Andrzej Szelmanowski

Helmet-Mounted Attitude Control Algorithms of the Opto-Electronic Surveillance System for Aircraft Search and Rescue Actions

Abstract 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.

Dynamic Properties Modeling of the Thermoelectric Fire Sensors in the Aircraft Fire Suppression System

Abstract 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).

Research method of dynamic capability of an actuating block of the SSP-FK aircraft fire suppression system in false alarm aspect

Numerous cases of self-activation of the SSP-FK aircraft fire suppression system (including commissioning of valves and extinguishing tanks) testify about the fact that it is not yet fully understood in the technical aspect, and because of the performed role on the aircraft is the basic element to ensure flight safety. Solving problems with false fire signalling of the SSP-FK system is an important issue for the safe operation of aircraft and military helicopters, because it is preventive (to warn the crew of the possibility of fire) and rescue system (aiming at extinguish the fire) in each phase of a flight. In addition, the SSP-FK system is used on many types of military aircraft (including helicopters from W-3/3W/3WA/3PL and Mi/8/14/17/24 family as well as An-28 and Tu-154M aircraft. The paper presents selected results of work in the Air Force Institute of Technology in the study of SSP-FK fire suppression system (as one of the main protection systems on-board) used on many types of military aircraft operated in the Polish Armed Forces. In determining the conditions of the false signalling of fire, simulation models of action blocks implementing of the SSP-FK fire suppression system were developed. The research on simulation models was performed in Matlab-Simulink and Circuit-Maker computing packages. The results of these works were used to diagnose selected modules and blocks of the SSP-FK system during the study of actual cases of their false activation.

Algorithm for determining the angular position of the pilot’s helmet to control the on-board weapon’s control system

The following paper presents a method of determining the angular position of the pilot’s helmet based on the measurement of magnetic field components, artificially generated on board the aircraft (similarly to the helmetmounted cueing systems of the F-16 aircraft). We presented a mathematical model, which describes determining of the angular position of the pilots helmet, based on the measurement of the magnetic field components in various moments of powering orthogonally fixed magnetic coils. We also defined modelling capabilities of the helmet-mounted cueing system, which uses the magnetic method to determine the angular position of the pilots helmet. It has been shown that the direction cosine matrix can be used for determining the angular position of the pilots helmet, specified based on the matrix formed from the magnetic field components in various moments of powering orthogonal magnetic coils. The paper ends with an outline of simulation tests, which enable to identify the errors of the system, using such a method.

Possibilities Concerning Diagnosis of the SSP-FK Aircraft Fire Suppression System in Terms of Determination of Reasons for False Fire Alarms / Możliwości Diagnozowania Lotniczego Systemu Przeciwpożarowego Ssp-Fk W Aspekcie Określania Przyczyn Fałszywego Sygnalizowania Pożaru

Abstract 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. Streszczenie W artykule przedstawiono wybrane wyniki prac realizowanych w Instytucie Technicznym Wojsk Lotniczych (ITWL) w zakresie badań instalacji przeciwpożarowej SSP-FK stosowanej na wielu typach wojskowych statków powietrznych eksploatowanych w Siłach Zbrojnych RP. Dla określania warunków fałszywego sygnalizowania pożaru opracowano modele symulacyjne działania bloków wykonawczych SSP-FK. Badania modeli symulacyjnych wykonano w pakietach obliczeniowych Matlab-Simulink i Circuit-Maker. Wyniki tych prac zostały wykorzystane do diagnostyki instalacji SSP-FK w trakcie badania rzeczywistych przypadków fałszywego zadziałania tych urządzeń.

Possibilities concerning diagnosis of the SSP-FK aircraft fire suppression system in terms of determination of reasons for false fire alarms

Abstract 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. Streszczenie W artykule przedstawiono wybrane wyniki prac realizowanych w Instytucie Technicznym Wojsk Lotniczych (ITWL) w zakresie badań instalacji przeciwpożarowej SSP-FK stosowanej na wielu typach wojskowych statków powietrznych eksploatowanych w Siłach Zbrojnych RP. Dla określania warunków fałszywego sygnalizowania pożaru opracowano modele symulacyjne działania bloków wykonawczych SSP-FK. Badania modeli symulacyjnych wykonano w pakietach obliczeniowych Matlab-Simulink i Circuit-Maker. Wyniki tych prac zostały wykorzystane do diagnostyki instalacji SSP-FK w trakcie badania rzeczywistych przypadków fałszywego zadziałania tych urządzeń.

Computer Aided Diagnosis of Technical Condition of the SWLP-1 Helmet Mounted Flight Parameters Display System / Komputerowe Diagnozowanie Stanu Technicznego Systemu Nahełmowego Wyświetlania Parametrów Lotu SWPL-1

Abstract 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. Streszczenie W artykule przedstawiono wybrane wyniki prac realizowanych w Instytucie Technicznym Wojsk Lotniczych (ITWL) w zakresie komputerowych badań diagnostycznych nahełmowego systemu wyświetlania parametrów lotu SWPL-1 Cyklop. System ten został zaprojektowany w taki sposób, aby alarmować pilota o wystąpieniu na pokładzie śmigłowca sytuacji niebezpiecznych, zagrażających bezpieczeństwu lotu (WARN) lub stanów awaryjnych (FAIL), informujących o niesprawności wybranych urządzeń pokładowych. Zbudowany system SWPL-1 otrzymał Nagrodę Prezydenta RP na XVII Międzynarodowym Salonie Przemysłu Obronnego MSPO’2009 w Kielcach.

Możliwości diagnozowania systemów nawigacji inercjalnej na bazie analizy wartości błędów Schulera

Streszczenie W artykule omówiono błędy czujników inercjalnych wykorzystywanych w systemach odniesienia kursu i pionu AHRS (ang. Attitude and Heading Reference Systems) i systemach nawigacji inercjalnej INS (ang. Inertial Navigation Systems) w zakresie prędkości kątowych i przyspieszeń liniowych. Przedstawiono zależności matematyczne określające ich wpływ na błędy wyliczanych parametrów pilotażowo-nawigacyjnych (takich jak prędkości liniowe i współrzędne pozycji nawigacyjnej) obrazowanych m.in. w nahełmowych systemach celowniczych. Przedstawiono problemy diagnozowania systemów nawigacji inercjalnej, zarówno tych najnowocześniejszych (np. centrali TOTEM-3000 z czujnikami laserowymi, stosowanej na śmigłowcu W-3PL GŁUSZEC), integrowanych na bazie cyfrowej szyny danych MIL-1553B lub ARINC-429, jak i „starszych” rozwiązań konstrukcyjnych (np. układów IKW-1 i IKW-8 stosowanych na samolotach Su-22). Podano metody badań torów przetwarzania sygnałów z czujników inercjalnych oraz wytyczne dla komputerowego systemu oceny stanu technicznego systemów nawigacji inercjalnej z przedłużanym resursem technicznym.

Feasibility to Diagnose Inertial Navigation Systems Through Analysis of Schuler Errors

Abstract The paper is intended to discuss errors in measurements of angular velocity and linear acceleration by means of electronic inertial sensors incorporated into the Attitude and Heading Reference Systems (AHRS) as well as Inertial Navigation Systems (INS). The mathematical equations are found out to establish how these errors affect deviations of flight parameters (such as linear speed and coordinates of the aircraft position indicated by navigation systems) that are calculated from the measurements and imaged e.g. in helmetmounted cueing systems. Some issues related to diagnostics of inertial navigation systems are addressed as well, both the most recent ones (e.g. the TOTEM-3000 central station with laser sensors installed on-board of the W-3PL GŁUSZEC helicopter) integrated via digital data buses MIL-1553B or ARINC-429 as well as more outdated solutions, such as IKW-1 and IKW-8 system used for Su-22 aircrafts. The methods of examination of the data processing paths for signals received from inertial sensors are presented with guidelines for development of the computer system for assessment of technical condition exhibited by systems of inertial navigation with prolonged technical resource.

The Method to Correct Transversional Errors in Measurements of Motion Parameters in Integrated Avionic Systems

The Method to Correct Transversional Errors in Measurements of Motion Parameters in Integrated Avionic Systems The paper presents results of the analysis that was carried out in the Air Force Institute of Technology (ITWL) and dedicated to impact of transversional interactions onto errors in measurements of aircraft motion parameters with use of conventional (electromechanical) gauges of angular speed and acceleration meters. The analysis covers relationships and timings for conical translocations produced with use of a model rig SRS-1 constructed in ITWL. Measurements were taken from angular speed gauges I-1426 manufactured by SFIM and acceleration meters MP-95 (former Soviet Union), which made it possible to develop models for transversional errors and to suggest methods for their correction on the basis of signals provided by the both instruments. Measurements of transversional errors were visualized for conical translocations along with efficiency of their correction with use of algorithms developed by ITWL.