Diagnostic Tools for Electronic Integrated Communication Systems in Air Transportation Systems
The paper has been intended to present research/testing tools used in the Air Force Institute of Technology to build integrated communication systems and test operation thereof, as far as both devices that compose the system and the applied software are concerned. Particular attention has been paid to the so-called integration station (built under the Mi-8, Mi-17, Mi-24 modernisation project), intended to activate communication systems integrated on the basis of digital data buses (MIL-1553B). Also, the mobile servicing and control set ZDZSŁ-1 to service and diagnose these systems has been discussed in details. Such equipment has allowed AFIT to gain the-state-of-the-art capabilities presented by western companies in the field of integrating new communication devices/systems, the already accomplished modernisation of the W-3PL helicopter ("Głuszec"/"Capercaillie") and a project of such a system for the TS-11F "Iskra" ("Spark") being perfect examples. Some selected tasks performed with this testing station engaged have been discussed. Also, problems arising while activating and testing the developed software to integrate communication devices/systems (including digitally controlled radio stations of the RF-5800H and XM-6013P types, and communication control panels of the PSŁ-1 type have been given consideration in the scope of the software functionality and reliability. Presented are also additional monitoring and measuring systems used to test this software, just to mention acoustic generators as well as special and navigation signals testers.
Methods of Checking the Reliability of Software Applications in the Avionic Systems Integrated Along the Digital Databus MIL-1553B
This The paper presents results of research that was carried out in the Air Force Institute of Technology (ITWL) with respect to test whether information in the avionic systems integrated along the digital databus MIL-1553B is processed correctly. The second part goes into details related to methods that are used in the ITWL to test the MIL-1553B databus on the stages when start up and validation of an integrated avionic system are carried out, in particular those that were applied for upgrading of aircrafts operated by the Air Forces of the Republic of Poland.
The paper presents selected results of work at the Air Force Institute of Technology (AFIT) in the concerning modeling the dynamic properties of fire detectors used in aviation fire protection systems. In order to determine the conditions of false fire signals, the simulation models of thermoelectric fire detectors have been developed. Simulation models were tested in Matlab-Simulink computational packages for various methods of heating and cooling the sensors (among others, changes in ambient air temperature of the sensor, caused by the EWU exhaust gas diffusers were simulated – these diffusers are used to distribute flue gases from helicopter engines).
This article presents selected results of work concerning the errors modeling of helmet-mounted cueing systems used for guided weapon and opto-electronic surveillance systems target homing (for realizing aircraft search and rescue actions). There were described algorithms of helmet angular position determination on the basis of inertial and magnetic methods, moreover, the possibilities of their modification. On this background there were presented the authorial method of pilot’s helmet angular position determination dedicated for helmet-mounted cueing systems for fighter helicopters. The method is based on the pilot’s helmet and aircraft body linear accelerations measurements, which then are used for the current quaternion evaluation to describe the helmet position relatively to the aircraft. Simulation models were tested in Matlab-Simulink and Borland C++ computational packages for various pilot’s helmet space orientation using specialized rotation test stands.
The article discusses the characteristics of measuring chains found in the gimbal inertial navigation systems of the IKW-8 type (used on Su-22 aircraft) are presented. The research paper also addresses the method for the identification of measurement chain properties of the gyroscopic KW-1 platform developed at AFIT, including sensors for the parameters of aircraft motion within an inertial space (linear accelerations and angular velocities) and signal processing systems (used to level and gyrocompass the platform). The methodology for the identification of measurement chain properties developed at AFIT found its application as a complementary technology in the process of assessing the technical condition of an IKW-8 inertial navigation system implemented in the conditions of a military unit operating Su-22 aircraft.
The article presents selected results of the analytical work carried out in the Air Force Institute of Technology and the Polish Air Force Academy by means of a computer simulation of noncommutativity phenomena submitting aircraft turnover on high-manoeuvrability flights. The results of these simulations allowed to define the guidelines for the method of “production” of noncommutativity phenomenon in specialized rotating positions for strapdown inertial navigation systems (to evaluate the errors of determining spatial orientation).
Also, it analysed the possibility of “production” noncommutativity rotational movement in mobile flight simulator used for testing pilots and candidates for pilots (to test the sensitivity of the pilot’s vestibular system in terms of feeling the impact of this phenomenon). The results of the assessment of “greatness” noncommutativity angular velocity vector, occurring in some parts of the high-manoeuvrability flight of aircraft on the example of a fighter-bomber airplane Su-22 were discussed as well.
The article presents the new built in Poland helmet mounted cueing system NSC-1 Orion with a magnetic method, dedicated to the multi-purpose helicopters W-3PL Gluszec. This system uses the magnetic field generated by the system of three mutually orthogonal electric coils. The principle of operation of this system is described and the method of determining the angular position of the pilot’s helmet relative to the helicopter’s cabin using the reference magnetic field and the directional cosines matrix are discussed. Electrical flat coils, constructed in the Polish Air Force Institute of Technology (AFIT), generating a magnetic field with curved symmetry axis characteristics, causing errors in determining the angular position of the pilot’s helmet are shown. As a way to minimize these errors, an original proprietary algorithm for correcting the negative impact of the magnetic field curvature generated by the on-board system has been presented. Mathematical relations describing the presented correction process as well as selected results of simulation and experimental investigations in the area of inaccuracy of the “before” and “after” systems of applying the developed algorithm were given. Inaccuracies determined from computer simulations of the developed mathematical relations were compared with experimental data from magnetic field measurements using the integrated three-axis sensor ADIS-16405, used in the laboratory of the AFIT Avionics Division for helmet control of the angular position of the moving observation and sighting head and reflector-search light.
The article presents selected results of the analytical work carried out in the Air Force Institute of Technology regarding the possibility of computer matching systems, digital display and analogue devices, both in the static states and in dynamic states while manoeuvring the aircraft. On the example of parameter of vertical speeds provided a method of matching the indications for the helicopter Mi-17-1V with built helmet-mounted display system of flight data SWPL-1 Cyclops (developed by the Air Force Institute of Technology and cooperating with analogue avionics). Adjusting the display of vertical speed achieved by an inertial element of first row, implemented programmatically in the computer graphics KG-1.
On the other hand, method of adjusting of indications on the information presented in the helmet-mounted cueing system NSC-1 Orion (built in the Air Force Institute of Technology for helicopter W-3PL Capercaillie) and obtained from the integrated avionics system (with digital avionics), exemplified by magnetic heading (obtained from heading layout KCS-305) and geographic heading (obtained from inertial navigation system EGI-3000).
Adjusting of indications realized by introducing amendments to the indications of the multifunctional monitor MW-1, translucent display HUD and helmet-mounted display WDN-1 (in the form of elected declination, implemented programmatically on the computer mission KM-1) and the amendments to the magnetic deviation (introduced periodically to heading compensator layout KCS-305).
The paper presents selected results of work at the Air Force Institute of Technology (AFIT) in the scope of testing of the SSP-FK fire suppression system used on many types of military aircraft operating in the Polish Armed Forces. For the purpose of determining conditions for false fire alarms, SSP-FK simulation models have been developed. The study was carried out on simulation models in Matlab-Simulink and Circuit-Maker packages. Results of this work have been used for diagnosis of the SSP-FK system during a test of real cases of false activation of these devices.
The paper presents selected results of the work carried out at the Air Force Institute of Technology (AFIT) in the scope of computer diagnostic tests of the SWPL-1 Cyklop helmet mounted flight parameters display system. This system has been designed in such a way that it warns the pilot of dangerous situations occurring on board the helicopter and threatening the flight safety (WARN) or faults (FAIL), which inform about a failure in given on-board equipment. The SWPL-1 system has been awarded the Prize of the President of the Republic of Poland during the 17. International Defense Industry Exhibition in Kielce.