Finally this application matrix and toolbox will be demonstrated on measurement tasks under industrial flight test conditions. Application rules for the techniques will be found and a decision matrix will be formed. The majority of advanced optical measurement techniques need similar tools to prepare, execute and evaluate effective tests.
A list of useful software tools is to be created, i. Useful tools in the toolbox will include:. Development of such a toolbox does allow users to optimise future measurement techniques in a standardised format across a range of applications. With respect to the developments in WP 2, in particular task 2. Input from task 2. The results of the test is to be compared with numerical calculations on the motor glider structural model by RUT.
But also students of aviation and space technology will be invited. Given a range of applications, the participants will then be shown how a suitable measurement technique can be chosen. In this case, hardware that has been flown on the RUT aircraft will be used to demonstrate this flight test. A special course book will be prepared for all participants. The results of WP2 and WP5 are used together with the application matrix and the tools from WP6 to complete a test on an Airbus A transport aircraft for the demonstration of combined image based flow and deformation measurements.
An attempt to install an antiskid system on the P aircraft several years ago resulted in the rupture of a number of landing gear components. The cause of this failure was connected to the landing gear geometry. Thus, simulators are now used routinely by pilots to substitute real flight hours for simulated flight hours for training for an aircraft type rating thereby reducing the cost of flight training. If the CFI presence could be reduced or eliminated for certain tasks this would mean a further cost savings to the pilot.
This would require that the flight simulator have a certain level of 'intelligence' in order to provide feedback on pilot performance similar to that of a CFI. The 'intelligent' flight simulator would have at least the capability to use data gathered from the flight to create a measure for the performance of the student pilot.
Also, to fully utilize the advances in computational power, the simulator would be capable of interacting with the student pilot using the best possible training interventions. This thesis reports on the two studies conducted at Tuskegee University investigating the effects of interventions on the learning of two flight maneuvers on a flight simulator and the robustness and accuracy of calculated performance indices as compared to CFI evaluations of performance.
The intent of these studies is to take a step in the direction of creating an 'intelligent' flight simulator. The first study deals with the comparisons of novice pilot performance trained at different levels of above real-time to execute a level S-turn. The second study examined the effect of out-of-the-window OTW visual cues in the form of hoops on the performance of novice pilots learning to fly a landing approach on the flight simulator.
Optimal starting conditions for the rendezvous maneuver: Analytical and computational approach. The three-dimensional rendezvous between two spacecraft is considered: The chaser spacecraft has variable mass, limited thrust, and its trajectory is governed by three controls, one determining the thrust magnitude and two determining the thrust direction.
We seek the time history of the controls in such a way that the propellant mass required to execute the rendezvous maneuver is minimized. Two cases are considered: The above problem has been studied by several authors under the assumption that the initial separation coordinates and the initial separation velocities are given, hence known initial conditions for the chaser spacecraft. In this paper, it is assumed that both the initial separation coordinates and initial separation velocities are free except for the requirement that the initial chaser-to-target distance is given so as to prevent the occurrence of trivial solutions.
Two approaches are employed: In Part A, analyses are performed with the multiple-subarc sequential gradient-restoration algorithm for optimal control problems. They show that the fuel-optimal trajectory is zero-bang, namely it is characterized by two subarcs: While the thrust direction of the powered subarc is continuously variable for the optimal trajectory, its replacement with a constant yet optimized thrust direction produces a very efficient guidance trajectory.
Indeed, for all values of the initial distance, the fuel required by the guidance trajectory is within less than one percent of the fuel required. Effects of maneuver dynamics on drag polars of the XA forward-swept-wing aircraft with automatic wing camber control.
A marked difference was noted between automatic wing camber control loop behavior in dynamic maneuvers and in stabilized flight conditions , which in turn affected subsonic aerodynamic performance. The degree of drag level increase was a direct function of maneuver rate. Attention is given to the aircraft flight drag polar effects of maneuver dynamics in light of wing camber control loop schedule. Increased root production in soybeans grown under space flight conditions. Protocols were designed to optimize root and shoot formation, gas exchange and moisture uniformity.
Six surface sterilized soybean seeds Glycine max cv McCall were inserted into each of 32 autoclaved plastic seed growth pouches containing an inner germination paper sleeve for a total of seeds. The pouches were stowed within a mid-deck locker until Mission Flight Day 10, at which time an astronaut added water to each pouch thereby initiating the process of seed germination on-orbit , and subsequently transferred them to four passive, light-tight aluminum canisters called BRICs Biological Research In Canisters.
We report here on the morphological characteristics of: No significant growth differences were found between the flight , ground control and clinorotated treatments for either the cotyledons or hypocotyls. There were, however, significantly longer primary roots produced in the flight population relative to the ground control population, which in turn had significantly longer primary roots than the clinorotated population. Taken together with previous literature reports, we believe that there is now sufficient evidence to conclude that plants grown under conditions of microgravity will generally exhibit enhanced root production relative to their ground control counterparts.
The mechanism underlying this phenomenon is open to speculation. Flight assessment of a large supersonic drone aircraft for research use. An assessment is made of the capabilities of the BQME supersonic drone aircraft as a test bed research vehicle. This assessment is made based on a flight conducted for the purpose of obtaining flight test measurements of wing loads at various maneuver flight conditions. Flight plan preparation, flight simulation, and conduct of the flight test are discussed along with a presentation of the test data obtained and an evaluation of how closely the flight test followed the test plan.
Improving flight condition situational awareness through Human Centered Design. In aviation, there is currently a lack of accurate and timely situational information, specifically weather data, which is essential when dealing with the unpredictable complexities that can arise while flying. For example, weather conditions that require immediate evasive action by the flight crew, such as isolated heavy rain, micro bursts, and atmospheric turbulence, require that the flight crew receive near real-time and precise information about the type, position, and intensity of those conditions.
Human factors issues arise in considering how to display the various sources of weather information to the users of that information and how to integrate this display into the existing environment. In designing weather information display systems, it is necessary to meet the demands of different users, which requires an examination of the way in which the users process and use weather information.
Using Human Centered Design methodologies and concepts will result in a safer, more efficient and more intuitive solution. Specific goals of this approach include 1 Enabling better fuel planning; 2 Allowing better divert strategies; 3 Ensuring pilots, navigators, dispatchers and mission planners are referencing weather from the same sources; 4 Improving aircrew awareness of aviation hazards such as turbulence, icing, hail and convective activity; 5 Addressing inconsistent availability of hazard forecasts outside the United States Air Defense Identification Zone ADIZ ; and 6 Promoting goal driven approaches versus event driven prediction.
Full Text Available Current fight boundary of the envelope protection in icing conditions is usually defined by the critical values of state parameters; however, such method does not take the interrelationship of each parameter and the effect of the external disturbance into consideration.
This paper proposes constructing the stability boundary of the aircraft in icing conditions through analyzing the region of attraction ROA around the equilibrium point. Nonlinear icing effect model is proposed according to existing wind tunnel test results. On this basis, the iced polynomial short period model can be deduced further to obtain the stability boundary under icing conditions using ROA analysis.
Simulation results for a series of icing severity demonstrate that, regardless of the icing severity, the boundary of the calculated ROA can be treated as an estimation of the stability boundary around an equilibrium point. The proposed methodology is believed to be a promising way for ROA analysis and stability boundary construction of the aircraft in icing conditions , and it will provide theoretical support for multiple boundary protection of icing tolerant flight. State estimation methods are popular means for validating aerodynamic database on aircraft flight maneuver performance characteristics.
In this work, the state estimation method during landing maneuver is explored for the first of its kind, using upper diagonal adaptive extended Kalman filter UD-AEKF with fuzzy based adaptive tunning of process noise matrix. The mathematical model for symmetrical landing maneuver consists of non-linear flight mechanics equation representing Aircraft longitudinal dynamics. These simulated measurement data is additively mixed with process and measurement noises, which are used as an input for UD-AEKF.
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Then, the governing states that dictate the landing loads at the instant of touch down are compared. The method is verified using flight data wherein, the vertical acceleration at the aircraft center of gravity CG is compared. Two possible outcome of purely relying on the aircraft measured data is highlighted. It is observed that, with the implementation of adaptive fuzzy logic based extended Kalman filter tuned to adapt for aircraft landing dynamics, the methodology improves the data quality of the states that are sourced from noisy measurements.
Poor weather conditions and flight operations: This paper examined various weather hazards which include thunderstorm, fog, dust haze and line squall that affect flight operation such as flight delays, diversion and cancellation. The study revealed that fog accounted for The combustion tests of the modified engine model were conducted using a large free-piston driven shock tunnel at flow conditions corresponding to the flight Mach number from 9 to CFD was also applied to the engine internal flows.
The results showed that the mixing and combustion heat release progress faster to the distance and the combustor performance similar to that of the previous engine was obtained with the modified engine. The reduction of the combustor size without the thrust performance loss is successfully achieved by applying the lower-height combustor.
Chapter 5 introduces an impulsive maneuvering strategy to deliver a spacecraft to its final Estimating maneuvers for precise relative orbit determination using GPS. Precise relative orbit determination is an essential element for the generation of science products from distributed instrumentation of formation flying satellites in low Earth orbit. In order to generate consistent and precise orbit products, a strategy for maneuver handling is mandatory in order to avoid discontinuities or precision degradation before, after and during maneuver execution.
Precise orbit determination offers the possibility of maneuver estimation in an adjustment of single-satellite trajectories using GPS measurements. However, a consistent formulation of a precise relative orbit determination scheme requires the implementation of a maneuver estimation strategy which can be used, in addition, to improve the precision of maneuver estimates by drawing upon the use of differential GPS measurements. The present study introduces a method for precise relative orbit determination based on a reduced-dynamic batch processing of differential GPS pseudorange and carrier phase measurements, which includes maneuver estimation as part of the relative orbit adjustment.
The results show the feasibility of obtaining precise relative orbits without degradation in the vicinity of maneuvers as well as improved maneuver estimates that can be used for better maneuver planning in flight dynamics operations.
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The Maneuver Automation Software MAS automates the process of generating commands for maneuvers to keep the spacecraft of the Cassini-Huygens mission on a predetermined prime mission trajectory. Before MAS became available, a team of approximately 10 members had to work about two weeks to design, test, and implement each maneuver in a process that involved running many maneuver -related application programs and then serially handing off data products to other parts of the team.
MAS enables a three-member team to design, test, and implement a maneuver in about one-half hour after Navigation has process-tracking data. MAS accepts more than 60 parameters and 22 files as input directly from users. MAS can also generate presentation materials, initiate electronic command request forms, and archive all data products for future reference.
Literature from academia, industry, and other Government agencies was surveyed to assess the state of the art in current Integrated Resilient Aircraft Control IRAC aircraft technologies. Over papers from 25 conferences from the time period to were reviewed. An assessment of the general state of the art in adaptive flight control is summarized first, followed by an assessment of the state of the art as applicable to 13 identified adverse conditions.
Specific areas addressed in the general assessment include flight control when compensating for damage or reduced performance, retrofit software upgrades to flight controllers, flight control through engine response, and finally test and validation of new adaptive controllers. The state-of-the-art assessment applicable to the adverse conditions include technologies not specifically related to flight control, but may serve as inputs to a future flight control algorithm.
Support and maneuvering device. A support and maneuvering device includes an elongated flexible inflatable enclosure having a fixed end and a movable end. The movable end is collapsible toward the fixed end to a contracted position when the enclosure is in a noninflated condition. Upon inflation, the movable end is movable away from the fixed end to an extended position. The movable end includes means for mounting an article such as a solar reflector thereon.
The device also includes a plurality of position controlling means disposed about the movable end to effect adjusting movement of portions thereof by predetermined amounts and for controlling an angle at which the article disposed at the movable end is oriented. The plurality of position controlling means limits a suitable number degrees of freedom of the movable end for transmitting a steering motion thereto and for controlling the position thereof. The position of the cockpit roll control The NASA F Intelligent Flight Control System project team developed a series of flight control concepts designed to demonstrate neural network-based adaptive controller benefits, with the objective to develop and flight -test control systems using neural network technology to optimize aircraft performance under nominal conditions and stabilize the aircraft under failure conditions.
This report presents flight -test results for an adaptive controller using stability and control derivative values from an online learning neural network. A dynamic cell structure neural network is used in conjunction with a real-time parameter identification algorithm to estimate aerodynamic stability and control derivative increments to baseline aerodynamic derivatives in flight. This open-loop flight test set was performed in preparation for a future phase in which the learning neural network and parameter identification algorithm output would provide the flight controller with aerodynamic stability and control derivative updates in near real time.
Two flight maneuvers are analyzed - pitch frequency sweep and automated flight -test maneuver designed to optimally excite the parameter identification algorithm in all axes. Frequency responses generated from flight data are compared to those obtained from nonlinear simulation runs. Flight data examination shows that addition of flight -identified aerodynamic derivative increments into the simulation improved aircraft pitch handling qualities. Normalization of informatisation parameter on airfield light-signal bar at flights in complex meteorological conditions.
Estimation of absorbed dose for poor shields under conditions of near-earth space flight. Estimation of electron absorbed dose in materials of a space vehicle for poor shields under conditions of near-earth space flight is carried out. Impact of power and angular distribution of incidence electrons and radiation scattering processes under conditions of complex geometry and multitude of materials of flight vehicle elements and nodes is studied through simulator model by example of isolating layer of aluminium-polyethylene assembly.
Maneuver from the Air Domain. The result is a proposed definition of maneuver from. Power conditioning for large dc motors for space flight applications. The design and performance of a prototype power- conditioning system for use with large brushless dc motors on NASA space missions are discussed in detail and illustrated with extensive diagrams, drawings, and graphs. The 5-kW 8-phase parallel module evaluated here would be suitable for use in the Space Shuttle Orbiter cargo bay.
A current-balancing magnetic assembly with low distributed inductance permits high-speed current switching from a low-voltage bus as well as current balancing between parallel MOSFETs. In this article, we analyze the effects of ambient light on Time of Flight ToF depth imaging for a plant's leaf in sunlight, shadow and room conditions. ToF imaging is sensitive to ambient light and we try to find the best possible integration times IT for each condition.
This is important in Canadarm2 Maneuvers Quest Airlock. American suits will not fit through Russion airlocks at the Station. The Boeing Company, the space station prime contractor, built the 6. Investigation of piloting aids for manual control of hypersonic maneuvers. An investigation of piloting aids designed to provide precise maneuver control for an air-breathing hypersonic vehicle is described. Stringent constraints and nonintuitive high-speed flight effects associated with maneuvering in the hypersonic regime raise the question of whether manual control of such a vehicle should even be considered.
The objectives of this research were to determine the extent of manual control that is desirable for a vehicle maneuvering in this regime and to identify the form of aids that must be supplied to the pilot to make such control feasible. A piloted real-time motion-based simulation of a hypersonic vehicle concept was used for this study, and the investigation focused on a single representative cruise turn maneuver. Piloting aids, which consisted of an auto throttle, throttle director, autopilot, flight director, and two head-up display configurations, were developed and evaluated.
The complete set of piloting aids, which consisted of the autothrottle, throttle director, and flight director, improved the average Cooper-Harper flying qualities ratings from 8 to 2. The flight director was determined to be the most critical of these aids, and the cruise turn maneuver was unachievable to adequate performance specifications in the absence of this flight director. Replacing manned aircraft's see-and-avoid capability in the absence of an onboard pilot is one of the key challenges associated with safe integration.
Sense-and-avoid SAA systems will have to achieve yet-to-be-determined required separation distances for a wide range of encounters. They will also need to account for the maneuver performance of the UAS they are paired with. The work described in this paper is aimed at developing an understanding of the trade space between UAS maneuver performance and SAA system performance requirements, focusing on a descent avoidance maneuver. An assessment of current manned and unmanned aircraft performance was used to establish potential UAS performance test matrix bounds.
Then, near-term UAS integration work was used to narrow down the scope. A simulator was developed with sufficient fidelity to assess SAA system performance requirements. The simulator generates closest-point-of-approach CPA data from the wide range of UAS performance models maneuvering against a single intruder with various encounter geometries. Initial attempts to model the results made it clear that developing maneuver performance groups is required. Discussion of the performance groups developed and how to know in which group an aircraft belongs for a given flight condition and encounter is included.
The groups are airplane, flight condition , and encounter specific, rather than airplane-only specific. Results and methodology for developing UAS maneuver performance requirements are presented for a descent avoidance maneuver. Results for the descent maneuver indicate that a minimum specific excess power magnitude can assure a minimum CPA for a given time-to-go prediction. However, smaller amounts of specific excess power may achieve or exceed the same CPA if the UAS has sufficient speed to trade for altitude.
The results of this study will. Flight activity and responses to climatic conditions of two subspecies of Melipona marginata Lepeletier Apidae, Meliponinae. The flight activity of two colonies of M. All colonies were hived except for one colony of M. The two subspecies showed the same responses to the climatic factors analyzed.
Flight activity was correlated positively with temperature and negatively with RH. In favorable conditions foraging took place throughout the day but both species were most active between 11 and 13 h. In the last observation period October January , when only two obscurior colonies were studied, flight activity was not correlated to RH, occurring even when RH was unfavorably high.
This was a very rainy season, and it is suggested that the behavior of the bees indicates a flexible response to prevailing weather conditions. This special condition also addresses flight control system mode annunciation. The primary objective of this research proposal was improved understanding of the fundamental vorticity and turbulent flow physics for a dynamically stalling airfoil at realistic helicopter flight conditions During the early design phase of the system, associate analysis is an essential design factor as the 1st LOI maneuver is the largest burn that utilizes the onboard propulsion system; the success of the lunar capture is directly affected by the performance achieved.
For the analysis, the spacecraft is assumed to have already approached the periselene with a hyperbolic arrival trajectory around the moon. In addition, diverse arrival conditions and mission constraints were considered, such as varying periselene approach velocity, altitude, and orbital period of the capture orbit after execution of the 1st LOI maneuver. The current analysis assumed an impulsive LOI maneuver , and two-body equations of motion were adapted to simplify the problem for a preliminary analysis. Monte Carlo simulations were performed for the statistical analysis to analyze diverse uncertainties that might arise at the moment when the maneuver is executed.
As a result, three major requirements were analyzed and estimated for the early design phase. First, the minimum requirements were estimated for the burn performance to be captured around the moon. Second, the requirements for orbit, attitude, and maneuver burn performances were simultaneously estimated and analyzed to maintain the 1st elliptical orbit achieved around the moon within the specified orbital period. Finally, the dispersion requirements on the B-plane aiming at target points to meet the target insertion goal were analyzed and can be utilized as reference target guidelines for a mid-course correction MCC maneuver during the transfer.
More detailed system requirements for the KPLO mission, particularly for the spacecraft bus itself and for the flight dynamics subsystem at the ground. Approaches in the determination of plant nutrient uptake and distribution in space flight conditions. The effective growth and development of vascular plants rely on the adequate availability of water and nutrients. Inefficiency in either the initial absorption, transportation, or distribution of these elements are factors which impinge on plant structure and metabolic integrity.
The potential effect of space flight and microgravity conditions on the efficiency of these processes is unclear.
Limitations in the available quantity of space-grown plant material and the sensitivity of routine analytical techniques have made an evaluation of these processes impractical. However, the recent introduction of new plant cultivating methodologies supporting the application of radionuclide elements and subsequent autoradiography techniques provides a highly sensitive investigative approach amenable to space flight studies.
Experiments involving the use of gel based 'nutrient packs' and the radionuclides calcium and iron were conducted on the Shuttle mission STS Uptake rates of the radionuclides between ground and flight plant material appeared comparable. Instruments on the lander, through a robotic arm able to deliver soil samples to the deck, will perform in-situ and remote-sensing investigations to characterize the chemistry of materials at the local surface, subsurface, and atmosphere. Lander instruments will also identify the potential history of key indicator elements of significance to the biological potential of Mars, including potential organics within any accessible water ice.
Precise trajectory control and targeting were necessary in order to achieve the accurate atmospheric entry conditions required for arriving at the desired landing site. The challenge for the trajectory control maneuver design was to meet or exceed these requirements in the presence of spacecraft limitations as well as other mission constraints. This paper describes the strategies used, including the specialized targeting specifically developed for PHX, in order to design and successfully execute the propulsive maneuvers that delivered the spacecraft to its targeted landing site while satisfying the planetary protection requirements in the presence of flight system constraints.
Review of Tracktable for Satellite Maneuver Detection. As a tool developed to translate geospatial data into geometrical descriptors, Tracktable offers a highly efficient means to detect anomalous flight and maritime behavior. Following the success of using geometrical descriptors for detecting anomalous trajectory behavior, the question of whether Tracktable could be used to detect satellite maneuvers arose. In answering this question, this re- port will introduce a brief description of how Tracktable has been used in the past, along with an introduction to the fundamental properties of astrodynamics for satellite trajectories.
This will then allow us to compare the two problem spaces, addressing how easily the methods used by Tracktable will translate to orbital mechanics. Based on these results, we will then be able to out- line the current limitations as well as possible path forward for using Tracktable to detect satellite maneuvers.
In , the U. Geological Survey, in cooperation with the U. Department of the Army, began an assessment of the spatial and temporal variations in precipitation, streamflow, suspended-sediment loads and yields, changes in land condition , effects of the tributaries on the Purgatoire River and the possible relation of effects from military training to hydrology and land conditions that have occurred at Pinon Canyon Maneuver Site PCMS from through Data were collected for precipitation 19 stations and streamflow and sediment load 5 tributary and 2 main-stem Purgatoire River stations during through for various time periods.
In addition, data were collected at two Purgatoire River stations: The rovers are essentially robotic geologists, sent on a mission to search for evidence in the rocks and soil pertaining to the historical presence of water and the ability to possibly sustain life. In order to conduct NASA's 'follow the water' strategy on opposite sides of the planet Mars, an interplanetary journey of over million miles culminated with historic navigation precision.
Rigorous trajectory targeting and control was necessary to achieve the atmospheric entry requirements for the selected landing sites. The propulsive maneuver design challenge was to meet or exceed these requirements while preserving the necessary design margin to accommodate additional project concerns. Landing site flexibility was maintained for both missions after launch, and even after the first trajectory correction maneuver for Spirit. The final targeting strategy was modified to improve delivery performance and reduce risk after revealing constraining trajectory control characteristics.
Flight results are examined and summarized for the six trajectory correction maneuvers that were planned for each mission. Optimizing interplanetary trajectories with deep space maneuvers. Analysis of interplanetary trajectories is a crucial area for both manned and unmanned missions of the Space Exploration Initiative. A deep space maneuver DSM can improve a trajectory in much the same way as a planetary swingby.
However, instead of using a gravitational field to alter the trajectory, the on-board propulsion system of the spacecraft is used when the vehicle is not near a planet. The purpose is to develop an algorithm to determine where and when to use deep space maneuvers to reduce the cost of a trajectory. The approach taken to solve this problem uses primer vector theory in combination with a non-linear optimizing program to minimize Delta V. A set of necessary conditions on the primer vector is shown to indicate whether a deep space maneuver will be beneficial.
Deep space maneuvers are applied to a round trip mission to Mars to determine their effect on the launch opportunities. Other studies which were performed include cycler trajectories and Mars mission abort scenarios. It was found that the software developed was able to locate quickly DSM's which lower the total Delta V on these trajectories. Flight software equations, flight test description and selected flight test data. This report describes the flight software equations of the DIALS which was designed using modern control theory direct-digital design methods and employed a constant gain Kalman filter.
- AIM² Advanced Flight Testing Workshop buy online.
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Selected flight test performance data is presented for localizer runway centerline capture and track at various intercept angles, for glideslope capture and track of 3, 4. Data is also presented to illustrate the system performance in the presence of cross, gust, and shear winds. The mean and standard deviation of the peak position errors for localizer capture were, respectively, 24 feet and 26 feet.
For mild wind conditions , glideslope and localizer tracking position errors did not exceed, respectively, 5 and 20 feet. For gusty wind conditions 8 to 10 knots , these errors were, respectively, 10 and 30 feet. Ten hands off automatic lands were performed. The standard deviation of the touchdown position and velocity errors from the mean values were, respectively, feet and 0.
Uncertainties in hover and high-speed data are characterized. The results are reported here to provide guidance for future wind tunnel tests, data processing, and data analysis. Studies on gene expressions analyses for Arabidopsis thaliana plants stimulated by space flight condition. We carried out whole-genome microarray to screen the transcript profile of Arabidopsis thaliana seedlings after three treatment: The result of microarray analysis is as followed: There were genes significantly differentially expressed in space microgravity condition compared with that in 1g centrifuge space condition.
Space radiation caused genes significantly differentially expressed between seedlings in 1g centrifuge space condition and ground control. Space conditions including microgravity and radiation caused genes significantly differentially expressed between seedlings in space microgravity condition and ground control.
Microgravity and radiation as a single factor can cause plant gene expression change, but two factors synergism can produce some new effects on plant gene expression. The function of differential expression genes were analyst by bioinformatics, and we found the expression of genes related with stress were more different, such as the dehydration of protein dehydrin Xero2 expression is up-regulated 57 times; low-temperature-induced protein expression is up-regulated in 49 times; heat shock protein expression is up-regulated 20 times; transcription factor DREB2A expression increase 25 times; protein phosphatase 2C expression is up-regulated 14 times; transcription factor NAM-like protein expression is up-regulated 13 times; cell wall metabolism related genes xyloglucan, endo-1, 4-beta-D-glucanase expression is down-regulated in 15 times.
The results provide scientific data for the mechanism of space mutation. The applicable airworthiness regulations do not contain adequate or This system provides an electronic interface between the pilot's flight controls and the flight control Associating crash avoidance maneuvers with driver attributes and accident characteristics: The current study focuses on the propensity of drivers to engage in crash avoidance maneuvers in relation to driver attributes, critical events, crash characteristics, vehicles involved, road characteristics, and environmental conditions.
The importance of avoidance maneuvers derives from the key role of proactive and state-aware road users within the concept of sustainable safety systems, as well as from the key role of effective corrective maneuvers in the success of automated in-vehicle warning and driver assistance systems. The analysis is conducted by means of a mixed logit model that represents the selection among 5 emergency lateral and speed control maneuvers i. Data for the analysis were retrieved from the General Estimates System GES crash database for the year by considering drivers for which crash avoidance maneuvers are known.
The results show that 1 the nature of the critical event that made the crash imminent greatly influences the choice of crash avoidance maneuvers , 2 women and elderly have a relatively lower propensity to conduct crash avoidance maneuvers , 3 drowsiness and fatigue have a greater negative marginal effect on the tendency to engage in crash avoidance maneuvers than alcohol and drug consumption, 4 difficult road conditions increase the propensity to perform crash avoidance maneuvers , and 5 visual obstruction and artificial illumination decrease the probability to carry out crash avoidance maneuvers.
- What is Kobo Super Points?.
- Handbook of Advanced In-Flight Measurement Techniques?
- Task 6.1. Creation of an Application Matrix for the advanced in-flight measurement techniques.
- Task 6.2. Development of useful tools for advanced in-flight measurement techniques.
The results emphasize the need for public awareness campaigns to promote safe driving style for senior drivers and warning about the risks of driving under fatigue and distraction being comparable to the risks of driving under the influence of alcohol and drugs. Moreover, the results suggest the need to educate drivers about hazard perception, designing. Numerical simulations of unsteady flows past two-bladed rotors in forward- flight conditions. The current paper presents time-accurate numerical simulations of compressible flows past two-bladed rotor configurations using a Chimera moving grid approach.
The simulations are performed for a variety of flow conditions and various blade aspect ratios. The rotor blades are rectangular, untapered and untwisted planforms. Their cross-sections are built using the NACA airfoil profile. The aerodynamic performance of the rotor is investigated using the Euler equations.
The pressure distributions are benchmarked against the experimental data from Caradonna and Tung and a number of previous Euler calculations by Agarwal and Deese and Chen et al. The comparisons indicate that the current simulations for the forward flight conditions can reproduce the pressure distributions on the blade surfaces and the prediction of shockwave locations with reasonably good accuracy. Study on the high speed scramjet characteristics at Mach 10 to 15 flight condition.
A scramjet engine model, designed to establish steady and strong combustion at free-stream conditions corresponding to Mach 12 flight , was tested in a large free-piston driven shock tunnel. Combustion tests of a previous engine model showed that combustion heat release obtained in the combustor was not sufficient to maintain strong combustion. For a new scramjet engine model, the inlet compression ratio was increased to raise the static temperature and density of the flow at the combustor entrance.
As a result of the aerodynamic design change, the pressure rise due to combustion increased and the duration of strong combustion conditions in the combustor was extended. A hyper-mixer injector designed to enhance mixing and combustion by introducing streamwise vortices was applied to the new engine model.
The results showed that the hyper mixer injector was very effective in promoting combustion heat release and establishing steady and strong combustion in the combustor. Ship maneuvering digital simulator; Simulador digital de manobras de navios. This paper reports on two case studies making use of a digital simulator to investigate the maneuvering motions of ships in canals with shallow and restricted waters. The first case study corresponds to a maneuvering analysis conducted for the Port of Rio Grande RS - Brazil , whose aim was to assess the potential impact upon maneuvers of the presence of a large offshore platform the PETROBRAS P which is to remain docked for several months at the Port to complete its construction.
The second study made use of the simulator to evaluate the maneuvering conditions along the approach route and maneuvering basin of the Port of Ponta do Felix PR - Brazil. The simulator includes a complete mathematical model of the ship dynamics in the horizontal plane when subjected to wind and current forces. It also comprises detailed models for the action of thrusters and propellers, both fixed and azimuth, employed to control maneuvers and dynamically position ships, as well as rudders and tugboats.
He models used by the simulator allow for the effects of shallow and restricted waters, including the increase in resistance and lateral forces, increase in additional mass and the appearance of lateral and vertical suction squatting. The simulator is implemented via an interactive interface through which the user is able to apply control actions rudder angle, main engine, thrusters and tugboats in real time during maneuvers , thereby reproducing to some extent the action of a pilot. The groups are specific to airplane, flight condition , and encounter, rather than airplane-only specific.
Results and methodology for developing UAS maneuver performance requirements are presented for each maneuver as well. Results for the vertical maneuver indicate that a minimum specific excess power value can assure a minimum CPA for a given time-to-go prediction. However, smaller values of specific excess power may achieve or exceed the same CPA if the UAS has sufficient speed to trade for altitude.
Level turn results are less impacted by specific excess power and are presented as a function of turn rate. The effect of altitude is also discussed for the turns. Next steps and future work are discussed. Future studies will lead to better quantification of the preliminary results and cover the remainder of the proposed test matrix.
For some years now, UAVs unmanned aerial vehicles are commonly used for different mobile mapping applications, such as in the fields of surveying, mining or archeology. To improve the efficiency of these applications an automation of the flight as well as the processing of the collected data is currently aimed at. One precondition for an automated mapping with UAVs is that the georeferencing is performed directly with cm-accuracies or better. Usually, a cm-accurate direct positioning of UAVs is based on an onboard multi-sensor system, which consists of an RTK-capable real-time kinematic GPS global positioning system receiver and additional sensors e.
In this case, the absolute positioning accuracy essentially depends on the local GPS measurement conditions. Especially during mobile mapping applications in urban areas, these conditions can be very challenging, due to a satellite shadowing, non-line-of sight receptions, signal diffraction or multipath effects. In this paper, two straightforward and easy to implement strategies will be described and analyzed, which improve the direct positioning accuracies for UAV-based mapping and surveying applications under challenging GPS measurement conditions.
Based on a 3D model of the surrounding buildings and vegetation in the area of interest, a GPS geometry map is determined, which can be integrated in the flight planning process, to avoid GPS challenging environments as far as possible.
maneuvering flight conditions: Topics by theranchhands.com
Simulations and results of field tests demonstrate the profit of both strategies. Orbital maneuvering end effectors. This invention relates to an end effector device for grasping and maneuvering objects such as berthing handles of a space telescope. The device includes a V-shaped capture window defined as inclined surfaces in parallel face plates which converge toward a retainer recess in which the handle is retained.
A pivotal finger 30 meshes with a pair of pivoted fingers which rotate in counterrotation. The fingers rotate to pull a handle within the capture window into recess where latches lock handle in the recess. To align the capture window, plates may be cocked plus or minus five degrees on base. Drive means is included in the form of a motor coupled with a harmonic drive speed reducer, which provides for slow movement of the fingers at a high torque so that large articles may be handled. Novelty of the invention is believed to reside in the combined intermeshing finger structure, drive means and the harmonic drive speed reducer, which features provide the required maneuverability and strength.
Pressure-volume-temperature gauging method experiment using liquid nitrogen under microgravity condition of parabolic flight. Measuring an exact amount of remaining cryogenic liquid propellant under microgravity condition is one of the important issues of rocket vehicle. A Pressure-Volume-Temperature PVT gauging method is attractive due to its minimal additional hardware and simple gauging process.
In this paper, PVT gauging method using liquid nitrogen is investigated under microgravity condition with parabolic flight. During microgravity condition , the inside of the liquid tank becomes near-isothermal condition within 1 K difference indicated by 6 silicon diode sensors vertically distributed in the middle of the liquid tank. Helium injection with higher mass flow rate after 10 seconds of the waiting time results in successful measurements of helium partial pressure in the tank. As a result, the applicability of PVT gauging method to liquid. These design features include an electronic flight control system Design Features The GVI has an electronic flight control system and no direct coupling from the cockpit Dynamics and cultural specifics of information needs under conditions of long-term space flight.
Life in conditions of space flight or chamber study with prolonged isolation is associated with lack of familiar stimuli sensory deprivation , monotony, significant limitation of communication, and deficit of information and media content Myasnikov V. Fulfillment of a simulation experiment or flight schedule implies necessity of performance of sophisticated tasks and decision making with limited means of external support. Thus, we suppose that one of the important goals of psychological support of space or space simulation crews should be forming of favorable conditions of information environment.
For that purpose, means of crew-MC information exchange quantitative characteristics and, if possible, content of radiograms, text and video messages, etc. In the space simulation experiment with day isolation, communication of international crew with external parties had been studied. It was shown that characteristics of information exchange. Emerald ash borer, Agrilus planipennis Fairmaire Coleoptera: Buprestidae , an invasive beetle from Asia, spreads through human-mediated movement and active flight. The effects of adult feeding and overwintering conditions on A. We conjectured that the potential energetic demands associated with the production of cryoprotectants might affect dispersal capacity and partially explain slower spread of A.
Two studies sought to measure the effects of adult feeding on lipid content and flight capacity. The second study compared the effects of adult feeding on energy reserves and flight capacity of A. Live adults consumed foliage at a constant rate, but lipid content percentage of fresh mass did not change with increases in feeding or flight. Adult glycogen content declined with flight and increased only slightly with feeding. Overwintering location affected survival rates but not energy reserves or flight capacity.
These results suggest that the flight capacity of A. The method using dynamic programming provides planning of aircraft conflict-free trajectory with minimum length. Full Text Available The article deals with methods of forecasting the level of aviation safety operation of aircraft systems on the basis of methods of evaluation the risks of negative situations as a consequence of a functional loss of initial properties of the system with critical violations of standard modes of the aircraft. The assessment of the level of safety and quality and management of aircraft, made not only from the standpoint of reliability quality and consumer properties, but also from the position of ICAO on the basis of a risk-based approach.
According to ICAO, the security assessment is performed by comparing the calculated risk with an acceptable level. The approach justifies the use of qualitative evaluation techniques safety in the forms of proactive forecasted and predictive risk management adverse impacts to aviation operations of various kinds, including the space sector and nuclear energy.
However, for the events such as accidents and disasters, accidents with the aircraft, fighters in a training flight , during the preparation of the pilots on the training aircraft, etc. Density of probability distribution p. Measurement of bullet impact conditions using automated in- flight photography system. Full Text Available Knowledge of impact conditions is critical to evaluating the terminal impact performance of a projectile.
For a small caliber bullet, in- flight velocity has been precisely measured for decades using detection screens, but accurately quantifying the orientation of the bullet on a target has been more challenging. This report introduces the Automated Small-Arms Photogrammetry ASAP analysis method used to measure, model, and predict the orientation of a small caliber bullet before reaching an impact surface.
ASAP uses advanced hardware developed by Sydor Technologies to record a series of infrared digital photographs. Individual images four orthogonal pairs are processed using computer vision algorithms to quantify the orientation of the projectile and re-project its precise position and orientation into a three-dimensional muzzle-fixed coordinate system. An epicyclic motion model is fit to the measured data, and the epicyclic motion is extrapolated to the target location. Analysis results are fairly immediate and may be reviewed during testing.
Prove-out demonstrations have shown that the impact-angle prediction capability is less than six hundredths of a degree for the 5. Improved Maneuver Criteria Evaluation Program. These comparisons show that the MCEP maneuvers are accurate for simulating these types of maneuvers. The applicable airworthiness regulations do Rendezvous maneuvers using Genetic Algorithm. The present paper has the goal of studying orbital maneuvers of Rendezvous, that is an orbital transfer where a spacecraft has to change its orbit to meet with another spacecraft that is travelling in another orbit. This transfer will be accomplished by using a multi-impulsive control.
A genetic algorithm is used to find the transfers that have minimum fuel consumption. Flow simulations past helicopters at different flight conditions using low and high order CFD methods. The present paper contains a comprehensive literature survey on helicopter flow analyses and describes some true unsteady flows past helicopter rotors obtained using low and high order CFD models.
The low order model is based on a panel method coupled with a viscous boundary layer approach and a compressibility correction. The high order model is based on Euler and Navier-Stokes equations.
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On the other hand, a quasi-steady approach, using the WIND code with the Navier-Stokes equations and the SST turbulence model, is used to assess the validity of the approach for the simulation of flows past a helicopter in forward flight conditions. When using the high order models, a Chimera grid technique is used to describe the blade motions within the parent stationary grid.
Comparisons with experimental data are performed and the true unsteady simulations provide a reasonable agreement with the available experimental data. The panel method and the quasisteady approach are found to overestimate the loads on the helicopter rotors. The USAERO panel code is found to produce more thrust owing to some error sources in the computations when a wake-surface collision occurs, as the blades interact with their own wakes.
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The automatic cutting of the wake sheets, as they approach the model surface, is not working properly at every time step. Control-oriented reduced order modeling of dipteran flapping flight. Flying insects achieve flight stabilization and control in a manner that requires only small, specialized neural structures to perform the essential components of sensing and feedback, achieving unparalleled levels of robust aerobatic flight on limited computational resources. An engineering mechanism to replicate these control strategies could provide a dramatic increase in the mobility of small scale aerial robotics, but a formal investigation has not yet yielded tools that both quantitatively and intuitively explain flapping wing flight as an "input-output" relationship.
This work uses experimental and simulated measurements of insect flight to create reduced order flight dynamics models. The framework presented here creates models that are relevant for the study of control properties. The work begins with automated measurement of insect wing motions in free flight , which are then used to calculate flight forces via an empirically-derived aerodynamics model. When paired with rigid body dynamics and experimentally measured state feedback, both the bare airframe and closed loop systems may be analyzed using frequency domain system identification.
Flight dynamics models describing maneuvering about hover and cruise conditions are presented for example fruit flies Drosophila melanogaster and blowflies Calliphorids. The results show that biologically measured feedback paths are appropriate for flight stabilization and sexual dimorphism is only a minor factor in flight dynamics. A method of ranking kinematic control inputs to maximize maneuverability is also presented, showing that the volume of reachable configurations in state space can be dramatically increased due to appropriate choice of kinematic inputs.