Airborne Computer Research Articles

An airborne object detection and location system based on deep inference

In recent years, with the development of sensors, communication networks, and deep learning, drones have been widely used in the field of object detection, tracking, and positioning. However, there are inefficient task execution and some complex algorithms still need to rely on large servers, which is intolerable in rescue and traffic scheduling tasks. Designing fast algorithms that can run on the airborne computer can effectively solve the problem. In this paper, an object detection and location system for drones is proposed. We combine the improved object detection algorithm ST-YOLO based on YOLOX and Swin Transformer with the visual positioning algorithm and deploy it on the airborne end by using TensorRT to realize the detection and location of objects during the flight of the drone. Field experiments show that the established system and algorithm are effective.

Improved airborne computer system strategy for swarm drones flying based on skybrush suite and inspired technique

In airborne swarm drones, there are a significant impact on daily life as a result of air advances in electronic communications. There are different types of UAVs (Unmanned Air Vehicles) being developed as possible. In this research, the ARDUPILOT or the so-called ARDUCOPTER is simulated as firmware with a MAV link (Micro Air Vehicle Communication Protocol) that is connected to the Skybrush through the communication layer. Where a swarm of drones consisting of 20 drones was studied and 3D displays were created in the drones taking into account the frequency of 2.4 GHz and the distance between the drones to avoid collisions that occur in the paths of the drones by using PSO (Particle Swarm Optimization) algorithm which happens in the swarm of drones. The trajectory of drone 5493 and a number of ports 9195 were obtained from the proposed system.

Capturing long‐tailed individual tree diversity using an airborne imaging and a multi‐temporal hierarchical model

AbstractMeasuring forest biodiversity using terrestrial surveys is expensive and can only capture common species abundance in large heterogeneous landscapes. In contrast, combining airborne imagery with computer vision can generate individual tree data at the scales of hundreds of thousands of trees. To train computer vision models, ground‐based species labels are combined with airborne reflectance data. Due to the difficulty of finding rare species in a large landscape, many classification models only include the most abundant species, leading to biased predictions at broad scales. For example, if only common species are used to train the model, this assumes that these samples are representative across the entire landscape. Extending classification models to include rare species requires targeted data collection and algorithmic improvements to overcome large data imbalances between dominant and rare taxa. We use a targeted sampling workflow to the Ordway Swisher Biological Station within the US National Ecological Observatory Network (NEON), where traditional forestry plots had identified six canopy tree species with more than 10 individuals at the site. Combining iterative model development with rare species sampling, we extend a training dataset to include 14 species. Using a multi‐temporal hierarchical model, we demonstrate the ability to include species predicted at <1% frequency in landscape without losing performance on the dominant species. The final model has over 75% accuracy for 14 species with improved rare species classification compared to 61% accuracy of a baseline deep learning model. After filtering out dead trees, we generate landscape species maps of individual crowns for over 670 000 individual trees. We find distinct patches of forest composed of rarer species at the full‐site scale, highlighting the importance of capturing species diversity in training data. We estimate the relative abundance of 14 species within the landscape and provide three measures of uncertainty to generate a range of counts for each species. For example, we estimate that the dominant species, Pinus palustris accounts for c. 28% of predicted stems, with models predicting a range of counts between 160 000 and 210 000 individuals. These maps provide the first estimates of canopy tree diversity within a NEON site to include rare species and provide a blueprint for capturing tree diversity using airborne computer vision at broad scales.

Performance Evaluation Based on Multi-UAV in Airborne Computer Network System

Performance Evaluation Based on Multi-UAV in Airborne Computer Network System

A Generative adversarial learning strategy for enhanced lightweight crack delineation networks

Traditional manual crack detection has been gradually replaced by unmanned aerial vehicles (UAVs) since automation and intelligence became the inevitable trends in routine bridge maintenance. Deep learning-based real-time crack detection is an important link in this automation process. However, due to the limitations of the field of view and airborne computer performance, it is challenging to balance crack detection accuracy and efficiency at the same time. To address this issue, a novel Generative Adversarial Network (GAN)-based strategy is proposed in this paper. Different from the traditional ways, the GAN-based strategy can introduce the morphological difference between the predictions and the manual labels into training process, further improving the network performance while ensuring detection efficiency. Three lightweight networks with different depths are designed based on the Dense Block to analyze the impact of the proposed method. Novel Fault-Tolerance (FT) indexes are proposed to reflect the morphological differences in predictions. Finally, the effectiveness and robustness of the proposed method are verified by the crack detection of highway bridge piers. Results show that the proposed method can effectively improve the detection scores of UAV-captured images under limited network parameters.

Airborne Computer System Based Collision-Free Flight Path Finding Strategy Design for Drone Model

Airborne Computer System Based Collision-Free Flight Path Finding Strategy Design for Drone Model

WAYS OF DIMINISHING OF ERRORS OF CALCULATIONS OF COMPUTER OF AUTONOMOUS MOBILE OBJECT ARE FOR ALGORITHMS OF SLAM OF NAVIGATION

A question is in-process considered, in relation to the lead through of estimation of complication of algorithms of EKF-SLAM and construction of map of locality in accordance with supporting points, from point of his algorithmically programmatic realization. It enables to determine the ways of subsequent development and adaptation of the known mathematical correlations of algorithms of EKF-SLAM and DP-SLAM for diminishing of errors of calculations of co-ordinates airborne COMPUTERS of autonomous mobile object for realization of algorithms. The estimation of the state of off-line mobile unit is arrived at by filtration of particles. The great number of hypotheses which are an eventual number is generated, which show by itself the predictable place of location of robot. Every meaningful element of map, that orienteer, in every particle can be appraised with the use of the extended filters of Kalmana, particles of robot conditioned position. And the coefficient of weight of particles settles accounts for determination of probability of hit of certain part in a final set, which will present not only the real place of location of autonomous mobile object on a map but also position of found out all orienteers. The way of modification of the known mathematical correlations of filters of Kalmana offered in-process from point of their adaptation to the features of algorithmic and programmatic realization in airborne COMPUTERS provides economy of memory of airborne COMPUTER and diminishing of necessary calculable resource It is noticed that the algorithms of realization of SLAM of navigation are changed the offered way use less of particles, than methods, based only on a frequency filter. The error of initial calculation of co-ordinates of orienteer is taken to the minimum and does not accumulate in course of time in mathematical sense.

Mathematical modelling of an airborne technical vision system development

An airborne technical vision system of a modern aircraft is, on the one hand, a complex of multispectral sensors and, on the other, airborne computer equipment. The onboard computer solves a wide range of complex digital image processing tasks. The strict requirements are imposed on the computer mathematical software on the image processing time and on the quality of the result displayed on the pilot screen. The software development for such a complex system involves mathematical modelling and use modern information technologies in process of computational algorithms development for task solving. The proposed work discusses ways of solving subtasks of one of the most important subsystems of the airborne complex - the image fusion subsystem and solving the inverse navigation problem. The subsystem is represented by two blocks of tasks: tasks of primary image processing and high-level tasks. The primary processing unit solves the problems of image noise suppression, image enhancement, image fusion and edge detection. In the high-level block of tasks, the tasks of key points detection on real and virtual images, the tasks of a geometric transformation estimation of one image to the plane of another, and the task of a 3D model construction of the underlying surface are solved. The paper presents the results of mathematical modelling in the process of algorithms development for above problems solving. The new results of mathematical modelling of the noise estimation problem are presented in detail. The description of methods and results of other problems solving is less detailed due to article limit but provided with links to the corresponding publications of the authors.

Research on Strapdown Inertial Navigation and Laser Doppler Combination Navigating Algorithm

In the current strapdown inertial navigation system, there are errors in the calculation model set by the airborne computer and the accuracy of related equipment, and the errors accumulate over time, which will lead to lower navigation accuracy and larger speed deviation. In order to solve the above problems, a new integrated navigation algorithm is proposed in this paper, which takes strapdown inertial navigation system as the main body and calculates the velocity and attitude of the aircraft. Laser Doppler assisted velocity measurement system is used as the auxiliary navigation system to correct and eliminate the velocity error of strapdown inertial navigation system. At the same time, Kalman filter technology is used to modify the velocity data of integrated navigation system. The simulation results show that the integrated navigation algorithm can reduce the speed error and improve the navigation accuracy, which verifies the effectiveness and feasibility of the integrated navigation algorithm.

Distributed Architecture Optimal Design for Aircraft Thrust Management System with Safety Method

In order to ensure the safety and reliability of aircraft thrust management system design and reduce the risk of engineering development, the distributed optimization architecture design based on the aircraft safety method for thrust management system has been put forward in this paper. First, the thrust management function requirement is analysed; second, the distributed architecture design method for thrust management is presented by following the SAE ARP4754 and ARP4761; then the automatic take-off thrust control system function which is not available in Airbus and Boeing civil aircraft thrust management architecture is designed by using this method. The results show that the method proposed in this paper is feasible and effective. The usage efficiency of airborne computer is improved and the aircraft weight is decreased, which greatly enhanced the safety and reliability of aircraft thrust management system.

Research on Fault-Tolerant Flight Control Computer for High Altitude Long Endurance Unmanned Air Vehicle

With the development of high altitude long endurance UAV, Flight Control System in high altitude long endurance UAV must have so strong failure tolerance ability that it can improve the whole system reliability. Using redundancy technique can extremely improve failure tolerance and reliability of flight control system. Compared among civil and military aircraft and UAV, the architectures and redundancy management of fault-tolerant flight control computer (FCC)systems are introduced. Then, give a new architectures and redundancy management of fault-tolerant FCC systems for high altitude long endurance UAV. The experimental results show that the system meets the UAV's demand of high reliability, low cost and good expansibility, maximize the utilization of system resources and effectively improve the fault tolerant capability of airborne computer and the reliability of sensor subsystem. With fault injection test method, the results show that the fault tolerant methods improve fault detection rate and fault isolation rate.

Passepartout Sherpa – A low-cost, reusable transportation system into the stratosphere for small experiments

The Passepartout sounding balloon transportation system for low-mass (<1200g) experiments or hardware for validation to an altitude of 35km is described. We present the general flight configuration, set-up of the flight control system, environmental and position sensors, power system, buoyancy considerations as well as the ground control infrastructure including recovery operations. In the telemetry and command module the integrated airborne computer is able to control the experiment, transmit telemetry and environmental data and allows for a duplex communication to a control centre for tele-commanding. The experiment module is mounted below the telemetry and command module and can either work as a standalone system or be controlled by the airborne computer. This spacing between experiment- and control unit allows for a high flexibility in the experiment design. After a parachute landing, the on-board satellite based recovery subsystems allow for a rapid tracking and recovery of the telemetry and command module and the experiment. We discuss flight data and lessons learned from two representative flights with research payloads.

IMPLEMENTATION OF STORAGE DEVICE (RAM) USING MULTISIM

Read access memory (RAM) considers an important part in several systems such as computer and communication systems; and there is several applications software that used for implements the digital circuits of RAM. In this project, multisim 9 application software was used to implement and simulate several logic circuits of RAM with many sizes at which implement RAM circuit from sub RAM. Also, it may be prepared as apart of equipments for the airborne computer system

Principles for implementing and optimizing mathematical image processing algorithms based on programmable logic

Typical approaches for implementing some mathematical algorithms based on programmable logic (reconfigurable logical integrated circuits) are proposed. Within the implementation of this approach, a hardware-software solution based on Xilinx FPGA of the Virtex family was designed and created that can be used to test the implemented algorithms and measure their performance for real problems. Two main specialized data processing modules are developed for practical testing. Along with the PCI-X computer interface and a parallel interface for different video devices, one of them was developed as an airborne computer on-board the satellite. The second module is designed for collecting, processing, and transferring large data flows (650 Mb/s) to PC via the external PCI-E ×4.

Thermal Design of an Airborne Computer Chassis With Air-Cooled, Cast Pin Fin Coldwalls

This paper documents the thermal design process required to provide effective thermal management for an airborne computer, consisting of 24 modules (two P/S modules and 22 PWB modules), which are edge-cooled to two cast, pin fin coldwalls. The computer chassis is mounted in an electronics pod mounted underneath the centerline of an aircraft. The pod consists of several electronics bays and a self-contained, air-cycle, environmental control system (ECS). The computer chassis is mounted in the forward bay, and the ECS is mounted in the rear bay of the electronics pod. The ECS is an air-cycle refrigeration system, which operates on captured ram air directed by an inlet/diffuser to an expansion turbine. This turbine produces low-pressure, chilled air, which is then directed through an air-to-liquid, load heat exchanger to produce chilled liquid. The chilled liquid is piped through small liquid lines to the forward bay of the pod, where the air-cooled computer chassis is located. The chilled liquid is converted back to chilled air in an air-to-liquid heat exchanger. The chilled air is supplied to the forward bay volume and is drawn through the computer chassis coldwalls by a fan integral to the computer chassis. The temperature of the chilled air, produced in this manner, becomes a strong function of the altitude and flight speed of the aircraft, because of the effect of these two parameters on the ram air mass flow rate and temperature at the inlet to the expansion turbine. The mass flow of the air used to cool the chassis is also a variable, because the density of the air is a function of the flight altitude and the fan has altitude-dependent operating characteristics. This fan provides the flow of air through the chassis. Emphasis is placed in the design process on the effect of the operating characteristics of the fan at altitude and the determination of the system performance curve associated with the pin fin coldwalls. This performance curve is controlled by the pressure drop characteristics of the pin fin coldwalls, which are a function of the Fanning f-factor and Colburn j-factor characteristics of the cast pin fin design. Design examples are used to demonstrate the design process.

Reports &amp; Surveys

It is reported by the British Aerospace (BAE Systems) that their researchers have developed a revolutionary airborne computer system that, they claim, can land aircraft safely without the need of human air traffic controllers. The new system will allow a pilot to determine an aircraft's landing by pressing a button in the cockpit to initiate the computer system.

Synthetic Vision-a view in the fog

A program called the Synthetic Vision Technology Demonstration Program, which is aimed at evaluating and demonstrating technologies permitting aircraft to land in very low visibilities over a wide range of airports, is described. The idea is to provide an electronic image of the runway to the pilot on a head-up display with an overlay on the display of symbology providing all the navigation and performance information needed to fly and land the aircraft. Millimeter-wave radar, infrared sensor, head-up display, and airborne computer processing technologies are being tested. The theoretical performance of the system concept at 35 GHz is compared to the actual performance of the 35-GHz experimental demonstration system for typical approach and runway intrusion detection conditions.< <ETX xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">&gt;</ETX>

The Sandia Airborne Computer (SANDAC)

The Sandia Airborne Computer (SANDAC) is a small, modular, high performance, multi-processor computer originally designed for aerospace applications. It can use a combination of Motorola 68020 and 68040 based processor modules along with AT&T DSP32C based signal processing modules. The system is designed to use up to 15 processors in almost any combination and a complete system can include up to 20 modules. Depending on the mix of processors, total computational throughput can range from 2.5 to greater than 225 million instructions per second (MIPS). The system is designed so that processors can access all resources in the machine and the inter-processor communication details are completely transparent to the software. In addition to processors, the system includes input/output, memory, and special function modules. Because of its ease of use, small size, durability, and configuration flexibility, SANDAC has been used on applications ranging from missile navigation, guidance and control systems to medical imaging systems.

On closed-loop controls in pursuit-evasion

A hybrid algorithm is introduced in order to generate optimal closed-loop controls in a pursuit-evasion problem. The algorithm is composed of a differential dynamic programming method and a singular perturbation technique. The first mentioned method is used in those parts where the latter is weak. The method so created has an open-loop character. By having the open-loop solution updated as often as possible when new measures of the states have been estimated, the method will be near-optimal closed-loop. The game problem is discussed in terms of optimistic or pessimistic strategies, based on assumptions of the evader's strategy. In practice, the evader he may not do his best. The demonstrative example is in the horizontal plane, formulated as a game of degree. The pursuer uses a variable speed model with throttle and turn controls. The computer requirements can be kept to a reasonable level, and the new algorithm can be implemented on an airborne computer.

Chip Carriers Mounted on Large Thick Film Multilayer Boards

Two memory systems with 8 MHz clock frequency have been designed. One system contains 67 chip carriers mounted on an alumina substrate 9 x 12.5 cm and the other system contains 79 chip carriers mounted on an alumina substrate 9 x 14 cm. The experiences from the prototype manufacturing and testing are reported. Electrical measurements are made and the signals are compared with the same signals in a wire-wrapped prototype. Comparisons are also made with the capacitances usual in epoxy multilayer boards (MLB's). From an electrical point of view the ceramic multilayer boards made with thick film technique have both advantages and disadvantages compared with epoxy two-sided and multi!ayer boards. Thermal measurements are reported and a building technique is presented which allows a very powerful airborne computer consisting of 650 chip carriers to be built occupying a volume of 3 x 16 x 23 cm, i.e., 1.1 liters. It is shown that the combination of this building system with the chip carriers mounted on big alumina substrates give a system which is very reliable and occupies a very small volume compared with conventional technique (dual in-line packages (DIP's) and printed circuit boards (PCB's)). Yet the total hardware cost of the system is the same or lower for the chip carrier system as for the conventional system.