CN104326079A - Adaptive active thermal protection device and aircraft - Google Patents
Adaptive active thermal protection device and aircraft Download PDFInfo
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- CN104326079A CN104326079A CN201410541748.2A CN201410541748A CN104326079A CN 104326079 A CN104326079 A CN 104326079A CN 201410541748 A CN201410541748 A CN 201410541748A CN 104326079 A CN104326079 A CN 104326079A
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- leading edge
- storage box
- exhaust passage
- air gate
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Abstract
The invention provides an adaptive active thermal protection device and an aircraft, the thermal protection device comprises at least one exhaust passage arranged in the leading edge of the machine body and a storage box for storing a cooling working medium; an air inlet hole of the exhaust passage is arranged on the incident flow side of the sharp leading edge of the machine body, an air outlet hole of the exhaust passage is arranged on the lee side of the sharp leading edge of the machine body, a flexible diaphragm is arranged on one side of the storage box, the side of the storage box is close to the air inlet hole, the flexible diaphragm can deform along with pressure increase of the air inlet hole, and squeeze the cooling working medium in the storage box, and the storage box is communicated with the air outlet hole through a liquid discharging port. When the aircraft is in flight, by use of air flow pressure difference between the air inlet hole and the air outlet hole, the cooling working medium in the storage box is actively sprayed on the tip of the leading edge, the tip temperature is reduced, the air flow field near the sharp leading edge may not be disturbed, and the resistance of the leading edge may not be increased.
Description
Technical field
The present invention relates to high hypersonic aircraft leading edge Aerodynamic Heating guard technology, particularly relate to a kind of self adaptation active thermal protective device and aircraft, be specially adapted to the leading edge thermal protection with tipping leading edge aircraft (as Air-breathing hypersonic vehicle etc.).
Background technology
Aircraft is when endoatmosphere high-speed flight, aircraft ambient air is subject to strong compression and violent rubbing effect, and most of kinetic transformation of air-flow is heat energy, and the temperature around aircraft is sharply raised, high-temperature gas heats aircraft, and Aerodynamic Heating problem also produces thus.Even to this day, thermal protection is still the major issue must considered in all kinds of high-speed aircraft pocket and Spacecraft guidance and control.Thermal protection problem is the most outstanding with aircraft leading edge Aerodynamic Heating, and the Aerodynamic Heating in this region is mainly derived from airflow collision rapid stagnation to aircraft leading edge of high-speed motion, and a large amount of molecular kinetic-energy conversion is heat energy.Generally speaking, this region is that whole flight vehicle aerodynamic heats region the most serious.
Aerodynamic Heating protection question is a complicated multidisciplinary problem, all directly related with the profile of aircraft, material and structure etc.Existing technological means is except adopting advanced heat proof material (as carbon-to-carbon, carbon-silicon composite etc.), leading edge thermal protection generally by the means change of flight device profiles such as passivation, jet flow, increase pole and surrounding flow field thereof, reaches the object reducing front edge area hot-fluid.The cardinal principle of passivation solar heat protection utilizes stationary point hot-fluid and the inversely proportional relation of local passivation radius, aircraft leading edge carried out Passivation Treatment to reduce hot-fluid.This mode is most widely used.But while reducing leading edge hot-fluid, the resistance of aircraft will inevitably increase.Spray method is perforate near stationary point, eject the liquid contrary with carrying out flow path direction to reduce the hot-fluid in region, stationary point, but this method can destroy the flow field in region, whole stationary point from hole.Pole method leans out a thin bar in aircraft leading edge, and, protected the leading edge of aircraft by the ablation of pole awing, this method can destroy the flow field near leading edge equally.On the basis of the above, also have scholar to propose the new ideas such as cavity method, pole spray method, pneumatic dish method, press over system, but these methods are still in the research and probe stage.
From current practical application, direct passivation solar heat protection is still the most simply and the method be most widely used.But passivation solar heat protection to sacrifice the aeroperformance of aircraft for cost, must need balance during application between drag reduction and thermal protection.In addition, for the course of new aircraft such as Waverider or hypersonic airbreather, body and driving engine are coupled completely, and this just needs aircraft leading edge must adopt tipping leading edge, and the flow field near leading edge should not be interfered.This problem directly facilitates the research of Novel hot protective system, and the present invention proposes mainly for this background and demand.
Summary of the invention
The invention provides a kind of self adaptation active thermal protective device and aircraft, for overcoming defect of the prior art, there is adaptation function, and airflow field near aircraft leading edge is interference-free, does not increase the resistance of aircraft leading edge.
The invention provides a kind of self adaptation active thermal protective device, comprising:
At least one is arranged on the exhaust passage and of body leading edge inside for storing the storage box of cooling working medium;
Described exhaust passage has induction opening and for cooling working medium in described hutch is sprayed to the air gate of body tipping leading edge tip;
The induction opening of described exhaust passage is arranged on the fluoran stream surface of described body tipping leading edge, and the air gate of described exhaust passage is arranged on the lee side of body tipping leading edge;
Described storage box is provided with near the side of induction opening can be increased with described induction opening pressure and produce and be out of shape and extrude the flexible partition of storage box internal cooling working medium, and described storage box is communicated with described air gate by leakage fluid dram.
Wherein:
Exhaust passage between described leakage fluid dram and described air gate is provided with flow control valve.
Further:
The leakage fluid dram of described storage box is connected with mozzle;
Described mozzle forms the exhaust passage between described storage box and described air gate;
Described flow control valve is arranged on described mozzle.
Particularly:
There is between described air gate and described mozzle a spray chamber;
Described spray chamber is communicated with described air gate and described mozzle.
On the basis of above-described embodiment:
Described body tipping leading edge has tip;
Described most advanced and sophisticated rear portion has a step surface;
Described induction opening is arranged on this step surface.
Wherein:
Described tip is provided with heat conduction cover.
Further:
Described heat conduction cover lateral surface is fillet surface.
Further:
The shape of described air gate is horn-like, and the necking end of described air gate is near exhaust passage, the tangential lateral surface towards heat conduction cover of flared end.
Again further:
It is inner that described flexible partition is arranged on described storage box, and described storage box inside is divided into upper and lower two cavitys by described flexible partition;
The inner cavity be positioned at below flexible partition of described storage box is funnel-form, and the necking end of this funnelform cavity is communicated with described induction opening.
The present invention also provides a kind of aircraft, at least comprises body, and described body has tipping leading edge, and described tipping leading edge has fluoran stream surface and lee side;
Described aircraft also comprises a temperature barrier, and described temperature barrier is above-mentioned self adaptation active thermal protective device.
Self adaptation active thermal protective device provided by the invention and aircraft, aircraft flight or launch before, storage box is filled cooling working medium, now, flexible partition automatically to shrink below storage box and blocks induction opening, and liquid cooled working medium is completely enclosed within storage box inside; When aircraft takeoff or transmitting, owing to there is difference of pressure between induction opening and air gate, high pressure air is entered by induction opening, and by flexible partition jack-up, liquid cooling working medium injects leading edge tip along exhaust passage, now, under the effect of Aerodynamic Heating, leading edge tip has had higher temperature, and liquid cooled working medium enters rear rapid evaporator strip and walks heat, the temperature of cavity and heat conduction cover is reduced, and the cooling working medium after gasification is discharged backward along air gate; When aircraft Mach number increases, the pressure reduction between induction opening and air gate increases, and the flow velocity of cooling working medium is accelerated, the more heat of Absorbable rod in the unit time; Otherwise when flight Mach number reduces then, thus make this thermal protection system have adaptation function, the airflow field near tipping leading edge is interference-free, and can not increase the resistance of leading edge.
Accompanying drawing explanation
The structural representation of the self adaptation active thermal protective device that Fig. 1 provides for the embodiment of the present invention;
The structural representation of fluoran stream surface and lee side in the self adaptation active thermal protective device that Fig. 2 provides for the embodiment of the present invention;
The structural representation of exhaust passage in the self adaptation active thermal protective device that Fig. 3 provides for the embodiment of the present invention.
Detailed description of the invention
As shown in Figure 1, the invention provides a kind of self adaptation active thermal protective device, this device comprises exhaust passage 1 and the storage box 2 that at least one is arranged on body leading edge inside, and exhaust passage 1 has induction opening 1a and for cooling working medium 21 in described hutch 2 is sprayed to the air gate 1b of body tipping leading edge tip; The induction opening 1a of exhaust passage is arranged on the fluoran stream surface 10 of body tipping leading edge, and the air gate 1b of exhaust passage is arranged on the lee side 20 of body tipping leading edge; Storage box 2 is for storing cooling working medium, storage box 2 is provided with near the side of induction opening 1a can be increased with induction opening 1a pressure and produce and be out of shape and extrude the flexible partition 2a of storage box 2 internal cooling working medium 21, and storage box 2 passes through leakage fluid dram 2b and is communicated with the air gate 1b of exhaust passage.
Under high-speed flight condition, the induction opening 1a of exhaust passage is owing to being located on fluoran stream surface 10, therefore elevated pressures is born, the air gate 1b of exhaust passage is owing to being arranged on lee side 1b, therefore pressure is lower, due to the effect of difference of pressure, the cooling working medium be stored in storage box 2 sprays through exhaust passage 1, liquid cooled working medium is sprayed in leading edge tip, heat up after carrying out interchange of heat with tip and gasify, leading edge tip is lowered the temperature, cooling working medium after gasification sprays backward, certain boundary layer bleed function can be had, increase with flight Mach number, the difference of pressure of induction opening and air gate increases, cooling working medium flow increases, stronger cooling function will be had, thus there is adaptive characteristic.
Here storage box 2 can be arranged on internal body, two ends are all communicated with exhaust passage 1, flexible partition 2a arranges demand fulfillment when there is pressure reduction between induction opening and air gate, can heave under the effect of pressure reduction, and the cooling working medium of compact storage case inside, bosher's mass-energy is discharged from leakage fluid dram, and finally spray through air gate, the position of air gate is located near most advanced and sophisticated place, such cooling working medium through air gate out after be conducive to the most advanced and sophisticated position being directly sprayed on leading edge, and then tip to be cooled.Flexible partition is positioned at storage box inside, mainly in order to air-isolation and cooling working medium, prevents air from entering rear directly ejection through liquid by induction opening 1a and forms short circuit, should cover the wall of whole storage box after flexible partition 2b launches completely.
In order to carry out interchange of heat faster and better, can arrange heat conduction cover 3 at the tip of leading edge, heat conduction cover 3 can adopt the higher material of permeability of heat to make, such as high temperature alloy, the mechanical property that can it be kept at a higher temperature good, and has good thermal conduction characteristic; Like this, cooling working medium 21 be sprayed at heat conduction cover 3 on the surface time, can rapidly and heat conduction cover 3 carry out interchange of heat and gasify, heat conduction cover 3 temperature is reduced, and then reaches and reduce the object of tip temperature.What heat conduction cover 3 was aircraft directly meets stream part, and the design of its outer rim can adopt tipping leading edge profile or suitably passivation according to the demand of practical flight device.Heat conduction cover 3 lateral surface is for being preferably fillet surface.
The part that exhaust passage 1 in the present embodiment is communicated with the leakage fluid dram 2b of storage box 2 can adopt mozzle 4, namely mozzle 4 is utilized to replace this part exhaust passage 1 be connected between leakage fluid dram 2b and air gate 1b, the parts that internal body is installed are more, need not arrange exhaust passage separately at internal body.In addition, by a mozzle 4 connected drainage mouth 2b and air gate 1b, on mozzle 4, flow control valve 5 can be installed, install flow control valve relative on the exhaust passage 1 (exhaust passage 1 is formed by establishing structure in body) between storage box 2 and air gate 1b, it is more convenient to install.The effect of flow control valve 5 is the delivery rate of controlled cooling model working medium 21, and when working without the need to thermal protection system, this flow control valve 5 is in closed condition.
Arrange induction opening 1a at the fluoran stream surface of body, set out pore 1b at the lee side of body, arrange a storage box 2 at internal body, it is inner that flexible partition 2a is arranged on described storage box, and storage box inside is divided into upper and lower two cavitys by flexible partition 2a; Storage box inside is positioned at cavity above flexible partition for storing cooling working medium 21, and the inner cavity be positioned at below flexible partition of storage box is funnel-form, and the necking end of this funnelform cavity is communicated with induction opening 1a.Like this, when high pressure draft enters in storage box 2 through induction opening 1a, a buffer action is had to high pressure draft, high pressure gas fails to be convened for lack of a quorum along funnel-form inwall and slowly enters in storage box, and evenly extrude flexible partition, avoid air-flow to flexible partition 2b local crushing failure at high speed and unbalance stress, extend the service life of flexible partition.
There is in the exhaust passage 1 at heat conduction cover 3 rear a spray chamber 6; Spray chamber 6 is communicated with air gate 1b and flow control valve 5.This spray chamber 6 can be formed at leading edge tip inside, when cooling working medium 21 injects this spray chamber 6 after flow-controlling gate 5 out, reverse direction flow is through air gate 1b, be sprayed onto streamlined reefer housing 3 surface again, because the direction of air gate 1b is different from the direction of exhaust passage 1 or mozzle 4, cooling working medium 21 needs to change direction behind exhaust passage 1 or mozzle 4, and the orientation angle (obtuse angle) changed is larger, in change Chu Ji exhaust passage, direction 1 and air gate 1b infall or mozzle 4, spray chamber 6 is set with air gate 1b infall, for cushioning cooling working medium stream, in addition, the impact that the cooling working medium flow decreasing air gate 1b receives because changing direction.
The shape of air gate 1b can in horn-like, and necking end is near exhaust passage 1, flared end tangential towards heat conduction cover 3 lateral surface, exit skirt is conducive to cooling working medium 21 and discharges and abrupt release pressure from air gate 1b, the shape of flared end ensures that the cooling working medium of maximum can be sprayed on heat conduction cover 3 exactly, avoids waste.
Self adaptation active thermal protective device provided by the invention, aircraft flight or launch before, fill cooling working medium by storage box, close flow control valve 5; Now, flexible partition 2b automatically to shrink below storage box 2 and blocks induction opening, and it is inner that liquid cooled working medium 21 is completely enclosed within storage box 2; Aircraft takeoff or transmitting initial stage, because flight Mach number is lower, without the need to thermal protection system work, although now have certain pressure reduction between induction opening 1a and air gate 1b, but because flow control valve 5 is closed, it is inner that incompressible liquid cooled working medium 21 is still closed in storage box 2; Increase with flight Mach number, when needing thermal protection system to start working, turn-on flow rate regulates the valves 5 and be adjusted to correct position, owing to there is difference of pressure between induction opening 1a and air gate 1b, high pressure air is entered by induction opening, heaved by flexible partition 2b, liquid cooling working medium 21 injects the spray chamber 6 at leading edge heat conduction cover 3 rear after flow control valve 5 along mozzle 4.Now, under the effect of Aerodynamic Heating, leading edge heat conduction cover 3 and this spray chamber 6 have had higher temperature, and liquid cooled working medium 21 enters rear rapid evaporator strip and walks heat, and the temperature of spray chamber 6 and heat conduction cover 3 is reduced.Cooling working medium 21 after gasification is discharged backward along air gate 1b; When flight Mach number increases, the pressure reduction between induction opening 1a and air gate 1b increases, and the flow velocity of cooling working medium 21 is accelerated, the more heat of Absorbable rod in the unit time; Otherwise when flight Mach number reduces then, thus, this thermal protection system has adaptation function, the airflow field near tipping leading edge is interference-free, and can not increase the resistance of leading edge.
As the optimal way of above-described embodiment, as shown in Figure 2:
Body tipping leading edge has tip; Most advanced and sophisticated rear portion has a step surface 50; This step surface 50 forms lee side 20.
Fig. 2 gives the difference of pressure diagram being obtained fluoran stream surface and lee side by the appropriate design in leading edge shape face.As shown in Figure 2, after flowing through aircraft precursor, produce oblique shock wave 30 from leading edge locus, after flowing through oblique shock wave 30, pressure raises, the formation higher-pressure region, region 11 between oblique shock wave 30 and fluoran stream surface 10.If make a step surface 50 near wall leading edge on board the aircraft, then can produce expansion wave 40 after flowing through step surface 50, after air-flow overexpansion shock 40, pressure reduces rapidly, and expansion wave 40 and lee side 20 form meiobar 12.Thus, as shown in Figure 2, can produce higher-pressure region 11 and region, 12 two, meiobar by such Configuration Design, the difference of pressure in these two regions strengthens with the increase of flight Mach number.
The preferred version that exhaust passage is arranged is as follows, as shown in Figure 3:
Open an aperture and induction opening 1a in the windward side of aircraft and fluoran stream surface 10, this hole is upward through body 60, and its outlet is step 50 place of leading edge lee face 20.Obviously, when high-speed flight, because the air-flow that exists of aforementioned pressure difference flows through this aperture by according to the instruction of arrow in figure, and flow velocity increases with the increase of flight Mach number, and namely the present invention utilizes this principle by increasing the object that cooling working medium reaches leading edge solar heat protection in the middle of stream.
The present invention also provides a kind of aircraft, at least comprises body, and body has tipping leading edge, and tipping leading edge has fluoran stream surface and lee side; Aircraft also comprises a temperature barrier, and this temperature barrier is the self adaptation active thermal protective device of above-mentioned any embodiment.
Air gate 1a described in the embodiment of the present invention is positioned at above aircraft, does not thus disturb the flow field below aircraft precursor, is therefore extremely suitable for the design requirement of Waverider aircraft or Air-breathing hypersonic vehicle etc.
Only give principle of design and the two-dimensional representation of this temperature barrier herein, for the three-dimensional aircraft configurations of reality, the parameters such as the perforate number of induction opening 1a and air gate 1b, pitch of holes, cross section, hole and section shape, need specifically determine by calculating or testing according to actual design requirement.When induction opening 1a and air gate 1b is multiple, same storage box 2 still can be shared.
During thermal protection system work, air gate 1b sprays the flow direction of gaseous working medium with to carry out flow path direction consistent, thus can play the effect of boundary layer bleed to a certain extent, and this resistance for reduction aircraft is also favourable.
Cooling working medium storage box can be positioned at any part of aircraft in theory, but must consider in actual design that liquid refrigerant is in the internal resistance of water conservancy diversion Bottomhole pressure, should reduce the length of mozzle 4 as far as possible.In addition, with the increase of flight time, cooling working medium constantly evaporates minimizing, and the weight of aircraft also constantly alleviates.The change of aircraft barycenter will be caused thus.Also should consider in reality that this is because usually designing the position of storage box.
If the recyclable and repeated usage of aircraft, this device also again can be annotated after cooling working medium and be reworked.
Claims (10)
1. a self adaptation active thermal protective device, is characterized in that, comprising:
At least one is arranged on the exhaust passage and of body leading edge inside for storing the storage box of cooling working medium;
Described exhaust passage has induction opening and for cooling working medium in described hutch is sprayed to the air gate of body tipping leading edge tip;
The induction opening of described exhaust passage is arranged on the fluoran stream surface of described body tipping leading edge, and the air gate of described exhaust passage is arranged on the lee side of body tipping leading edge;
Described storage box is provided with near the side of induction opening can be increased with described induction opening pressure and produce and be out of shape and extrude the flexible partition of storage box internal cooling working medium, and described storage box is communicated with described air gate by leakage fluid dram.
2. self adaptation active thermal protective device according to claim 1, is characterized in that:
Exhaust passage between described leakage fluid dram and described air gate is provided with flow control valve.
3. self adaptation active thermal protective device according to claim 2, is characterized in that:
The leakage fluid dram of described storage box is connected with mozzle;
Described mozzle forms the exhaust passage between described storage box and described air gate;
Described flow control valve is arranged on described mozzle.
4. self adaptation active thermal protective device according to claim 3, is characterized in that:
There is between described air gate and described mozzle a spray chamber;
Described spray chamber is communicated with described air gate and described mozzle.
5., according to the arbitrary described self adaptation active thermal protective device of claim 1-4, it is characterized in that:
Described body tipping leading edge tip rear portion has a step surface;
Described induction opening is arranged on this step surface.
6. self adaptation active thermal protective device according to claim 1, is characterized in that:
Described body tipping leading edge tip is provided with heat conduction cover.
7. self adaptation active thermal protective device according to claim 6, is characterized in that:
Described heat conduction cover lateral surface is fillet surface.
8. the self adaptation active thermal protective device according to claim 6 or 7, is characterized in that:
The shape of described air gate is horn-like, and the necking end of described air gate is near exhaust passage, the tangential lateral surface towards heat conduction cover of flared end.
9. self adaptation active thermal protective device according to claim 1, is characterized in that:
It is inner that described flexible partition is arranged on described storage box, and described storage box inside is divided into upper and lower two cavitys by described flexible partition;
The inner cavity be positioned at below flexible partition of described storage box is funnel-form, and the necking end of this funnelform cavity is communicated with described induction opening.
10. an aircraft, at least comprises body, and described body has tipping leading edge, and described tipping leading edge has fluoran stream surface and lee side, it is characterized in that:
Described aircraft also comprises a temperature barrier, and described temperature barrier is the arbitrary described self adaptation active thermal protective device of claim 1-9.
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| CN201410541748.2A CN104326079B (en) | 2014-10-14 | 2014-10-14 | Self adaptation active thermal preventer and aircraft |
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| CN201410541748.2A CN104326079B (en) | 2014-10-14 | 2014-10-14 | Self adaptation active thermal preventer and aircraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106394938A (en) * | 2016-09-29 | 2017-02-15 | 湖北航天技术研究院总体设计所 | Thermal protection device of attitude control system for hypersonic-speed and large-attack-angle reentry vehicle |
| CN106882400A (en) * | 2017-03-14 | 2017-06-23 | 清华大学 | A kind of film cooling system and method containing injector |
| CN111301723A (en) * | 2020-03-17 | 2020-06-19 | 北京卫星环境工程研究所 | Black barrier weakening device based on gas film protection |
| CN113148222A (en) * | 2021-05-24 | 2021-07-23 | 北京航空航天大学 | Close curved surface wave-rider positive design method suitable for complex leading edge shape |
| CN113928536A (en) * | 2021-11-05 | 2022-01-14 | 北京航空航天大学 | Method for reducing intensity of infrared radiation signal of hypersonic aircraft |
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| CN113148222A (en) * | 2021-05-24 | 2021-07-23 | 北京航空航天大学 | Close curved surface wave-rider positive design method suitable for complex leading edge shape |
| CN113148222B (en) * | 2021-05-24 | 2023-01-31 | 北京航空航天大学 | Close curved surface wave-rider positive design method suitable for complex leading edge shape |
| CN113928536A (en) * | 2021-11-05 | 2022-01-14 | 北京航空航天大学 | Method for reducing intensity of infrared radiation signal of hypersonic aircraft |
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| CN104326079B (en) | 2016-07-06 |
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