CN110466742B - Integrated infrared suppression system and method for helicopter rear fuselage slotting - Google Patents
Integrated infrared suppression system and method for helicopter rear fuselage slotting Download PDFInfo
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- CN110466742B CN110466742B CN201910699609.5A CN201910699609A CN110466742B CN 110466742 B CN110466742 B CN 110466742B CN 201910699609 A CN201910699609 A CN 201910699609A CN 110466742 B CN110466742 B CN 110466742B
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- 230000001629 suppression Effects 0.000 title claims abstract description 24
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- 230000005855 radiation Effects 0.000 claims abstract description 21
- 230000000694 effects Effects 0.000 claims description 7
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- 230000007423 decrease Effects 0.000 claims 1
- 238000010438 heat treatment Methods 0.000 abstract description 10
- 230000002349 favourable effect Effects 0.000 abstract description 2
- 238000013461 design Methods 0.000 description 5
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- 238000005516 engineering process Methods 0.000 description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses an integrated infrared suppression system and a method for slotting a rear fuselage of a helicopter.A guide plate and a baffle plate are respectively arranged on the inner side and the outer side of a special-shaped pipe, the guide plate organizes the flow of rotor downwash airflow in the rear fuselage, the flow loss is reduced, the rotor downwash airflow can flow into the rear fuselage, and the guide plate can block the special-shaped pipe from heating other devices in the rear fuselage; the baffle plate can prevent the high-temperature special pipe from directly radiating and heating the rear machine body, the surface temperature of the rear machine body is greatly reduced, and the louver flow deflectors on the baffle plate are favorable for guiding more downward washing air flow to cool the high-temperature special pipe. The invention leads the lower washing air flow to flow out through the slit to cool the lower side wall of the rear machine body, thereby greatly reducing the temperature of the lower side wall of the rear machine body and infrared radiation signals.
Description
Technical Field
The invention relates to an integrated infrared suppression system and method for slotting a helicopter rear fuselage, and belongs to the technical field of design and infrared suppression of an aircraft engine exhaust system.
Background
Military helicopters are essentially a multi-functional platform whose functions can be expanded according to mission requirements. When the device is used as an ultra-low-altitude fire platform, various ground, water surface, underwater and ultra-low-altitude targets can be effectively and accurately struck, the device plays more and more important roles in small-scale local conflict, miniaturized local warfare and international anti-terrorism action, and obtains good combat effect; when the helicopter is used as a non-fire platform, the helicopter can be used for executing various tasks such as mine sweeping, mine laying, air command and early warning, emergency transportation and the like, obtains good effects and fully displays the unique functions of the helicopter. Therefore, the helicopter has irreplaceable status and function in modern naval, terrestrial and air integrated battles, is an important target for national defense development, and is one of the main defense targets of air defense weapons. With the development of infrared detection and tracking technology and the application of infrared guided weapons, the survival capability of helicopters is greatly threatened, and the research and analysis of the infrared radiation characteristics of helicopter targets becomes one of the key points of air defense weapons, and is more the key of the air target research.
Since the 80 s in the 20 th century, a great deal of basic and application research is carried out by many researchers at home and abroad aiming at the infrared characteristics of helicopters and the inhibition technology thereof, great progress is made, and a third-generation exhaust nozzle infrared inhibition device is formed. The first generation sleeve type infrared suppression device is mainly used for resisting the threat of the infrared guided missile with the wave band of 1-3 mu m; the bent mixing pipe is adopted to shield high-temperature components of the engine so as to reduce the radiation of a hot metal part of the rear hemisphere at the tail of the engine, and no effective measure is taken for high-temperature tail gas; a typical application of which is represented by the exhaust deflector of the ASTAZON engine of the french little antelope helicopter. The wavelength range of the countermeasures of the second generation of injection type infrared suppression device is 3-5 mu m, the radiation of a high-temperature solid component is reduced, the temperature of exhaust gas is required to be greatly reduced, and the radiation of tail flames is reduced; the principle is that the exhaust kinetic energy of the engine is used for pumping the ambient cold air and mixing the ambient cold air with the hot jet flow; the core technology is an injection nozzle structure with large injection flow ratio, high mixing efficiency and low flow loss; typical structures are lobe jet nozzles, and a large amount of equipment is obtained on helicopters such as French dolphin SA365C, British mountain cat Lynx-3, Russian Mi-28 and the like. The third generation integrated infrared suppression device has the infrared stealth function of the double wave bands of 3-5 mu m and 8-14 mu m. The integrated infrared suppression is developed on the basis of a second generation infrared suppressor, an infrared suppression system is fused into a tail beam of a rear fuselage, and the core mechanism of the integrated infrared suppression is that the mixing and cooling functions of downwash airflow of a rotor wing and the shielding and heat insulation functions of the fuselage are fully utilized; the representative application is the Komanchi RAH-66 helicopter which is jointly developed by the United states Boeing and West Kesky company; the integrated design of the exhaust system and the helicopter body is beneficial to meeting the requirements of the helicopter on radar, infrared, visual and acoustic omnibearing stealth, and the overall aerodynamic layout is considered while the internal space of the tail beam is effectively utilized.
At present, the research on the infrared suppressors mainly aims at the second generation of injection type infrared suppressors, the research on the integrated infrared suppressors is relatively less, and the design of the integrated infrared suppressors represented by the Coleman helicopter is the development direction of stealth design of future helicopters. The temperature of the skin of the rear fuselage of the existing integrated infrared suppressor is still high, the highest temperature of the skin of the fuselage is about 60-80K higher than the ambient temperature, and the integrated infrared suppressor still has a large improvement space and needs to be optimally designed.
Disclosure of Invention
The purpose of the invention is as follows: the invention discloses an integrated infrared suppression system for slotting a rear fuselage of a helicopter, which blocks direct radiation heating of a high-temperature mixing pipe on the side wall surface of the rear fuselage through a shutter radiation shielding structure, and greatly reduces the temperature of the upper side wall surface of the rear fuselage; through the slit opening, the lower washing air flow is guided to cool the temperature rise of the lower side wall surface caused by high-temperature exhaust radiation heating, so that the infrared radiation signal of the whole fuselage skin is reduced to the greatest extent.
The technical scheme for realizing the purpose is as follows:
an integrated infrared suppression system for a helicopter rear body slot comprises a special pipe positioned in a rear body, wherein an outlet of the special pipe is positioned on a concave platform in the middle of the rear body, and a lower washing air inlet is formed in the top wall surface of the rear body right above the special pipe; the annular opening on the periphery of the outlet of the special pipe on the concave platform in the middle of the rear machine body is a lower washing airflow outlet.
Furthermore, the outside of mechanical tubes is equipped with the shielding plate, and the shielding plate shunts the lower washing air current that gets into the back fuselage, and it has a plurality of tripe water conservancy diversion opening to open on the shielding plate, and tripe water conservancy diversion piece that the lower side limit of tripe water conservancy diversion opening is connected with the slant and becomes the acute angle with the upside of shielding plate, and from the side of the back fuselage lateral wall face, the shutter radiation shelter from the structure that shielding plate and tripe water conservancy diversion piece formed can shelter from the high temperature region of mechanical tubes completely.
Furthermore, a guide plate is arranged on the inner side of the special pipe, the upper side of the guide plate is overlapped with the inner side edge of the rotor wing downwash air inlet on the upper portion of the rear machine body, the middle portion of the lower side of the guide plate is connected with the slit channel plate, and the guide plate divides the special pipe positioned in the rear machine body and the rest space into two parts.
Further, the slit channel plate is located the inboard of back fuselage middle part indent platform downside wall to form narrow passageway with back fuselage middle part indent platform downside wall, be equipped with a plurality of slit opening on the downside wall of this department, be equipped with a plurality of pocket aerofoil in the narrow passageway, the one end of pocket aerofoil is fixed in slit open-ended downside limit, and the length that extends and extend in the passageway is gone up to the other end slant and the pocket aerofoil of lower extreme seals the lower extreme of narrow passageway. Part of the lower washing air flow flows out from the lower washing air flow outlet, and part of the lower washing air flow flows out from the slit opening under the guidance of the guide plate, the slit channel and the wind pocket plate.
Furthermore, the width of the slit opening is 10-20mm, and the number of the openings is multiple.
Further, the outlet area of the section tube is not smaller than the inlet area of the section tube.
Further, the cross section area of the outlet section of the special pipe along the flow direction is gradually reduced, and the sum of the area of any cross section of the outlet section of the special pipe along the flow direction and the area of the outlet of the special pipe before the cross section is not less than the area of the inlet of the special pipe.
An integrated infrared suppression method for helicopter rear fuselage slotting comprises the following steps:
the rotor wing downwash airflow enters the rear fuselage from a downwash airflow inlet, and the downwash airflow is divided into three strands by the special pipe and the baffle plate; a first strand of lower washing air flow enters a gap between the shielding plate and the upper side wall surface of the rear machine body, wherein part of the lower washing air flow flows to a lower washing air flow outlet under the flow guide effect of the shielding plate to cool the shielding plate and the upper side wall surface of the rear machine body, and part of the lower washing air flow enters the gap between the shielding plate and the special pipe through the shutter flow guide opening; the second downward washing airflow flows to the downward washing airflow outlet from the gap between the shielding plate and the special pipe to cool the outer wall surface of the special pipe; the third downward washing air flow enters the gap between the guide plate and the special pipe, part of the air flow flows to the downward washing air outlet under the guide action of the guide plate to cool the inner side wall surface of the special pipe, and part of the air flow flows out through the slit opening under the guide action of the slit channel plate and the air pocket plate to cool the lower side wall of the rear machine body.
Has the advantages that:
according to the invention, the guide plates and the louver radiation shielding structures are respectively arranged on the inner side and the outer side of the special pipe, the guide plates organize the flow of the rotor wing downwash airflow in the rear machine body, the flow loss is reduced, the rotor wing downwash airflow can flow into the rear machine body conveniently, and meanwhile, the guide plates prevent the special pipe from heating other devices in the rear machine body; the shutter radiation shielding structure can prevent the high-temperature special pipe from directly radiating and heating the rear machine body, the surface temperature of the rear machine body is greatly reduced, and the shutter flow deflectors on the shutter radiation shielding structure are favorable for guiding more downwash airflow to cool the high-temperature special pipe. The air flow discharged by the special pipe still has higher temperature, and has stronger radiation heating effect on the lower side wall surface of the rear machine body; according to the invention, the slit opening is formed on the wall surface of the rear machine body below the exhaust outlet of the special pipe, so that the lower washing air flow is guided to flow out through the slit to cool the lower side wall of the rear machine body, and thus the temperature of the lower side wall surface of the rear machine body and infrared radiation signals are greatly reduced.
Drawings
FIG. 1 is a schematic overall view of a slotted integrated infrared suppression system for a helicopter rear fuselage in accordance with the present invention;
FIGS. 2(a), (b), (c) and (d) are sectional views of a slotted integrated IR suppression system for a helicopter aft fuselage in accordance with the present invention;
FIGS. 3(a) and (b) are schematic views of the combination structure of the baffle and the louver;
fig. 4(a), (b), (c) and (d) are schematic structural diagrams of the special pipe, and (d) shows any cross section of the outlet section of the special pipe along the flow direction and the outlet of the special pipe before the cross section;
FIG. 5 is a schematic view of a baffle;
FIGS. 6(a), (b), (c) and (d) are schematic views of the whole structure of the slit passage plate and the air inlet plate and the assembly structure of the components;
FIG. 7 is a schematic view of a cross-sectional position of a slotted integrated IR suppression system for a helicopter aft fuselage in accordance with the present invention;
FIG. 8 is a schematic view of the structure and flow at section A-A;
wherein, 1 is a rear machine body, 2 is a guide plate, 3 is a special pipe, 4 is a slit opening, 5 is a lower washing air inlet, 6 is a baffle plate, 7 is a shutter guide plate, 8 is a lower washing air outlet, 9 is a special pipe outlet, 10 is a wind-pocket plate, 11 is a shutter guide opening, and 12 is a slit channel plate.
Detailed Description
The invention provides an integrated infrared suppression system for helicopter rear fuselage slotting, and in order to make the purpose, technical scheme and effect of the invention clearer and clearer, the invention will be described in more detail by referring to the attached drawings in the embodiment of the invention and the embodiment. It should be noted that the specific embodiments described herein are merely illustrative of the invention and do not limit the invention.
Referring to fig. 1 to 8, the integrated infrared suppression system for helicopter rear fuselage slotting comprises a rear fuselage 1, a guide plate 2, a special pipe 3, a baffle plate 6, a shutter guide plate 7, an air inlet plate 10 and a slit channel plate 12. The special pipe 3 is embedded in the rear machine body 1, a lower washing air flow inlet 5 is arranged right above the special pipe, namely on the upper side wall surface of the rear machine body 1, and an outlet of the special pipe 3 is positioned at a long and narrow outlet of the lower abdomen of the rear machine body 1.
The exhaust gas at the outlet of the primary injection spray pipe enters the special pipe 3, is mixed in a longer mixing pipe flow passage and then is discharged through the long and narrow special pipe outlet 9, and then the heating of the exhaust tail flame to the skin of the rear fuselage is effectively reduced by the rotor wing downwash airflow, so that the exhaust temperature is greatly reduced, and the distribution of the core area of the exhaust tail flame is improved; rotor downwash airflow enters the rear fuselage 1 from the downwash airflow inlet 5, the wall temperature of the high-temperature special pipe can be reduced, and the heating of the high-temperature special pipe to the wall surface of the rear fuselage is weakened, so that the skin temperature of the fuselage is reduced, and the high-temperature components of an engine exhaust system are completely shielded by the integrated structural design. Because the wall surface temperature of the special pipe is high, strong radiation heat exchange exists between the special pipe 3 and the wall surface of the rear machine body 1, and a shutter radiation shielding structure consisting of a shielding plate 6 and shutter flow deflectors 7 is arranged between the special pipe 3 and the upper side wall surface of the rear machine body 1, so that direct radiation heating of the high-temperature special pipe to the wall surface of the rear machine body can be blocked, and the temperature of the upper side wall surface of the rear machine body can be greatly reduced. The lower washing air flow entering the rear machine body 1 flows out of the slit opening 4 under the guiding organization of the guide plate 2, the slit channel plate 12 and the wind pocket plate 10, so that the heat exchange between the lower side wall surface of the rear machine body and surrounding fluid is enhanced, and the wall surface temperature and the infrared radiation intensity of the rear machine body are reduced.
Fig. 3 is a schematic view of a combined structure of a shielding plate and a louver guide vane, in an embodiment of the present invention, a louver guide opening 11 is formed in the shielding plate 6, one side of the louver guide vane 7 is connected to a lower side of the louver guide opening 11, and obliquely grows upward to form an acute angle with an upper side of the shielding plate 6, and a downward washing air flow outside the shielding plate 6 is introduced between the special pipe 3 and the shielding plate 6 to cool the high-temperature special pipe 3 and the shielding plate 6. The louver radiation shielding structure can completely shield the high-temperature area of the special pipe 3 when viewed from the side wall surface side of the rear machine body 1.
Fig. 4 is a schematic structural diagram of a special pipe, in the embodiment of the present invention, a special pipe 3 is embedded in a rear machine body 1, an inlet and an outlet of the special pipe are deflected by 90 °, and the outlet of the special pipe 3 is located in the middle of a side wall surface of the rear machine body 1; due to the limitation of the space in the rear machine body, the special-shaped pipe inclines to the inner side of the rear machine body by a certain angle, and the whole special-shaped pipe is of an asymmetric structure; the direction of the exhaust outlet of the special pipe forms a certain angle with the vertical plane, and the special pipe exhausts air obliquely downwards. The outlet area of the profile tube 3 is not smaller than the inlet area thereof. The cross section area of the outlet section of the special pipe 3 along the flowing direction is gradually reduced, and the sum of the area of any cross section of the outlet section of the special pipe 3 along the flowing direction and the area of the outlet 9 of the special pipe before the cross section is not less than the inlet area of the special pipe 3.
Fig. 5 is a schematic view of a deflector, in the embodiment of the present invention, the deflector 2 is located inside the mechanical tubes 3, and divides the mechanical tubes 3 located in the rear fuselage 1 into two parts with the rest space; the upper side of the guide plate 2 is superposed with the inner side edge of a rotor wing lower washing air inlet 5 at the upper part of the rear fuselage 1; the lower middle part of the baffle 2 is connected to a slit channel plate 12.
FIG. 6 is a schematic view of a combined structure of a slit passage plate and a wind inlet plate, in an embodiment of the present invention, three rows of parallel slit openings 4 are formed on a lower side wall surface of a rear body 1, and the width of the slit openings is 10mm, which is 3 in total; the slit channel plate 12 and the lower side wall surface of the rear machine body 1 form a narrow channel, three air inlet plates 10 are arranged in the channel, the extension lengths of the air inlet plates to the narrow channel are different, wherein the extension length of the bottom air inlet plate is the largest, and the lower end of the slit channel formed by the slit channel plate 12 and the lower side wall surface of the rear machine body 1 is sealed.
Fig. 7 is a schematic diagram of a certain cross-sectional position, fig. 8 is a schematic diagram of the structure and flow at the cross-sectional position shown in fig. 7, the lower washing airflow enters the rear body 1 through the lower washing airflow inlet 5, the lower washing airflow flows downward around the special pipe under the guidance of the guide plate 2, part of the airflow flows out of the rear body through the lower washing airflow outlet 8, and part of the airflow flows out through the slit opening 4 under the flow guide effect of the slit channel plate 12 and the air inlet plate 10, so that the cooling of the lower side wall surface of the rear body is realized.
The above examples are only for illustrating the technical solutions of the present invention, and are not intended to limit the present invention. It should be noted that modifications can be made by those skilled in the art without departing from the principle of the present invention, and these modifications should be construed as the scope of the present invention.
Claims (5)
1. An integrated infrared suppression system for a helicopter rear body slot comprises a special pipe positioned in a rear body, wherein an outlet of the special pipe is positioned on an inwards concave platform in the middle of the rear body; the annular opening on the periphery of the outlet of the special pipe on the concave platform in the middle of the rear machine body is a lower washing airflow outlet;
the outer side of the special pipe is provided with a baffle plate, the baffle plate divides the downward washing air flow entering the rear machine body, the baffle plate is provided with a plurality of shutter flow guide openings, and the lower side edges of the shutter flow guide openings are connected with shutter flow guide sheets which are obliquely upward and form an acute angle with the upper side of the baffle plate; the shutter radiation shielding structure formed by the shielding plate and the shutter flow deflectors can completely shield the high-temperature area of the special pipe;
the narrow channel plate is positioned on the inner side of the lower side wall surface of the concave platform in the middle of the rear machine body and forms a narrow channel with the lower side wall surface of the concave platform in the middle of the rear machine body, a plurality of slit openings are formed in the lower side wall surface of the narrow channel, a plurality of air pocket plates are arranged in the narrow channel, one ends of the air pocket plates are fixed on the lower side of the slit openings, the other ends of the air pocket plates extend upwards in an inclined mode into the narrow channel, the extending lengths of the air pocket plates are different, and the air pocket plate at the lowest end seals the lower end of the narrow channel;
the inner side of the special pipe is provided with a guide plate, the guide plate divides the special pipe positioned in the rear machine body into two parts with the rest space, the upper side of the guide plate is superposed with the inner side edge of a rotor wing downwash airflow inlet on the upper part of the rear machine body, and the middle part of the lower side of the guide plate is connected with the slit channel plate.
2. The helicopter rear fuselage slotted integrated infrared suppression system of claim 1, wherein the slot opening width is 10-20 mm.
3. The helicopter rear fuselage slotted integrated infrared suppression system of claim 1, characterized in that the exit area of said profile tube is not less than its entrance area.
4. The slotted integrated infrared suppression system for the aft fuselage of a helicopter of claim 1, wherein the cross-sectional area of the exit section of said profiled tube in the flow direction decreases gradually, and the sum of the area of any cross-section of the exit section of the profiled tube in the flow direction and the area of the exit of the profiled tube before that cross-section is not less than the area of the entrance of the profiled tube.
5. An integrated infrared suppression method for helicopter rear fuselage slotting based on any one of the systems of claims 1-4, characterized by comprising the steps of:
the rotor wing downwash airflow enters the rear fuselage from a downwash airflow inlet, and the downwash airflow is divided into three strands by the special pipe and the baffle plate; a first strand of lower washing air flow enters a gap between the shielding plate and the upper side wall surface of the rear machine body, wherein part of the lower washing air flow flows to a lower washing air flow outlet under the flow guide effect of the shielding plate to cool the shielding plate and the upper side wall surface of the rear machine body, and part of the lower washing air flow enters the gap between the shielding plate and the special pipe through the shutter flow guide opening; the second downward washing airflow flows to the downward washing airflow outlet from the gap between the shielding plate and the special pipe to cool the outer wall surface of the special pipe; the third downward washing air flow enters the gap between the guide plate and the special pipe, part of the air flow flows to the downward washing air outlet under the guide action of the guide plate to cool the inner side wall surface of the special pipe, and part of the air flow flows out through the slit opening under the guide action of the slit channel plate and the air pocket plate to cool the lower side wall of the rear machine body.
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| CN201910699609.5A CN110466742B (en) | 2019-07-31 | 2019-07-31 | Integrated infrared suppression system and method for helicopter rear fuselage slotting |
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| CN201910699609.5A CN110466742B (en) | 2019-07-31 | 2019-07-31 | Integrated infrared suppression system and method for helicopter rear fuselage slotting |
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| CN110466742B true CN110466742B (en) | 2022-04-05 |
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Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2007106188A2 (en) * | 2006-02-27 | 2007-09-20 | Sikorsky Aircraft Corporation | Infrared suppression system with spiral septum |
| US10273018B2 (en) * | 2012-10-10 | 2019-04-30 | Sikorsky Aircraft Corporation | Upturned exhaust system for rotary wing aircraft |
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2019
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