Blue Origin New Shepard research flight scheduled for the first half of 2018.

Development of Dual Power Multirotor System

Vertical take-off and landing (VTOL) aircraft has good flight characteristics and system performance without runway. The multirotor system has been tried to expand into larger size for longer endurance or higher payload. But the motor power to endurance ratio has been limited. Due to the specific energy of gasoline being much higher than battery, introducing gasoline engine into multirotor system can be considered. This paper proposes a dual power multirotor system to combine a quadrotor using gasoline engines to provide major lift in shorter arm with another quadrotor using brushless DC motors to offer most controllable force with longer arm. System design, fabrication, and verification of the proposed dual power multirotor system development are presented. Preliminary flights have achieved 16 kg payload for long endurance flight. This is useful for various applications with advanced improvements.

Finite Element Analysis of System-Level Electronic Packages for Space Applications

Thermal analysis was required in order to aid in the design and testing of a radiation tolerant computing (RTC) system using a radiation sensor. During development of the system, different test beds were employed in order to characterize the radiation sensor and its supporting electronic systems. The most common preliminary tests are high altitude balloon tests which allow the sensor to experience cosmic radiation at high altitudes, consistent with space flight operations. In this study, finite element analysis (FEA) was used to evaluate primary system architecture, system support structures, and the flight payload in order to determine if the system would survive preliminary and future testing. ANSYS FEA software was used to create thermal models which accurately simulated convective cooling, system heat generation, and solar radiation loading on the exterior of the payload. The results of the models were then used to optimize payload PC board (PCB) design to ensure that the internal electronic systems would be within acceptable operating temperatures.

Multi-instrument comparisons of D-region plasma measurements

Abstract. The ECOMA (Existence and Charge state Of Meteoric dust grains in the middle Atmosphere) series of sounding rocket flights consisted of nine flights with almost identical payload design and flight characteristics. All flights carried a radio wave propagation experiment together with a variety of plasma probes. Three of these measured electron densities, two ion densities. The rockets were all launched from the Andøya Rocket Range, Norway, in four campaigns between 2006 and 2010. Emphasis is on the final three flights from 2010 where the payloads were equipped with four instruments capable of measuring plasma densities in situ, among them a novel probe flown for the first time in conjunction with a wave propagation experiment. Deviation factors of all probe data relative to the wave propagation results were derived and revealed that none of the probe data were close to the wave propagation results at all heights, but – more importantly – the instruments showed very different behaviour at different altitudes. The novel multi-needle Langmuir probe exhibits the best correlation to the wave propagation data, as there is minimal influence of the payload potential, but it is still subject to aerodynamics, especially at its location at the rear of the payload. For all other probe types, the deviation factor comes closer to unity with increasing plasma density. No systematic difference of the empirical deviation factor between day and night can be found. The large negative payload potential in the last three flights may be the cause for discrepancies between electron and ion probe data below 85 km.

A dynamic paracellular pathway serves diuresis in mosquito Malpighian tubules

Female mosquitoes gorge on vertebrate blood, a rich nutrient source for developing eggs, but gorging meals increase the risk of predation. Mosquitoes are quick to reduce the flight payload with a potent diuresis. Diuretic peptides of the insect kinin family induce a tenfold reduction in the paracellular resistance of Malpighian tubules and increase the paracellular permeation of Cl(-), the counterion of the transepithelial secretion of Na(+) and K(+). As a result, the transepithelial secretion of NaCl and KCl and water increases. Insect kinins signal the opening of the paracellular pathway via G protein-coupled receptors and the elevation of intracellular [Ca(2+)], which leads to the reorganization of the cytoskeleton associated with the septate junction (SJ). The reorganization may affect the septate junctional proteins that control the barrier and permselectivity properties of the paracellular pathway. The proteins involved in the embryonic formation of the SJ and in epithelial polarization are largely known for ectodermal epithelia, but the proteins that form and mediate the dynamic functions of the SJ in Malpighian tubules remain to be determined.

Remote sensing of the Moon's subsurface with multifrequency microwave radiometers: A numerical study

Within the renewed interest in the study of the Moon, in 2006 the European Space Agency approved a feasibility study for the European Student Moon Orbiter (ESMO) mission. In order to accomplish the ESMO mission objectives, a Microwave Radiometric Sounder (MiWaRS) was selected as a possible payload for flight on the ESMO satellite. This work summarizes the results of a numerical analysis of MiWaRS sounding capabilities. An (inhomogeneous) multilayer model of the microwave emission from the Moon's subsurface is presented, focusing the attention on the Moon's morphological, thermal, and dielectric properties. These properties have been determined and parameterized after a thorough investigation of available measurements and models. To this end, a radiative transfer numerical model, neglecting volume scattering, is coupled with a nonlinear thermal equation to simulate the microwave emission of the Moon's subsurface. Numerical simulations between L and Ka bands are performed to investigate the capability of MiWaRS to sound the characteristics of the Moon's regolith subsurface and detect the presence of rocks and ice under the near‐surface regolith layer. Under these forward model assumptions, results show that the Moon's brightness temperature response allows the detection of discontinuities within regolith media down to 2 and 5 m depth when channels at 3 and 1 GHz are used, respectively. Lunar near‐surface temperature may be also estimated within an accuracy less than a few kelvins. The discrimination of ice from rock by MiWaRS is hardly practicable and is limited to the presence of ice in the upper layers (with a depth less than 20 cm) beneath the lunar crust.

Preparation Status of Payload Operations for the First Experiment in JEM

Japan Aerospace Exploration Agency (JAXA) is now preparing the first utilization activities in “KIBO”. JAXA already completed the hardware productions of the first experiment facilities and succeeded their launch to the International Space Station in March 2008. JAXA plans the fluid physics and material science experiments, several lifescience experiments, measurement of the radiation environment in “KIBO”, demonstration of high definition television system, some educational and commercial programs in 2008. Most of the preparation works of making the operational products for the execution of each activity have already done. The setup of the ground operation system in JAXA Tsukuba Space Center for KIBO operation was completed and the end to end communication data flow was validated. The establishment of a JAXA payload flight controller team are also undergoing right now and the general training of the team has completed.

Design of formation control laws for manoeuvred flight

AbstractThis paper presents identification, control synthesis and simulation results for an YF-22 aircraft model designed, built, and instrumented at West Virginia University. The ultimate goal of the project is the experimental demonstration of formation flight for a set of 3 of the above models. In the planned flight configuration, a pilot on the ground maintains controls of the leader aircraft while a wingman aircraft is required to maintain a pre-defined position and orientation with respect to the leader. The identification of both a linear model and a nonlinear model of the aircraft from flight data is discussed first. Then, the design of the control scheme is presented and discussed with an emphasis on the amount of information, relative to the leader aircraft, needed by the wingman to maintain formation. Using the developed nonlinear model, the control laws for a maneuvered flight of the formation are then simulated with Simulink® and displayed with the Virtual Reality Toolbox®. Simulation studies have been performed to evaluate the effects of specific parameters and the system robustness to atmospheric turbulence. The conclusions from this analysis have allowed the formulation of specific guidelines for the design of the electronic payload for formation flight.

Gravity Probe B payload verification and test program

Most of the Flight Payload hardware for the Gravity Probe B Relativity Mission is currently being manufactured. The design, fabrication, and integration of this hardware has already been subjected to an extensive program of full scale prototyping and testing in order to provide maximum assurance that the payload will meet all requirements. Full scale prototyping is considered to be a crucial aspect of the payload development because of the complexity of the payload, the stringency of its requirements, and the necessity for integration of a warm cryostat probe into a dewar maintained at liquid helium temperature. This latter requirement is derived from the fact that the dewar contains a superconducting ultralow magnetic field shield which provides an ambient magnetic field environment for the probe of < 10 pT (0.1 μG).