Thermal trajectory enhancer system

Abstract

The present invention relates to: a body (2) located on an aircraft vehicle; at least one engine (E) capable of driving the body (2) connected thereto; a thermal unit (3) positioned on the body (2) spaced apart from the engine (E) and capable of generating hot gas to enhance the thermal trajectory; at least one air inlet (4) disposed in the thermal unit (3) and capable of allowing air to enter the thermal unit (3) from the atmosphere; at least one combustion chamber (5) capable of generating hot gas due to the chemical reaction of fuel with air entering through the air inlet (4); a heat-conducting surface (6) capable of enhancing the thermal trajectory by heat conduction with hot gas leaving the combustion chamber (5) and impacting the heat-conducting surface itself; and at least one exhaust port (7) capable of allowing gas that has heated the thermal surface (6) to leave the thermal unit (3).

Description

[0001] This invention relates to a system for generating temperature-controlled thermal trajectories for target aircraft.

[0002] The target aircraft is typically an unmanned aerial vehicle (UAV) that, in military exercises or missile development projects, can mimic enemy aircraft and missiles in terms of speed, maneuverability, thermodynamics, or radar trajectory. With these capabilities, they can be used in missile development projects such as air-to-air / surface-to-air missile systems or air defense systems, in military training and exercises such as air defense firing and radar tracking, and in many different tasks such as measuring opportunities and capabilities for target detection and tracking of fighter jets.

[0003] To generate the thermal trajectory required for a target aircraft, a heating system is typically installed on the nose of the aircraft in a manner that does not compromise its aerodynamic integrity. The thermal trajectory, or radiation, generated by this system is proportional to the system's surface temperature. This high radiation ensures that infrared seekers or thermal measurement devices are locked onto the target at greater distances. For these thermal trajectory enhancement systems, two types of methods are typically employed: fuel-powered and electric. While both types of methods have their advantages, the primary deciding criterion is their suitability for existing aircraft.

[0004] The existing technology includes a Taiwanese patent document, TWM281166, which describes a switch-type heater system that can bring a thermal target to a predetermined temperature for use in thermally guided missile testing. A temperature sensor in the system configuration can continuously measure the combustion temperature of the combustion chamber, and when the temperature value is lower than the predetermined value, the temperature sensor can activate a switch and transfer power to the ignition mechanism for ignition, thereby ensuring that the predetermined temperature is reached through ignition and combustion.

[0005] The prior art includes UK patent document EP0876579, which relates to a thermal unit with a temperature sufficient to be detected and monitored by an infrared search and defense weapon system. This thermal unit, mounted on an aerial target, includes a thermally conductive surface for generating a thermal trajectory and a combustion chamber using propane or MAP GAS as fuel, thereby providing continuous heating to the surface.

[0006] The thermal trajectory enhancer system developed by this invention ensures that the temperature is regulated to the required value and can be activated at any desired time. Due to its low fuel consumption, this system provides a solution for target aircraft that does not limit aircraft operating time, requires no external cooling, can reach high temperatures due to the absence of rotating components at high temperatures, and has low maintenance costs.

[0007] A thermal trajectory enhancer system (defined in the first claim and claims dependent on it), implemented to achieve the objectives of the present invention, is coupled to the body of an air vehicle of the target aircraft / target unmanned aerial vehicle type to provide propulsion and enable the air vehicle to move using at least one engine. Performance testing and simulation of the thermal trajectory enhancement and infrared sensing equipment can be performed by positioning the thermal unit at a location on the body different from the engine (preferably in the nose region where the body first encounters wind). To enhance the thermal trajectory, the thermal unit is provided with at least one combustion chamber in which a combustion reaction occurs to generate hot gases, and the air required for the combustion reaction enters the combustion chamber through at least one air inlet, and fuel is supplied accordingly. The hot gases released from the combustion reaction in the combustion chamber then impact an almost spherical hot surface to increase the temperature of the heat-conducting surface, and then exit the thermal unit through at least one exhaust port.

[0008] The thermal trajectory enhancer system according to the invention includes a compressor located in a thermal unit for compressing air entering from the atmosphere through an intake port, reducing the air volume and increasing its pressure, and then supplying the high-pressure air to the combustion chamber for combustion reaction, thereby improving the efficiency of the combustion process. The compressor is triggered during its rotational operation by at least one actuator located in the cold zone of the thermal unit. The flow rate of the air drawn into the compressor is regulated by adjusting the number of rotations of the actuator using a signal transmitted from a control unit to the actuator, and the temperature of the hot surface is maintained at a user-desired temperature.

[0009] In one embodiment of the invention, the thermal trajectory enhancer system does not require an additional fuel tank because both the engine that enables the aircraft to move and the thermal unit that enhances the thermal trajectory are supplied with kerosene and its derivatives or diesel and its derivatives, thus saving weight and volume.

[0010] In one embodiment of the invention, the thermal trajectory enhancer system includes at least one fuel pump, which is capable of controlling the amount of fuel required for combustion in the combustion chamber by means of a signal transmitted from the control unit, thereby adjusting the temperature of the hot surface to a value desired by the user.

[0011] In one embodiment of the invention, the thermal trajectory enhancer system can control the airflow received by the thermal unit via a signal transmitted from the control unit to the actuator, and control the amount of fuel delivered to the combustion chamber via a signal transmitted from the control unit to the fuel pump. Since the airflow and fuelflow can be controlled independently of each other, the temperature of the hot surface can be maintained at the user-desired value even at lower ambient temperatures and higher airflow velocities.

[0012] In one embodiment of the invention, the thermal trajectory enhancer system can adjust the temperature on a hot surface to a user-desired value using at least one thermocouple, which is used to obtain instantaneously measured temperature data from the hot surface or exhaust port. The instantaneous temperature data measured by the at least one thermocouple is transmitted to a control unit for evaluation, and when the hot surface temperature is lower than the user-desired value, the amount of incoming air and / or fuel is increased via instructions transmitted from the control unit to the actuator and / or fuel pump. Since the thermal unit may be damaged or pose a fire risk when the hot surface temperature is higher than the user-desired value, the amount of incoming air and / or fuel can be reduced via instructions transmitted from the control unit to the actuator and / or fuel pump, respectively.

[0013] In one embodiment of the thermal trajectory enhancer system of the present invention, the control unit uses data measured by at least one sensor on the aircraft to detect the aircraft's speed, altitude, ambient temperature, static air pressure, and dynamic air pressure, and transmits the signals to the actuator and / or fuel pump respectively to control the flow rate of air and the amount of fuel supplied to the thermal unit, thereby enabling the thermal surface to reach the temperature required by the user.

[0014] In one embodiment of the invention, the thermal trajectory enhancer system includes: at least one fuel supply line used by an aircraft to deliver kerosene and its derivatives or diesel and its derivatives to a combustion chamber; and an evaporator for vaporizing the liquid fuel delivered by the fuel supply line and injecting it into the combustion chamber for combustion reaction.

[0015] In one embodiment of the thermal trajectory enhancer system of the present invention, an igniter disposed in the combustion chamber and having a temperature sufficient to vaporize the fuel triggers a combustion reaction by providing a spark, causing a chemical reaction between the fuel injected into the combustion chamber through the evaporator and the pressurized air from the compressor. Since combustion can only continue under the action of fuel and air, the use of an igniter is crucial for initiating the combustion reaction.

[0016] In one embodiment of the thermal trajectory enhancer system of the present invention, the thermal unit can be activated during flight without ground operation and thus saves fuel and energy because the control unit has the following capabilities: activating / deactivating and controlling the level of the igniter that provides the first ignition, activating / deactivating and controlling the level of the fuel pump that regulates the amount of fuel, and activating / deactivating and controlling the level of the actuator that regulates the flow of air.

[0017] In one embodiment of the invention, the thermal trajectory enhancer system provides heating to a hot surface by allowing hot gas to pass through at least one opening on the inner surface, which is the first contact surface with the hot gas released from the combustion reaction in the combustion chamber. Preferably, the opening on the dome-shaped inner surface is located at the center of the top of the dome. The distance between the inner surface and the hot surface narrows towards the exhaust port, and the hot surface is heated more effectively due to the passage of hot gas through the narrowed volume.

[0018] In one embodiment of the thermal trajectory enhancer system of the present invention, in order to bring the temperature of the hot surface to a temperature that can be detected by infrared sensing devices (such as air defense systems, missiles under test, etc.), the control unit controls the actuator and / or fuel pump to adjust the hot surface.

[0019] In one embodiment of the invention, the thermal trajectory enhancer system actively cools the temperature of the hot surface by adjusting the amount of air drawn in by the compressor and by the control unit shutting down the thermal unit, thereby preventing the risk of the aircraft catching fire or damaging the thermal unit at high temperatures.

[0020] In one embodiment of the invention, the thermal trajectory enhancer system utilizes an electric motor to actuate an axial or centrifugal compressor that rotates during thermal unit operation. The electric motor can be a brushed DC motor or a brushless DC motor. Brushless DC motors are preferred as actuators due to their compact design, high speed, and low maintenance costs.

[0021] In one embodiment of the invention, the thermal trajectory enhancer system measures the number of rotations of the actuator in real time and transmits this data to the control unit, thereby controlling the number of rotations through a closed-loop control system. Therefore, by comparing the measured number of rotations with the number of rotations determined based on the signal transmitted from the control unit, the number of rotations providing the required airflow can be controlled.

[0022] The thermal trajectory enhancer system implemented to achieve the objectives of the present invention is shown in the accompanying drawings, in which...

[0023] Figure 1 This is a schematic diagram of a thermal trajectory enhancer system.

[0024] Figure 2 This is a cross-sectional view of the thermal unit.

[0025] Figure 3 It is a schematic diagram of the combustion chamber, evaporator, igniter, and fuel supply lines.

[0026] Figure 4 This is a schematic diagram of a thermal unit and a thermocouple.

[0027] Figure 5 This is a block diagram of the control unit.

[0028] The components shown in the accompanying drawings are independently assigned reference numbers, and the corresponding terms for these numbers are as follows.

[0029] 1. Thermal Track Enhancer System

[0030] 2.Ontology

[0031] 3. Thermal unit

[0032] 4. Air Inlet

[0033] 5. Combustion chamber

[0034] 6. Hot surface

[0035] 7. Exhaust port

[0036] 8. Compressor

[0037] 9. Actuator

[0038] 10. Control Unit

[0039] 11. Fuel pump

[0040] 12. Thermocouple

[0041] 13. Sensors

[0042] 14. Fuel supply pipelines

[0043] 15. Evaporator

[0044] 16. Igniter

[0045] 17. Inner surface

[0046] 18. Opening

[0047] 19. Rotational speed sensor

[0048] (E) Engine

[0049] The thermal trajectory enhancer system (1) includes: a body (2) located on an aircraft vehicle; at least one engine (E) capable of moving the body (2) to which it is connected; a thermal unit (3) positioned on the body (2) spaced apart from the engine (E) and capable of generating hot gas to enhance the thermal trajectory; at least one air inlet (4) disposed in the thermal unit (3) and capable of allowing air to enter the thermal unit (3) from the atmosphere; at least one combustion chamber (5) capable of chemically reacting fuel with air entering through the air inlet (4) to generate hot gas; a heat-conducting surface (6) capable of enhancing the thermal trajectory by conducting heat with the hot gas leaving the combustion chamber (5) and impacting the heat-conducting surface itself; and at least one exhaust port (7) capable of allowing the gas heating the thermal surface (6) to leave the thermal unit (3). Figure 1 ).

[0050] The thermal trajectory enhancer system (1) according to the present invention includes: a compressor (8) located in a thermal unit (3) capable of compressing air entering from an air inlet (4) and transmitting it to a combustion chamber (5) to improve combustion efficiency; an actuator (9) capable of causing the compressor (8) to rotate; and a control unit (10) for adjusting the number of revolutions of the actuator (9) so that the temperature on the hot surface (6) reaches the temperature required by the user.

[0051] The thermal unit (3) can be heated to a higher temperature to enhance the thermal trajectory. The thermal unit is positioned on an aerodynamic surface called the body (2) on an aircraft, which can be any target aircraft / target UAV. The thermal unit (3) is preferably located in the nose area, i.e., the surface on which the aircraft first encounters the wind. The thermal unit (3), positioned separately from at least one engine (E) capable of moving the aircraft, is heated by hot gases formed in at least one combustion chamber (5), where fuel reacts chemically with air entering through at least one air inlet (4) on the thermal unit (3). The hot gases generated in the combustion chamber (5) heat the heat-conducting surface (6) in a convective manner and improve thermal visibility through equipment such as missiles and air defense systems. At least one exhaust port (7) is provided to allow the hot gases impacting the hot surface (6) to exit the thermal unit (3). Figure 1 )

[0052] Because of the compressor (8) in the thermal unit (3), the air entering from the atmosphere through the intake port (4) is compressed and its pressure increases due to its radial or axial movement, thereby improving the performance and efficiency of the combustion reaction in the combustion chamber (5). The number of rotations of the compressor (8) is adjusted according to the instructions transmitted by the control unit (10) via an actuator (9) that provides the radial movement required for the operation of the compressor (8), thereby increasing or decreasing the flow rate of the incoming air and maintaining the temperature of the hot surface (6) at a user-preferred value. Figure 2 )

[0053] In one embodiment of the thermal trajectory enhancer system (1) of the present invention, the thermal unit (3) burns kerosene and its derivatives or diesel and its derivatives used by the engine (E) to generate hot gas. The thermal unit (3) capable of enhancing the thermal trajectory and the engine (E) capable of moving the aircraft are located in separate positions, but both use kerosene and its derivatives or diesel and its derivatives as fuel to achieve their functions. By using fuel from the same housing ( Figure 5 Use the same type of fuel to save volume.

[0054] In one embodiment of the invention, the heat trajectory enhancer system (1) includes at least one fuel pump (11) capable of bringing the hot surface (6) to a user-desired temperature by adjusting the flow rate of fuel used in the combustion process in the combustion chamber (5). Increasing the amount of fuel used in the combustion reaction can increase the temperature of the hot surface (6). Similarly, decreasing the amount of fuel can decrease the temperature of the hot surface (6). The ability to adjust the temperature of the hot surface (6) to the user-desired value can be achieved by controlling the flow rate of fuel using the fuel pump (11).

[0055] In one embodiment of the thermal trajectory enhancer system (1) of the present invention, the control unit (10) allows the temperature of the hot surface (6) to be maintained and controlled at a value desired by the user by independently adjusting the air flow rate using instructions transmitted to the actuator (9) and independently adjusting the amount of fuel using instructions transmitted to the fuel pump (11). The air flow rate of the combustion chamber (5) can be independently controlled by the signal transmitted from the control unit (10) to the actuator (9), and the amount of fuel received in the combustion chamber (5) can be independently controlled by the signal transmitted to the fuel pump (11), thereby allowing the user to adjust the temperature of the hot surface (6) to the desired value.

[0056] In one embodiment of the thermal trajectory enhancer system (1) of the present invention, the control unit (10) controls the actuator (9) and / or the fuel pump (11) based on temperature data received by means of at least one thermocouple (12) located on the hot surface (6) and / or the exhaust port (7) to maintain the temperature at a value desired by the user. Temperature data is measured instantaneously by means of the thermocouple (12) located on the hot surface (6) and / or the exhaust port (7), the measured data is evaluated in the control unit (10), and the signal is transmitted by the control unit (10) to the actuator (9) and / or the fuel pump (11), thereby allowing the temperature of the hot surface (6) to be adjusted to a value desired by the user. Figure 4 ).

[0057] In one embodiment of the invention, the thermal trajectory enhancer system (1) includes at least one sensor (13) on the aircraft, capable of measuring the aircraft's speed, altitude, air temperature, static air pressure, and / or dynamic air pressure data, such that the control unit (10) controls the actuator (9) and / or fuel pump (11) based on the data transmitted to it by the sensor (13), and maintains the temperature of the hot surface (6) at a value desired by the user. The aircraft's speed, ambient temperature, static air pressure, and / or dynamic air pressure are measured in real time by the sensor (13) located on the aircraft, and the data is transmitted to the control unit (10). Instructions generated by the control unit (10) based on the received data are sent to the actuator (9) and / or fuel pump (11), such that the hot surface (6) can achieve the user-desired temperature.

[0058] In one embodiment of the invention, the thermal trajectory enhancer system (1) includes: at least one fuel supply line (14) capable of delivering fuel from an aircraft vehicle to a combustion chamber (5); and at least one evaporator (15) converting liquid fuel from the fuel supply line (14) into a gaseous form so that it can be injected into the combustion chamber (5). To ensure the use of liquid fuel for the combustion process in the thermal unit (3) to initiate the combustion process, the liquid fuel delivered through the fuel supply line (14) is injected into the combustion chamber (5) via the evaporator (15) and delivered in a gaseous form. Thereby, the liquid fuel chemically reacts with air to form a hot gas (…). Figure 3 ).

[0059] In one embodiment of the invention, the heat trail enhancer system (1) includes at least one igniter (16) whose temperature is sufficient to vaporize and ignite fuel in the combustion chamber (5). The temperature of the igniter (16) allows the fuel to vaporize and ignite the fuel injected into the combustion chamber (5) via the evaporator (15), thereby initiating the first combustion. Once the first combustion begins and the temperature of the combustion chamber (5) reaches a certain value ( Figure 3 The igniter will then stop working.

[0060] In one embodiment of the thermal trajectory enhancer system (1) of the present invention, the control unit (10) is able to operate the thermal unit (3) during flight by sending commands to the igniter (16), the fuel pump (11), and the actuator (9). Since the control unit (10) sends commands to the igniter (16) to ignite the injected fuel, to the actuator (9) to adjust the number of rotations to regulate the amount of compressed air in the combustion chamber (5), and to the fuel pump (11) to regulate the amount of fuel delivered to the combustion chamber (5), it is not necessary to initiate the combustion process on the ground. By igniting the fuel and continuing the combustion process during flight, it is ensured that the hot surface (6) can be adjusted to the user's desired value.

[0061] In one embodiment of the invention, the heat trajectory enhancer system (1) includes: an inner surface (17) that is the first contact surface when hot gas leaves the combustion chamber (5); and at least one opening (18) on the inner surface (17) to allow the hot gas to heat the heat-conducting surface (6) by passing through the inner surface (17); and the inner surface (17) is shaped such that the distance between the hot surface (6) and the inner surface itself narrows toward the exhaust port (7). The hot gas formed by the combustion reaction in the combustion chamber (5) passes through the opening (18) on the inner surface (17), thereby impacting and heating the heat-conducting surface (6). In order for the hot air to better transfer its thermal energy to the hot surface (6), the distance between the hot surface (6) and the inner surface (17) narrows toward the exhaust port (7). This narrowing is due to the fact that the hot surface (6) is almost entirely a hemispherical shape conforming to the aerodynamic flow, the inner surface (17) is almost entirely a semi-dome shape with a top cutout, and the inner surface (17) is disposed within the hot surface (6).

[0062] In one embodiment of the thermal trajectory enhancer system (1) of the present invention, the temperature of the hot surface (6) can be adjusted by the control unit (10) according to the temperature required for detection by the device capturing the infrared image. The user can adjust the temperature of the hot surface (6) to the desired value by controlling the actuator (9) and / or the fuel pump (11) with the aid of the control unit (10), because the user has pre-input the temperature required by the detection device such as missiles, air defense systems, etc. into the control unit (10).

[0063] In one embodiment of the thermal trajectory enhancer system (1) of the present invention, the compressor (8) is able to cool the hot surface (6) using air entering through the air inlet (4), thereby reducing the thermal trajectory of the aircraft. The cold air entering through the air inlet (4) is used to ensure the elimination of the risk of fire due to overheating of the hot surface (6), or other risks due to the hot components of the thermal unit (3) reaching temperatures that are structurally unbearable.

[0064] In one embodiment of the thermal trajectory enhancer system (1) of the present invention, the actuator (9) is an electric motor capable of actuating an axial compressor or a centrifugal compressor (8). The electric motor can be a brushed DC motor or a brushless DC motor. Specifically, a brushless DC motor is preferably used to drive an axial compressor or a centrifugal compressor (8) to rotate because it is easy to maintain, occupies little space, is easy to control, and can reach high speeds.

[0065] In one embodiment of the invention, the thermal trajectory enhancer system (1) includes at least one rotation speed sensor (19) that detects the number of rotations of the actuator (9) and transmits the rotation speed signal to the control unit (10). To maintain the hot surface (6) at the value required by the user, the required airflow must enter the thermal unit (3). To adjust the airflow, the rotation speed sensor (19) detects the number of rotations of the actuator (9) and transmits it to the control unit (10), such that the value measured by the rotation speed sensor (19) is compared with the signal transmitted by the control unit (10), thereby causing the actuator (9) to operate at an appropriate number of rotations using the newly transmitted signal from the control unit (10).

Claims

1. A thermal trajectory enhancer system (1), comprising: Body (2), located on an air vehicle; at least one engine (E) capable of driving the body (2) connected to at least one of the engines. A thermal unit (3) is positioned on the body (2) at a distance from the engine (E), and the thermal unit is capable of generating hot gas to enhance the thermal trajectory; At least one air inlet (4) is provided in the thermal unit (3) to supply air from the atmosphere to the thermal unit (3); at least one combustion chamber (5) is capable of generating hot gas due to the chemical reaction of fuel with air entering through the air inlet (4); The heat-conducting surface (6) can be heated by heat conduction with the hot gas leaving the combustion chamber (5) and impacting the heat-conducting surface itself, thereby enhancing the thermal trajectory; The system includes at least one exhaust port (7) for discharging gas that heats the hot surface (6) from the heat unit (3), characterized in that the heat trajectory enhancer system further includes: a compressor (8) located within the heat unit (3), the compressor being able to compress air entering through the air inlet (4) and transmit the air to the combustion chamber (5) to improve combustion efficiency; an actuator (9) for rotating the compressor (8); and a control unit (10) for adjusting the number of rotations of the actuator (9) to enable the hot surface (6) to achieve the temperature desired by the user.

2. The thermal trajectory enhancer system (1) according to claim 1, characterized in that, The thermal unit (3) burns kerosene and its derivatives or diesel and its derivatives, which are used as fuel for the engine (E), to generate hot gas.

3. The thermal trajectory enhancer system (1) according to claim 1 or 2, characterized in that, The thermal trajectory enhancer system also includes at least one fuel pump (11) capable of adjusting the flow rate of fuel used for the combustion process in the combustion chamber (5) to achieve the desired temperature of the hot surface (6).

4. The thermal trajectory enhancer system (1) according to claim 3, characterized in that, The control unit (10) can independently adjust the airflow through instructions transmitted from the control unit to the actuator (9) and independently adjust the amount of fuel through instructions transmitted from the control unit to the fuel pump (11), thereby maintaining and controlling the temperature of the hot surface (6) at the value desired by the user.

5. The thermal trajectory enhancer system (1) according to claim 3, characterized in that, The control unit (10) controls the actuator (9) and / or the fuel pump (11) based on temperature data received from at least one thermocouple (12) to maintain the temperature at a value desired by the user, the at least one thermocouple being located at the hot surface (6) and / or the exhaust port (7).

6. The thermal trajectory enhancer system (1) according to claim 3, characterized in that, The thermal trajectory enhancer system includes at least one sensor (13) positioned on the aircraft, capable of measuring the aircraft's speed, altitude, air temperature, static pressure, and / or dynamic pressure data, such that the control unit (10) controls the actuator (9) and / or the fuel pump (11) based on the data transmitted from the sensor (13) to the control unit, and maintains the temperature of the hot surface (6) at a value desired by the user.

7. The thermal trajectory enhancer system (1) according to claim 3, characterized in that, The thermal trajectory enhancer system includes: at least one fuel supply line (14) capable of supplying fuel from an aircraft vehicle to the combustion chamber (5); and at least one evaporator (15) converting liquid fuel from the fuel supply line (14) into a gaseous form so that it can be injected into the combustion chamber (5).

8. The thermal trajectory enhancer system (1) according to claim 7, characterized in that, The thermal trajectory enhancer system includes at least one igniter (16) having a temperature that causes fuel to evaporate and ignite fuel injected into the combustion chamber (5) via the evaporator (15) to initiate initial combustion.

9. The thermal trajectory enhancer system (1) according to claim 8, characterized in that, The control unit (10) can enable the thermal unit (3) to operate during flight by sending commands to the igniter (16), the fuel pump (11) and the actuator (9).

10. The thermal trajectory enhancer system (1) according to claim 1, characterized in that, The heat trajectory enhancer system includes: an inner surface (17) which is the first contact surface when hot gas leaves the combustion chamber (5); at least one opening (18) located on the inner surface (17) and capable of heating the hot surface (6) by allowing hot gas to pass over the inner surface (17), the inner surface (17) being shaped such that the distance between the hot surface (6) and the inner surface narrows toward the exhaust port (7).

11. The thermal trajectory enhancer system (1) according to claim 1, characterized in that, The temperature of the hot surface (6) can be adjusted by the control unit (10) to the temperature required for detection by the device that captures infrared images.

12. The thermal trajectory enhancer system (1) according to claim 1, characterized in that, The compressor (8) can cool the hot surface (6) by using the air entering through the air inlet (4), thereby reducing the thermal trajectory of the aircraft.

13. The thermal trajectory enhancer system (1) according to claim 1, characterized in that, The actuator (9) is an electric motor capable of actuating an axial compressor or a centrifugal compressor (8).

14. The thermal trajectory enhancer system (1) according to claim 1, characterized in that, The thermal trajectory enhancer system includes at least one rotation speed sensor (19) that detects the number of rotations of the actuator (9) and transmits the rotation number signal to the control unit (10).

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