Airplane drainage ground air source device capable of normally working at low temperature

Abstract

The invention discloses a ground air source device capable of normally working at low temperature for airplane drainage, and relates to the technical field of ground air source devices for airplanes, the ground air source device comprises a mounting box body, and an inner cavity of the mounting box body is divided into a first mounting cavity and a second mounting cavity; an air source mechanism; the air source mechanism comprises a machine body, a main air inlet heating pipe, an auxiliary air inlet heating pipe, a valve mechanism and an air inlet pipe. The other end of the air inlet pipe is communicated with the main air inlet heating pipe and the auxiliary air inlet heating pipe; the valve mechanism is installed on the auxiliary air inlet heating pipe. A heating unit; the heating part is arranged in the first mounting cavity and is connected with the main air inlet heating pipe and the auxiliary air inlet heating pipe; the temperature self-adjusting mechanism is arranged in the second mounting cavity and is connected with the air inlet pipe so as to detect the temperature of the air inlet pipe; the temperature self-adjusting mechanism is in transmission connection with the valve mechanism. The working temperature of the gas source device can be lowered in the low-temperature environment, so that the normal working state of the ground gas source device is guaranteed, and the service life of the ground gas source device is prolonged.

Description

Technical Field

[0001] The invention relates to the technical field of ground air source devices for aircraft, and in particular to a ground air source device for aircraft drainage that can work normally at low temperatures. Background Art

[0002] The water tank is one of the important parts of the aircraft. In winter, when the temperature is low, the water in the water tank is easy to freeze. When the water freezes, it expands and easily damages the pipeline. Therefore, when the aircraft is grounded, it is necessary to use high-pressure gas to drain the water. Generally, APU bleed air is used for drainage. At this time, the engine must be kept in working condition, and the fuel consumption is large. The use of ground air source devices for auxiliary drainage can effectively save energy. Although the current air source devices can meet certain usage requirements, in low temperature environments, the internal structure may not work reliably or even be damaged due to the low temperature. How to maintain the normal operation of the ground air source device in low temperature environments is a problem that needs to be considered.

[0003] After searching, a Chinese patent (application number CN202010686284.X) discloses an air compressor that can use an onboard power supply and a method for low-temperature water discharge of an aircraft. The air compressor is mainly composed of a body, which is driven by an electric motor to produce compressed air. The air outlet of the body is connected to the air outlet pipe, and the end of the pipe is connected to the equipment that uses gas. Its uniqueness lies in the integration of a frequency converter, the input end of which is connected to the onboard power supply system of the aircraft, and the output end is connected to the aforementioned electric motor. However, according to the description of the document, the air compressor system still has room for improvement; although it can provide the aircraft with the necessary compressed gas to meet the gas supply needs, under extreme low temperature conditions, such as the apron temperature in the severe winter in the north may drop to minus fifty degrees Celsius, which may cause the air compressor to be unable to operate effectively, thereby affecting the efficiency and quality of the gas supply operation.

[0004] Therefore, how to provide a ground air source device for aircraft drainage that can work normally at low temperatures, and can adjust the working temperature of the air source device in an external low temperature environment to ensure the normal working state of the ground air source device and improve the service life of the ground air source device is an urgent problem that technical personnel in this field need to solve. Summary of the invention

[0005] In view of this, the present invention proposes a ground air source device for aircraft drainage that can work normally at low temperatures, aiming to solve the technical problem of unstable working state of traditional air source devices when operating in low temperature environments.

[0006] In order to achieve the above object, the present invention adopts the following technical solution:

[0007] The present invention provides a ground air source device for aircraft drainage that can work normally at low temperatures, comprising:

[0008] An installation box, wherein the inner cavity of the installation box is divided into a first installation cavity and a second installation cavity by a separator;

[0009] The air source mechanism comprises a body installed in the first installation cavity, a main air intake heating pipe, a secondary air intake heating pipe, a valve mechanism and an air intake pipe installed in the second installation cavity; one end of the air intake pipe is connected to the outside atmosphere, and the other end passes through the separator and connects the main air intake heating pipe and the secondary air intake heating pipe; the valve mechanism is installed on the secondary air intake heating pipe to open and close the secondary air intake heating pipe;

[0010] The heating unit is arranged in the first installation cavity and is connected to the main air intake heating pipe and the auxiliary air intake heating pipe to preheat the inhaled cold air;

[0011] A temperature self-regulating mechanism, wherein the temperature self-regulating mechanism is arranged in the second installation cavity and connected to the intake pipe to detect the temperature of the intake pipe; the temperature self-regulating mechanism is transmission-connected to the valve mechanism to open the valve mechanism when the temperature of the intake pipe drops to a preset temperature, thereby increasing the preheating power of the inhaled cold air.

[0012] The installation box of the ground air source device for aircraft drainage that can work normally at low temperature of the present invention plays a certain role in protecting and heat-insulating the air source mechanism; because the separator has a certain heat-insulating effect, the air source mechanism located in the first installation cavity will not interfere with the temperature detection and control function of the temperature self-regulating mechanism located in the second installation cavity. The heating part warms up the interior of the fuselage by preheating the cold air inhaled by the air source mechanism, so as to avoid the low-temperature cold air from the outside from continuously entering the inner cavity of the fuselage and affecting its working performance. Under low-temperature environment, the heating part preferentially heats the cold air inhaled in the main air intake heating pipe to warm up the interior of the fuselage; the low-temperature air from the outside enters the air intake pipe, which can cool down the air intake pipe; as the temperature of the outside air further decreases, the temperature self-regulating mechanism indirectly senses and judges the temperature of the outside air by detecting the temperature of the air intake pipe, and when it is detected that the temperature of the air intake pipe reaches the preset temperature condition, the transmission control opens the valve mechanism so that the heating part heats the cold air inhaled in the auxiliary air intake heating pipe, so as to form a dual-channel preheating and heating of the cold air inhaled, thereby increasing the preheating power of the cold air inhaled and improving the heating efficiency. In addition, the heat dissipated by the heating part is spatially constrained by the first installation cavity, which can further improve the heating efficiency of the fuselage and the utilization efficiency of thermal energy. The present invention realizes the function of adjusting the working temperature of the air source device under the external low temperature environment to ensure the normal working state of the ground air source device, thereby improving the service life of the ground air source device.

[0013] As a further improvement of the above technical solution, the heating unit includes an air intake heating unit and a fuselage heating unit;

[0014] The air intake heating unit is connected to the main air intake heating pipe and the auxiliary air intake heating pipe to preheat the inhaled cold air; and the fuselage heating unit is connected to the fuselage to heat the fuselage.

[0015] The beneficial effects of the above technical solution are: the air intake heating unit preheats the inhaled cold air through the main air intake heating pipe and the auxiliary air intake heating pipe to increase the inner cavity temperature of the fuselage, thereby realizing heating from the inside to the outside; the fuselage heating unit directly heats the fuselage from the outside to the inside; the heating efficiency and uniformity of the air source mechanism are greatly improved, and stable working temperature conditions for the air source mechanism can be quickly established.

[0016] As a further improvement of the above technical solution, the air intake heating unit includes a heating body and a heating seat; the fuselage heating unit includes a heating device, a circulating heating pipe assembly and a heat transfer chain assembly;

[0017] The circulating heating pipe assembly is installed on the heating device to form a circulating heating loop; one end of the heat transfer chain assembly is connected to the circulating heating pipe assembly to absorb heat, and the other end of the heat transfer chain assembly is detachably wound around the fuselage to heat the fuselage;

[0018] A heating chamber is formed on the main air intake heating pipe; the heating body is installed in the heating chamber and electrically connected to the heating device to heat the inhaled cold air flowing through the main air intake heating pipe; the circulating heating pipe assembly passes through the heating seat to circulate heat; the heating seat is installed on the secondary air intake heating pipe to heat the inhaled cold air diverted to the secondary air intake heating pipe.

[0019] The beneficial effects of the above technical solution are: the heating device can control the heating body to heat the inhaled cold air in the heating chamber, so as to achieve preheating of the cold air in the main air intake heating pipe, thereby achieving heating of the fuselage from the inside to the outside; at extremely low temperatures, the heating device can transport heat to the heating seat through the circulating heating pipe assembly, and the heating seat preheats the cold air in the secondary air intake heating pipe, thereby further improving the heating efficiency of the fuselage from the inside to the outside; the heating device can also transport heat to the heat transfer chain assembly through the circulating heating pipe assembly, and the heat transfer chain assembly further conducts the heat to the fuselage, thereby achieving heating of the fuselage from the outside to the inside.

[0020] As a further improvement of the above technical solution, the valve mechanism includes a first valve body, a second valve body, a valve core and an elastic connection part; one end of the first valve body is connected to and communicated with the heating chamber, and the other end of the first valve body is sealed and communicated with one end of the second valve body through the elastic connection part; the other end of the second valve body is slidably nested and sealedly connected with the auxiliary air intake heating pipe;

[0021] The temperature self-regulating mechanism is transmission-connected to the second valve body to drive the second valve body to slide axially along the auxiliary air intake heating tube; one end of the valve core is fixed inside the second valve body, and the other end of the valve core is adapted to be movably inserted into the valve cavity of the first valve body to open and close the valve cavity channel of the first valve body under the sliding drive of the second valve body.

[0022] The beneficial effect of the above technical solution is that when the temperature self-regulating mechanism detects that the temperature of the intake pipe reaches the preset temperature, the temperature self-regulating mechanism can drive the second valve body to slide axially along the auxiliary air intake heating pipe, and then control the valve core to open the valve cavity channel of the first valve body, so as to divert part of the air in the heating chamber to the auxiliary air intake heating pipe, thereby realizing dual-channel preheating and improving the heating efficiency.

[0023] As a further improvement of the above technical solution, the heat transfer chain assembly includes a heat transfer seat, a heat transfer wire and a plurality of heat transfer blocks;

[0024] The heat transfer seat is installed on the circulating heating tube assembly for heat exchange; the heat transfer wire is wound around the fuselage and both ends of the heat transfer wire are connected to the heat transfer seat to transfer the heat of the heat transfer seat to the fuselage; a plurality of heat transfer blocks can be slidably connected to the heat transfer wire along the length direction of the heat transfer wire and adhered to the fuselage to form a multi-point distributed heat transfer structure for transferring heat to fixed positions on the fuselage.

[0025] The beneficial effects of the above technical solution are: the heat transfer seat is used to exchange heat with the circulating heating tube assembly to transfer heat to the heat transfer wire, and the heat transfer wire further transfers heat along the length direction; the heat transfer wire can be easily wound and arranged on the fuselage to adapt to the fuselage structure with a complex shape, so as to achieve effective temperature increase from the outside to the inside of the fuselage. The heat transfer wire can further transfer heat to the heat transfer block; the heat transfer block sliding along the length direction of the heat transfer wire can be easily arranged on the key heating parts of the fuselage, so as to quickly build the temperature conditions for the stable operation of the gas source mechanism.

[0026] As a further improvement of the above technical solution, the heat transfer chain assembly further includes a wire clamp; the wire clamp is installed on the heat transfer wire to fix the two ends of the heat transfer wire.

[0027] The beneficial effect of the above technical solution is that the wire clamp can be convenient for tightening and fixing the two ends of the heat transfer wire wrapped around the fuselage, so as to improve the stability of the installation of the heat transfer wire on the fuselage.

[0028] As a further improvement of the above technical solution, the heat transfer block includes a first clamping block and a second clamping block; the first clamping block and the second clamping block are symmetrically arranged on both sides of the heat transfer wire and fastened by fasteners to adapt to clamping on the heat transfer wire; the side of the first clamping block away from the second clamping block is attached to the fuselage.

[0029] The beneficial effects of the above technical solution are: the first clamp block and the second clamp block are adapted to clamp and wrap the heat transfer wire, which can improve the heat conduction efficiency; loosening the fasteners can facilitate the position adjustment of the first clamp block and the second clamp block on the heat transfer wire; the side of the first clamp block fits against the fuselage to transfer heat to the key working parts.

[0030] As a further improvement of the above technical solution, an anti-slip strip is installed on the side of the first clamping block away from the second clamping block.

[0031] The beneficial effect of the above technical solution is that the anti-slip strip can make the first clamping block fit more stably on the fuselage to prevent it from shifting when the fuselage vibrates during operation.

[0032] As a further improvement of the above technical solution, the temperature self-regulating mechanism includes a heat exchange tube, an elastic telescopic airbag and a transmission component;

[0033] The heat exchange tube is spirally wound on the air intake pipe to exchange heat with the air intake pipe;

[0034] The fixed end of the elastic telescopic airbag is connected to the heat exchange tube and is sealed and connected to the inner cavity of the heat exchange tube so as to be telescopic when the internal gas temperature rises or falls; one end of the transmission component is transmission-connected to the valve mechanism; the telescopic end of the elastic telescopic airbag is transmission-connected to the other end of the transmission component so as to telescope and drive the transmission component to move and thereby control the opening and closing of the valve mechanism.

[0035] The beneficial effects of the above technical solution are: the elastic telescopic airbag is connected to the inner cavity of the heat exchange tube to construct a closed and connected gas cavity inside; when the heat exchange tube and the air intake pipe exchange heat, the gas in the gas cavity expands and contracts to drive the elastic telescopic airbag to perform telescopic movement, and then the opening and closing of the valve mechanism is driven by the transmission component.

[0036] As a further improvement of the above technical solution, the transmission assembly includes a push rod 1, a guide tube, a transmission ball chain and a push rod 2;

[0037] The guide tube passes through and is sealed and fixed on the separator, and one end of the guide tube is located in the second installation cavity, and the other end of the guide tube is located in the first installation cavity; the transmission ball chain is sealed and slidably arranged in the tube cavity of the guide tube;

[0038] One end of the push rod 2 is transmission-connected to the valve mechanism, and the other end of the push rod 2 is movably inserted into the tube cavity of one end of the guide tube corresponding to the first installation cavity and fixedly connected to one end of the transmission ball chain;

[0039] One end of the push rod is movably inserted into the tube cavity of one end of the guide tube corresponding to the second installation cavity and is fixedly connected to the other end of the transmission ball chain; the telescopic end of the elastic telescopic airbag is transmission-connected to the other end of the push rod, so that the transmission ball chain can be pushed and pulled along the tube cavity of the guide tube by the push rod one, and then the push rod two can be pushed and pulled to move the valve mechanism to open and close.

[0040] The beneficial effects of the above technical solution are: the guide tube can be arranged in a curved manner, and the transmission ball chain can slide along the curved path in the guide tube, thereby realizing the transmission connection between the push rod 1 and the push rod 2, making the transmission more stable and smooth. During operation, the guide tube and the separator do not move relative to each other, thereby avoiding conduction between the first installation cavity and the second installation cavity. The installation of the guide tube will not damage the thermal insulation performance of the separator, thereby ensuring the temperature stability of the first installation cavity and ensuring the reliability of the temperature detection of the temperature self-regulating mechanism in the second installation cavity.

[0041] It can be seen from the above technical solutions that, compared with the prior art, the present invention discloses a ground air source device for aircraft drainage that can work normally at low temperatures, and has the following advantages and beneficial effects:

[0042] 1. The present invention can directly detect the intake temperature of the intake pipe by setting a temperature self-regulating mechanism, and then when the temperature is too low, the auxiliary intake heating pipe is turned on, so that part of the air flow is auxiliary heated by the heating seat and then input into the air source mechanism, thereby better ensuring the reliable operation of the air source mechanism in a low temperature environment.

[0043] 2. The temperature self-regulating mechanism of the present invention is designed based on the principle of thermal expansion and contraction. It exchanges heat with the intake pipe through the heat exchange tube. When the temperature is too low, it can drive the elastic telescopic airbag to shrink, thereby driving the valve mechanism to open through the transmission component to achieve the conduction of the auxiliary intake heating pipe, and assist in heating the inhaled cold air, ultimately achieving the self-regulating function of the intake temperature.

[0044] 3. The present invention can transmit more smoothly by setting push rod 1, guide tube, transmission ball chain and push rod 2, and avoids conduction between the first installation cavity and the second installation cavity, thereby ensuring that the temperature of the first installation cavity is appropriate and ensuring the temperature detection reliability of the temperature self-regulating mechanism.

[0045] 4. The present invention can wind the heat transfer wire around the body of the air source mechanism by arranging structures such as heat transfer wire and heat transfer block, and heat and keep the body of the air source mechanism warm by utilizing the heat transfer of the heat transfer seat, heat transfer wire and heat transfer block, thereby improving the working reliability. Moreover, since the heat transfer wire and the heat transfer block are movably installed, they can be fixed by a cable tie after adjusting the position, thereby improving the flexibility of the arrangement.

[0046] 5. The present invention improves the friction force to a certain extent by installing an anti-slip strip on the first clamping block, thereby preventing the heat transfer block from sliding on the surface of the air source mechanism body and improving reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0048] Figure 1 A schematic diagram of the internal structure of a ground air source device for aircraft drainage that can work normally at low temperatures according to the present invention;

[0049] Figure 2 A schematic diagram of the structure of an air source mechanism of a ground air source device for aircraft drainage that can work normally at low temperatures according to the present invention;

[0050] Figure 3 A schematic structural diagram of a heating part of a ground air source device for aircraft drainage that can work normally at low temperatures according to the present invention;

[0051] Figure 4 A schematic diagram of the structure of a temperature self-regulating mechanism of a ground air source device for aircraft drainage that can work normally at low temperatures according to the present invention;

[0052] Figure 5 A schematic diagram of the structure of a transmission component of a ground air source device for aircraft drainage that can work normally at low temperatures according to the present invention;

[0053] Figure 6 A schematic diagram of a valve mechanism of a ground air source device for aircraft drainage that can work normally at low temperatures according to the present invention;

[0054] Figure 7 A schematic structural diagram of a heat transfer chain assembly of a ground air source device for aircraft drainage that can work normally at low temperatures according to the present invention;

[0055] Figure 8 A schematic diagram of the installation state of the heat transfer wire and the heat transfer block of a ground air source device for aircraft drainage that can work normally at low temperatures according to the present invention;

[0056] Fig. 9 A schematic diagram of the structure of a walking vehicle body of a ground air source device for aircraft drainage that can work normally at low temperatures according to the present invention;

[0057] In the figure: 1. installation box; 11. partition; 12. first installation cavity; 13. second installation cavity; 2. air source mechanism; 21. fuselage; 22. main air intake heating pipe; 221. heating chamber; 23. auxiliary air intake heating pipe; 24. valve mechanism; 241. first valve body; 2411. guide rod; 2412. spring; 242. second valve body; 2421. annular plate; 243. valve core; 244. elastic connection part; 25. air intake pipe; 26. air delivery pipe; 3. heating part; 31. air intake heating part; 311. heating body; 312. heating seat; 313. installation rod; 314. electrical connection line; 32. fuselage heating part; 321. heating device; 322. circulation heating Heat pipe assembly; 323, heat transfer chain assembly; 3231, heat transfer seat; 3232, heat transfer wire; 3233, heat transfer block; 3233A, first clamp; 3233B, second clamp; 3233C, slot; 3233D, anti-slip strip; 3234, cable clamp; 3235, fastener; 4, temperature self-regulating mechanism; 41, heat exchange tube; 411, spiral support wire; 42, elastic telescopic airbag; 43, transmission assembly; 431, push rod one; 432, guide tube; 433, transmission ball chain; 4331, sliding ball; 4332, connecting rope; 434, push rod two; 435, slide frame; 436, push frame; 437, guide frame; 5, walking vehicle body; 51, outer box body. DETAILED DESCRIPTION

[0058] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0059] In the description of the present invention, it is necessary to understand that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0060] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0061] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0062] like Figures 1 to 9 As shown, a ground air source device for aircraft drainage that can work normally at low temperatures includes:

[0063] An installation box 1, wherein the inner cavity of the installation box 1 is divided by a separator 11 to form a first installation cavity 12 and a second installation cavity 13;

[0064] The air source mechanism 2 comprises a body 21 installed in the first installation cavity 12, a main air intake heating pipe 22, an auxiliary air intake heating pipe 23, a valve mechanism 24 and an air intake pipe 25 installed in the second installation cavity 13; one end of the air intake pipe 25 passes through the wall of the installation box 1 and is connected to the external atmosphere, and the other end passes through the partition 11 and is connected to the main air intake heating pipe 22 and the auxiliary air intake heating pipe 23; the valve mechanism 24 is installed on the auxiliary air intake heating pipe 23 to open and close the auxiliary air intake heating pipe 23;

[0065] The heating unit 3 is disposed in the first mounting cavity 12 and is connected to the main air intake heating pipe 22 and the auxiliary air intake heating pipe 23 to preheat the inhaled cold air;

[0066] The temperature self-regulating mechanism 4 is arranged in the second installation cavity 13 and connected to the intake pipe 25 to detect the temperature of the intake pipe 25; the temperature self-regulating mechanism 4 is transmission-connected to the valve mechanism 24 to open the valve mechanism 24 when the temperature of the intake pipe 25 drops to a preset temperature, thereby increasing the preheating power of the inhaled cold air.

[0067] The installation box 1 of the ground air source device for aircraft drainage that can work normally at low temperatures in this embodiment plays a certain role in protecting and insulating the air source mechanism 2; because the partition 11 has a certain heat insulation effect, the air source mechanism 2 located in the first installation cavity 12 will not interfere with the temperature detection and control function of the temperature self-regulating mechanism 4 located in the second installation cavity 13. The heating part 3 preheats the cold air inhaled by the air source mechanism 2 to increase the temperature inside its fuselage 21, so as to prevent the low-temperature cold air from the outside from continuously entering the inner cavity of the fuselage 21 and affecting its working performance. In a low-temperature environment, the heating unit 3 preferentially heats the inhaled cold air in the main air intake heating pipe 22 to increase the temperature inside the fuselage 21; the external low-temperature air enters the air intake pipe 25, which can cool the air intake pipe 25; as the temperature of the outside air further decreases, the temperature self-regulating mechanism 4 indirectly senses and judges the temperature of the outside air by detecting the temperature of the air intake pipe 25, and when it is detected that the temperature of the air intake pipe 25 reaches the preset temperature condition, the transmission control opens the valve mechanism 24 to allow the heating unit 3 to heat the inhaled cold air in the auxiliary air intake heating pipe 23, so as to form a dual-channel preheating and warming of the inhaled cold air, thereby increasing the preheating power of the inhaled cold air and improving the warming efficiency. In addition, the heat dissipated by the heating unit 3 is spatially constrained by the first installation cavity 12, which can further improve the heating efficiency of the fuselage and the utilization efficiency of thermal energy. The present invention realizes the function of adjusting the working temperature of the air source device in an external low-temperature environment to ensure the normal working state of the ground air source device, thereby increasing the service life of the ground air source device.

[0068] Specifically, the air source mechanism 2 further includes an air delivery pipe 26; the body 21 is a compressor body; the main air intake heating pipe 22 and the auxiliary air intake heating pipe 23 are both connected to the air intake of the working chamber of the body 21; one end of the air delivery pipe 26 is connected to the exhaust port of the working chamber of the body 21, and the other end passes through the wall of the installation box 1. The partition 11 uses a partition plate with a heat insulation function.

[0069] In some embodiments, the heating unit 3 includes an air intake heating unit 31 and a body heating unit 32;

[0070] The air intake heating unit 31 is connected to the main air intake heating pipe 22 and the auxiliary air intake heating pipe 23 to preheat the inhaled cold air; the fuselage heating unit 32 is connected to the fuselage 21 to heat the fuselage 21 .

[0071] The air intake heating unit 31 preheats the inhaled cold air through the main air intake heating pipe 22 and the auxiliary air intake heating pipe 23 to increase the inner cavity temperature of the fuselage 21, thereby achieving heating from the inside to the outside; the fuselage heating unit 32 directly heats the fuselage 21 from the outside to the inside; the heating efficiency and uniformity of the air source mechanism 2 are greatly improved, and a stable working temperature condition of the air source mechanism 2 can be quickly established.

[0072] In some embodiments, the air intake heating unit 31 includes a heating body 311 and a heating seat 312; the fuselage heating unit 32 includes a heating device 321, a circulating heating pipe assembly 322 and a heat transfer chain assembly 323;

[0073] The circulating heating pipe assembly 322 is installed on the heating device 321 to form a circulating heating loop; one end of the heat transfer chain assembly 323 is connected to the circulating heating pipe assembly 322 to absorb heat, and the other end of the heat transfer chain assembly 323 can be detachably wound around the fuselage 21 to heat the fuselage 21;

[0074] A heating chamber 221 is formed on the main air intake heating pipe 22; the heating body 311 is installed in the heating chamber 221 and is electrically connected to the heating device 321 through an electrical connection line 314 to heat the inhaled cold air flowing through the main air intake heating pipe 22; the circulating heating pipe assembly 322 passes through the heating seat 312 to circulate heat; the heating seat 312 is installed on the auxiliary air intake heating pipe 23 to heat the inhaled cold air diverted to the auxiliary air intake heating pipe 23.

[0075] The heating device 321 can control the heating body 311 to heat the inhaled cold air in the heating chamber 221, so as to realize the preheating of the cold air in the main air intake heating pipe 22, thereby realizing the heating of the fuselage 21 from the inside to the outside; at extremely low temperatures, the heating device 321 can transfer heat to the heating seat 312 through the circulating heating pipe assembly 322, and the heating seat 312 preheats the cold air in the auxiliary air intake heating pipe 23, thereby further improving the heating efficiency of the fuselage 21 from the inside to the outside; the heating device 321 can also transfer heat to the heat transfer chain assembly 323 through the circulating heating pipe assembly 322, and the heat transfer chain assembly 323 further conducts the heat to the fuselage 21, thereby realizing the heating of the fuselage 21 from the outside to the inside.

[0076] Specifically, a mounting rod 313 is fixedly installed in the first mounting cavity 12, and one end of the mounting rod 313 penetrates into the interior of the heating chamber 221 and is fixedly connected to and supports the heating body 311. The heating chamber 221 corresponds to one end of the air inlet pipe 25 as a truncated cone-shaped cavity, and the heating body 311 corresponds to one end of the air inlet pipe 25 as a truncated cone-shaped structure adapted to the truncated cone-shaped cavity, so as to define a truncated cone-shaped annular air inlet channel between the heating body 311 and the truncated cone-shaped cavity; so as to increase the contact area between the inhaled cold air and the heating body 311 and improve the heat exchange efficiency. The heating body 311 is an electric heating body, and the heating device 321 can control the heating power of the heating body 311.

[0077] Specifically, one end of the auxiliary air intake heating pipe 23 is connected to and communicates with the peripheral wall of the heating chamber 221; the other end is connected to and communicates with the air inlet of the working chamber of the fuselage 21; the auxiliary air intake heating pipe 23 is connected to the inner cavity of the heating seat 312 to guide the inhaled air into the inner cavity of the heating seat 312 for auxiliary heating. The heating seat 312 is fixedly installed in the first installation cavity 12 by a bracket.

[0078] In some embodiments, the valve mechanism 24 includes a first valve body 241, a second valve body 242, a valve core 243 and an elastic connection portion 244; one end of the first valve body 241 is connected to and communicated with the peripheral wall of the heating chamber 221, and the other end of the first valve body 241 is sealed and communicated with one end of the second valve body 242 through the elastic connection portion 244; the other end of the second valve body 242 is slidably nested and sealedly connected with the auxiliary air intake heating pipe 23;

[0079] The temperature self-regulating mechanism 4 is transmission-connected to the second valve body 242 to drive the second valve body 242 to slide axially along the auxiliary air intake heating pipe 23; one end of the valve core 243 is fixed inside the second valve body 242, and the other end of the valve core 243 is adapted to be movably inserted into the valve cavity of the first valve body 241 to open and close the valve cavity channel of the first valve body 241 under the sliding drive of the second valve body 242.

[0080] Specifically, the first valve body 241, the second valve body 242 and the elastic connection part 244 are all cylindrical and coaxially arranged; the elastic connection part 244 can be made of elastic rubber material; the side end of the first valve body 241 close to the second valve body 242 has a valve cavity in the shape of a bell mouth, and the valve core 243 is adapted to be located in the valve cavity in the shape of a bell mouth, and cooperates with each other to realize the opening and closing of the valve cavity channel. The maximum diameter of the valve core 243 is smaller than the inner diameter of the second valve body 242 and the elastic connection part 244. The other end of the second valve body 242 is slidably sleeved on one end of the auxiliary air intake heating pipe 23, and the second valve body 242 and the auxiliary air intake heating pipe 23 are sealed by an annular connection membrane. The second valve body 242 and the auxiliary air intake heating pipe 23 can also be sealed with a sealing ring in the prior art.

[0081] When the temperature self-regulating mechanism 4 detects that the temperature of the intake pipe 25 reaches the preset temperature, the temperature self-regulating mechanism 4 can drive the second valve body 242 to slide axially along the auxiliary intake heating pipe 23, and then control the valve core 243 to open the valve cavity channel of the first valve body 241, so as to divert a part of the air in the heating chamber 221 to the auxiliary intake heating pipe 23, thereby realizing dual-channel preheating and improving the heating efficiency.

[0082] In some embodiments, in order to improve the reliability of the sliding of the second valve body 242, a guide rod 2411 is fixed on the outer wall of the first valve body 241, and an annular plate 2421 is provided on the outer peripheral side of the end of the second valve body 242. A through hole is opened on the annular plate 2421, and one end of the guide rod 2411 is slidably penetrated in the through hole of the annular plate 2421 to guide the sliding of the second valve body 242, thereby improving the reliability of the movement of the second valve body 242. The other end of the guide rod 2411 and the annular plate 2421 are connected by a spring 2412; the spring 2412 and the elastic connecting part 244 can jointly ensure that the valve core 243 is reliably reset to close the valve cavity channel of the first valve body 241.

[0083] In some embodiments, the heat transfer chain assembly 323 includes a heat transfer seat 3231, a heat transfer wire 3232 and a plurality of heat transfer blocks 3233;

[0084] The heat transfer seat 3231 is installed on the circulating heating tube assembly 322 for heat exchange; the heat transfer wire 3232 is wound on the fuselage 21 and both ends of the heat transfer wire 3232 are connected to the heat transfer seat 3231 to transfer the heat of the heat transfer seat 3231 to the fuselage 21; multiple heat transfer blocks 3233 can be slidably connected to the heat transfer wire 3232 along the length direction of the heat transfer wire 3232 and attached to the fuselage 21 to form a multi-point distributed heat transfer structure for transferring heat to fixed positions on the fuselage 21.

[0085] The heat transfer seat 3231 is used to exchange heat with the circulating heating tube assembly 322 to transfer heat to the heat transfer wire 3232, and the heat transfer wire 3232 further transfers heat along the length direction; the heat transfer wire 3232 can be easily wound and arranged on the fuselage 21 to adapt to the fuselage structure with a complex shape, so as to achieve effective temperature increase from the outside to the inside of the fuselage 21. The heat transfer wire 3232 can further transfer heat to the heat transfer block 3233; the heat transfer block 3233 sliding along the length direction of the heat transfer wire 3232 can be easily arranged at the key heating position on the fuselage 21, so as to quickly build the temperature conditions for the stable operation of the gas source mechanism 2.

[0086] In some embodiments, the heat transfer chain assembly 323 further includes a cable clamp 3234 ; the cable clamp 3234 is installed on the heat transfer wire 3232 to fix the two ends of the heat transfer wire 3232 .

[0087] The wire clamp 3234 can be used to tighten and fix the two ends of the heat transfer wire 3232 wound around the fuselage 21 , so as to improve the stability of the installation of the heat transfer wire 3232 on the fuselage 21 .

[0088] In some embodiments, the heat transfer block 3233 includes a first clamp block 3233A and a second clamp block 2323B; the first clamp block 3233A and the second clamp block 2323B are symmetrically arranged on both sides of the heat transfer wire 3232 and are fastened by fasteners 3235 to adapt to clamping on the heat transfer wire 3232; the side of the first clamp block 3233A away from the second clamp block 2323B is attached to the fuselage 21.

[0089] The first clamp block 3233A and the second clamp block 2323B are adapted to clamp and wrap the heat transfer wire 3232, which can improve the heat conduction efficiency; loosening the fastener 3235 can facilitate the position adjustment of the first clamp block 3233A and the second clamp block 2323B on the heat transfer wire 3232; the side of the first clamp block 3233A is attached to the fuselage 21 to transfer heat to the key working parts.

[0090] Specifically, the wall surfaces opposite to the first clamp block 3233A and the second clamp block 2323B both have grooves that can fit on the outer peripheral wall of the heat transfer wire 3232. The grooves of the first clamp block 3233A and the second clamp block 2323B together enclose a through hole for passing the heat transfer wire 3232. The fastener 3235 is a bolt.

[0091] In some embodiments, an anti-slip strip 3233D is installed on the side of the first clamp block 3233A away from the second clamp block 2323B.

[0092] Specifically, a slot 3233C is provided on the side of the first clamping block 3233A away from the second clamping block 2323B, and an anti-slip strip 3233D that can abut against the fuselage 21 is detachably installed in the slot 3233C.

[0093] The anti-slip strip 3233D can make the first clamping block 3233A fit more stably on the fuselage 21 to prevent it from shifting when the fuselage 21 vibrates during operation.

[0094] In some embodiments, the temperature self-regulating mechanism 4 includes a heat exchange tube 41, an elastic and telescopic airbag 42, and a transmission component 43;

[0095] The heat exchange tube 41 is spirally wound around the air intake pipe 25 to exchange heat with the air intake pipe 25;

[0096] The fixed end of the elastic telescopic airbag 42 is connected to the heat exchange tube 41 and is sealed and connected to the inner cavity of the heat exchange tube 41 so that it can be expanded and contracted when the internal gas temperature rises or falls; one end of the transmission component 43 is transmission-connected to the valve mechanism 24; the telescopic end of the elastic telescopic airbag 42 is transmission-connected to the other end of the transmission component 43 so that the transmission component 43 can be moved to control the opening and closing of the valve mechanism 24 through expansion and contraction.

[0097] The elastic telescopic airbag 42 is connected to the inner cavity of the heat exchange tube 41 to construct a closed and connected gas cavity inside; when the heat exchange tube 41 exchanges heat with the intake pipe 25, the gas in the gas cavity expands and contracts to drive the elastic telescopic airbag 42 to perform telescopic movement, and then the transmission component 43 is used to drive the valve mechanism 24 to open and close.

[0098] Specifically, in order to prevent the spirally wound heat exchange tube 41 from being deformed due to heat and thermal expansion and contraction of the internal gas and failing to fit well with the intake pipe 25 for heat exchange; a spiral supporting steel wire 411 matched with the heat exchange tube 41 is fixed on the outside of the heat exchange tube 41 to ensure that the heat exchange tube 41 is always tightly attached to the outer wall of the intake pipe 25.

[0099] Specifically, there are two elastic and telescopic airbags 42 , and both of the two elastic and telescopic airbags 42 are arranged perpendicular to the air inlet pipe 25 , and the fixed ends thereof are respectively connected to and communicated with the two ports of the heat exchange pipe 41 .

[0100] In some embodiments, the transmission assembly 43 includes a push rod 1 431, a guide tube 432, a transmission ball chain 433, a push rod 2 434, a slide 435, a push frame 436 and a guide frame 437;

[0101] The guide tube 432 penetrates and is sealed and fixed on the separator 11, and one end of the guide tube 432 is located in the second installation cavity 13, and the other end of the guide tube 432 is located in the first installation cavity 12; the transmission ball chain 433 is sealed and slidably arranged in the tube cavity of the guide tube 432;

[0102] The guide frame 437 is fixedly mounted on the side wall of the second mounting cavity 13, and the slide 435 is slidably connected to the guide frame 437;

[0103] The push frame 436 is fixed on the outer wall of the second valve body 242, and one end of the push rod 434 is fixed to the push frame 436, and the second valve body 242 of the valve mechanism 24 can be pushed by the push frame 436; the other end of the push rod 434 is movably inserted into the tube cavity of one end of the guide tube 432 corresponding to the first installation cavity 12 and fixedly connected to one end of the transmission ball chain 433;

[0104] One end of the push rod 431 is movably inserted into the tube cavity of one end of the guide tube 432 corresponding to the second installation cavity 13 and is fixedly connected to the other end of the transmission ball chain 433; the telescopic end of the elastic telescopic airbag 42 is fixedly connected to the slide 435, and the slide 435 is fixedly connected to the other end of the push rod 431. The elastic telescopic airbag 42 pushes and pulls the push rod 431 through the slide 435, and the push rod 431 pushes and pulls the transmission ball chain 433 to slide along the tube cavity of the guide tube 432, and then pushes and pulls the push rod 434. The push rod 434 moves by pushing and pulling the push frame 436 to open and close the valve mechanism 24.

[0105] The guide tube 432 can be arranged in a curved manner, and the transmission ball chain 433 can slide along a curved path in the guide tube 432, thereby realizing the transmission connection between the push rod 1 431 and the push rod 2 434, making the transmission more stable and smooth. During operation, the guide tube 432 and the separator 11 do not move relative to each other, thereby avoiding the conduction between the first installation cavity 12 and the second installation cavity 13. The installation of the guide tube 432 will not damage the heat insulation performance of the separator 11, thereby ensuring the temperature stability of the first installation cavity 12 and the reliability of the temperature detection of the temperature self-adjusting mechanism 4 in the second installation cavity 13.

[0106] Specifically, the transmission ball chain 433 includes a plurality of sliding balls 4331 and a connecting rope 4332. The plurality of sliding balls 4331 are movably installed in the guide tube 432, and the sliding balls 4331 are located between the push rod 1 431 and the push rod 2 434. A through hole is provided on the sliding ball 4331, and two ends of the connecting rope 4332 are respectively fixed on the push rod 1 431 and the push rod 2 434, and the push rod 1 431 and the push rod 2 434 are respectively abutted on the corresponding sliding balls 4331. The connecting rope 4332 passes through the through holes of the plurality of sliding balls 4331 in sequence to connect the plurality of sliding balls 4331 in series on the connecting rope 4332.

[0107] In some embodiments, the ground air source device can be installed on a walking body 5 for easy mobile deployment; the walking body 5 has an outer box 51, and the installation box 1 is installed inside the outer box 51. There is a cavity between the outer box 51 and the installation box 1, and the cavity is filled with insulation material to insulate the installation box 1.

[0108] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification.

[0109] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A ground air source device for aircraft drainage that can work normally at low temperatures, characterized in that: include: An installation box (1), wherein the inner cavity of the installation box (1) is divided by a separator (11) to form a first installation cavity (12) and a second installation cavity (13); An air source mechanism (2); the air source mechanism (2) comprises a body (21) installed in the first installation cavity (12), a main air intake heating pipe (22), a secondary air intake heating pipe (23), a valve mechanism (24), and an air intake pipe (25) installed in the second installation cavity (13); one end of the air intake pipe (25) is connected to the outside atmosphere, and the other end passes through the separator (11) and connects the main air intake heating pipe (22) and the secondary air intake heating pipe (23); the valve mechanism (24) is installed on the secondary air intake heating pipe (23) to open and close the secondary air intake heating pipe (23); A heating part (3); the heating part (3) is arranged in the first installation cavity (12) and is connected to the main air intake heating pipe (22) and the auxiliary air intake heating pipe (23) to preheat the inhaled cold air; A temperature self-regulating mechanism (4), the temperature self-regulating mechanism (4) being arranged in the second installation cavity (13) and connected to the air intake pipe (25) so as to detect the temperature of the air intake pipe (25); the temperature self-regulating mechanism (4) is transmission-connected to the valve mechanism (24) so ​​as to open the valve mechanism (24) when the temperature of the air intake pipe (25) drops to a preset temperature, thereby increasing the preheating power of the inhaled cold air.

2. According to claim 1, a ground air source device for aircraft drainage that can work normally at low temperatures is characterized in that: The heating unit (3) comprises an air intake heating unit (31) and a body heating unit (32); The air intake heating unit (31) is connected to the main air intake heating pipe (22) and the auxiliary air intake heating pipe (23) to preheat the inhaled cold air; and the fuselage heating unit (32) is connected to the fuselage (21) to heat the fuselage (21).

3. According to claim 2, a ground air source device for aircraft drainage that can work normally at low temperatures is characterized in that: The air intake heating unit (31) comprises a heating body (311) and a heating seat (312); the fuselage heating unit (32) comprises a heating device (321), a circulating heating pipe assembly (322) and a heat transfer chain assembly (323); The circulating heating pipe assembly (322) is installed on the heating device (321) to form a circulating heat supply loop; one end of the heat transfer chain assembly (323) is connected to the circulating heating pipe assembly (322) to absorb heat, and the other end of the heat transfer chain assembly (323) is detachably wound around the fuselage (21) to heat and increase the temperature of the fuselage (21); A heating chamber (221) is formed on the main air intake heating pipe (22); the heating body (311) is installed in the heating chamber (221) and is electrically connected to the heating device (321) to heat the inhaled cold air flowing through the main air intake heating pipe (22); the circulating heating pipe assembly (322) passes through the heating seat (312) to circulate heat; the heating seat (312) is installed on the auxiliary air intake heating pipe (23) to heat the inhaled cold air diverted to the auxiliary air intake heating pipe (23).

4. According to claim 3, a ground air source device for aircraft drainage that can work normally at low temperatures is characterized in that: The valve mechanism (24) comprises a first valve body (241), a second valve body (242), a valve core (243) and an elastic connecting portion (244); one end of the first valve body (241) is connected to and communicated with the heating chamber (221), and the other end of the first valve body (241) is sealed and communicated with one end of the second valve body (242) via the elastic connecting portion (244); the other end of the second valve body (242) is slidably nested and sealedly connected with the auxiliary air intake heating pipe (23); The temperature self-regulating mechanism (4) is transmission-connected to the second valve body (242) to drive the second valve body (242) to slide axially along the auxiliary air intake heating pipe (23); one end of the valve core (243) is fixed inside the second valve body (242), and the other end of the valve core (243) is adapted to be movably inserted into the valve cavity of the first valve body (241) to open and close the valve cavity channel of the first valve body (241) under the sliding drive of the second valve body (242).

5. According to claim 3, a ground air source device for aircraft drainage that can work normally at low temperatures is characterized in that: The heat transfer chain assembly (323) comprises a heat transfer seat (3231), a heat transfer wire (3232) and a plurality of heat transfer blocks (3233); The heat transfer seat (3231) is installed on the circulating heating tube assembly (322) for heat exchange; the heat transfer wire (3232) is wound on the body (21) and both ends of the heat transfer wire (3232) are connected to the heat transfer seat (3231) to transfer the heat of the heat transfer seat (3231) to the body (21); a plurality of heat transfer blocks (3233) can be slidably connected to the heat transfer wire (3232) along the length direction of the heat transfer wire (3232) and attached to the body (21) to form a multi-point distributed heat transfer structure for transferring heat to fixed positions on the body (21).

6. The ground air source device for aircraft drainage that can work normally at low temperatures according to claim 5, characterized in that: The heat transfer chain assembly (323) further comprises a wire clamp (3234); the wire clamp (3234) is installed on the heat transfer wire (3232) to fix the two ends of the heat transfer wire (3232).

7. According to claim 5, a ground air source device for aircraft drainage that can work normally at low temperatures is characterized in that: The heat transfer block (3233) comprises a first clamping block (3233A) and a second clamping block (2323B); the first clamping block (3233A) and the second clamping block (2323B) are symmetrically arranged on both sides of the heat transfer wire (3232) and fastened by fasteners (3235) to be adapted to be clamped on the heat transfer wire (3232); the side of the first clamping block (3233A) away from the second clamping block (2323B) is attached to the fuselage (21).

8. The ground air source device for aircraft drainage that can work normally at low temperatures according to claim 7, characterized in that: An anti-slip strip (3233D) is installed on the side of the first clamping block (3233A) away from the second clamping block (2323B).

9. The ground air source device for aircraft drainage that can work normally at low temperatures according to claim 1, characterized in that: The temperature self-regulating mechanism (4) comprises a heat exchange tube (41), an elastic and telescopic airbag (42) and a transmission component (43); The heat exchange tube (41) is spirally wound on the air intake tube (25) to exchange heat with the air intake tube (25); The fixed end of the elastic telescopic airbag (42) is connected to the heat exchange tube (41) and is sealed and connected to the inner cavity of the heat exchange tube (41) so as to be telescopic when the internal gas temperature rises or falls; one end of the transmission component (43) is transmission-connected to the valve mechanism (24); the telescopic end of the elastic telescopic airbag (42) is transmission-connected to the other end of the transmission component (43) so as to telescope and drive the transmission component (43) to move and thereby control the opening and closing of the valve mechanism (24).

10. A ground air source device for aircraft drainage that can work normally at low temperatures according to claim 9, characterized in that: The transmission assembly (43) comprises a push rod 1 (431), a guide tube (432), a transmission ball chain (433) and a push rod 2 (434); The guide tube (432) passes through and is sealed and fixed on the separator (11), and one end of the guide tube (432) is located in the second installation cavity (13), and the other end of the guide tube (432) is located in the first installation cavity (12); the transmission ball chain (433) is sealed and slidably inserted into the cavity of the guide tube (432); One end of the push rod 2 (434) is transmission-connected to the valve mechanism (24), and the other end of the push rod 2 (434) is movably inserted into a tube cavity at one end of the guide tube (432) corresponding to the first installation cavity (12) and fixedly connected to one end of the transmission ball chain (433); One end of the push rod 1 (431) is movably inserted into one end of the tube cavity of the guide tube (432) corresponding to the second installation cavity (13) and is fixedly connected to the other end of the transmission ball chain (433); the telescopic end of the elastic telescopic airbag (42) is transmission-connected to the other end of the push rod 1 (431), so that the transmission ball chain (433) can be pushed and pulled along the tube cavity of the guide tube (432) by the push rod 1 (431) to slide, and then push and pull the push rod 2 (434) to move and open and close the valve mechanism (24).

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