TR202010266U5

TR202010266U5 - A testing system.

Info

Publication number: TR202010266U5
Application number: TR2020/10266U
Authority: TR
Inventors: Gül İsmai̇l
Original assignee: Tusaş Türk Havacilik Ve Uzay Sanayi̇i̇ Anoni̇m Şi̇rketi̇; Tusas Tuerk Havacilik Ve Uzay Sanayii Anonim Sirketi
Priority date: 2020-06-30
Filing date: 2020-06-30
Publication date: 2022-01-21

Abstract

Mevcut buluşla, bir hava aracındaki buz önleme sisteminin test edilmesi için bir test sistemi açıklanmaktadır. Bahsedilen test sistemi, en az bir gövdeyi (G); gövdede (G) yer alan, birinci ısıtıcı elemana bağlanmaya uygun olan, bağlandığı birinci ısıtıcı elemanın hava aracı ile bağlantısını kontrol eden en az bir birinci anahtarı (1); gövdede (G) yer alan, ikinci ısıtıcı elemana bağlanmaya uygun olan, bağlandığı ikinci ısıtıcı elemanın hava aracı ile bağlantısını kontrol eden en az bir ikinci anahtarı (2); gövdede (G) yer alan, birinci sıcaklık algılayıcıya bağlanmaya uygun olan, bağlandığı birinci sıcaklık algılayıcının hava aracı ile bağlantısını kontrol eden en az bir üçüncü anahtarı (3); gövdede (G) yer alan, ikinci sıcaklık algılayıcıya bağlanmaya uygun olan, bağlandığı ikinci sıcaklık algılayıcının hava aracı ile bağlantısını kontrol eden en az bir dördüncü anahtarı (4); en az bir tarafından gövdeye (G) bağlı olan, en az bir diğer tarafından buz önleme sistemine bağlanmaya uygun olan, birinci anahtarın (1), ikinci anahtarın (2), üçüncü anahtarın (3) ve dördüncü anahtarın (4) buz önleme sistemine bağlanmasını sağlayan en az bir birinci bağlantı hattını (5); en az bir tarafından gövdeye (G) bağlı olan, en az bir diğer tarafından hava aracına bağlanmaya uygun olan, birinci anahtarın (1), ikinci anahtarın (2), üçüncü anahtarın (3) ve dördüncü anahtarın (4) hava aracına bağlanmasını sağlayan en az bir ikinci bağlantı hattını (6) içermektedir.The present invention describes a test system for testing an anti-icing system in an aircraft. Said test system comprises at least one body (G); at least one first switch (1) located in the body (G), suitable for connecting to the first heater element, controlling the connection of the first heater element to which it is connected with the aircraft; at least one second switch (2) located in the body (G), suitable for connecting to the second heater element, controlling the connection of the second heater element to which it is connected with the aircraft; at least one third switch (3) located in the fuselage (G), suitable for connecting to the first temperature sensor, controlling the connection of the first temperature sensor to which it is connected with the aircraft; at least one fourth switch (4) located on the fuselage (G), suitable for connecting to the second temperature sensor, controlling the connection of the second temperature sensor to which it is connected, with the aircraft; connect the first switch (1), the second switch (2), the third switch (3) and the fourth switch (4) to the anti-icing system, which are connected to the body (G) on at least one side and suitable for connection to the anti-icing system on at least one other side. at least one first connecting line (5) providing it; at least one side is connected to the fuselage (G) and at least one other side is suitable for connection to the aircraft, providing the connection of the first key (1), the second key (2), the third key (3) and the fourth key (4) to the aircraft. comprising at least one second connecting line (6).

Description

TARIFNAME BIR TEST SISTEMI Mevcut bulus, hava araçlarinin buz önleme sistemlerinin çalismasini test eden bir test sistemi ile ilgilidir. DESCRIPTION A TEST SYSTEM The present invention is a test device that tests the operation of aircraft anti-icing systems. It's about the system.

Uçak ve helikopter gibi hava araçlari, özellikle yüksek irtifada uçarken düsük çevre sicakligina maruz kalmaktadir. Bahsedilen düsük sicaklik ve ortamdaki nem sebebiyle hava aracinin çesitli bölgelerinde buzlanma sorunu olusabilmektedir. Özellikle hava aracinin motorunda olusan buzlanma, motorun çalismasini olumsuz etkileyeceginden hava aracinin güvenligini tehlikeye atabilmektedir. Bu durumun önlenmesi için hava araçlarinda, özellikle motorun giris ve çikis bölümlerinde buz önleme sistemleri kullanilmaktadir. Bahsedilen buz önleme sistemleri, en az bir sicaklik algilayiciyi, en az bir isitici elemani, bahsedilen sicaklik algilayiciya ve isitici elemana bagli olup sicaklik algilayicidan aldigi bilgiler dogrultusunda isitici elemanin çalismasini kontrol eden en az bir kontrol birimini içermektedir. Aircraft such as planes and helicopters, especially when flying at high altitudes is exposed to heat. Due to the mentioned low temperature and humidity in the environment Icing problems may occur in various parts of the aircraft. especially the weather Since icing on the vehicle's engine will negatively affect the operation of the engine, may endanger the safety of the aircraft. To prevent this situation, air Anti-icing systems in vehicles, especially in the inlet and outlet sections of the engine is used. Said anti-icing systems include at least one temperature sensor, at least one The heating element is connected to the said temperature sensor and the heating element and the temperature It controls the operation of the heating element in line with the information received from the sensor. It includes a control unit.

Buz önleme sistemleri, hava aracinin güvenilir bir biçimde kullanilmasini saglayan yapilar oldugundan buz önleme sistemlerinin hatasiz bir biçimde çalismasi kritik önem tasimaktadir. Bu sebeple, bahsedilen buz önleme sistemlerinin belirli araliklarla (örnegin her 300 saatlik uçus sonrasinda) test edilmesi gerekmektedir. Anti-icing systems, structures that enable the safe use of the aircraft Therefore, it is critical that anti-icing systems operate flawlessly. is carrying. For this reason, it is recommended that the mentioned anti-icing systems be installed at certain intervals (e.g. It must be tested after every 300 hours of flight.

Bilinen teknikteki uygulamalarda hava aracinin buz önleme sisteminin test edilmesi, sicaklik algilayicilarin bulundugu ortamin sicakliginin belirli bir degerin (örnegin -5°C) altina indirilmesi ile saglanmaktadir. Bahsedilen sicaklik degerinin altinda, isitici elemanin aktif hale getirilmesi gerekmektedir. Ancak bu gibi uygulamalarda, hava aracinin bulundugu ortam sicakliginin düsürülmesi zahmetli olmaktadir. Bu durum da, test isleminin süresinin uzamasina neden olmaktadir. 4559/TR Mevcut bulusla, en az bir birinci isitici elemani ve en az bir birinci sicaklik algilayicisi, en az bir motor girisinde konumlu olan en az bir ikinci isitici elemani ve en az bir ikinci sicaklik algilayicisi bulunan en az bir buz önleme sistemini içeren bir hava aracinda, bahsedilen buz önleme sisteminin test edilmesi için kullanima uygun olan bir test sistemi açiklanmaktadir. Bahsedilen test sistemi, en az bir gövdeyi; gövdede yer alan, bahsedilen en az bir birinci isitici elemana baglanmaya uygun olan, baglandigi en az bir birinci isitici elemanin hava araci ile baglantisini kontrol eden en az bir birinci anahtari; gövdede yer alan, bahsedilen en az bir ikinci isitici elemana baglanmaya uygun olan, baglandigi en az bir ikinci isitici elemanin hava araci ile baglantisini kontrol eden en az bir ikinci anahtari; gövdede yer alan, bahsedilen en az bir birinci sicaklik algilayiciya baglanmaya uygun olan, baglandigi en az bir birinci sicaklik algilayicinin hava araci ile baglantisini kontrol eden en az bir üçüncü anahtari; gövdede yer alan, bahsedilen en az bir ikinci sicaklik algilayiciya baglanmaya uygun olan, baglandigi en az bir ikinci sicaklik algilayicinin hava araci ile baglantisini kontrol eden en az bir dördüncü anahtari; en az bir tarafindan gövdeye bagli olan, en az bir diger tarafindan buz önleme sistemine baglanmaya uygun olan, birinci anahtarin, ikinci anahtarin, üçüncü anahtarin ve dördüncü anahtarin buz önleme sistemine baglanmasini saglayan en az bir birinci baglanti hattini; en az bir tarafindan gövdeye bagli olan, en az bir diger tarafindan hava aracina baglanmaya uygun olan, birinci anahtarin, ikinci anahtarin, üçüncü anahtarin ve dördüncü anahtarin hava aracina baglanmasini saglayan en az bir ikinci baglanti hattini içermektedir. Testing the aircraft's anti-icing system in known technical applications, The temperature of the environment where the temperature sensors are located is above a certain value (for example -5°C). It is achieved by lowering it to the bottom. Below the mentioned temperature value, the heating element needs to be activated. However, in such applications, the aircraft It is difficult to reduce the ambient temperature. In this case, the test This causes the process to take longer. 4559/TR With the present invention, at least one first heating element and at least one first temperature sensor are at least one second heater element located at at least one engine inlet and at least one second In an aircraft that includes at least one anti-icing system with a temperature sensor, a test system suitable for use in testing said anti-icing system is explained. Said test system consists of at least one body; located in the body, mentioned At least one first heater to which it is connected, suitable for connection to at least one first heater element at least one first switch controlling the connection of the element to the aircraft; place in the body area, suitable for connection to at least one second heating element, to which it is connected, at least at least one second switch controlling the connection of a second heating element to the aircraft; Suitable for connection to said at least one first temperature sensor located on the body control the connection of at least one first temperature sensor to which it is connected and the aircraft. at least one third key; said at least one second heater located in the body Suitable for connecting to the sensor, at least one second temperature sensor is connected to the air at least a fourth switch controlling its connection with the device; by at least one connected to the body, suitable for connection to the anti-icing system from at least one other side What happens is that the first key, the second key, the third key and the fourth key are ice. at least one first connection line enabling connection to the prevention system; at least one attached to the fuselage on one side and suitable for attachment to the aircraft on at least one other side. which is the air of the first key, the second key, the third key and the fourth key. It includes at least one second connection line that allows it to be connected to the vehicle.

Mevcut bulusla gelistirilen test sisteminde, birinci anahtarin, ikinci anahtarin, üçüncü anahtarin ve dördüncü anahtarin hava araci ile buz önleme sisteminin bilesenleri arasina baglanmasi saglanmaktadir. Böylelikle, buz önleme sisteminin bilesenlerinin hava araci ile baglantisi kesilerek (bir diger deyisle bahsedilen bilesenler arizaya sokularak) buz önleme sisteminin çalismasi test edilebilmektedir. In the test system developed with the present invention, the first key, the second key, the third switch and fourth switch between the aircraft and components of the anti-icing system. connection is provided. This ensures that the components of the anti-icing system are not exposed to the aircraft. ice prevention by disconnecting (in other words, causing the mentioned components to fail) The operation of the system can be tested.

Bulusun Amaci Mevcut bulusun amaci, hava araçlarinin buz önleme sistemlerinin çalismasinin test edilmesi için bir test sistemi gelistirmektir. 4559/TR Mevcut bulusun bir diger amaci, buz önleme sisteminin çalismasinin pratik bir biçimde test edilmesini saglayan bir test sistemi gelistirmektir. Purpose of the Invention The purpose of the present invention is to test the operation of aircraft anti-icing systems. To develop a testing system for 4559/TR Another aim of the present invention is to ensure the operation of the anti-icing system in a practical way. To develop a testing system that allows testing.

Sekillerin Açiklamasi Mevcut bulusla gelistirilen test sisteminin uygulama örnekleri ekli sekillerde gösterilmis olup bu sekillerden; Sekil 1; gelistirilen test sisteminin bir perspektif görünüsüdür. Explanation of Figures Application examples of the test system developed with the present invention are shown in the attached figures. is one of these shapes; Figure 1; It is a perspective view of the developed test system.

Sekil 2; gelistirilen test sisteminde kullanilan bir gövdenin üstten bir görünüsüdür. Figure 2; It is a top view of a body used in the developed test system.

Sekillerdeki parçalar tek tek numaralandirilmis olup bu numaralarin karsiliklari asagida verilmistir: Birinci anahtar (1) Ikinci anahtar (2) Üçüncü anahtar (3) Dördüncü anahtar (4) Birinci baglanti hatti (5) Ikinci baglanti hatti (6) Birinci baglanti elemani (7) Ikinci baglanti elemani (8) Birinci rakor (9) Ikinci rakor (10) Bulusun Açiklamasi Uçak ve helikopter gibi hava araçlari, düsük çevre sicakligi sebebiyle motorda olusan buzlanmanin önlenmesi için buz 'Önleme sistemleri içerebilmektedir. Bahsedilen buz buzlanma olusmasini engellemektedir. Motor bölgesinde olusacak buzlanma, motorun çalismasini olumsuz etkileyeceginden hava aracinin güvenilir bir biçimde kullanilmasini 4559/TR engelleyebilmektedir. Dolayisiyla bahsedilen buz önleme sistemlerinin hatasiz bir biçimde çalismasi kritik önem tasimaktadir. Bu sebeple mevcut bulusla, hava araçlarinin buz önleme sistemlerinin çalismasinin test edilmesi için bir test sistemi gelistirilmektir. The parts in the figures are numbered one by one and the correspondences of these numbers are below. given: First key (1) Second key (2) Third key (3) Fourth key (4) First connection line (5) Second connection line (6) First fastener (7) Second fastener (8) First union (9) Second gland (10) Description of the invention Aircraft such as airplanes and helicopters suffer from engine damage due to low environmental temperature. It may contain ice prevention systems to prevent icing. Said ice It prevents icing from forming. Icing in the engine area may cause the safe operation of the aircraft as it may adversely affect its operation. 4559/TR can prevent it. Therefore, the mentioned anti-icing systems can be used flawlessly. work is of critical importance. For this reason, with the present invention, air vehicles' ice A test system is developed to test the operation of prevention systems.

Mevcut bulusla gelistirilen ve örnek görünüsleri sekil 1 ve 2'de verilen test sistemi, en az bir motor çikisinda konumlu olan en az bir birinci isitici elemani ve en az bir birinci sicaklik algilayicisi, en az bir motor girisinde konumlu olan en az bir ikinci isitici elemani ve en az bir ikinci sicaklik algilayicisi bulunan en az bir buz önleme sistemini içeren bir hava aracinda, bahsedilen buz önleme sisteminin test edilmesi için kullanima uygun olup, tercihen kutu formunda olan en az bir gövdeyi (G); gövdede (G) yer alan, bahsedilen en az bir birinci isitici elemana baglanmaya uygun olan, baglandigi en az bir birinci isitici elemanin hava araci ile baglantisini kontrol eden en az bir birinci anahtari (1); gövdede (G) yer alan, bahsedilen en az bir ikinci isitici elemana baglanmaya uygun olan, baglandigi en az bir ikinci isitici elemanin hava araci ile baglantisini kontrol eden en az bir ikinci anahtari (2); gövdede (G) yer alan, bahsedilen en az bir birinci sicaklik algilayiciya baglanmaya uygun olan, baglandigi en az bir birinci sicaklik algilayicinin hava araci ile baglantisini kontrol eden en az bir üçüncü anahtari (3); gövdede (G) yer alan, bahsedilen en az bir ikinci sicaklik algilayiciya baglanmaya uygun olan, baglandigi en az bir ikinci sicaklik algilayicinin hava araci ile baglantisini kontrol eden en az bir dördüncü anahtari (4); en az bir tarafindan gövdeye (G) bagli olan, en az bir diger tarafindan buz önleme sistemine baglanmaya uygun olan, birinci anahtarin (1), ikinci anahtarin (2), üçüncü anahtarin (3) ve dördüncü anahtarin (4) buz önleme sistemine baglanmasini saglayan en az bir birinci baglanti hattini (5); en az bir tarafindan gövdeye (G) bagli olan, en az bir diger tarafindan hava aracina baglanmaya uygun olan, birinci anahtarin (1), ikinci anahtarin (2), üçüncü anahtarin (3) ve dördüncü anahtarin (4) hava aracina baglanmasini saglayan en az bir ikinci baglanti hattini (6) içermektedir. The test system developed with the present invention and whose sample views are given in Figures 1 and 2, is at least at least one first heater element and at least one first temperature element located at an engine output sensor, at least one second heater element located at at least one engine inlet and at least an air conditioner comprising at least one anti-icing system having a second temperature sensor It is suitable for use in vehicles to test the mentioned anti-icing system, at least one body (G), preferably in box form; located on the body (G), the most At least one first heater element to which it is connected, suitable for connection to at least one first heater element at least one first switch (1) that controls the connection of the element with the aircraft; in the body (G) located, suitable for connection to at least one second heating element mentioned, At least one device that controls the connection of at least one second heating element to which it is connected and the aircraft. second key (2); to said at least one first temperature sensor located in the body (G). At least one first temperature sensor that is suitable for connection to the aircraft at least a third switch (3) that controls the connection; located on the body (G), mentioned Suitable for connection to at least one second temperature sensor, to which it is connected at least one second temperature sensor. At least one fourth switch that controls the connection of the temperature sensor to the aircraft (4); connected to the body (G) on at least one side, with at least one anti-icing device on the other side Suitable for connection to the system, the first switch (1), the second switch (2), the third switch which allows the connection of the switch (3) and the fourth switch (4) to the anti-icing system. at least a first connection line (5); connected to the body (G) from at least one side, at least one On the other hand, the first switch (1), which is suitable for connection to the aircraft, is connected to the second switch. Connect the switch (2), third switch (3) and fourth switch (4) to the aircraft. It contains at least one second connection line (6) that provides

Bulusun tercih edilen bir uygulamasinda bahsedilen birinci anahtar (1), 2 konumlu bir anahtar yapisindadir. Bu uygulamada birinci anahtar (1) sayesinde, birinci isitici elemanin hava aracina bagli oldugu durum (anahtarin kapali durumu) ve birinci isitici elemanin hava araciyla baglantisinin kesildigi durum (anahtarin açik durumu) arasinda seçim yapilabilmektedir. Böylelikle, örnegin birinci anahtar (1) açik duruma getirildiginde, birinci isiticinin hava aracindan ayrilmasi durumu ile ilgili hava aracinin pilot veya kopilot paneline bilgi iletilip iletilmedigi test edilebilmektedir. Benzer bir biçimde bahsedilen ikinci 4559/TR anahtar (2) da 2 konumlu bir anahtar yapisinda olup ikinci isitici elemanin hava aracina bagli oldugu durum (anahtarin kapali durumu) ve ikinci isitici elemanin hava araciyla baglantisinin kesildigi durum (anahtarin açik durumu) arasinda seçim yapilabilmektedir. In a preferred embodiment of the invention, the first switch (1) is a 2-position switch. It has a key structure. In this application, thanks to the first switch (1), the first heating element the state in which it is connected to the aircraft (switch closed state) and the condition of the first heater element. choice between disconnected from the aircraft (switch on state) It can be done. Thus, for example, when the first switch (1) is turned on, the first In case the heater is separated from the aircraft, the pilot or co-pilot of the aircraft It can be tested whether information is transmitted to the panel or not. Similarly, the second mentioned 4559/TR The switch (2) also has a 2-position switch structure and the second heater element is connected to the aircraft. the state to which it is connected (switch closed state) and the connection between the second heating element and the air A choice can be made between the disconnected state (switch on state).

Bulusun bir baska tercih edilen uygulamasinda üçüncü anahtar (3), 3 konumlu bir anahtar yapisindadir. Bu uygulamada üçüncü anahtar (3) sayesinde, birinci sicaklik algilayicinin hava aracina bagli oldugu durum (anahtarin normal durumu), birinci sicaklik algilayicinin hava araciyla baglantisinin kesildigi durum (anahtarin açik durumu) ve birinci sicaklik algilayicinin kisa devre yapildigi durum (anahtarin kapali durumu) arasinda seçim yapilabilmektedir. Burada, üçüncü anahtarin (3) açik konuma veya kisa devre konumuna getirilmesi sayesinde, birinci sicaklik algilayicinin çalisma durumu ile ilgili hava aracinin pilot veya kopilot panelinden bilgi alinabilmektedir. Üçüncü anahtara (3) benzer olarak dördüncü anahtar (4) da tercihen 3 konumlu bir anahtar yapisindadir. In another preferred embodiment of the invention, the third switch (3) is a 3-position switch. It is in its structure. In this application, thanks to the third switch (3), the first temperature sensor The state in which the first temperature sensor is connected to the aircraft (normal state of the switch) state in which it is disconnected from the aircraft (switch on state) and the first temperature choice between the state in which the sensor is short-circuited (switch off state) It can be done. Here, the third switch (3) is in the open position or short circuit position. Thanks to its introduction, the aircraft has information about the operating status of the first temperature sensor. Information can be obtained from the pilot or copilot panel. Similar to the third key (3) The fourth switch (4) preferably has a 3-position switch structure.

Bulusun tercih edilen bir diger uygulamasinda bahsedilen birinci baglanti hatti (5). en az iki elektrik kablosunu ve bahsedilen elektrik kablolarinin disinda yer alan en az bir koruma elemanini içermektedir. Burada, elektrik kablolari sayesinde birinci anahtarin (1), ikinci anahtarin (2), üçüncü anahtarin (3) ve dördüncü anahtarin (4) buz önleme sistemine elektriksel olarak baglanmasi saglanmaktadir. Bahsedilen koruma katmani ise, tercihen bir boru formunda olup elektrik kablolarinin dis etmenlere karsi korunmasini saglamaktadir. Birinci baglanti hattina (5) benzer olarak ikinci baglanti hatti (6) da en az iki elektrik kablosunu ve bahsedilen elektrik kablolarinin disinda yer alan en az bir koruma elemanini içermektedir. In another preferred embodiment of the invention, the first connection line (5) is mentioned. least two electrical cables and at least one shielding located outside said electrical cables. contains the element . Here, thanks to the electrical cables, the first switch (1) and the second The key (2), the third key (3) and the fourth key (4) must be installed in the anti-icing system. It is electrically connected. The protection layer in question is preferably It is in the form of a pipe and protects electrical cables against external factors. It provides. Similar to the first connection line (5), the second connection line (6) is at least two electrical cables and at least one shielding located outside said electrical cables. contains the element .

Bulusun bir diger tercih edilen uygulamasinda test sistemi, birinci baglanti hattinin (5) gövdeye (G) uzak olan bir tarafinda yer alan ve birinci baglanti hattinin (5) buz önleme sistemine baglanmasini saglayan en az bir birinci baglanti elemanini (7) içermektedir. In another preferred embodiment of the invention, the test system is connected to the first connection line (5). It is located on a side away from the body (G) and prevents the ice of the first connection line (5). It contains at least one first connection element (7) that enables it to be connected to the system.

Test sistemi ayrica, ikinci baglanti hattinin (6) gövdeye (G) uzak olan bir tarafinda yer alan ve ikinci baglanti hattinin (6) hava aracina baglanmasini saglayan en az bir ikinci baglanti elemanini (8) da içermektedir. Burada, test sistemi bahsedilen birinci baglanti elemani (7) ve ikinci baglanti elemani (8) üzerinden hava araci ile buz önleme sistemi arasina baglanmaktadir. 4559/TR Bulusun bir baska tercih edilen uygulamasinda test sistemi, birinci baglanti hattinin (5) gövdeye (G) baglanmasini saglayan en az bir birinci rakoru (9) ve ikinci baglanti hattinin (6) gövdeye (G) baglanmasini saglayan en az bir ikinci rakoru (10) içermektedir. Birinci rakor (9) ve ikinci rakor (10) sayesinde, birinci baglanti hattinin (5) ve ikinci baglanti hattinin (6) gövdeye (G) güvenilir ve saglam bir biçimde baglanmasi saglanmaktadir. The test system is also located on a side of the second connection line (6) away from the body (G). and at least one second connection that enables the second connection line (6) to be connected to the aircraft. It also contains element (8). Here, the test system is the first connection element (7) mentioned. and between the aircraft and the anti-icing system via the second connection element (8). is connected. 4559/TR In another preferred embodiment of the invention, the test system is connected to the first connection line (5). At least one first gland (9) that enables connection to the body (G) and the second connection line (6) contains at least one second gland (10) that enables its connection to the body (G). First Thanks to the gland (9) and the second gland (10), the first connection line (5) and the second connection line It ensures that the line (6) is connected to the body (G) in a reliable and robust manner.

Bulusun örnek bir uygulamasinda, bahsedilen test sistemi hava aracinin bir kontrol paneli ile birlikte kullanilmaktadir. Burada, öncelikle birinci anahtar (1) ve/veya ikinci anahtar (2) açik konuma getirilerek birinci isitici eleman ve ikinci isitici eleman açik devre konumuna alinmaktadir. Bu durumda, hava aracinin kontrol panelinde isitici elemanin baglantili oldugu motorda bir hata verilmesi beklenmektedir. Kontrol paneli üzerinden ilgili motorun buz önleme sistemi pasif konuma alindiginda, bahsedilen hata uyarisinin kapanmasi beklenmektedir. Böylelikle, bahsedilen birinci anahtar (1) ve/veya ikinci anahtar (2) kullanilarak kontrol panelinde hata uyarisi gösterilip gösterilmeme durumuna göre isitici elemanlarin baglantisi test edilmektedir. Bahsedilen algilayicilarin test edilmesi için ise, üçüncü anahtarin (3) ve/veya dördüncü anahtarin (4) konumlari seçilmektedir. Burada, üçüncü anahtar (3) ve/veya dördüncü anahtar (4) açik konuma getirildiginde, birinci sicaklik algilayici ve/veya ikinci sicaklik algilayici açik devre konumuna getirilmektedir. Bu durumda, kontrol paneli üzerinde bir uyari verilmesi beklenmektedir. Üçüncü anahtar (3) ve/veya dördüncü anahtar (4) kapali konuma getirildiginde ise bahsedilen algilayicilar vasitasiyla buzlanma oldugu bilgisinin kontrol paneline iletilmesi beklenmekte olup bu durumda kontrol paneli üzerinden buz önleme sisteminin aktive edildigi bilgisinin gösterilmesi beklenmektedir. Üçüncü anahtar (3) ve/veya dördüncü anahtar (4) normal konumuna getirildiginde ise bahsedilen algilayicilar, normal islevlerini yerine getirecek sekilde hava aracina bagli olarak birakilmaktadir. Böylelikle, isitici elemanlarin test edilmesi sirasinda sicaklik algilayicilarin normal islevini yerine getirmesi ve test islemini olumsuz etkilememesi saglanmaktadir. In an exemplary embodiment of the invention, the said test system is a control panel of the aircraft. It is used together with . Here, first the first key (1) and/or the second key (2) By turning it on, the first heating element and the second heating element are in the open circuit position. is taken. In this case, the connected connection of the heater element on the aircraft control panel It is expected that an error will occur in the engine where it occurs. the relevant engine via the control panel. When the anti-icing system is put in passive position, the mentioned error warning is turned off. is expected. Thus, the first key (1) and/or the second key (2) heater depending on whether an error warning is displayed on the control panel or not. The connection of the elements is tested. To test the mentioned sensors, The positions of the third switch (3) and/or the fourth switch (4) are selected. Here, When the third switch (3) and/or the fourth switch (4) is turned on, the first The temperature sensor and/or the second temperature sensor is brought to the open circuit position. This In this case, a warning is expected to be given on the control panel. Third key (3) and/or when the fourth switch (4) is turned off, the said sensors It is expected that the information that there is icing will be transmitted to the control panel through In this case, the information that the anti-icing system is activated is displayed on the control panel. is expected to be shown. The third key (3) and/or the fourth key (4) is normal When placed in position, the mentioned sensors will perform their normal functions. It is left attached to the aircraft as follows. Thus, the testing of the heating elements During the test, the temperature sensors perform their normal function and the testing process is completed. It is ensured that it does not have a negative impact.

Mevcut bulusla gelistirilen test sisteminde, birinci anahtarin (1), ikinci anahtarin (2), üçüncü anahtarin (3) ve dördüncü anahtarin (4) hava araci ile buz önleme sisteminin bilesenleri arasina baglanmasi saglanmaktadir. Böylelikle, buz önleme sisteminin bilesenlerinin hava araci ile baglantisi kesilerek (bir diger deyisle bahsedilen bilesenler arizaya sokularak) buz önleme sisteminin çalismasi test edilebilmektedir.In the test system developed with the present invention, the first key (1), the second key (2), The third switch (3) and the fourth switch (4) are connected to the aircraft and the anti-icing system. It is ensured that it is connected between the components. Thus, the anti-ice system components are disconnected from the aircraft (in other words, the said components The operation of the anti-icing system can be tested by malfunctioning it.

Claims

1. In an aircraft comprising at least one first heater element and at least one first temperature sensor, at least one second heater element located in at least one engine inlet and at least one anti-icing system with at least one second temperature sensor, said ice It is a test system suitable for testing the prevention system and its features are; at least one body (G); at least one first switch (1), located on the body (G), suitable for connection to said at least one first heating element, and controlling the connection of the at least one first heating element to which it is connected and the aircraft; at least one second switch (2), located on the body (G), suitable for connection to said at least one second heater element, and controlling the connection of the at least one second heater element to which it is connected and the aircraft; at least one third switch (3), which is suitable for connection to said at least one first temperature sensor located on the body (G), and which controls the connection of the at least one first temperature sensor to which it is connected, with the aircraft; at least one fourth switch (4), located on the body (G), suitable for connection to said at least one second temperature sensor, and controlling the connection of the at least one second temperature sensor to which it is connected, with the aircraft; The first key (1), the second key (2), the third key (3) and the fourth key (4), which are connected to the body (G) on at least one side and are suitable for connection to the anti-ice system on at least one other side, are connected to the anti-ice system. at least one first connection line (5); connected to the body (G) on at least one side, suitable for connection to the aircraft on at least one other side, allowing the first key (1), the second key (2), the third key (3) and the fourth key (4) to be connected to the aircraft. It contains at least a second connection line (6).

2. It is a test system in accordance with claim 1 and its feature is; The said first switch (1) has a 2-position switch structure. 4559/TR It is a test system in accordance with Claim 1 or 2 and its feature is; The said second switch (2) has a 2-position switch structure. It is a test system in accordance with any of the above claims and its feature is; The said third switch (3) has a 3-position switch structure. It is a test system in accordance with any of the above claims and its feature is; The said fourth switch (4) has a 3-position switch structure. It is a test system in accordance with any of the above claims and its feature is; The said first connection line (5) contains at least two electrical cables and at least one protection element located outside the said electrical cables. It is a test system in accordance with any of the above claims and its feature is; The said second connection line (6) contains at least two electrical cables and at least one protection element located outside the said electrical cables. It is a test system in accordance with any of the above claims and its feature is; It contains at least one first connection element (7) located on a side of the first connection line (5) that is far from the body (G) and enables the first connection line (5) to be connected to the anti-icing system. It is a test system in accordance with any of the above claims and its feature is; It contains at least one second connection element (8) located on a side of the second connection line (6) that is far from the body (G) and enables the second connection line (6) to be connected to the aircraft. It is a test system in accordance with any of the above claims and its feature is; It contains at least one first gland (9) that enables the first connection line (5) to be connected to the body (G) and at least one second gland (10) that allows the second connection line (6) to be connected to the body (G). 4559/TR