High-temperature air pre-cooling mechanism for internal and external air intake of airplane

Abstract

The invention belongs to the technical field of aircraft environment control systems, and particularly relates to an aircraft inside and outside air inlet high-temperature air pre-cooling mechanism which comprises an openable and closable stamping air inlet mechanism, an air inlet channel switching mechanism, a plate-fin heat exchanger and a controller. An inlet of the openable and closable stamping air inlet mechanism is communicated with the outside atmosphere, and an outlet is connected to a cold side inlet of the plate-fin heat exchanger; an inlet of the air inlet channel switching mechanism communicates with an aircraft air inlet channel, and an outlet of the air inlet channel switching mechanism is connected to a cold edge inlet of the plate-fin heat exchanger. The controller controls opening and closing switching of the openable and closable stamping air inlet mechanism and the air inlet channel switching mechanism according to a flight state signal, and cold edge air source switching is achieved. According to the low-detectability air inlet and air inlet channel switching system, a traditional stamping air inlet mode is replaced with a stamping air inlet and air inlet channel switching mode, and the low-detectability performance and the cruising ability of an aircraft are effectively improved.

Description

Technical Field

[0001] This application belongs to the field of aircraft environmental control system technology, and specifically relates to a high-temperature air precooling mechanism for aircraft internal and external air intake. Background Technology

[0002] The aircraft environmental control system supplies the cockpit with high-temperature, high-pressure air from the engine. The pre-cooling of the high-temperature air is generally achieved by using an external ram air intake, which requires an auxiliary ram air intake outside the aircraft's boundary layer. This method not only introduces aerodynamic drag during high Mach number flight but also has an adverse impact on the design requirements for low detectability that future aircraft are increasingly focusing on. Summary of the Invention

[0003] To address the aforementioned problems, this application provides a high-temperature air pre-cooling mechanism for aircraft internal and external air intakes, comprising:

[0004] It can open and close the ram air intake mechanism, the air intake conversion mechanism, the plate-fin heat exchanger, and the controller; the plate-fin heat exchanger is an air-to-air heat exchanger.

[0005] The inlet of the openable and closable ram air intake mechanism is connected to the outside atmosphere, and the outlet is connected to the cold side inlet of the plate-fin heat exchanger.

[0006] The inlet of the air intake conversion mechanism is connected to the aircraft air intake, and the outlet is connected to the cold side inlet of the plate-fin heat exchanger.

[0007] The controller controls the opening and closing of the ram air intake mechanism and the air intake conversion mechanism according to the flight status signal, so as to realize the conversion of the cold side air source;

[0008] The hot-side inlet of the plate-fin heat exchanger is connected to the engine, and the hot-side outlet is connected to the outlet of the next stage radiator.

[0009] Preferably, the outlets of the openable and closable ram air intake mechanism and the intake duct conversion mechanism converge at the main duct, and are opened and closed by a control mechanism:

[0010] During low-speed flight: the ram air intake mechanism is open, the intake duct conversion mechanism is closed, and the cold side air is the external ram air;

[0011] During high-speed flight: the ram air intake mechanism is closed, the intake duct conversion mechanism is opened, and the cold side air is the air inside the intake duct.

[0012] Preferably, the controller executes the following logic according to the flight phase:

[0013] Takeoff phase: Open the closable ram air intake mechanism and close the air intake conversion mechanism;

[0014] During low-speed flight: Keep the slammer intake mechanism open;

[0015] High-speed flight phase: Close the ram air intake mechanism and open the air intake conversion mechanism;

[0016] Landing preparation phase: Activate the openable and closable ram air intake mechanism and close the air intake conversion mechanism;

[0017] Landing shutdown phase: Close the openable ram air intake mechanism and open the air intake switching mechanism.

[0018] Preferably, the intake manifold switching mechanism includes a coaxially mounted rotating baffle that is switched between two positions by a motor drive:

[0019] First position: Block the intake passage, so that the main passage is only connected to the openable and closable ram air intake mechanism;

[0020] Second position: Block the openable and closable ram air intake mechanism, so that the main flow channel is only connected to the intake channel.

[0021] Preferably, the input signals of the controller include flight speed signals and landing gear retraction / extension signals, and the dividing speed between low-speed and high-speed flight is Mach 0.5.

[0022] Preferably, the openable ram air intake mechanism includes a fuselage baffle, an auxiliary air intake duct opened on the fuselage, and a motor that drives the fuselage baffle. The motor is controlled by a controller. When the main air intake duct is connected only to the main air intake duct, the fuselage baffle blocks the auxiliary air intake duct. When the main air intake duct is connected only to the openable ram air intake mechanism, the fuselage baffle opens the auxiliary air intake duct.

[0023] The advantages of this application include: compared with the traditional external auxiliary ramjet inlet, the method of using an openable and closable ramjet inlet mechanism and an inlet duct conversion mechanism can not only meet the pre-cooling requirements of high-temperature air, but also significantly reduce the reduction of the aircraft's low observability performance caused by the auxiliary opening, thus greatly improving the aircraft's survivability; in addition, since aircraft that need to perform low observability missions are in a high Mach number flight state, closing the openable and closable mechanism can reduce the aircraft's aerodynamic drag, thereby improving the aircraft's aerodynamic performance and range. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the high-temperature air precooling mechanism for the internal and external air intakes of an aircraft, according to a preferred embodiment of this application.

[0025] Figure 2 This is a schematic diagram of the components of a high-temperature air precooling mechanism for aircraft internal and external air intakes according to a preferred embodiment of this application.

[0026] Figure 3This is a schematic diagram of the physical model of the high-temperature air precooling mechanism for the internal and external air intake of an aircraft, according to a preferred embodiment of this application, showing the open state of the ram air intake mechanism.

[0027] Figure 4 This is a schematic diagram of the open state of the high-temperature air pre-cooling mechanism for the internal and external air intakes of an aircraft, according to a preferred embodiment of this application. Detailed Implementation

[0028] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0029] like Figures 1-4 As shown, a high-temperature air precooling mechanism for aircraft internal and external air intake includes:

[0030] It can open and close the stamping intake mechanism, intake duct conversion mechanism, plate-fin heat exchanger, and controller;

[0031] The inlet of the openable and closable ram air intake mechanism is connected to the outside atmosphere, and the outlet is connected to the cold side inlet of the plate-fin heat exchanger.

[0032] The inlet of the air intake conversion mechanism is connected to the aircraft air intake, and the outlet is connected to the cold side inlet of the plate-fin heat exchanger.

[0033] The controller controls the opening and closing of the ram air intake mechanism and the air intake conversion mechanism according to the flight status signal, so as to realize the conversion of the cold side air source;

[0034] The hot-side inlet of the plate-fin heat exchanger is connected to the engine, and the hot-side outlet is connected to the outlet of the next stage radiator.

[0035] In some alternative embodiments, the outlets of the openable / closable ram air intake mechanism and the intake duct conversion mechanism converge at the main duct, and are opened and closed by a control mechanism:

[0036] During low-speed flight: the ram air intake mechanism is open, the intake duct conversion mechanism is closed, and the cold side air is the external ram air;

[0037] During high-speed flight: the ram air intake mechanism is closed, the intake duct conversion mechanism is opened, and the cold side air is the air inside the intake duct.

[0038] In some alternative implementations, the controller executes the following logic according to the flight phase:

[0039] Takeoff phase: Open the slewing ram air intake mechanism and close the intake duct conversion mechanism; specifically: after the engine starts, the slewing ram air intake opens, the intake duct conversion mechanism closes, and the cold side airflow is the ram air entering through the slewing ram air intake mechanism.

[0040] During low-speed flight: Keep the ram air intake open; specifically: when the landing gear is retracted, keep the air intake of the ram air intake open according to the aircraft speed signal, and allow air to enter through the air intake of the ram air intake.

[0041] High-speed flight phase: Close the ram air intake mechanism and open the air intake switching mechanism; specifically: based on the flight speed signal, control the ram air intake mechanism to close and switch the air intake switching mechanism to the air intake state, using the air intake to provide cooling air for the pre-cooled air radiator.

[0042] Landing preparation phase: Open the ram air intake mechanism and close the air intake switching mechanism; Specifically: When the aircraft is about to land, the flight speed decreases, the ram air intake mechanism opens, the air intake switching mechanism is switched to the air intake closed state, and ram air is used to provide cooling air for the pre-cooled air radiator until the aircraft lands.

[0043] Landing Closure Phase: The ram air intake mechanism is closed, and the air intake switching mechanism is activated. Specifically: After the aircraft comes to a stop on the ground, the ram air intake mechanism closes, and the air intake switching mechanism switches to the air intake position until the aircraft reaches the parking position.

[0044] In some alternative embodiments, the intake manifold switching mechanism includes a coaxially mounted rotating baffle, as shown in Mechanism 2, which is switched between two positions by a motor drive:

[0045] First position: Block the intake passage, so that the main passage is only connected to the openable and closable ram air intake mechanism;

[0046] Second position: Block the openable and closable ram air intake mechanism, so that the main flow channel is only connected to the intake channel.

[0047] In some alternative implementations, the input signals of the controller include flight speed signals and landing gear retraction / extension signals, with a dividing speed of Mach 0.5 between low-speed and high-speed flight.

[0048] In some alternative embodiments, the openable and closable ram air intake mechanism includes a fuselage baffle, as shown in Mechanism 1, an auxiliary air intake duct opened on the fuselage, and a motor that drives the fuselage baffle, as shown in Mechanism 1. The motor is controlled by a controller. When the main flow channel is only connected to the air intake duct, the fuselage baffle blocks the auxiliary air intake duct. When the main flow channel is only connected to the openable and closable ram air intake mechanism, the fuselage baffle opens the auxiliary air intake duct.

[0049] This invention employs an electrically operated openable and closable air intake conversion mechanism to provide cold air for pre-cooling and heat dissipation of the environmental control system. In low-speed flight, the openable and closable mechanism allows air to enter from outside the aircraft. In high-speed flight, the openable and closable mechanism is closed, and the conversion mechanism connected to the aircraft's air intake is used to utilize the air inside the air intake, thereby achieving the air pre-cooling function.

[0050] The high-temperature air pre-cooling mechanism for the aircraft's internal and external air intakes consists of an openable ram air intake mechanism, an intake duct conversion mechanism, a plate-fin heat exchanger, and a controller. When the openable ram air intake mechanism is open, the inlet is connected to the outside atmosphere, and the outlet is connected to the heat exchanger inlet. The intake duct conversion mechanism's inlet is connected to the air intake duct, and its outlet is connected to the heat exchanger inlet. During low-speed flight and non-low-observable missions, the openable ram air intake mechanism is open, and the intake duct conversion mechanism closes the air intake duct passage. Rammed air flows through the channel into the cold side of the radiator, cooling the high-temperature air. During high-speed flight, the openable ram air intake mechanism is closed, and the intake duct conversion mechanism opens the passage to the air intake duct. Air from the air intake duct enters the cold side of the heat exchanger, dissipating heat from the high-temperature air.

[0051] By replacing the traditional ram air intake with a combination of ram air intake and intake duct switching, the low-observability performance and range of the aircraft are effectively improved, resolving the contradiction between the heat dissipation requirements of low-observability aircraft and the insufficient availability of heat sinks. While ensuring that the low-observability performance is not reduced during mission execution, the fluid characteristics of the aircraft's exterior and the air intake are fully considered to achieve effective switching and utilization of air heat sinks in different flight modes. This alleviates the contradiction between the surge in overall aircraft heat dissipation demands and insufficient heat sink capacity, and avoids the aerodynamic and low-observability performance degradation caused by auxiliary air intake methods.

[0052] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A high-temperature air precooling mechanism for aircraft internal and external air intakes, characterized in that, include: It can open and close the stamping intake mechanism, intake duct conversion mechanism, plate-fin heat exchanger, and controller; The inlet of the openable and closable ram air intake mechanism is connected to the outside atmosphere, and the outlet is connected to the cold side inlet of the plate-fin heat exchanger. The inlet of the air intake conversion mechanism is connected to the aircraft air intake, and the outlet is connected to the cold side inlet of the plate-fin heat exchanger. The controller controls the opening and closing of the ram air intake mechanism and the air intake conversion mechanism according to the flight status signal, so as to realize the conversion of the cold side air source; The hot-side inlet of the plate-fin heat exchanger is connected to the engine, and the hot-side outlet is connected to the outlet of the next stage radiator.

2. The high-temperature air pre-cooling mechanism for aircraft internal and external air intakes as described in claim 1, characterized in that, The outlets of the openable and closable ram air intake mechanism and the intake duct conversion mechanism converge at the main duct, and are opened and closed by a control mechanism. During low-speed flight: the ram air intake mechanism is open, the intake duct conversion mechanism is closed, and the cold side air is the external ram air; During high-speed flight: the ram air intake mechanism is closed, the intake duct conversion mechanism is opened, and the cold side air is the air inside the intake duct.

3. The high-temperature air pre-cooling mechanism for aircraft internal and external air intakes as described in claim 1, characterized in that, The controller executes the following logic according to the flight phase: Takeoff phase: Open the closable ram air intake mechanism and close the air intake conversion mechanism; During low-speed flight: Keep the slammer intake mechanism open; High-speed flight phase: Close the ram air intake mechanism and open the air intake conversion mechanism; Landing preparation phase: Activate the openable and closable ram air intake mechanism and close the air intake conversion mechanism; Landing shutdown phase: Close the openable ram air intake mechanism and open the air intake switching mechanism.

4. The high-temperature air pre-cooling mechanism for aircraft internal and external air intakes as described in claim 2, characterized in that: The intake manifold switching mechanism includes a coaxially mounted rotating baffle that is switched between two positions by a motor drive: First position: Block the intake passage, so that the main passage is only connected to the openable and closable ram air intake mechanism; Second position: Block the openable and closable ram air intake mechanism, so that the main flow channel is only connected to the intake channel.

5. The high-temperature air pre-cooling mechanism for aircraft internal and external air intakes as described in claim 1, characterized in that: The controller's input signals include flight speed signals and landing gear retraction / extension signals, with a dividing speed of Mach 0.5 between low-speed and high-speed flight.

6. The high-temperature air pre-cooling mechanism for aircraft internal and external air intakes as described in claim 4, characterized in that: The openable and closable ram air intake mechanism includes a fuselage baffle, an auxiliary air intake duct opened on the fuselage, and a motor that drives the fuselage baffle. The motor is controlled by a controller. When the main air intake duct is connected only to the main air intake duct, the fuselage baffle blocks the auxiliary air intake duct. When the main air intake duct is connected only to the openable and closable ram air intake mechanism, the fuselage baffle opens the auxiliary air intake duct.

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