GB2621956A - A thermal trace enhancer system - Google Patents
A thermal trace enhancer system Download PDFInfo
- Publication number
- GB2621956A GB2621956A GB2318439.3A GB202318439A GB2621956A GB 2621956 A GB2621956 A GB 2621956A GB 202318439 A GB202318439 A GB 202318439A GB 2621956 A GB2621956 A GB 2621956A
- Authority
- GB
- United Kingdom
- Prior art keywords
- thermal
- enabling
- trace
- enhancer system
- air
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000003623 enhancer Substances 0.000 title claims 15
- 239000000446 fuel Substances 0.000 claims abstract 15
- 238000002485 combustion reaction Methods 0.000 claims abstract 12
- 239000007789 gas Substances 0.000 claims abstract 11
- 238000006243 chemical reaction Methods 0.000 claims abstract 2
- 238000010438 heat treatment Methods 0.000 claims abstract 2
- 238000001514 detection method Methods 0.000 claims 1
- 239000003350 kerosene Substances 0.000 claims 1
- 239000007788 liquid Substances 0.000 claims 1
- 230000003068 static effect Effects 0.000 claims 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J2/00—Reflecting targets, e.g. radar-reflector targets; Active targets transmitting electromagnetic or acoustic waves
- F41J2/02—Active targets transmitting infrared radiation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- General Engineering & Computer Science (AREA)
- Air-Conditioning For Vehicles (AREA)
- Exhaust Gas After Treatment (AREA)
Abstract
The present invention relates to a body (2) situated on an air vehicle, at least one engine (E) enabling to drive the body (2) to which it is connected, a thermal unit (3) situated on the body (2) so as to be spaced apart from the engine (E), enabling to generate hot gases to increase the thermal trace, at least one air intake (4) provided in the thermal unit (3), enabling air to enter into the thermal unit (3) from the atmosphere, at least one combustion chamber (5) enabling hot gases to be generated as a result of the chemical reaction of fuel and the air taken through the air intake (4), a conductive thermal surface (6) enabling to increase the thermal trace by heat transfer with hot gases leaving the combustion chamber (5) hitting on itself, and at least one exhaust outlet (7) enabling the gases heating up the thermal surface (6) to exit the thermal unit (3).
Claims (14)
1. A thermal trace enhancer system (1) comprising a body (2) situated on an air vehicle, at least one engine (E) enabling to drive the body (2) to which it is connected, a thermal unit (3) situated on the body (2) so as to be spaced apart from the engine (E), enabling to generate hot gases to increase the thermal trace, at least one air intake (4) provided in the thermal unit (3), enabling air supply to the thermal unit (3) from the atmosphere, at least one combustion chamber (5) enabling hot gases to be generated as a result of the chemical reaction of fuel and the air taken through the air intake (4), a conductive thermal surface (6) enabling to increase the thermal trace by becoming heated via heat transfer with hot gases leaving the combustion chamber (5) and hitting on itself, and at least one exhaust outlet (7) enabling the gases heating up the thermal surface (6) to be discharged from the thermal unit (3), characterized by a compressor (8) situated in the thermal unit (3), enabling to compress the air taken through the air intake (4) and to transmit it to the combustion chamber (5), thereby increasing the combustion efficiency, an actuator (9) enabling the compressor (8) to make a rotational motion, and a control unit (10) adjusting the number of revolutions of the actuator (9), thereby enabling to achieve a user-preferred temperature for the thermal surface (6).
2. A thermal trace enhancer system (1) according to claim 1, characterized in that the thermal unit (3) burns kerosene and its derivatives or diesel and its derivatives used as fuel by the engine (E) to generate hot gases.
3. A thermal trace enhancer system (1) according to claim 1 or claim 2, characterized by at least one fuel pump (11) enabling to achieve a user-preferred temperature for the thermal surface (6) by adjusting the flow rate of fuel to be used for the combustion process in the combustion chamber (5).
4. A thermal trace enhancer system (1) according to claim 3, characterized in that the control unit (10) enables to keep and control of the temperature of the thermal surface (6) at the user-preferred value by independently adjusting the flow rate of air through a command it transmits to the actuator (9) and the amount of fuel through a command it transmits to the fuel pump (11).
5. A thermal trace enhancer system (1) according to claim 3 or claim 4, characterized in that the control unit (10) controls the actuator (9) and/or the fuel pump (11) according to temperature data it receives from at least one thermocouple (12) situated at the thermal surface (6) and/or the exhaust outlet (7) to keep the temperature at a user-preferred value.
6. A thermal trace enhancer system (1) according to claims 3 to 5, characterized by at least one sensor (13) situated on the air vehicle, enabling to measure of the air vehicle's speed, altitude, air temperature, static and/or dynamic air pressure data so that the control unit (10) controls the actuator (9) and/or the fuel pump (11) according to the data transmitted to it by the sensor (13) and keeps the temperature of the thermal surface (6) at a user-preferred value.
7. A thermal trace enhancer system (1) according to any of the above claims, characterized by at least one fuel supply line (14) enabling to supply the air vehicle's fuel into the combustion chamber (5), and at least one evaporator (15) converting the liquid fuel from the fuel supply line (14) into a gaseous form so that it can be injected into the combustion chamber (5).
8. A thermal trace enhancer system (1) according to any of the above claims, characterized by at least one igniter (16) having a temperature that evaporates the fuel and enables it to be ignited in the combustion chamber (5).
9. A thermal trace enhancer system (1) according to claim 8, characterized in that the control unit (10) enables the thermal unit (3) to be operated during flight by sending commands to the igniter (16), the fuel pump (11) and the actuator (9).
10. A thermal trace enhancer system (1) according to any of the above claims, characterized by an inner surface (17), which is the first contact surface of hot gases exiting the combustion chamber (5), at least one opening (18) situated on the inner surface (17), enabling hot gases to heat the thermal surface (6) by passing over the inner surface (17), said inner surface (17) having a form in which the distance between the thermal surface (6) and itself becomes narrower towards the exhaust outlet (7).
11. A thermal trace enhancer system (1) according to any of the above claims, characterized in that the temperature of the thermal surface (6) can be adjusted by the control unit (10) to a temperature as required for detection by devices taking infrared images.
12. A thermal trace enhancer system (1) according to any of the above claims, characterized in that the compressor (8) enables to cool the thermal surface (6) in order to reduce the thermal trace in the air vehicle by making use of the air taken through the air intake (4).
13. A thermal trace enhancer system (1) according to any of the above claims, characterized in that the actuator (9) is in the type of an electric motor enabling to actuate the axial or centrifugal compressor (8) .
14. A thermal trace enhancer system (1) according to any of the above claims, characterized by at least one revolution speed sensor (19) that detects the number of revolutions of the actuator (9) and transmits the number of revolutions signal to the control unit (10).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| TR2021009278 | 2021-06-07 | ||
| PCT/TR2022/050532 WO2022260629A2 (en) | 2021-06-07 | 2022-06-06 | A thermal trace enhancer system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB202318439D0 GB202318439D0 (en) | 2024-01-17 |
| GB2621956A true GB2621956A (en) | 2024-02-28 |
Family
ID=84425135
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2318439.3A Pending GB2621956A (en) | 2021-06-07 | 2022-06-06 | A thermal trace enhancer system |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20240263923A1 (en) |
| CN (1) | CN117441087A (en) |
| GB (1) | GB2621956A (en) |
| WO (1) | WO2022260629A2 (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0876579A1 (en) * | 1996-01-22 | 1998-11-11 | Meggitt Defence Systems Limited | Aerial target system |
| TWM281166U (en) * | 2005-07-15 | 2005-11-21 | Pegasus Aviat Technology Co Lt | Infrared generator of aircraft target plane |
| EP2287556A2 (en) * | 2009-08-16 | 2011-02-23 | Eltics Ltd | Network centric system and method for active thermal stealth or deception |
-
2022
- 2022-06-06 CN CN202280040702.5A patent/CN117441087A/en active Pending
- 2022-06-06 WO PCT/TR2022/050532 patent/WO2022260629A2/en active Application Filing
- 2022-06-06 GB GB2318439.3A patent/GB2621956A/en active Pending
- 2022-06-06 US US18/565,713 patent/US20240263923A1/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0876579A1 (en) * | 1996-01-22 | 1998-11-11 | Meggitt Defence Systems Limited | Aerial target system |
| TWM281166U (en) * | 2005-07-15 | 2005-11-21 | Pegasus Aviat Technology Co Lt | Infrared generator of aircraft target plane |
| EP2287556A2 (en) * | 2009-08-16 | 2011-02-23 | Eltics Ltd | Network centric system and method for active thermal stealth or deception |
Also Published As
| Publication number | Publication date |
|---|---|
| GB202318439D0 (en) | 2024-01-17 |
| WO2022260629A3 (en) | 2023-03-02 |
| CN117441087A (en) | 2024-01-23 |
| WO2022260629A2 (en) | 2022-12-15 |
| US20240263923A1 (en) | 2024-08-08 |
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