Airborne International (Netherlands)

Radio frequency fingerprinting identification (RFFI) plays a vital role in achieving wireless communication security. The vast majority of the existing RFFI schemes are implemented under the closed set RFFI, which is not robust in the open electromagnetic spectrum environment. The open set RFFI is promising to solve the above drawback. However, the existing open set RFFI schemes are committed to reducing the distance between the same class without increasing the distance between different classes, which may cause the known samples and the unknown open samples to map to the same location in the feature space. In order to improve the robustness in the open electromagnetic spectrum environment while maintaining the identification accuracy of known samples, an accurate open set RFFI scheme is proposed by utilizing a novel hierarchical autoencoder network based on shuffle attention (SA-HANet). The SA-HANet is exploited to extract the high-level features for better distinguishing the known samples and the unknown open samples. Moreover, a loss function based on metric learning is used to minimize the distance to the ground-truth anchor point while maximizing the distance to other classes. The simulation results demonstrate that our designed SA-HANet scheme can better extract the characteristics of the known samples and retain the characteristics of the unknown open samples. Moreover, the identification accuracy of the open set RFFI is improved while the identification accuracy of the closed set RFFI is better than the baseline schemes.

The infrared radiation characteristics of aircraft skin is an important research content for evaluating and improving the infrared stealth performance of aircraft, and this paper proposes an energy-based emissivity measurement method for the surface skin coating material of aircraft in low temperature environment. The geometric model of a typical aircraft is established by CATIA software, the heat flow of solar radiation is obtained by the inverse Monte Carlo method, and the three-dimensional temperature field of the aircraft as well as the infrared emissivity field in the 3~5μm and 8~14μm bands are simulated by the method of control variables. The relationship between the solar radiation and the infrared radiation characteristics of the aircraft surface as well as the influence of flight altitude on the infrared radiation performance are obtained through simulation and analysis, and the research in this paper provides important technical and theoretical support for the infrared stealth design of aircraft.

The physical and neuropsychiatric overstrain of the personnel of the team participating in the “Аirborne platoon” competition is caused by the influence of harmful factors of military service, the volume of training activities and entails a decrease in the functional state, which can cause injury to the participants of the competition. This will lead to disruption of the sports training of the entire team and to poor-quality performance of military personnel at the international stage of the competition. And a timely assessment of the functional state with the help of modern hardware and software systems for the analysis of heart rate variability will help in assessing the functional state and regulating the process of preparing the national team. The purpose of the study was to assess the functional state of military personnel, participants in the field training competition “Landing Platoon”, in the pre-competition period with the help of modern hardware and software systems and to develop proposals for regulating the process of training soldiers-athletes. In the course of the study, it was found that modern hardware and software systems for assessing the functional state, based on the analysis of heart rate variability, can help in constant dynamic monitoring of the reactivity of regulatory systems that determine the effectiveness of adaptive mechanisms, and on the basis of the results obtained, make adjustments to sports training plans. Физическое и нервно психическое перенапряжение личного состава команды, участницы конкурса «Десантный взвод», вызвано воздействием вредных факторов военной службы, объемами тренировочных мероприятий и влечет за собой понижение функционального состояния, которое может вызвать травмирование участников состязаний. Это приведет к срыву спортивной подготовки всей команды и к некачественному выступлению военнослужащих на международном этапе конкурса. А своевременная оценка функционального состояния с помощью современных аппаратно-программных комплексов по анализу вариабельности сердечного ритма поможет в оценке функционального состояния и регулировании процесса подготовки сборной команды. Целью исследования была оценка функционального состояния военнослужащих, участников конкурса по полевой выучке «Десантный взвод», в предсоревновательный период с помощью современных аппаратно-программных комплексов и разработка предложений по регулированию процесса подготовки воинов-спортсменов. В ходе исследования было установлено, что современные аппаратно-программные комплексы по оценке функционального состояния, на основе анализа вариабельности сердечного ритма, могут помочь в постоянном динамическом контроле за реактивностью регуляторных систем, определяющих эффективность работы адаптационных механизмов, и на основе полученных результатов, вносить корректировку в планы спортивной подготовки.

This document summarizes the results of the Dynamic Extraction Tests (DET) that were completed with ExoMars MP1 and MP2 parachutes built by Airborne Systems. The purpose of the test was to verify that a clean, orderly, and damage-free deployment from the deployment bag could be achieved at flight-like velocities. The DET utilizes a horizontal variant of the high velocity test bed developed for the Low Density Supersonic Decelerator (LDSD) program. The tests were completed at the Jet Propulsion Laboratory in Pasadena, CA. Test definition and planning was provided by Vorticity Ltd, with design and test support provided by the Jet Propulsion Laboratory (JPL/Cal-Tech). The ExoMars Rosalind Franklin Rover and Kazachok Surface Platform, a joint collaboration between ESA and Roscosmos respectively, were planned to land on Mars June 10th, 2023. Conflict between Russia and Ukraine has led to the indefinite delay of this mission. The parachute system architecture for this system, jointly developed by Vorticity Ltd and Thales Alenia Space, consists of four parachutes in total. The first main parachute (MP1) is a 15m Do disk-gap-band type, is deployed by a mortar deployed disk gap band pilot parachute. The second main parachute (MP2) is a 35m Do ring slot type, deployed by a second mortar deployed disk-gap-band pilot parachute. The MP1 parachute will be supplied by Airborne Systems for flight, the remaining three parachutes will be supplied by a European vendor.

The Radio Interferometric Positioning System (RIPS) is a phase-based localization scheme that achieves high accuracy with low-cost devices. Indoor localization with RIPS is, however, a challenge due to dense multipath. In this paper, we propose holographic radio interferometry (HRI) to cope with multipath effect. HRI builds hologram out of phase measurements in radio interferometry for the mobile target. It is built on an important observation that spatial diversity induced by dense multipath resembles that induced by random noise. We implement HRI with GNU Radio/USRP N210 and test it in lab environments. With mobility data from only one step, HRI achieves a median positioning error of 21 cm, in contrast to 151 cm with the original RIPS. It is also verified that HRI is robust to errors in mobility data. The median positioning error is no more than 66 cm with a speed error of the target up to 15 cm/s and a direction error up to 2.5°.

During the developmental testing program for CPAS (Capsule Parachute Assembly System), the parachute system for the NASA Orion Crew Module, simulation revealed that high loads may be experienced by the pilot risers during the most devere deployment conditions. As the role of the pilot parachutes is to deploy the main parachutes, these high loads introduced the possibility of main deployment failure. In order to mitigate these high loads, a set of energy modulators was incorporated between the pilot riser and the main deployment bag. An extensive developmental program was implemented to ensure the adequacy of these energy modulators. After initial design comparisons, the energy modulator design was validated through slow-speed joint tests as well as through high-speed bungee tests. This paper documents the design, development, and results of multiple tests completed on the final design.

This work highlights some of the achievements obtained within the EU FP7 SmartFiber project, aiming to develop a fully embeddable optical fiber sensor system including the interrogator chip. The focus is on resolving issues holding back the industrial uptake of optical sensing technology. In a first section, the development of a placement head for automated lay-down of an optical sensor line (including the SmartFiber interrogator system) during composite manufacturing is discussed. In a second section, the attention is shifted to the occurrence of resin pockets surrounding inclusions such as the SmartFiber interrogator. A computationally efficient F.E. approach is presented capable of accurately predicting resin pocket geometries. Both small (i.e. optical fiber sensors) and large (i.e. the SmartFiber interrogator) inclusions are considered, and the F.E. predictions are validated with experimental observations. doi: 10.12783/SHM2015/123

This paper describes the development and results of numerical models describing system level parachute performance. The numerical models were developed to replicate a series of parachute drop tests conducted in the early 1950s. Wright Air Development Division Report AFTR 5867 documents 700 parachute drop tests, using twenty seven different parachutes, at the Goodyear Aircraft Corporation airship dock in Akron, Ohio between 1952 and 1954. The data from these tests were compiled into charts and referenced in the Parachute Recovery Systems Design Manual (T.W. Knacke). The numerical models were developed using Fluid Structure Interaction (FSI) techniques in the commercially available transient dynamic finite element code LS-DYNA. This paper describes the development of an 11.9 ft Nominal Diameter (D0) 10% extended skirt parachute model. Parachute drag, maximum oscillation angle, and frequency of oscillation are calculated for the parachute for ranges of rate of descent and suspension line length ratio, and compared with test data from AFTR 5867. This paper proposes a benchmarking parachute test series for current and future FSI numerical models.