CN114789793A - Tail gas recycling system for fixed-wing unmanned aerial vehicle - Google Patents
Tail gas recycling system for fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN114789793A CN114789793A CN202210227163.8A CN202210227163A CN114789793A CN 114789793 A CN114789793 A CN 114789793A CN 202210227163 A CN202210227163 A CN 202210227163A CN 114789793 A CN114789793 A CN 114789793A
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- 238000004064 recycling Methods 0.000 title claims abstract description 17
- 239000012530 fluid Substances 0.000 claims abstract description 71
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 24
- 229910002804 graphite Inorganic materials 0.000 claims description 21
- 239000010439 graphite Substances 0.000 claims description 21
- 239000007921 spray Substances 0.000 claims description 15
- 230000005855 radiation Effects 0.000 claims description 5
- 238000005507 spraying Methods 0.000 claims description 3
- 238000000926 separation method Methods 0.000 abstract description 16
- 239000002245 particle Substances 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 9
- 238000012546 transfer Methods 0.000 description 7
- LYCAIKOWRPUZTN-UHFFFAOYSA-N Ethylene glycol Chemical compound OCCO LYCAIKOWRPUZTN-UHFFFAOYSA-N 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 229920006254 polymer film Polymers 0.000 description 6
- 238000007664 blowing Methods 0.000 description 5
- 238000010438 heat treatment Methods 0.000 description 5
- 239000012535 impurity Substances 0.000 description 5
- 238000010521 absorption reaction Methods 0.000 description 4
- 238000007599 discharging Methods 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 230000002411 adverse Effects 0.000 description 3
- 230000002528 anti-freeze Effects 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 230000008021 deposition Effects 0.000 description 3
- 230000008014 freezing Effects 0.000 description 3
- 238000007710 freezing Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 239000002518 antifoaming agent Substances 0.000 description 2
- 239000013556 antirust agent Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 230000003111 delayed effect Effects 0.000 description 2
- 239000012153 distilled water Substances 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000013618 particulate matter Substances 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000003915 air pollution Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/14—Attitude, flight direction, or altitude control by jet reaction the jets being other than main propulsion jets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a tail gas recycling system of a fixed-wing unmanned aerial vehicle, belonging to the technical field of unmanned aerial vehicles.A tail gas heat exchanger outlet is respectively communicated with an inlet of a wing heat exchanger and an inlet of an empennage heat exchanger through pipelines; the inlet of the tail gas heat exchanger is respectively communicated with the outlet of the wing heat exchanger and the outlet of the empennage heat exchanger through pipelines; the wing heat exchanger is arranged inside the wing; the tail fin heat exchanger is arranged in the tail fin; the tail gas heat exchanger is used for absorbing the heat of the tail gas of the unmanned aerial vehicle; the pump set is used for providing power for fluid exchange in the tail gas heat exchanger, the wing heat exchanger, the tail gas heat exchanger and the empennage heat exchanger. The tail gas recycling system of the fixed-wing unmanned aerial vehicle reduces the possibility of icing of the unmanned aerial vehicle in flight, fully utilizes the tail gas, reduces the pollution of particles in the air, has good control effect on wing airflow separation, enables the unmanned aerial vehicle to fly at a larger attack angle, and improves the maneuvering capability of the unmanned aerial vehicle.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a tail gas recycling system of a fixed-wing unmanned aerial vehicle.
Background
Along with the rapid development of fixed wing uavs, require fixed wing uavs to adapt to different atmospheric flight environments. Atmospheric temperature, humidity, wind level, etc. all affect the flight of an aircraft. When the atmospheric temperature is lower and the humidity is higher, the surface of the airplane is frozen, so that the pneumatic performance and the flying quality of the airplane are reduced, and the flying safety is influenced. The front edge of the wing and the front edge of the tail wing of the unmanned aerial vehicle are easy-to-freeze areas, and when the atmospheric environment reaches a freeze condition, an ice layer can be formed quickly. According to the icing wind tunnel test data, the icing thickness of 2-3 inches can be formed within five minutes when the icing condition is serious. The ice accretion formed at the leading edge of the wing can affect the aerodynamic profile of the entire wing and alter the flight quality of the aircraft. The influence on aerodynamic performance is obviously increased after the front edge of the horizontal tail is frozen. Therefore, the problem of icing of the unmanned aerial vehicle needs to be solved well.
There are four more common ways of protecting an aircraft from ice: gas-heated anti-icing, electric-heated anti-icing, mechanical de-icing and chemical liquid anti-icing. The air-heating ice-preventing and removing method is characterized in that a hot air source is guided to the front edge of an airfoil, an empennage and other parts needing ice prevention to prevent icing, and because tail gas is sprayed to the inner side of the front edge, impurities such as carbon deposition and the like can be generated on the inner side of the front edge, the surface of the airfoil can be polluted for a long time, the heat transfer efficiency of the surface of the front edge is reduced, and the ice-preventing and removing effect is weakened. The electrothermal deicing is characterized in that a strip-shaped, wire-shaped or film-shaped heating element is embedded into the part of the airplane easy to freeze, and deicing is carried out in an electrifying heating mode. Mechanical deicing refers to the fact that a layer of expandable rubber pipe belts is arranged on the front edge of the wing, the rubber pipe belts are attached to the wing in a clinging mode at ordinary times, after the rubber pipe belts are frozen, pressure is charged and discharged to the rubber pipe belts, periodic expansion and contraction are generated, the ice layer on the surface can be broken and blown away by airflow, and the mode is high in cost and can influence the aerodynamic appearance of the wing. The chemical solution deicing is to spray an antifreeze solution on the icing surface of the airplane for deicing and preventing freezing, the antifreeze solution is a chemical liquid with a very low freezing point, and the antifreeze solution lowers the freezing point of water to melt an formed ice layer.
For wings, the greater problem of icing is that the airfoil airflow can be separated so that longitudinal or lateral instability of the drone can occur. Various control surfaces are generally adopted on the unmanned aerial vehicle as main means of flight control, but the efficiency of the control surfaces is reduced due to airflow separation under a large deflection angle of the control surfaces, and the stability control characteristic of the aircraft is seriously influenced. At present, the chord direction air blowing control method is applied to the separation flow control of the control surface, wherein an air blowing flap and a jet flap are taken as typical representatives. The blowing flap technology is to place the deflecting flap directly downstream of the high-speed jet of the engine to obtain high lift. The high-speed jet flow of the engine blows out the separated airflow and increases the circulation quantity for the wing profile, so that the wing obtains high lift force. The jet flap is ejected backwards and downwards at a high speed along the whole wingspan through a gap of the trailing edge of the wing by utilizing compressed air or gas flow led out from an engine to form a jet curtain, thereby playing the role of increasing the lift of the flap. But the above two methods are not well suited for fixed wing drones.
The tail gas of the engine of the existing fixed wing unmanned aerial vehicle has heat, is not fully utilized, and is directly discharged into the air to pollute the environment. If the tail gas can be used for solving the problems of icing of wings and empennages and the problem of separation of wing surface airflow, the tail gas generator has good commercial prospect.
Disclosure of Invention
The invention aims to provide a tail gas recycling system of a fixed-wing unmanned aerial vehicle aiming at the defects, and aims to solve the problems of icing of the fixed-wing unmanned aerial vehicle in flight, air pollution caused by tail gas, influence on flight control caused by wing airflow separation and the like. In order to achieve the purpose, the invention provides the following technical scheme:
the fixed wing unmanned aerial vehicle tail gas recycling system comprises a tail gas heat exchanger 1, a wing heat exchanger 2, an empennage heat exchanger 3 and a pump set; the outlet of the tail gas heat exchanger 1 is respectively communicated with the inlet of the wing heat exchanger 2 and the inlet of the empennage heat exchanger 3 through pipelines; an inlet of the tail gas heat exchanger 1 is respectively communicated with an outlet of the wing heat exchanger 2 and an outlet of the empennage heat exchanger 3 through pipelines; the wing heat exchanger 2 is arranged in the wing; the empennage heat exchanger 3 is arranged inside the empennage; the tail gas heat exchanger 1 is used for absorbing heat of tail gas of the unmanned aerial vehicle; the pump set is used for providing power for fluid exchange in the tail gas heat exchanger 1, the wing heat exchanger 2, the tail gas heat exchanger 1 and the empennage heat exchanger 3. According to the structure, high-temperature tail gas exhausted by an engine of the unmanned aerial vehicle passes through the tail gas heat exchanger 1, the fluid in the tail gas heat exchanger 1 absorbs the heat of the tail gas and then becomes high-temperature fluid, and the high-temperature fluid flows to the inlet of the wing heat exchanger 2 and the inlet of the empennage heat exchanger 3 through pipelines from the outlet of the tail gas heat exchanger 1. The wing heat exchanger 2 is arranged in the wing, high-temperature fluid entering the inlet of the wing heat exchanger 2 exchanges heat with the skin of the wing, after the skin of the wing absorbs heat, icing is avoided, at the moment, the fluid is cooled, and low-temperature fluid flows to the inlet of the tail gas heat exchanger 1 from the outlet of the wing heat exchanger 2 again to continuously absorb the heat of tail gas; the tail fin heat exchanger 3 is arranged in the tail fin, high-temperature fluid entering from an inlet of the tail fin heat exchanger 3 exchanges heat with skin of the tail fin, after the skin of the tail fin absorbs heat, icing is avoided, at the moment, the fluid is cooled, and low-temperature fluid flows to an inlet of the tail gas heat exchanger 1 from an outlet of the tail fin heat exchanger 3 again to continuously absorb heat of tail gas; the pump set provides power for fluid exchange in the tail gas heat exchanger 1, the wing heat exchanger 2, the tail gas heat exchanger 1 and the tail wing heat exchanger 3, so that the skins of the wings and the tail wing continuously have heat to absorb, particularly the front edge part, the occurrence of icing is avoided, and the series of unstable flight problems caused by wing profile deformation caused by icing are avoided. The tail gas recycling system of the fixed wing unmanned aerial vehicle can utilize the heat of tail gas to perform anti-icing and deicing on the skin surfaces of the wings and the empennage, so that impurities such as carbon deposition and the like on the inner walls of the wings and the empennage can not be caused, the high-efficiency heat transfer capacity can be kept only by periodically dismounting and cleaning the tail gas heat exchanger 1, large power is not occupied, the aerodynamic appearance of the wings is not influenced, and deicing can be performed in the air. The tail gas heat exchanger 1, the wing heat exchanger 2 and the tail wing heat exchanger 3 can be made of oxygen-free copper materials, and the internal fluid can be made of ethylene glycol, an antifoaming agent, an antirust agent, distilled water and the like.
Further, the tail gas heat exchanger 1 comprises an inner cylinder 4 and an outer cylinder 5; the inner cylinder 4 is arranged in the outer cylinder 5, and an annular cavity 6 is arranged between the inner cylinder 4 and the outer cylinder 5; the annular cavity 6 is communicated with an outlet of the tail gas heat exchanger 1 and an inlet of the tail gas heat exchanger 1; one end of the inner cylinder 4 is provided with a tail gas inlet 7, and the other end is provided with a tail gas outlet 8; a plurality of heat-conducting plates 9 are arranged between the tail gas inlet 7 and the tail gas outlet 8; the heat conducting plate 9 is in radiation connection with the inner wall of the inner barrel 4 from the central axis of the inner barrel 4. According to the structure, low-temperature fluid enters the annular cavity 6 from the inlet of the tail gas heat exchanger 1, high-temperature tail gas enters the inner cylinder 4 from the tail gas inlet 7 and is discharged from the tail gas outlet 8, the tail gas fully heats the fluid in the annular cavity 6, and the high-temperature fluid flows out from the outlet of the tail gas heat exchanger 1. In the tail gas heat exchanger 1, the center of the inner cylinder 4 forms a tail gas circulation channel, so that high-temperature tail gas is not excessively blocked when heating fluid in the annular cavity 6, and the heat-conducting plates 9 are in radiation connection with the inner wall of the inner cylinder 4 from the center axis of the inner cylinder 4 to uniformly separate the tail gas circulation channel, so that the annular cavity 6 uniformly absorbs heat in a large area and the tail gas emission is not blocked. The heat conducting plate 9 may be a hollow structure, so that fluid may be present in both the annular cavity 6 and the heat conducting plate 9 for absorbing heat of the exhaust gas. The outlet of the tail gas heat exchanger 1 and the inlet of the tail gas heat exchanger 1 can be respectively arranged on the upper side of one end of the outer cylinder 5 and the lower side of the other end of the outer cylinder 5, so that the circulation path of the fluid is prolonged, and the heat is fully absorbed.
Further, heat conducting graphite films are paved on the surface of the heat conducting plate 9 and the inner wall of the inner cylinder 4. According to the structure, the heat-conducting graphite film has high heat-conducting performance and is made of a highly-oriented graphite polymer film, so that the heat-absorbing capacity of the heat-conducting plate 9 and the inner cylinder 4 is improved, and the heat exchange of fluid and tail gas is accelerated.
Further, the wing heat exchanger 2 comprises a first heat exchange main pipe 10; the inlet of the wing heat exchanger 2 and the outlet of the wing heat exchanger 2 are positioned at two ends of the first heat exchange main pipe 10; a plurality of first heat exchange channels 12 are arranged on the side wall of the first heat exchange main pipe 10; the first heat exchange channel 12 is connected with the inner side of the wing; and a heat-conducting graphite film is laid at the joint of the first heat exchange channel 12 and the inner side of the wing. According to the structure, high-temperature fluid enters the first heat exchange main pipe 10 from the inlet of the wing heat exchanger 2, fills the first heat exchange channel 12, then transfers heat to the inner side of the wing, so that the wing skin is heated to deice or prevent icing, and the cooled fluid flows out from the outlet of the wing heat exchanger 2. The heat-conducting graphite film has high heat-conducting performance, is made of a highly oriented graphite polymer film, improves the heat absorption capacity of the skin, and accelerates the heat exchange between fluid and the skin. For the front edge part which is easy to freeze, the first heat exchange channels 12 can be arranged densely, so that the anti-icing and deicing capabilities are improved.
Further, the empennage heat exchanger 3 comprises a second heat exchange main pipe; the inlet of the empennage heat exchanger 3 and the outlet of the empennage heat exchanger 3 are positioned at two ends of the second heat exchange main pipe; a plurality of second heat exchange channels are arranged on the side wall of the second heat exchange main pipe; the second heat exchange channel is connected with the inner side of the tail wing; and a heat-conducting graphite film is laid at the joint of the second heat exchange channel and the inner side of the tail wing. According to the structure, high-temperature fluid enters the second heat exchange main pipe from the inlet of the tail fin heat exchanger 3, fills the second heat exchange channel, then transfers heat to the inner side of the tail fin, so that the tail fin skin is heated to deice or prevent icing, and the cooled fluid flows out from the outlet of the tail fin heat exchanger 3. The heat-conducting graphite film has high heat-conducting performance, is made of a highly oriented graphite polymer film, improves the heat absorption capacity of the skin, and accelerates the heat exchange between fluid and the skin. For the front edge part which is easy to freeze, the second heat exchange channels can be arranged densely, so that the anti-icing and deicing capabilities are improved.
Further, the device also comprises an air compressor 13, a gas storage cylinder 14, a flow control valve 15 and a spray pipe assembly 16; the inlet of the air compressor 13 is communicated with the tail gas outlet 8 through a pipeline; the outlet of the air compressor 13 is communicated with the inlet of the gas storage bottle 14 through a pipeline; the outlet of the gas storage bottle 14 is communicated with a spray pipe assembly 16 through a pipeline; a flow control valve 15 is arranged on a pipeline between the gas storage bottle 14 and the spray pipe assembly 16; the nozzle assembly 16 is used to spray air onto the upper surface of the wing. According to the structure, the high-temperature tail gas is cooled after heat exchange through the tail gas heat exchanger 1, so that the tail gas is absorbed by the air compressor 13 and compressed into the gas storage cylinder 14, and the exhaust pressure of the engine is reduced by the air compressor 13, so that the power required by the engine is reduced; the impurity in the tail gas deposits in gas bomb 14, and the tail gas of discharging is cleaner environmental protection like this, avoids directly discharging the particulate matter in the tail gas in the atmosphere. The flow control valve 15 controls the flow rate of the exhaust gas in the cylinder 14 from the nozzle assembly 16, and the nozzle assembly 16 is used for spraying air on the upper surface of the wing. The wings are the main aerodynamic lift sources of the aircraft. When the fixed-wing unmanned aerial vehicle takes off, lands or flies at a large attack angle under other special conditions, the airflow originally attached to the airfoil may flow and separate due to the fact that the adverse pressure gradient cannot be overcome. Flow separation causes increased noise, vibration of the machine body, and reduced rudder efficiency. Severe flow separation can result in aircraft stall, greatly affecting flight safety. Aiming at the problem that the aerodynamic performance of the unmanned aerial vehicle is seriously affected by the airflow separation phenomenon easily occurring on the surface of a wing under a large attack angle, the tail gas recycling system of the fixed-wing unmanned aerial vehicle can effectively avoid the airflow separation, and the principle of the tail gas recycling system of the fixed-wing unmanned aerial vehicle is that high-speed airflow is sprayed near the upper wing surface of the trailing edge of the wing to inject energy into the flow which is low in energy and is about to be separated or is separated, so that the airflow is pushed to overcome the adverse pressure gradient and continuously flow towards the trailing edge. The flow in the boundary layer of the wing surface is interfered by blowing of compressed gas at the rear edge part of the wing, so that the separation of the flow in the boundary layer can be effectively delayed, the laminar flow area of the wing surface is enlarged, and the purposes of increasing lift and reducing drag are achieved. The purpose of macroscopically effectively controlling is achieved by applying extremely small disturbance to the flowing critical point at a proper position and time, and the method has a good prospect in the aspect of engineering application. The spray pipe assembly 16 comprises a plurality of nozzles, the included angle between the nozzles on the upper surface of the wing and the horizontal direction is-30 degrees, and wind tunnel experiment data show that the layout mode can achieve better effect and can improve the attack angle of the airplane by more than 2 degrees. When the attack angle of the unmanned aerial vehicle is larger than 10 degrees, the system is started, the gas flow speed of the nozzle is 10m/s, the gas is sprayed once at an interval of 30s, and the gas flow lasts for 0.2 s. When the unmanned aerial vehicle continuously increases the attack angle, the central controller controls the flow rate of the nozzle to increase the gas flow rate of the nozzle, and the duration of the gas flow is increased to 1s at most. The air compressor 13 and the flow control valve 15 are controlled by a central controller.
Further, a safety valve 17 is arranged on the gas storage cylinder 14. As can be seen from the above construction, the safety valve 17 ensures that the interior of the cylinder 14 is not over pressurized.
Further, a filter screen 18 is arranged in the gas storage cylinder 14; the filter screen 18 extends from the upper left to the lower right, and divides the space in the gas storage cylinder 14 into an air inlet cavity 19 positioned at the lower left and an air outlet cavity 20 positioned at the upper right; the inlet of the gas storage bottle 14 is communicated with a gas inlet cavity 19; the outlet of the gas storage bottle 14 is communicated with a gas outlet cavity 20. According to the structure, the tail gas enters the gas inlet cavity 19 from the inlet of the gas storage bottle 14, then the pollution particles are blocked by the obliquely arranged filter screen 18, the particles in the tail gas are precipitated at the bottom of the filter screen 18, and the clean tail gas enters the gas outlet cavity 20 and then is discharged from the outlet of the gas storage bottle 14.
Further, the pump group includes a first pump 21 and a second pump 22; the first pump 21 is used for providing power for fluid exchange in the tail gas heat exchanger 1 and the wing heat exchanger 2; the second pump 22 is used to provide the power for the fluid exchange in the tail gas heat exchanger 1 and the tail fin heat exchanger 3. As can be seen from the above structure, the first pump 21 and the second pump 22 can be operated under the control of the central controller, thereby controlling the speed of the fluid exchange in the tail gas heat exchanger 1 and the wing heat exchanger 2 and the speed of the fluid exchange in the tail gas heat exchanger 1 and the tail fin heat exchanger 3.
Further, a first temperature sensor 23 is arranged at the outlet of the wing heat exchanger 2; a second temperature sensor 24 is arranged at the outlet of the empennage heat exchanger 3; and a third temperature sensor 25 is arranged at the outlet of the tail gas heat exchanger 1. With the above structure, the first temperature sensor 23 can monitor the temperature of the outlet fluid of the wing heat exchanger 2, the second temperature sensor 24 can monitor the temperature of the outlet fluid of the tail heat exchanger 3, and the third temperature sensor 25 can monitor the temperature of the outlet fluid of the tail gas heat exchanger 1. The first temperature sensor 23, the second temperature sensor 24, and the third temperature sensor 25 transmit temperature information to the central controller. The central controller controls the operation of the first pump 21 and the second pump 22 according to the 3 temperature information. Specifically, when the temperatures monitored by the first temperature sensor 23 and the second temperature sensor 24 are less than 10 ℃, which indicates that the temperature of the leading edge of the wing or the tail wing is low and the risk of icing exists, the central controller will increase the power of the first pump 21 and the second pump 22, so that the flow speed of the fluid in the pipeline is increased, and the heat transmission is increased. When the temperature difference between the third temperature sensor 25 and the first temperature sensor 23 is less than 30 ℃ and the temperature difference between the third temperature sensor 25 and the second temperature sensor 24 is less than 30 ℃, which indicates that the temperature of the leading edge of the wing or the empennage is high and no icing risk exists, the central controller reduces the power of the liquid delivery pump to enable the whole system to be in a low-power-consumption operation state or a starting standby state.
The beneficial effects of the invention are:
the invention discloses a fixed wing unmanned aerial vehicle tail gas recycling system, which belongs to the technical field of unmanned aerial vehicles and comprises a tail gas heat exchanger, a wing heat exchanger, an empennage heat exchanger and a pump set; the outlet of the tail gas heat exchanger is respectively communicated with the inlet of the wing heat exchanger and the inlet of the empennage heat exchanger through pipelines; the inlet of the tail gas heat exchanger is respectively communicated with the outlet of the wing heat exchanger and the outlet of the empennage heat exchanger through pipelines; the wing heat exchanger is arranged inside the wing; the tail fin heat exchanger is arranged in the tail fin; the tail gas heat exchanger is used for absorbing the heat of the tail gas of the unmanned aerial vehicle; the pump set is used for providing power for fluid exchange in the tail gas heat exchanger, the wing heat exchanger, the tail gas heat exchanger and the empennage heat exchanger. According to the tail gas recycling system for the fixed-wing unmanned aerial vehicle, the possibility of icing of the unmanned aerial vehicle in flight is reduced by recycling the tail gas, the pollution of particles in the air is reduced by fully utilizing the tail gas, the wing airflow separation is well controlled, the unmanned aerial vehicle can fly at a larger attack angle, and the maneuvering capability of the unmanned aerial vehicle is improved.
Drawings
FIG. 1 is a schematic three-dimensional structure of a tail gas heat exchanger according to the present invention;
FIG. 2 is a schematic view of the wing structure of the present invention;
FIG. 3 is a schematic diagram of the working principle of the present invention;
in the drawings: the system comprises a tail gas heat exchanger 1, a wing heat exchanger 2, a tail wing heat exchanger 3, an inner cylinder 4, an outer cylinder 5, an annular cavity 6, a tail gas inlet 7, a tail gas outlet 8, a heat conducting plate 9, a first heat exchange main pipe 10, a first heat exchange channel 12, an air compressor 13, an air storage bottle 14, a flow control valve 15, a spray pipe 16, a safety valve 17, a filter screen 18, an air inlet cavity 19, an air outlet cavity 20, a first pump 21, a second pump 22, a first temperature sensor 23, a second temperature sensor 24 and a third temperature sensor 25.
Detailed Description
The present invention will be described in further detail below with reference to the drawings and the embodiments, but the present invention is not limited to the following examples.
The first embodiment is as follows:
see figures 1-3. The tail gas recycling system of the fixed wing unmanned aerial vehicle comprises a tail gas heat exchanger 1, a wing heat exchanger 2, an empennage heat exchanger 3 and a pump set; the outlet of the tail gas heat exchanger 1 is respectively communicated with the inlet of the wing heat exchanger 2 and the inlet of the empennage heat exchanger 3 through pipelines; an inlet of the tail gas heat exchanger 1 is respectively communicated with an outlet of the wing heat exchanger 2 and an outlet of the empennage heat exchanger 3 through pipelines; the wing heat exchanger 2 is arranged in the wing; the empennage heat exchanger 3 is arranged inside the empennage; the tail gas heat exchanger 1 is used for absorbing heat of tail gas of the unmanned aerial vehicle; the pump set is used for providing power for fluid exchange in the tail gas heat exchanger 1, the wing heat exchanger 2, the tail gas heat exchanger 1 and the empennage heat exchanger 3. According to the structure, high-temperature tail gas discharged by an engine of the unmanned aerial vehicle passes through the tail gas heat exchanger 1, fluid in the tail gas heat exchanger 1 absorbs the heat of the tail gas and then becomes high-temperature fluid, and the high-temperature fluid flows to the inlet of the wing heat exchanger 2 and the inlet of the empennage heat exchanger 3 through pipelines from the outlet of the tail gas heat exchanger 1. The wing heat exchanger 2 is arranged in the wing, high-temperature fluid entering the inlet of the wing heat exchanger 2 exchanges heat with the skin of the wing, after the skin of the wing absorbs heat, icing is avoided, at the moment, the fluid is cooled, and low-temperature fluid flows to the inlet of the tail gas heat exchanger 1 from the outlet of the wing heat exchanger 2 again to continuously absorb the heat of tail gas; the tail fin heat exchanger 3 is arranged in the tail fin, high-temperature fluid entering from the inlet of the tail fin heat exchanger 3 exchanges heat with the skin of the tail fin, after the skin of the tail fin absorbs heat, icing is avoided, the fluid is cooled, and low-temperature fluid flows to the inlet of the tail gas heat exchanger 1 from the outlet of the tail fin heat exchanger 3 again to continuously absorb the heat of tail gas; the pump set provides power for fluid exchange in the tail gas heat exchanger 1, the wing heat exchanger 2, the tail gas heat exchanger 1 and the tail wing heat exchanger 3, so that the skins of the wings and the tail wing can continuously absorb heat, particularly the front edge part, the occurrence of icing is avoided, and the series of unstable flight problems caused by wing profile deformation caused by icing are avoided. The tail gas recycling system of the fixed wing unmanned aerial vehicle can utilize the heat of tail gas to perform anti-icing and deicing on the skin surfaces of the wings and the empennage, so that impurities such as carbon deposition and the like on the inner walls of the wings and the empennage can not be caused, the high-efficiency heat transfer capacity can be kept only by periodically dismounting and cleaning the tail gas heat exchanger 1, large power is not occupied, the aerodynamic appearance of the wings is not influenced, and deicing can be performed in the air. The tail gas heat exchanger 1, the wing heat exchanger 2 and the empennage heat exchanger 3 can be made of oxygen-free copper materials, and the internal fluid can be made of ethylene glycol, an antifoaming agent, an antirust agent, distilled water and the like.
The second embodiment:
see figures 1-3. On the basis of the first embodiment, the tail gas heat exchanger 1 comprises an inner cylinder 4 and an outer cylinder 5; the inner cylinder 4 is arranged in the outer cylinder 5, and an annular cavity 6 is arranged between the inner cylinder 4 and the outer cylinder 5; the annular cavity 6 is communicated with an outlet of the tail gas heat exchanger 1 and an inlet of the tail gas heat exchanger 1; one end of the inner cylinder 4 is provided with a tail gas inlet 7, and the other end is provided with a tail gas outlet 8; a plurality of heat-conducting plates 9 are arranged between the tail gas inlet 7 and the tail gas outlet 8; the heat conducting plate 9 is in radiation connection with the inner wall of the inner barrel 4 from the central axis of the inner barrel 4. According to the structure, low-temperature fluid enters the annular cavity 6 from the inlet of the tail gas heat exchanger 1, high-temperature tail gas enters the inner cylinder 4 from the tail gas inlet 7 and is discharged from the tail gas outlet 8, the tail gas fully heats the fluid in the annular cavity 6, and the high-temperature fluid flows out from the outlet of the tail gas heat exchanger 1. In the tail gas heat exchanger 1, the center of the inner cylinder 4 forms a tail gas circulation channel, so that high-temperature tail gas is not excessively blocked when heating fluid in the annular cavity 6, and the heat-conducting plates 9 are in radiation connection with the inner wall of the inner cylinder 4 from the center axis of the inner cylinder 4 to uniformly separate the tail gas circulation channel, so that the annular cavity 6 uniformly absorbs heat in a large area and the tail gas emission is not blocked. The heat conducting plate 9 may be a hollow structure, so that fluid may be present in both the annular cavity 6 and the heat conducting plate 9 for absorbing heat of the exhaust gas. The outlet of the tail gas heat exchanger 1 and the inlet of the tail gas heat exchanger 1 can be respectively arranged on the upper side of one end of the outer cylinder 5 and the lower side of the other end of the outer cylinder 5, so that the flow path of the fluid is prolonged, and the heat is fully absorbed.
Example three:
see figures 1-3. On the basis of the second embodiment, the heat conducting graphite film is paved on the surface of the heat conducting plate 9 and the inner wall of the inner cylinder 4. According to the structure, the heat-conducting graphite film has high heat-conducting performance and is made of a highly-oriented graphite polymer film, so that the heat-absorbing capacity of the heat-conducting plate 9 and the inner cylinder 4 is improved, and the heat exchange of fluid and tail gas is accelerated.
The wing heat exchanger 2 comprises a first heat exchange main pipe 10; the inlet of the wing heat exchanger 2 and the outlet of the wing heat exchanger 2 are positioned at two ends of the first heat exchange main pipe 10; a plurality of first heat exchange channels 12 are arranged on the side wall of the first heat exchange main pipe 10; the first heat exchange channel 12 is connected with the inner side of the wing; and a heat-conducting graphite film is laid at the joint of the first heat exchange channel 12 and the inner side of the wing. According to the structure, high-temperature fluid enters the first heat exchange main pipe 10 from the inlet of the wing heat exchanger 2, fills the first heat exchange channel 12, then transfers heat to the inner side of the wing, so that the wing skin is heated to deice or prevent icing, and the cooled fluid flows out from the outlet of the wing heat exchanger 2. The heat-conducting graphite film has high heat-conducting performance, is made of a highly-oriented graphite polymer film, improves the heat absorption capacity of the skin, and accelerates the heat exchange between fluid and the skin. For the front edge part which is easy to freeze, the first heat exchange channels 12 can be arranged densely, so that the anti-icing and deicing capabilities are improved.
The empennage heat exchanger 3 comprises a second heat exchange main pipe; the inlet of the empennage heat exchanger 3 and the outlet of the empennage heat exchanger 3 are positioned at two ends of the second heat exchange main pipe; a plurality of second heat exchange channels are arranged on the side wall of the second heat exchange main pipe; the second heat exchange channel is connected with the inner side of the tail wing; and a heat-conducting graphite film is laid at the joint of the second heat exchange channel and the inner side of the tail wing. According to the structure, high-temperature fluid enters the second heat exchange main pipe from the inlet of the tail fin heat exchanger 3, fills the second heat exchange channel, then transfers heat to the inner side of the tail fin, so that the tail fin skin is heated to deice or prevent icing, and the cooled fluid flows out from the outlet of the tail fin heat exchanger 3. The heat-conducting graphite film has high heat-conducting performance, is made of a highly-oriented graphite polymer film, improves the heat absorption capacity of the skin, and accelerates the heat exchange between fluid and the skin. For the front edge part which is easy to freeze, the second heat exchange channels can be arranged densely, so that the anti-icing and deicing capabilities are improved.
The device also comprises an air compressor 13, a gas storage bottle 14, a flow control valve 15 and a spray pipe component 16; the inlet of the air compressor 13 is communicated with the tail gas outlet 8 through a pipeline; the outlet of the air compressor 13 is communicated with the inlet of the gas storage bottle 14 through a pipeline; the outlet of the gas storage bottle 14 is communicated with a spray pipe assembly 16 through a pipeline; a flow control valve 15 is arranged on a pipeline between the gas storage bottle 14 and the spray pipe assembly 16; the nozzle assembly 16 is used to spray air on the upper surface of the wing. According to the structure, the high-temperature tail gas is cooled after heat exchange through the tail gas heat exchanger 1, so that the tail gas is absorbed by the air compressor 13 and compressed into the gas storage cylinder 14, and the exhaust pressure of the engine is reduced by the air compressor 13, so that the power required by the engine is reduced; the impurity in the tail gas deposits in gas bomb 14, and the tail gas of discharging is cleaner environmental protection like this, avoids directly discharging the particulate matter in the tail gas in the atmosphere. The flow control valve 15 controls the flow rate of the exhaust gas in the cylinder 14 from the nozzle assembly 16, and the nozzle assembly 16 is used for spraying air on the upper surface of the wing. The wings are the main aerodynamic lift sources of the aircraft. When the fixed-wing unmanned aerial vehicle takes off, lands or flies at a large attack angle under other special conditions, the airflow originally attached to the airfoil may flow and separate due to the fact that the adverse pressure gradient cannot be overcome. Flow separation causes increased noise, body vibration, and reduced rudder efficiency. Severe flow separation can result in aircraft stall, greatly affecting flight safety. Aiming at the problem that the aerodynamic performance of the unmanned aerial vehicle is seriously influenced by the airflow separation phenomenon which is easy to occur on the surface of the wing under a large attack angle, the tail gas recycling system of the fixed wing unmanned aerial vehicle can effectively avoid the occurrence of the airflow separation. The flow in the boundary layer of the wing surface is interfered by blowing of compressed gas at the rear edge part of the wing, so that the separation of the flow in the boundary layer can be effectively delayed, the laminar flow area of the wing surface is enlarged, and the purposes of increasing lift and reducing drag are achieved. The purpose of macroscopically effectively controlling is achieved by applying extremely small disturbance to the flowing critical point at a proper position and time, and the method has a good prospect in the aspect of engineering application. The spray pipe assembly 16 comprises a plurality of nozzles, the included angle between the nozzles on the upper surface of the wing and the horizontal direction is-30 degrees, and wind tunnel experiment data show that the layout mode can achieve better effect and can improve the attack angle of the airplane by more than 2 degrees. When the attack angle of the unmanned aerial vehicle is larger than 10 degrees, the system is started, the gas flow speed of the nozzle is 10m/s, the gas is sprayed once at an interval of 30s, and the gas flow lasts for 0.2 s. When unmanned aerial vehicle lasts the increase angle of attack, central controller control nozzle velocity of flow improves the nozzle gas velocity of flow, and it is longest to 1s to improve the duration of air current. The air compressor 13 and the flow control valve 15 are controlled by a central controller.
The gas storage bottle 14 is provided with a safety valve 17. As can be seen from the above construction, the safety valve 17 ensures that the interior of the cylinder 14 is not over pressurized.
A filter screen 18 is arranged in the gas storage cylinder 14; the filter screen 18 extends from the upper left to the lower right, and divides the space in the gas storage cylinder 14 into an air inlet cavity 19 positioned at the lower left and an air outlet cavity 20 positioned at the upper right; the inlet of the gas storage bottle 14 is communicated with a gas inlet cavity 19; the outlet of the gas storage cylinder 14 is communicated with a gas outlet cavity 20. According to the structure, the tail gas enters the gas inlet cavity 19 from the inlet of the gas storage bottle 14, then the pollution particles are blocked by the obliquely arranged filter screen 18, the particles in the tail gas are precipitated at the bottom of the filter screen 18, and the clean tail gas enters the gas outlet cavity 20 and then is discharged from the outlet of the gas storage bottle 14.
The pump group includes a first pump 21 and a second pump 22; the first pump 21 is used for providing power for fluid exchange in the tail gas heat exchanger 1 and the wing heat exchanger 2; the second pump 22 is used to provide the power for the fluid exchange in the tail gas heat exchanger 1 and the tail fin heat exchanger 3. As can be seen from the above structure, the first pump 21 and the second pump 22 can be controlled by the central controller to operate, thereby controlling the speed of fluid exchange in the tail gas heat exchanger 1 and the wing heat exchanger 2 and the speed of fluid exchange in the tail gas heat exchanger 1 and the tail wing heat exchanger 3.
A first temperature sensor 23 is arranged at the outlet of the wing heat exchanger 2; a second temperature sensor 24 is arranged at the outlet of the empennage heat exchanger 3; and a third temperature sensor 25 is arranged at the outlet of the tail gas heat exchanger 1. With the above structure, the first temperature sensor 23 can monitor the temperature of the outlet fluid of the wing heat exchanger 2, the second temperature sensor 24 can monitor the temperature of the outlet fluid of the tail fin heat exchanger 3, and the third temperature sensor 25 can monitor the temperature of the outlet fluid of the tail gas heat exchanger 1. The first temperature sensor 23, the second temperature sensor 24, and the third temperature sensor 25 transmit temperature information to the central controller. The central controller controls the operation of the first pump 21 and the second pump 22 according to the 3 temperature information. Specifically, when the temperatures monitored by the first temperature sensor 23 and the second temperature sensor 24 are less than 10 ℃, which indicates that the wing or the empennage leading edge has a low temperature and is at risk of icing, the central controller will increase the power of the first pump 21 and the second pump 22, so that the flow rate of the fluid in the pipeline is increased, and the heat transmission is increased. When the temperature difference between the third temperature sensor 25 and the first temperature sensor 23 is less than 30 ℃ and the temperature difference between the third temperature sensor 25 and the second temperature sensor 24 is less than 30 ℃, which indicates that the temperature of the leading edge of the wing or the empennage is high and no icing risk exists, the central controller reduces the power of the liquid delivery pump to enable the whole system to be in a low-power-consumption operation state or a standby state.
The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. Fixed wing unmanned aerial vehicle tail gas system of recycling, its characterized in that: comprises a tail gas heat exchanger (1), a wing heat exchanger (2), a tail wing heat exchanger (3) and a pump set; an outlet of the tail gas heat exchanger (1) is respectively communicated with an inlet of the wing heat exchanger (2) and an inlet of the empennage heat exchanger (3) through pipelines; an inlet of the tail gas heat exchanger (1) is respectively communicated with an outlet of the wing heat exchanger (2) and an outlet of the empennage heat exchanger (3) through pipelines; the wing heat exchanger (2) is arranged inside the wing; the empennage heat exchanger (3) is arranged inside the empennage; the tail gas heat exchanger (1) is used for absorbing heat of tail gas of the unmanned aerial vehicle; the pump set is used for providing power for fluid exchange in the tail gas heat exchanger (1), the wing heat exchanger (2), the tail gas heat exchanger (1) and the empennage heat exchanger (3).
2. The fixed-wing drone tail gas reuse system of claim 1, characterized in that: the tail gas heat exchanger (1) comprises an inner cylinder (4) and an outer cylinder (5); the inner cylinder (4) is arranged in the outer cylinder (5), and an annular cavity (6) is arranged between the inner cylinder (4) and the outer cylinder (5); the annular cavity (6) is communicated with an outlet of the tail gas heat exchanger (1) and an inlet of the tail gas heat exchanger (1); one end of the inner cylinder (4) is provided with a tail gas inlet (7), and the other end is provided with a tail gas outlet (8); a plurality of heat-conducting plates (9) are arranged between the tail gas inlet (7) and the tail gas outlet (8); the heat conducting plate (9) is in radiation connection with the inner wall of the inner barrel (4) from the central axis of the inner barrel (4).
3. The fixed-wing drone tail gas reuse system of claim 2, characterized in that: and heat-conducting graphite films are paved on the surface of the heat-conducting plate (9) and the inner wall of the inner cylinder (4).
4. The fixed-wing drone tail gas reuse system of claim 1, characterized in that: the wing heat exchanger (2) comprises a first heat exchange main pipe (10); the inlet of the wing heat exchanger (2) and the outlet of the wing heat exchanger (2) are positioned at two ends of the first heat exchange main pipe (10); a plurality of first heat exchange channels (12) are arranged on the side wall of the first heat exchange main pipe (10); the first heat exchange channel (12) is connected with the inner side of the wing; and a heat-conducting graphite film is laid at the joint of the first heat exchange channel (12) and the inner side of the wing.
5. The fixed-wing drone tail gas reuse system of claim 1, characterized in that: the empennage heat exchanger (3) comprises a second heat exchange main pipe; the inlet of the empennage heat exchanger (3) and the outlet of the empennage heat exchanger (3) are positioned at two ends of the second heat exchange main pipe; a plurality of second heat exchange channels are arranged on the side wall of the second heat exchange main pipe; the second heat exchange channel is connected with the inner side of the tail wing; and a heat-conducting graphite film is laid at the joint of the second heat exchange channel and the inner side of the tail wing.
6. The fixed-wing drone tail gas reuse system of claim 2, characterized in that: the device also comprises an air compressor (13), a gas storage bottle (14), a flow control valve (15) and a spray pipe component (16); the inlet of the air compressor (13) is communicated with the tail gas outlet (8) through a pipeline; the outlet of the air compressor (13) is communicated with the inlet of the gas storage bottle (14) through a pipeline; the outlet of the gas storage bottle (14) is communicated with a spray pipe component (16) through a pipeline; a flow control valve (15) is arranged on a pipeline between the gas storage bottle (14) and the spray pipe component (16); the nozzle assembly (16) is used for spraying air on the upper surface of the wing.
7. The fixed wing drone tail gas reuse system of claim 6, characterized in that: and a safety valve (17) is arranged on the gas storage bottle (14).
8. The fixed-wing drone tail gas reuse system of claim 6, characterized in that: a filter screen (18) is arranged in the gas storage bottle (14); the filter screen (18) extends from the upper left to the lower right, and divides the space in the gas storage bottle (14) into a gas inlet cavity (19) positioned at the lower left and a gas outlet cavity (20) positioned at the upper right; the inlet of the gas storage bottle (14) is communicated with the gas inlet cavity (19); the outlet of the gas storage bottle (14) is communicated with the gas outlet cavity (20).
9. The fixed-wing drone tail gas reuse system of claim 1, characterized in that: the pump group comprises a first pump (21) and a second pump (22); the first pump (21) is used for providing power for fluid exchange in the tail gas heat exchanger (1) and the wing heat exchanger (2); the second pump (22) is used for providing power for fluid exchange in the tail gas heat exchanger (1) and the tail wing heat exchanger (3).
10. The fixed-wing drone tail gas reuse system of claim 9, characterized in that: a first temperature sensor (23) is arranged at an outlet of the wing heat exchanger (2); a second temperature sensor (24) is arranged at the outlet of the empennage heat exchanger (3); and a third temperature sensor (25) is arranged at the outlet of the tail gas heat exchanger (1).
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| CN202210227163.8A CN114789793A (en) | 2022-03-08 | 2022-03-08 | Tail gas recycling system for fixed-wing unmanned aerial vehicle |
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| CN202210227163.8A CN114789793A (en) | 2022-03-08 | 2022-03-08 | Tail gas recycling system for fixed-wing unmanned aerial vehicle |
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| CN209612547U (en) * | 2019-03-04 | 2019-11-12 | 王涛 | A kind of exhaust-gas treatment purification device |
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| CN113636085A (en) * | 2020-04-27 | 2021-11-12 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle and control method of anti-icing and deicing system of unmanned aerial vehicle |
| WO2021242463A2 (en) * | 2020-04-27 | 2021-12-02 | Jetoptera, Inc. | Vertical take off and landing aircraft with fluidic propulsion system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN209612547U (en) * | 2019-03-04 | 2019-11-12 | 王涛 | A kind of exhaust-gas treatment purification device |
| CN113525694A (en) * | 2020-04-17 | 2021-10-22 | 西安京东天鸿科技有限公司 | Deicing system is prevented to wing |
| CN113636085A (en) * | 2020-04-27 | 2021-11-12 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle and control method of anti-icing and deicing system of unmanned aerial vehicle |
| WO2021242463A2 (en) * | 2020-04-27 | 2021-12-02 | Jetoptera, Inc. | Vertical take off and landing aircraft with fluidic propulsion system |
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