CN209776813U - anti-icing and deicing device for wings and empennage of turboprop - Google Patents

Abstract

The utility model relates to an anti-icing defroster of turboprop aircraft wing, fin, the device includes system closed loop, TKS liquid storage pot heating circuit, anti-icing deicing heat transfer loop heat pipe, distribution loop heat pipe and TKS deicing mechanism, system closed loop, TKS liquid storage pot heating circuit and heat transfer loop share one set of heat transfer evaporimeter (1), under the anti-icing state, TKS liquid storage pot heating circuit, anti-icing deicing heat transfer loop heat pipe and distribution loop heat pipe effect; under the deicing state, the TKS deicing mechanism works. Compared with the prior art, the utility model greatly improves the deicing efficiency of the TKS system, reduces the icing phenomenon of wings and empennage, ensures the flight stability of the airplane, and has safe and reliable system; and the waste heat of the exhaust pipe is used as a heat source, so that the comprehensive utilization rate of the energy of the single-engine turboprop aircraft is improved.

Description

Anti-icing and deicing device for wings and empennage of turboprop

Technical Field

The utility model relates to an aircraft anti-icing deicing technique especially relates to an anti-icing defroster of turboprop aircraft wing, fin.

background

With the continuous progress of propeller technology, the propulsion efficiency of the turboprop aircraft is greatly improved, the noise level is greatly reduced, and the riding comfort is equivalent to that of a turbofan aircraft. Meanwhile, the turboprop aircraft has good runway adaptability, can take off and land on runways such as sandy soil, gravel, grassland and the like, and the slip flow of the propellers can greatly improve the take-off/landing performance of the aircraft and allow shorter take-off/landing running distance, so the turboprop aircraft is always a common model of military aircraft. In addition, the turboprop aircraft is good in fuel economy, convenient and fast to maintain and guarantee, and is also a common model for primary and intermediate-level coaches and reconnaissance/attack unmanned aerial vehicles. At present, the turboprop has a wide application prospect.

Icing has been one of the main causes of aircraft flight accidents, and especially icing on the leading edges of the wings and the tail wings of the aircraft can cause increase of wing resistance, reduction of lift force and deterioration of maneuverability and stability, thus causing out-of-control of the maneuverability of the aircraft in take-off, landing or flying states, and finally causing serious flight accidents. For turboprop aircraft, the flight height is low, typically below 7000 m, and the flight speed is low, typically not more than 500 km/h. And the height below 7000 m is the height at which the aircraft is most easily frozen, and the aircraft is more easily influenced by natural factors such as wind, rain, thunder, electricity and the like during flying. The wings and the empennage are frozen and have low flying speed, and the airplane is easy to stall caused by airflow disturbance after freezing, so that the turboprop has higher requirements on the anti-icing and deicing of the wings and the empennage, and has important application value in terms of the application prospect of the turboprop.

in the problem of anti-icing and deicing of wings and empennages of turbofan aircrafts in the flying process, a hot air deicing technology is widely adopted at present, namely, hot air led out by an air compressor of an aircraft engine is used for deicing in the flying process, and the technology is mature at present. Compared with a turbofan engine, the turboprop engine has less air intake amount, and hot air compressed by a compressor is only enough for combustion in a combustion chamber, so that the turboprop cannot guide the hot air of the compressor of the engine to perform anti-icing and deicing on wings and empennages like a turbofan airplane.

to the problem of single turboprop wing, fin anti-icing deicing, present main deicing technique has:

The deicing technology for the deicing sleeve (deicing-boot) has the main defects that: (1) ice bridges are easily formed on the deicing sleeve. (2) If the deicing sleeve is unreasonably designed, ice ridges are easily formed behind the deicing sleeve, and airflow of the wing is disturbed.

and secondly, a Tecalamit-Kilfrost-Sheepbridge (TKS) anti-icing and deicing technology. The main disadvantages are: (1) the carried TKS liquid is limited, and the TKS liquid cannot be used for ice prevention and deicing at any time, and can only be used for about 2 hours generally. (2) The TKS solution is expensive and cannot meet good economy.

And thirdly, an electric heating auxiliary deicing technology. The main disadvantages are: (1) it is only possible to de-ice the leading edge of the wing, not enough to de-ice the entire wing surface. (2) When the calorific value is insufficient, the leading edge of the wing can be secondarily frozen to form ice accretion, and the ice accretion can cause dangers such as resistance surge and lift reduction.

In conclusion, the problem of deicing the wings of the single-engine turboprop is not thoroughly solved, and the development of a novel safe, reliable, efficient and energy-saving anti-icing and deicing technology for the wings and the empennage of the single-engine turboprop has important significance.

loop Heat Pipes (LHP) are efficient vapor-liquid two-phase Heat transfer devices, and comprise evaporators, vapor lines, condensers, liquid lines, working media and compensation chambers. The basic principle is that a capillary core in an evaporator generates capillary force to drive a loop to work, and heat is transferred by utilizing evaporation and condensation of working media. The basic working mode is that the evaporator absorbs heat of a heat source, a liquid working medium in the capillary core of the evaporator is evaporated into steam, the steam working medium moves to the condenser along a steam line to release heat and is condensed into liquid, and the liquid returns to the compensation chamber through a liquid line, so that primary heat exchange is completed.

Compared with the common Heat Pipe (HP), the loop Heat pipe can transfer more Heat in a longer distance and smaller temperature difference, the flow direction of the working medium is not easy to change, and the design is more flexible. In the aerospace field, there have been successful cases of deploying loop heat pipes on satellites and demonstrating long term effective operation against microgravity conditions. The loop heat pipe model, which has also been applied to the columbia space shuttle, also proves the effectiveness of the loop heat pipe for thermal management.

however, the application of loop heat pipes to single-engine turboprop aircraft still has some drawbacks: (1) when the aircraft is performing maneuvers, the loop heat pipe may experience adverse accelerations and changes in tilt angle that may cause the cooling liquid of the loop heat pipe to diminish or fail to return to the evaporator, and in severe cases may cause drying out of the evaporator's internal wick and the loop heat pipe may not properly transfer heat. (2) The ice and ice protection of the wings and empennage of an aircraft requires a large amount of heat to be consumed and a single loop heat pipe is not sufficient to provide such a high level of power. If the power requirement is simply met by increasing the number of loop heat pipes, the mass of the structure is increased, and the space occupied by the structure is increased. Therefore, the problems that how to make the loop heat pipe better adapt to the flight environment and how to ensure that the structure has light weight and small occupied space under the condition of meeting the requirements of preventing and removing ice on the wings and the empennage of the airplane are needed to be solved.

TKS is a technology for preventing and removing ice by using a chemical method, in which a main component of a deicing fluid (TKS fluid) is ethylene glycol. Because the freezing point of the TKS liquid is lower than-60 ℃, the TKS liquid is suitable for the flight environment of all single-engine turboprop aircrafts.

The TKS liquid is dispersed from the pores of the laser drilling titanium plate arranged on the front edge of the wing and the empennage through a pump, and is mixed with the supercooled water in the cloud to reduce the freezing point of the supercooled water, so that the mixture flows out of the surface of the airplane without freezing, and the anti-icing effect is achieved. Furthermore, TKS liquids can also chemically break the bond between ice and fuselage when the aircraft is frozen. The TKS liquid can reduce the melting point of ice, so that the ice is easy to melt, and the melted ice is blown away by airflow, thereby achieving the deicing effect. When the TKS liquid seeps from the leading edge, it flows over the leading edge surface to the wing trailing surface, thereby forming an anti-icing protective layer over the entire wing surface. Therefore, the TKS liquid can realize large-range ice prevention and deicing of the surface of the wing.

TKS technology also has some drawbacks: (1) the limited amount of TKS fluid carried requires consideration of whether the flight plan allows for flight during anti-icing and de-icing times. Most TKS equipped aircraft are protected for 1.5-2.5 hours under normal conditions. (2) The TKS device on time is difficult to grasp, and if it is opened too early, it causes waste of TKS liquid. If the aircraft wing is opened again under the condition that the wing is frozen, the TKS liquid is not fast to permeate into the ice and cannot be rapidly deiced like a deicing sleeve, so that the deicing time can be prolonged, and the possibility of accidents of the aircraft due to freezing is increased. Therefore, how to improve the efficiency and remove more ice from less TKS liquid and how to accurately open the TKS is a problem to be solved.

SUMMERY OF THE UTILITY MODEL

The object of the present invention is to provide an anti-icing and de-icing device for the wings and the empennage of a turboprop aircraft, which overcomes the drawbacks of the prior art.

The purpose of the utility model can be realized through the following technical scheme:

An apparatus for deicing and anti-icing a wing or tail of a turboprop, comprising:

TKS deicing mechanism: the TKS liquid storage device comprises a TKS liquid storage tank, a penetration panel connected with the TKS liquid storage tank, and a pressure pump for driving TKS liquid to penetrate;

A system closes a loop: the heat transfer evaporator and the first valve are sequentially connected end to end along the flowing direction of the working medium, so that the steam of the evaporator can be ensured to circulate in a loop, and the dangerous condition is avoided;

TKS liquid storage pot heating loop: the device comprises a heat transfer evaporator, a steam line, a TKS condenser fixed on a TKS liquid storage tank, a liquid line and a third valve which are sequentially connected end to end along the working medium flowing direction;

Anti-icing deicing heat transfer loop heat pipe: the deicing heat transfer loop comprises a heat transfer evaporator, a steam line, an deicing condenser, a liquid line and a second valve which are sequentially connected end to end along the flowing direction of a working medium;

The system closing loop, the TKS liquid storage tank heating loop and the heat transfer loop share one set of heat transfer evaporator.

further, anti-icing condenser and deicing condenser pass through the distribution loop heat pipe with heat transfer to the wing and the fin of treating anti-icing deicing, the distribution loop heat pipe includes along working medium flow direction in proper order end to end distribution condenser, liquid line, distribution evaporimeter and vapour line, the distribution condenser arranges on the wing and the fin of treating anti-icing deicing, the distribution evaporimeter carries out the heat exchange with deicing condenser and anti-icing condenser.

furthermore, the heat transfer evaporator is provided with double compensation chambers, including two compensation chambers arranged at two ends of the heat transfer evaporator, when the loop is in an unfavorable acceleration state or changes the inclination angle of the loop, the capillary core of the evaporator is dry, at the moment, the double compensation chambers can effectively supply liquid working media to keep the whole core wet, and the heat pipe of the whole loop is in a normal working state.

Furthermore, the distribution evaporator and the deicing condenser are connected through a pipe-in-pipe structure, the deicing condenser is spirally wound in a hollow pipe, the distribution evaporator is directly inserted into the hollow pipe to carry out heat exchange, and the pipe-in-pipe structure can realize the disassembly and the respective maintenance between the distribution evaporator and the deicing condenser;

the distribution evaporator and the anti-icing condenser are connected through a pipe-in-pipe structure, the anti-icing condenser is spirally wound in a hollow pipe, the distribution evaporator is directly inserted into the hollow pipe to perform heat exchange, and the pipe-in-pipe structure can realize the disassembly and respective maintenance between the distribution evaporator and the anti-icing condenser.

Furthermore, the distributed condenser is arranged along the chord direction of the wing and the empennage in an S-shaped laying mode, the distributed condenser is in interference fit with the condensation saddle, and the condensation saddle is fixed on the inner surfaces of the outer skins of the wing and the empennage.

Furthermore, the distribution loop heat pipe is divided into an anti-icing state distribution loop heat pipe and a deicing state distribution loop heat pipe according to the working state.

Furthermore, the anti-icing state distribution loop heat pipe is a single distribution loop heat pipe which works independently, the working power of the anti-icing state distribution loop heat pipe is small, the anti-icing state distribution loop heat pipe is used for anti-icing, the influence of overlarge heating power on the service lives of the wing and the empennage can be prevented, and the distribution condenser is laid in the wing and the empennage.

Furthermore, the deicing state distribution loop heat pipe is a plurality of distribution loop heat pipes which are connected in parallel and work cooperatively, the number of the loop heat pipes is n (n is more than 1), the number of the loop heat pipes can be specifically determined according to the power required by the turboprop aircraft to deice, so that the working power is high, the distribution loop heat pipes are used for deicing, the problem that the deicing speed is too slow due to insufficient heating power can be solved, the distribution condensers are laid in the wings and the horizontal stabilizing surface, and the distribution condensers of the deicing state distribution loop heat pipes in the vertical stabilizing surface are enough in power to deice because the deicing state distribution loop heat pipes in the vertical stabilizing surface receive the heat of the left and right side transportation loop heat pipes, so that the distribution condensers of the deicing.

further, the infiltration panel is located the leading edge of wing, fin, the infiltration panel is planking, porous membrane and inner panel from outside to inside in proper order, install the detector that freezes that is used for detecting the condition of freezing on the planking, the planking is connected with the TKS liquid storage pot.

Furthermore, the outer plate is strictly manufactured according to the design requirements of wings and tail wing leading edges, dense micropores are distributed on the outer plate, a space for storing TKS liquid is reserved between the outer plate and the inner plate, and a porous membrane between the outer plate and the inner plate ensures that the TKS liquid uniformly flows to the outer plate and is uniformly distributed.

Further, an icing detector for detecting icing is further mounted on the outer plate, a TKS condensation saddle is connected to the inner plate, the inner plate is made of titanium, a space is reserved between the inner plate and the outer plate to form a space for storing TKS liquid, and the porous membrane between the outer plate and the inner plate ensures that the TKS liquid uniformly flows to the outer plate and is uniformly distributed.

Furthermore, a TKS temperature sensor for measuring the temperature of the TKS liquid is arranged in the TKS liquid storage tank.

Further, the TKS liquid storage pot is located the fuselage middle part of single-engine turboprop aircraft and is located the position of leaning back, according to different models, provides enough TKS liquid that use in order to satisfy flight plan demand, and the external force pump of TKS sealed lid, and installation TKS liquid storage pot temperature sensor.

Furthermore, three capillary cores are placed in the heat transfer evaporator in series, and the compact design can reduce the mass of the whole structure and reduce the space occupied by the structure under the condition of meeting the working requirement.

Furthermore, the heat transfer evaporator is a cylindrical tube-shaped evaporator, the cylindrical tube-shaped evaporator is in interference fit with an evaporation saddle, and the evaporation saddle is fixed on an exhaust pipeline of the turboprop engine through a bolt, so that the heat transfer evaporator can fully absorb the waste heat of tail gas.

Furthermore, the control valves comprise a fourth valve and a fifth valve which are distributed on each deicing heat transfer loop.

Furthermore, a second valve is further arranged on the bus of the heat transfer loop and the TKS liquid storage tank heating loop. When the first valve is opened and the second valve is closed, the system closes the loop to work, and the whole loop heat pipe system is in a closed state. When the first valve is closed and the second valve is opened, the anti-icing state distribution loop heat pipe in the loop heat pipe system starts to work. Then the third valve is opened, the heating loop of the TKS liquid storage tank works, and the TKS liquid starts to be preheated. And then the valves of the fourth valve and the fifth valve are opened, and the deicing state distribution loop heat pipe in the loop heat pipe system starts to work.

Furthermore, the aircraft is also provided with a program control system, the program control system is positioned in the avionics equipment cabin and comprises a program controller and circuits connected with the sensors, and the program controller controls the whole device to be opened and closed according to the atmospheric temperature information fed back by the atmospheric temperature sensor. And automatically controlling the opening and closing of the TKS deicing mechanism and the opening and closing of the deicing state distribution loop heat pipe according to the icing information fed back by the icing detector. And controlling the temperature of the TKS liquid according to the temperature information of the TKS liquid fed back by the TKS liquid storage tank temperature sensor.

Furthermore, the atmospheric temperature sensor is positioned in a non-heating area to ensure that the atmospheric temperature can be accurately detected.

Furthermore, the icing detector is positioned on the outer surfaces of the outer skins of the wings and the empennage so as to ensure accurate detection of the ice layer on the wings. For safety reasons, the icing state is concluded in the control program whether the icing detector on the wing detects icing, or whether the icing detector on the tail wing detects icing, or whether the icing detector on the wing and the tail wing simultaneously detects icing.

Further, the TKS liquid storage tank temperature sensor is located at the sealing cover of the TKS liquid storage tank and contacts the TKS liquid.

An anti-icing and de-icing device for the wings and empennage of a turboprop, comprising, in use, the steps of:

(A) Starting all control valves and closing the pressure pump;

(B) Detecting the atmospheric temperature:

If the atmospheric temperature is higher than 5 ℃, switching on a system in the loop heat pipe system to close the loop, and keeping the pressure pump out of work, wherein the airplane is in a closed state of the anti-icing and deicing system;

if the atmospheric temperature is lower than 5 ℃, the anti-icing state heat transfer loop is connected, the TKS liquid storage tank heating loop is connected, the pressure pump does not work, the airplane is in an anti-icing state, the temperature of the TKS liquid is detected, if the temperature is lower than 80 ℃, the TKS liquid storage tank heating loop is opened, and if the temperature is higher than 90 ℃, the TKS liquid storage tank heating loop is disconnected;

(C) detecting an icing condition:

If icing is detected, the anti-icing state heat transfer loop is connected, the deicing state heat transfer loop is connected, the TKS liquid storage tank heating loop is connected, the pressure pump works, the airplane is in the deicing state, the TKS liquid problem is detected, if the temperature is lower than 80 ℃, the TKS liquid storage tank heating loop is opened, and if the temperature is higher than 90 ℃, the TKS liquid storage tank heating loop is disconnected;

(D) And (4) landing the airplane, closing all the control valves and the pressure pump, and finishing the anti-icing and deicing.

Compared with the prior art, the utility model discloses following beneficial effect has:

1. the waste heat of the exhaust pipe of the engine is fully utilized, energy is saved, the environment is protected, meanwhile, the efficiency of the engine is indirectly improved, and the problem that the power of the turboprop aircraft is insufficient due to air entraining is avoided.

2. The design of the Double Compensation Chambers (DCC) solves the problem that the loop heat pipe system is possibly out of work due to unfavorable acceleration and inclination angles, and improves the reliability of the system.

3. The two types of heat pipe designs, Transport Loop Heat Pipe (TLHP) and Distributed Loop Heat Pipe (DLHP), can transfer heat further than conventional single Loop Heat Pipe (LHP) designs. The two are connected by connecting the detachable port, so that not only can heat exchange be realized, but also respective maintenance can be realized.

TKS liquid preheats, can improve TKS liquid to the penetration rate of ice, lets ice faster melting, is blown away by the air current more easily, improves deicing efficiency. Meanwhile, the consumption of TKS liquid of ice in unit area is reduced, the service time of the TKS system is prolonged, and the TKS system is more economical.

5. add temperature sensor and detect the temperature of TKS liquid in the TKS liquid storage tank, avoid the high temperature and take place danger.

6. The anti-icing deicing mode is switched according to signals transmitted back by the atmospheric temperature sensor and the icing detector, so that the TKS system is accurately opened in required time, the service time of the TKS system is prolonged, and the TKS system is more economical.

Drawings

fig. 1 is a schematic view of the installation position of the main components of the present invention on an airplane;

fig. 2 is a schematic structural diagram of the present invention (taking the right side of the airplane as an example, the left side and the right side of the airplane are completely the same);

fig. 3 is a schematic view of the installation of the distributed condenser on the wing of the present invention;

FIG. 4 is a schematic view of the installation of the distributed condenser of the present invention on a horizontal stabilizer;

FIG. 5 is a schematic view of the installation of the distributed condenser of the present invention on a vertical stabilizer;

FIG. 6 is a cross-sectional view of a penetration panel of the present invention positioned on a wing or tail;

Fig. 7 is a schematic diagram of the TKS de-icing mechanism of the present invention;

Fig. 8 is a flow chart of the present invention.

The reference numbers in the figures indicate:

1-heat transfer evaporator, 2-detachable interface, 3-distribution condenser, 4-TKS liquid storage tank, 5-pressure pump, 6-permeation panel, 7-atmospheric temperature sensor, 8-icing detector, 9-TKS liquid storage tank temperature sensor, 10-outer plate, 11-porous membrane, 12-inner plate, 13-distribution evaporator, 14-first valve, 15-second valve, 16-third valve, 17-fourth valve, 18-fifth valve, 19-double compensation chamber, 20-anti-icing condenser, 21-deicing condenser, 22-wing, 23-horizontal stabilizing surface and 24-vertical stabilizing surface.

Detailed Description

the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

Examples

The installation position of the main components of the present embodiment on the airplane is shown in fig. 1.

aiming at the defects of the single turboprop airplane anti-icing and deicing technology and the defects of the application of the loop heat pipe and the TKS to the airplane anti-icing and deicing, the efficient, economic and reliable anti-icing and deicing device and method of the loop heat pipe assisted TKS system using the waste heat of the engine are provided on the basis of the improvement of the loop heat pipe. The single-engine turboprop aircraft mainly performs anti-icing and deicing on wings and empennages of the single-engine turboprop aircraft.

an apparatus for deicing and anti-icing a wing or tail of a turboprop, comprising:

A system closes a loop: the heat transfer evaporator comprises a heat transfer evaporator 1 and a first valve 14 which are sequentially connected end to end along the flowing direction of a working medium;

TKS liquid storage pot heating loop: the device comprises a heat transfer evaporator 1, a steam line, a TKS condenser fixed on a TKS liquid storage tank 4, a liquid line and a third valve 16 which are sequentially connected end to end along the working medium flowing direction;

a heat transfer loop: the deicing heat transfer loop comprises a plurality of anti-icing heat transfer loops and a plurality of deicing heat transfer loops which are connected in parallel, wherein the anti-icing heat transfer loops comprise a heat transfer evaporator 1, a steam line, an anti-icing condenser 20, a liquid line and a second valve 15 which are sequentially connected end to end along the flowing direction of a working medium, and the deicing heat transfer loops comprise a heat transfer evaporator 1, a deicing condenser 21 and a control valve which are sequentially connected end to end along the flowing direction of the working medium;

The system closing loop, the TKS liquid storage tank heating loop and the heat transfer loop share one set of heat transfer evaporator 1;

Distributed loop heat pipes: the device comprises a distribution condenser 3, a liquid line, a distribution evaporator 13 and a liquid line which are sequentially connected end to end along the flowing direction of a working medium, wherein the distribution condenser 3 is arranged on a wing 22 and a tail wing to be anti-iced and de-iced, and the distribution evaporator 13 exchanges heat with a de-icing condenser 21 and an anti-icing condenser 20;

TKS deicing mechanism: the TKS liquid storage tank comprises a TKS liquid storage tank 4, a penetration panel 6 connected with the TKS liquid storage tank 4, and a pressure pump 5 for driving TKS liquid to penetrate.

the heat transfer evaporator 1 and the distribution evaporator 13 are provided with double compensation chambers 19, including two compensation chambers arranged at two ends of the heat transfer evaporator 1 or the distribution evaporator 13, when the loop heat pipe is in an adverse acceleration state or changes the inclination angle thereof, the capillary core of the heat transfer evaporator or the distribution evaporator 13 is dried up, at this time, the double compensation chambers 19 can effectively supply liquid working medium to keep the whole core wet, and the whole loop heat pipe is in a normal working state.

the distribution evaporator 13 is connected with the deicing condenser 21 through the detachable interface 2 and is of a pipe-in-pipe structure, the deicing condenser 21 is spirally wound in a hollow pipe, the distribution evaporator 13 is directly inserted into the hollow pipe to carry out heat exchange, and the pipe-in-pipe structure can realize detachment and respective maintenance between the distribution evaporator 13 and the deicing condenser 21; the distribution evaporator 13 and the anti-icing condenser 20 are connected through a pipe-in-pipe structure, the anti-icing condenser 20 is spirally wound in a hollow pipe, the distribution evaporator 13 is directly inserted into the hollow pipe to perform heat exchange, and the pipe-in-pipe structure can realize the disassembly and the respective maintenance between the distribution evaporator 13 and the anti-icing condenser 20.

The distributed condenser 3 is arranged along the chord direction of the wing 22 and the empennage in an S-shaped laying mode, the distributed condenser 3 is in interference fit with a condensation saddle, and the condensation saddle is fixed on the inner surfaces of the wing 22 and the empennage outer skin.

The distribution loop heat pipe is divided into an anti-icing state distribution loop heat pipe and a deicing state distribution loop heat pipe according to the working state:

the anti-icing state distribution loop heat pipe is a single distribution loop heat pipe which works independently, the working power of the anti-icing state distribution loop heat pipe is small, the anti-icing state distribution loop heat pipe is used for anti-icing, the influence of overlarge heating power on the service lives of the wing 22 and the empennage can be prevented, and the distribution condenser 3 is paved in the wing 22 and the empennage.

The deicing state distribution loop heat pipe is a plurality of parallel cooperative distribution loop heat pipes, wherein the number of the loop heat pipes is n (n is more than 1), the number of the loop heat pipes can be specifically determined according to the power required by the turboprop aircraft deicing, so the working power of the distribution loop heat pipe is high, the distribution loop heat pipe is used for deicing, the problem that the deicing speed is too slow due to insufficient heating power can be solved, the distribution condenser 3 is laid in the wing 22 and the horizontal stabilizing surface 23, and the distribution condenser 3 of the deicing state distribution loop heat pipe is not laid in the vertical stabilizing surface 24 because the deicing state distribution loop heat pipe in the vertical stabilizing surface 24 receives the heat of the left and right side transportation loop heat pipes, so the power is sufficient for deicing.

The penetration panel 6 is sequentially provided with an outer plate 10, a porous membrane 11 and an inner plate 12 from outside to inside, the outer plate 10 is provided with an icing detector 8 for detecting icing conditions, and the outer plate 10 is connected with the TKS liquid storage tank 4. The outer plate 10 is made strictly according to the design requirements of the wing 22 and the tail front edge, dense micropores are distributed on the outer plate, a space for storing TKS liquid is reserved between the outer plate 10 and the inner plate 12, and the porous membrane 11 between the outer plate 10 and the inner plate 12 ensures that the TKS liquid uniformly flows to the outer plate 10 and is uniformly distributed.

an icing detector 8 for detecting icing is further mounted on the outer plate 10, a TKS condensation saddle is connected to the inner plate 12, the inner plate 12 is made of titanium, a space is reserved between the inner plate 12 and the outer plate 10 to form a space for storing TKS liquid, and the porous membrane 11 between the outer plate 10 and the inner plate 12 ensures that the TKS liquid flows to the outer plate 10 uniformly and is distributed uniformly.

And a TKS temperature sensor for measuring the temperature of the TKS liquid is also arranged in the TKS liquid storage tank 4. The TKS liquid storage tank 4 is located in the middle rear position of the airplane body of the single-engine turboprop airplane, enough TKS liquid is provided according to different airplane types to meet the requirement of a flight plan, the TKS sealing cover is externally connected with the pressure pump 5, and the TKS liquid storage tank temperature sensor 9 is installed.

three capillary cores are placed in series in the heat transfer evaporator 1, and the compact design can reduce the mass of the whole structure and reduce the occupied space of the structure under the condition of meeting the working requirement. The heat transfer evaporator 1 is a cylindrical tube-shaped evaporator, the cylindrical tube-shaped evaporator is in interference fit with an evaporation saddle, and the evaporation saddle is fixed on an exhaust pipeline of the turboprop engine through a bolt, so that the heat transfer evaporator 1 can fully absorb the waste heat of tail gas.

And a second valve 15 is also arranged on the bus of the heat transfer loop and the TKS liquid storage tank heating loop. When the first valve 14 is opened and the second valve 15 is closed, the system closes the loop to work, and the whole loop heat pipe system is in a closed state. When the first valve 14 is closed and the second valve 15 is opened, the anti-icing state distribution loop heat pipe in the loop heat pipe system starts to work. Then the third valve 16 is opened, the TKS reservoir heating circuit is operated and the TKS liquid starts to be preheated. And then a fourth valve 17 and a fifth valve 18 on the deicing heat transfer pipeline are opened, and the deicing state distribution loop heat pipe starts to work.

The aircraft is also provided with a program control system which is positioned in the avionics equipment cabin and comprises a program controller and circuits connected with the sensors, and the program controller controls the opening and closing of the whole device according to the atmospheric temperature information fed back by the atmospheric temperature sensor 7. And automatically controlling the opening and closing of the TKS deicing mechanism and the opening and closing of the deicing state distribution loop heat pipe according to the icing information fed back by the icing detector 8. And controlling the temperature of the TKS liquid according to the temperature information of the TKS liquid fed back by the TKS liquid storage tank temperature sensor 9. And an atmospheric temperature sensor 7 is positioned in the non-heating area to ensure that the atmospheric temperature can be accurately detected.

The ice detector 8 is located on the outer surface of the wing 22, the tail outer skin, to ensure accurate detection of the ice layer on the wing 22. For safety reasons, the icing state is concluded in the control program whether the icing detector 8 on the wing 22 detects icing, or the icing detector 8 on the tail detects icing, or both the wing 22 and the tail detect icing.

And the TKS liquid storage tank temperature sensor 9 is positioned on the sealing cover of the TKS liquid storage tank and contacts the TKS liquid.

the aircraft is divided into three working states: the anti-icing and deicing system is in an off state, an anti-icing state and a deicing state.

the three working states of the airplane are subjected to state control by opening and closing valves of a program control system.

As shown in fig. 2, the heat transfer evaporator 1 installed on the surface of the exhaust pipe of the turboprop engine is used to absorb the heat of the exhaust waste heat of the engine, so that the working medium in the heat transfer evaporator 1 is evaporated into vapor, the evaporated working medium moves along three loops and finally returns to the double compensation chamber 19, thereby achieving three different heat transfer purposes of the present embodiment and realizing three different working states of the present embodiment.

As shown in fig. 3-6, the distribution evaporator 13 in the distribution loop heat pipe absorbs heat from the detachable interface 2, so that the working medium in the distribution evaporator 13 is evaporated, the evaporated working medium moves along the steam line, the working medium moves to the wing and the empennage under the action of capillary force to exchange heat and is condensed into liquid through the distribution condenser 3, and the liquid returns to the double compensation chambers 19 of the distribution evaporator 13 through the liquid line for the next evaporation, thereby completing one heat transfer.

in the embodiment of the TKS deicing mechanism, as shown in fig. 7, the TKS liquid in the TKS reservoir 4 can flow to the penetration panel 6 by the pressure provided by the pressure pump 5, and is uniformly pressed out of the holes of the dense outer plate 10 by the uniform distribution of the porous film 11 between the outer plate 10 and the inner plate 12. The TKS liquid penetrates into the ice layer, so that the melting point of the ice can be reduced, the ice penetrating the surface of the panel 6 is rapidly melted, and then the ice is blown away by airflow. Due to the viscous effect of the TKS liquid, the TKS liquid will continue to de-ice towards the rear of the permeate panel 6.

off state of the anti-icing and deicing system:

When the first valve 14 is opened and the second valve 15 is closed, the pressure pump 5 does not work, and the system closes the loop to work. The TKS liquid storage tank heating loop and the heat transfer loop do not work, and the loop heat pipe system is closed. The TKS system pressure pump 5 does not work and the TKS system is turned off. At this time, the airplane enters an anti-icing and deicing system closed state.

And (3) an anti-icing state:

When the second valve 15 is opened, the third valve 16 controls the preheating of the TKS liquid, and the first valve 14, the fourth valve 17 and the fifth valve 18 are closed, the anti-icing state heat transfer loop in the TKS liquid storage tank heating loop and the heat transfer loop starts to work, and the system closing loop does not work. At which point the aircraft enters an anti-icing condition.

The anti-icing state heat transfer loop carries out long-distance heat transmission, the evaporated working medium moves to the detachable connector 2 to carry out heat exchange and is condensed into liquid, and the liquid returns to the double compensation chambers 19 of the heat transfer evaporator 1 through liquid lines for next evaporation, so that one heat transfer is completed.

The TKS liquid storage tank heating circuit performs preheating on the TKS liquid, and the temperature of the TKS liquid is maintained between 80 and 90 ℃ under the control of the third valve 16, so that the TKS liquid can be rapidly deiced when wings are frozen.

and (3) deicing state:

when No. two valves 15, No. four valves 17, No. five valves 18 are opened, No. three valve 16 control the preheating of TKS liquid, No. one valve 14 is closed, when TKS force pump 5 is opened, TKS liquid storage pot heating circuit, heat transfer circuit and TKS deicing mechanism work, the system closes the return circuit and does not work. At this point the aircraft enters a de-icing state.

the anti-icing state heat transfer loop and the deicing state heat transfer loop carry out long-distance heat transportation, the evaporated working medium moves to the detachable connector 2 to carry out heat exchange and is condensed into liquid, and the liquid returns to the double compensation chambers 19 of the heat transfer evaporator 1 through liquid lines for next evaporation, so that one heat transfer is completed.

the TKS reservoir heating circuit performs TKS liquid preheating, and the TKS liquid is maintained at 80-90 ℃ under the control of the third valve 16.

When the airplane enters a deicing state, the TKS deicing mechanism works.

Embodiment of the program control system:

the valve is controlled to open or close by the sensor signal.

the atmospheric temperature sensor 7 detects the atmospheric temperature and controls the first valve 14 and the second valve 15. The TKS liquid storage tank temperature sensor 9 detects the temperature of the TKS liquid and controls the third valve 16. The icing detector 8 detects whether icing occurs and controls the four-way valve 17, the five-way valve 18 and the pressure pump 5.

The flow of the anti-icing and deicing method is shown in FIG. 8:

The method comprises the following steps: initially, the aircraft starts, and the first valve 14, the second valve 15, the third valve 16, the fourth valve 17, and the fifth valve 18 are in a closed state.

Step two: the atmospheric temperature sensor 7 detects whether the atmospheric temperature is higher than 5 ℃.

If the temperature is higher than 5 ℃, the first valve 14 is opened, the second valve 15 is closed, and the airplane is in a closed state of the anti-icing and deicing system;

If the temperature is lower than 5 ℃, the second valve 15 is opened, and the third valve 16 controls the preheating of the TKS liquid. The pre-adding control method of the TKS liquid comprises the following steps: the third valve 16 is opened at the temperature lower than 80 ℃, the TKS liquid is heated, the third valve 16 is closed at the temperature higher than 90 ℃, and the temperature of the TKS liquid is reduced along with the ambient temperature.

Step three: the icing detector 8 detects whether the wings and the empennage are iced.

If no ice exists, the second valve 15 is opened, the third valve 16 controls the preheating of the TKS liquid, and the 1, 4 and fifth valves 14, 17 and 18 are closed. The airplane is in an anti-icing state;

If ice exists, the second valve 15, the fourth valve 17 and the fifth valve 18 are opened, the third valve 16 controls the preheating of the TKS liquid, the first valve 14 is closed, the TKS pressure pump 5 is opened, and the airplane enters a deicing state.

Step four: repeating the two and three steps.

Step five: and (4) the first valve 14, the second valve 15, the third valve 16, the fourth valve 17 and the fifth valve 18 are closed after the airplane lands, and the process is finished.

The embodiments described above are intended to facilitate the understanding and use of the invention by those skilled in the art. It will be readily apparent to those skilled in the art that various modifications to these embodiments may be made, and the generic principles described herein may be applied to other embodiments without the use of the inventive faculty. Therefore, the present invention is not limited to the above embodiments, and those skilled in the art should make improvements and modifications within the scope of the present invention according to the disclosure of the present invention.

Claims (9)

1. An anti-icing and de-icing assembly for the wings and empennage of a turboprop, comprising:

TKS deicing mechanism: comprises a TKS liquid storage tank (4), a penetration panel (6) connected with the TKS liquid storage tank (4), and a pressure pump (5) for driving TKS liquid to penetrate;

TKS liquid storage pot heating loop: the TKS condenser is arranged on the outer surface of the TKS liquid storage tank (4), and a third valve (16) are sequentially connected end to end along the working medium flowing direction;

Anti-icing deicing heat transfer loop heat pipe: the deicing heat transfer loop comprises a heat transfer evaporator (1), an deicing condenser (20) and a second valve (15) which are sequentially connected end to end along the flowing direction of a working medium, the deicing heat transfer loop comprises the heat transfer evaporator (1), the deicing condenser (21) and a control valve which are sequentially connected end to end along the flowing direction of the working medium, and the deicing condenser (20) and the deicing condenser (21) exchange heat with wings;

The TKS liquid storage tank heating loop and the anti-icing and deicing heat transfer loop heat pipe share one set of heat transfer evaporator (1).

2. The device for preventing and removing ice on the wing and the empennage of a turboprop according to claim 1, wherein the ice-preventing condenser (20) and the ice-removing condenser (21) transfer heat to the wing (22) and the empennage to be prevented and removed by a distributed loop heat pipe, the distributed loop heat pipe comprises a distributed condenser (3) and a distributed evaporator (13) which are sequentially connected end to end along the flowing direction of a working medium, the distributed condenser (3) is arranged on the wing (22) and the empennage to be prevented and removed by ice, and the distributed evaporator (13) exchanges heat with the ice-removing condenser (21) and the ice-removing condenser (20).

3. The device for deicing and deicing the wings and the tail of a turboprop according to claim 2, characterized in that said heat transfer evaporators (1) and said distribution evaporators (13) are each equipped with a double compensation chamber (19).

4. The device according to claim 2, characterized in that said distributed evaporator (13) and said deicing condenser (21) are connected by a tube-in-tube structure, said deicing condenser (21) being spirally wound around a hollow tube, said distributed evaporator (13) being directly inserted into the hollow tube for heat exchange;

the distribution evaporator (13) is connected with the anti-icing condenser (20) through a pipe-in-pipe structure, the anti-icing condenser (20) is spirally wound in a hollow pipe, and the distribution evaporator (13) is directly inserted into the hollow pipe to perform heat exchange.

5. The device of claim 1, wherein the penetration panel (6) comprises an outer plate (10), a porous membrane (11) and an inner plate (12) from outside to inside in sequence, the outer plate (10) is provided with an icing detector (8) for detecting icing conditions, and the outer plate (10) is connected with the TKS liquid storage tank (4).

6. The device according to claim 5, characterized in that said outer plate (10) has dense micropores, and a space for storing TKS liquid is left between said outer plate (10) and said inner plate (12).

7. The device for deicing and preventing ice on the wings and the tail of a turboprop according to claim 1, characterized in that a TKS temperature sensor for measuring the temperature of TKS is further arranged in the TKS liquid storage tank (4).

8. the device for deicing and preventing ice on the wings and the tail of a turboprop according to claim 1, characterized in that three capillary cores are placed in series inside said heat-transfer evaporator (1).

9. The device for preventing and removing ice from the wings and the empennage of a turboprop according to claim 1, characterized in that the heat transfer evaporators (1) are connected end to end in sequence with a valve to form a system closed loop.