Air inlet distortion suppression system and method for ski-jump process of shipboard aircraft

Abstract

The invention provides an air inlet distortion suppression system and method for the ski-jump process of a shipboard aircraft, and belongs to the technical field of aero-engines, the air inlet distortion suppression system comprises jet flow injection openings formed in decks on the two sides of the initial position of the shipboard aircraft, and air jet flows flowing out of the jet flow injection openings point to the positions below auxiliary air inlet valves of the shipboard aircraft; the high-pressure gas tank is arranged in the deck cabin; the connecting pipeline is used for connecting the jet flow jet orifice and the high-pressure gas tank, and a control valve is arranged on the connecting pipeline; in the ski-jump take-off process of the shipboard aircraft, jet flow pointing to the lower portion of the auxiliary air inlet valve is jetted out through the jet flow jetting opening, and the jet flow can restrain aircraft belly position backflow tail gas induced by a large-scale backflow area of the aircraft belly position of the shipboard aircraft. Therefore, engine air inlet temperature distortion caused by the fact that high-temperature tail gas entrained by a flow baffle on the rear side of the shipboard aircraft flows back and then is sucked into the engine is reduced.

Description

Technical Field

[0001] The present application belongs to the field of aero-engine technology, and in particular relates to an intake distortion suppression system and method for a carrier-based aircraft during a ski-jump process. Background Art

[0002] A carrier-based aircraft is an aircraft that takes off from a mobile ship platform. In combat, whether a carrier-based aircraft can take off quickly and reliably is an important technical condition to ensure its combat effectiveness. Unlike land-based takeoffs, the attached decks and baffles of the mobile ship platform make the aerodynamic environment of the carrier-based aircraft complicated, especially in the case of ski-jumps, when the engine is in the afterburner state, the engine exhaust is blocked by the baffle, and the high-temperature exhaust gas is easily sucked into the engine after reflux, causing engine intake distortion, weakening the engine's stability margin, and adversely affecting the safety of the carrier-based aircraft. Therefore, it is very necessary to suppress the intake distortion of the carrier-based aircraft during the ski-jump process, which can provide support for the safe operation of the carrier-based aircraft.

[0003] However, although there are some solutions for suppressing intake distortion in the prior art, these solutions are all aimed at the flight process or ground test of aircraft engines. Currently, there is no solution for the unsteady intake distortion caused by the ski jump of carrier-based aircraft. Summary of the invention

[0004] The purpose of the present application is to provide an intake distortion suppression system and method for a carrier aircraft during a ski jump, so as to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: an intake distortion suppression system for a carrier aircraft during a ski jump, comprising:

[0006] Jet injection ports are arranged on the decks on both sides of the initial position of the carrier aircraft, and the air jets flowing out of the jet injection ports are directed to the lower side of the auxiliary air intake valve of the carrier aircraft;

[0007] High-pressure gas tanks located in deck tanks; and

[0008] A connecting pipeline connecting the jet injection port and the high-pressure gas tank, wherein a control valve is provided on the connecting pipeline;

[0009] During the ski-jump takeoff of the carrier aircraft, a jet airflow directed to the bottom of the auxiliary air intake valve is ejected through the jet injection port, and the jet airflow can suppress the recirculation exhaust gas at the belly position induced by the large-scale recirculation zone at the belly position of the carrier aircraft, thereby reducing the engine intake temperature distortion caused by the recirculation of high-temperature exhaust gas induced by the baffle at the rear side of the carrier aircraft and then being sucked into the engine.

[0010] In a preferred embodiment of the present application, the distance between the jet injection port and the baffle is set to 2.5m to 5m, and the angle between the axis of the jet injection port and the flight trajectory is 15° to 60°.

[0011] In a preferred embodiment of the present application, the mass flow rate of the gas ejected from the jet injection port is 1 Kg / s to 3.5 Kg / s, the speed is 15 m / s to 45 m / s, and the jet injection duration is 0.1 s to 2 s.

[0012] In a preferred embodiment of the present application, it also includes an electric cover, which shields the jet injection port. When a carrier-based aircraft takes off by ski jump, the electric cover opens to expose the jet injection port. When no carrier-based aircraft takes off by ski jump, the electric cover closes to hide the jet injection port.

[0013] On the other hand, the technical solution provided by the present application is: a method for suppressing intake distortion using any of the above-described intake distortion suppression systems for a carrier aircraft ski-jump process, comprising:

[0014] Before the carrier aircraft takes off by ski jump, a predetermined pulse frequency is used to control the jet nozzle to eject airflow;

[0015] When the carrier aircraft starts, the pulse jet of the jet nozzle is controlled to be changed into continuous jet, and the jet direction of the jet nozzle is always directed to the bottom of the auxiliary air intake valve of the carrier aircraft during the ski-jump takeoff of the carrier aircraft, so that the recirculated exhaust gas at the belly position induced by the large-scale recirculation area at the belly position of the carrier aircraft is suppressed by the jet airflow, and the high-temperature exhaust gas flowing into the auxiliary air intake valve is eliminated;

[0016] The mass flow rate of the jet gas flowing from the high-pressure gas tank to the jet injection port is adjusted by a control valve, so that the high-temperature reflux of the carrier-based aircraft during the ski-jump process is always suppressed.

[0017] In a preferred embodiment of the present application, the predetermined frequency is 10 Hz to 50 Hz.

[0018] The intake distortion control system and method for the ski-jump process of carrier-based aircraft in the present application adopts jet injection of fresh air, which can, on the one hand, suppress the reflux of high-temperature exhaust gas and reduce the intake distortion of the engine. The jet injected by the low-temperature jet is sucked into the engine through the auxiliary intake valve, and the gas flow entering the engine is increased. On the other hand, the flow and frequency of the pulse jet are in a modulatable state, which can save the gas source flow and reduce the power of the high-pressure air pump. The system is installed under the deck and has no effect on the flight activities of the aircraft carrier. It has high efficiency, small size and simple control. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0020] Figure 1The diagram is a schematic diagram of the layout of a carrier aircraft using the air intake distortion suppression system of the present application.

[0021] Figure 2 Schematic diagram of the intake distortion suppression system of the present application.

[0022] Figure 3 Schematic diagram of the flow field near the belly of a carrier-based aircraft when there is no intake distortion suppression system.

[0023] Figure 4 Schematic diagram of the flow field near the belly of a carrier-based aircraft when the intake distortion suppression system is in place.

[0024] Figure 5 Schematic diagram of real-time matching of jet flow control and carrier-based aircraft speed.

[0025] Reference numerals:

[0026] 1- Deck

[0027] 2- Baffle

[0028] 3-intake distortion suppression system, 31-jet injection port, 32-connecting pipeline, 33-control valve, 34-high-pressure gas tank

[0029] 4-Carrier aircraft, 41-Engine inlet, 42-Auxiliary air intake valve

[0030] 5-Reflow exhaust gas

[0031] 6-Large scale reflux area DETAILED DESCRIPTION

[0032] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0033] In order to overcome the problem that the intake distortion suppression scheme in the prior art is difficult to solve the problem of high-temperature exhaust gas reflux during the ski-jump of the carrier-based aircraft, resulting in the high-temperature exhaust gas being sucked in by the auxiliary intake valve, thereby causing the intake distortion problem of the engine during the ski-jump of the carrier-based aircraft, the present application proposes an intake distortion suppression system based on pulse jet injection control, which is used to suppress the unsteady intake distortion of the engine during the ski-jump of the carrier-based aircraft.

[0034] like Figure 1 and Figure 2As shown, the carrier aircraft 4 is located on the deck 1 of the mobile ship platform, and a baffle 2 is provided on the rear side thereof. When the carrier aircraft 4 takes off in a ski-jump manner, the baffle 2 rises, causing the carrier aircraft 4 to inhale the high-temperature exhaust gas discharged by its engine, resulting in air intake distortion. To this end, the carrier aircraft ski-jump process intake distortion suppression system provided by the present application is based on the pulse jet control technology, and the intake distortion suppression system 3 includes a jet injection port 31, a connecting pipe 32, a control valve 33 and a high-pressure gas tank 34. The jet injection port 31 is arranged on the deck 1 on both sides of the initial position of the carrier aircraft 4, and the high-pressure gas tank 34 can be arranged in the deck cabin. The jet injection port 31 is connected to the high-pressure gas tank 34 through a connecting pipe 32 and a control valve 33.

[0035] In some embodiments of the present application, the distance between the jet injection port 31 and the baffle 2 is generally set to 2.5m to 5m, and the angle between the axis of the jet injection port 31 and the flight trajectory is 15° to 60°. The mass flow rate of the gas flowing out of the jet injection port 31 is 1Kg / s to 3.5Kg / s, the speed is 15m / s to 45m / s, and the jet injection duration is 0.1s to 2s. Furthermore, the gas jet flowing out of the jet injection port 31 is directed to the lower part of the auxiliary air intake valve 42 of the carrier aircraft 4.

[0036] In some embodiments of the present application, the jet injection port 31 can be shielded by an electric cover, which can be set on the outside of the deck 1 or on the inside of the deck 1. When a carrier-based aircraft 4 takes off by ski jump, the electric cover opens to expose the jet injection port 31. When no carrier-based aircraft 4 takes off by ski jump, the electric cover closes and the jet injection port 31 is in a hidden state, thereby not affecting other functions of the deck 1.

[0037] like Figure 3 The flow field diagram near the belly of the carrier aircraft without the intake distortion suppression system is shown. When the carrier aircraft 4 is ski jumping, it is blocked by the baffle 2. The high-temperature exhaust gas of the tail nozzle of the carrier aircraft 4 flows back and is sucked into the engine, causing the engine intake temperature distortion. The intake temperature rise comes from the high-temperature gas on both sides of the engine being sucked in along the intake duct, and from the high-temperature gas under the belly being sucked in by the auxiliary intake valve 42. Among them, the proportion of the intake by the auxiliary intake valve 42 is the largest.

[0038] like Figure 4 The flow field diagram near the belly of the carrier aircraft with the intake distortion suppression system shown in the figure is as follows: Figure 5The schematic diagram of real-time matching of jet flow control and carrier aircraft speed is shown. Before the carrier aircraft 4 ski-jumps, a pulse jet with a working frequency of 10Hz to 50Hz is used. At the moment of starting the carrier aircraft 4, the pulse jet becomes a continuous jet, and the jet direction is always directed to the bottom of the auxiliary air intake valve 42 during the movement of the carrier aircraft 4, thereby suppressing the belly position reflux exhaust gas 5 induced by the large-scale reflux area 6 at the belly position, so that the air flowing into the auxiliary air intake valve 42 is "fresh" air instead of the high-temperature "exhaust gas" of the engine inlet 41. The outflow gas mass from the high-pressure gas tank 34 to the jet injection port 31 is adjusted by the control valve 33, so that the high-temperature reflux of the carrier aircraft 4 during the ski-jump process is always suppressed.

[0039] Compared with the prior art, the intake distortion control system and method for the ski-jump process of carrier-based aircraft in the present application adopts jet injection of fresh air, which can, on the one hand, suppress the reflux of high-temperature exhaust gas and reduce the intake distortion of the engine. The jet injected by the low-temperature jet is sucked into the engine through the auxiliary intake valve, and the gas flow entering the engine is increased. On the other hand, the flow and frequency of the pulse jet are in a modulatable state, which can save the gas source flow and reduce the power of the high-pressure air pump. The system is installed under the deck and has no effect on the flight activities of the aircraft carrier. It has high efficiency, small size and simple control.

[0040] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An air intake distortion suppression system for a carrier aircraft during a ski jump, characterized in that: include: Jet injection ports are arranged on the decks on both sides of the initial position of the carrier aircraft, and the air jets flowing out of the jet injection ports are directed to the lower side of the auxiliary air intake valve of the carrier aircraft; High-pressure gas tanks installed in deck tanks; as well as A connecting pipeline connecting the jet injection port and the high-pressure gas tank, wherein a control valve is provided on the connecting pipeline; During the ski-jump takeoff of the carrier aircraft, a jet airflow directed to the bottom of the auxiliary air intake valve is ejected through the jet injection port, and the jet airflow can suppress the recirculation exhaust gas at the belly position induced by the large-scale recirculation zone at the belly position of the carrier aircraft, thereby reducing the engine intake temperature distortion caused by the recirculation of high-temperature exhaust gas induced by the baffle at the rear side of the carrier aircraft and then being sucked into the engine.

2. The air intake distortion suppression system for a carrier aircraft ski jump process according to claim 1, characterized in that: The distance between the jet injection port and the baffle is set to be 2.5m-5m, and the angle between the axis of the jet injection port and the flight trajectory is 15°-60°.

3. The air intake distortion suppression system for a carrier aircraft ski jump process according to claim 2, characterized in that: The gas mass flow rate ejected from the jet injection port is 1 Kg / s to 3.5 Kg / s, the speed is 15 m / s to 45 m / s, and the jet injection duration is 0.1 s to 2 s.

4. The air intake distortion suppression system for a carrier aircraft during a ski jump according to claims 1 to 3, characterized in that: It also includes an electric cover, which is used to shield the jet injection port. When a carrier-based aircraft takes off by ski jump, the electric cover is opened to expose the jet injection port. When no carrier-based aircraft takes off by ski jump, the electric cover is closed to hide the jet injection port.

5. A method for suppressing intake distortion using the intake distortion suppression system for a carrier aircraft ski jump process according to any one of claims 1 to 4, characterized in that: include: Before the carrier aircraft takes off by ski jump, a predetermined pulse frequency is used to control the jet nozzle to eject airflow; When the carrier aircraft starts, the pulse jet of the jet nozzle is controlled to be changed into continuous jet, and the jet direction of the jet nozzle is always directed to the bottom of the auxiliary air intake valve of the carrier aircraft during the ski-jump takeoff of the carrier aircraft, so that the recirculated exhaust gas at the belly position induced by the large-scale recirculation area at the belly position of the carrier aircraft is suppressed by the jet airflow, and the high-temperature exhaust gas flowing into the auxiliary air intake valve is eliminated; The mass flow rate of the jet gas flowing from the high-pressure gas tank to the jet injection port is adjusted by a control valve, so that the high-temperature reflux of the carrier-based aircraft during the ski-jump process is always suppressed.

6. The method according to claim 5, characterized in that The predetermined frequency is 10 Hz to 50 Hz.

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