阅读说明：本技术 一种作动式导流超音速进气道堵盖和飞行器 (Actuating type flow guide supersonic air inlet channel plug cover and aircraft ) 是由 赵政衡 安平 王天绥 刘涛 卢杰 任志文 赵胜海 王春利 陈尊敬 万丽颖 高骏冬 于 2019-12-05 设计创作，主要内容包括：本发明实施例公开了一种作动式导流超音速进气道堵盖和飞行器,进气道堵盖包括：堵盖本体、转动轴、收缩作动筒、发动机进气口和进气阶梯密封口,进气道的排气口和排气阶梯密封口；转轴设置在堵盖本体的一端,收缩作动筒的一端连接在排气口壁面上,另一端连接在堵盖本体的中部；收缩作动筒,被配置为通过收缩,带动堵盖本体沿转动轴进行转动,从进气阶梯密封口的位置转动到排气阶梯密封口的位置。本发明实施例解决了当前常规机械式进气道堵盖具有安装不便,阻力大,堵盖抛放控制难度高的问题。(The embodiment of the invention discloses an actuating type diversion supersonic inlet blocking cover and an aircraft, wherein the inlet blocking cover comprises: the plug cover comprises a plug cover body, a rotating shaft, a contraction actuating cylinder, an engine air inlet, an air inlet stepped sealing port, an air outlet of an air inlet channel and an air outlet stepped sealing port; the rotating shaft is arranged at one end of the plugging cover body, one end of the contraction actuating cylinder is connected to the wall surface of the exhaust port, and the other end of the contraction actuating cylinder is connected to the middle part of the plugging cover body; and the contraction actuator cylinder is configured to contract to drive the plugging cover body to rotate along the rotating shaft and rotate from the position of the air inlet stepped sealing port to the position of the air outlet stepped sealing port. The embodiment of the invention solves the problems of inconvenient installation, large resistance and high difficulty in throwing and placing control of the conventional mechanical air inlet channel plug cover.)

1. An actuating type guide supersonic inlet blocking cover is characterized by comprising: the plug cover comprises a plug cover body, a rotating shaft, a contraction actuating cylinder, an engine air inlet, an air inlet stepped sealing port, an air outlet of an air inlet channel and an air outlet stepped sealing port;

the rotating shaft is arranged at one end of the plugging cover body, one end of the contraction actuating cylinder is connected to the wall surface of the exhaust port, and the other end of the contraction actuating cylinder is connected to the middle of the plugging cover body;

the contraction actuator cylinder is configured to be contracted to drive the plug cover body to rotate along the rotating shaft, and the plug cover body rotates from the position of the air inlet stepped sealing opening to the position of the air outlet stepped sealing opening.

2. The actuated flow directing supersonic inlet closure of claim 1, wherein said inlet, inner channel, said inlet and said outlet form a Y-shaped flow path structure.

3. The actuated inducer supersonic inlet closure of claim 2,

the air inlet channel blocking cover is arranged at a shunting position in the Y-shaped flow channel structure of the air inlet channel.

4. The actuated inducer supersonic inlet closure of claim 2,

the inlet duct blanking cover is configured to be in a boosting stage, the blanking cover body is located at the position of the air inlet stepped sealing opening, and air flow passing through the compression surface, the inlet duct lip and the inlet duct inner channel is discharged to the outside of the aircraft through the air outlet.

5. The actuated inducer supersonic inlet closure of claim 4,

the air inlet blocking cover is configured to be arranged behind the engine stage change, the blocking cover body is located at the position of an exhaust step sealing opening, and air flow passing through a compression surface, an air inlet lip and an air inlet inner channel is supplied for the engine through an engine air inlet.

6. The actuated inducer supersonic inlet closure of any of claims 1 to 5, wherein said retraction ram is a powder ram configured to be energized after an engine revolution such that said powder ram retracts.

7. The cap of any one of claims 1 to 5, wherein one end of the retracting actuator is hinged to the wall of the exhaust port, and the cap body is driven to rotate by the hinge during the retracting process of the retracting actuator.

8. An aircraft, characterized in that it comprises: the supersonic flow-guiding closure of any one of claims 1 to 6, and an engine comprising a fuel tank and a combustion chamber in communication with the closure via an engine inlet.

Technical Field

The application relates to the technical field of aerospace power, in particular to an actuating type diversion supersonic inlet blocking cover and an aircraft.

Background

The supersonic aircraft with the air-breathing combined power device has an air inlet system with a double-plug cover design scheme of an inlet and an outlet. An outlet plug cover is required to be designed at the outlet of the air inlet channel to bear the pressure of fuel gas so as to ensure the normal work of the rocket booster. Meanwhile, an inlet blocking cover is required to be arranged at the head of the air inlet channel, so that the phenomenon that the inlet of the air inlet channel is open, the resistance is large, and even surging occurs is prevented.

Because the outer compression surface of the supersonic inlet is too long, the lip of the inlet is sharp, and the front blanking cover is difficult to install. The front blocking cover directly stopping incoming flow has large resistance and high throwing control difficulty, and the phenomenon that the blocking cover is thrown to a projectile body or even a control surface is easy to happen, and even the flight safety is influenced. In addition, two sets of actuating and controlling systems are needed by adopting the mode of blocking the inlet and the outlet, so that the requirements of power supply and control are improved.

Therefore, a novel supersonic air inlet duct actuated flow guide mechanical plug cover is needed, and has the advantages of simple structure, convenience in installation, small flight resistance in a boosting stage and low difficulty in throwing and placing control of the transition stage plug cover.

Disclosure of Invention

In order to solve the technical problems, the embodiment of the invention provides an actuating type flow guide supersonic air inlet blocking cover and an aircraft, and aims to solve the problems that the conventional mechanical air inlet blocking cover is inconvenient to install, large in resistance and high in blocking cover throwing control difficulty.

The embodiment of the invention provides an actuating type diversion supersonic inlet blocking cover, which comprises: the plug cover comprises a plug cover body, a rotating shaft, a contraction actuating cylinder, an engine air inlet, an air inlet stepped sealing port, an air outlet of an air inlet channel and an air outlet stepped sealing port;

the rotating shaft is arranged at one end of the plugging cover body, one end of the contraction actuating cylinder is connected to the wall surface of the exhaust port, and the other end of the contraction actuating cylinder is connected to the middle of the plugging cover body;

the contraction actuator cylinder is configured to be contracted to drive the plug cover body to rotate along the rotating shaft, and the plug cover body rotates from the position of the air inlet stepped sealing opening to the position of the air outlet stepped sealing opening.

Optionally, in the actuated diversion supersonic inlet blocking cover as described above, the inner channel, the air inlet and the air outlet form a Y-shaped flow channel structure in the inlet.

Optionally, in the actuated diversion supersonic inlet cap as described above,

the air inlet channel blocking cover is arranged at a shunting position in the Y-shaped flow channel structure of the air inlet channel.

Optionally, in the actuated diversion supersonic inlet cap as described above,

the inlet duct blanking cover is configured to be in a boosting stage, the blanking cover body is located at the position of the air inlet stepped sealing opening, and air flow passing through the compression surface, the inlet duct lip and the inlet duct inner channel is discharged to the outside of the aircraft through the air outlet.

Optionally, in the actuated diversion supersonic inlet cap as described above,

the air inlet blocking cover is configured to be arranged behind the engine stage change, the blocking cover body is located at the position of an exhaust step sealing opening, and air flow passing through a compression surface, an air inlet lip and an air inlet inner channel is supplied for the engine through an engine air inlet.

Optionally, in the actuated guided supersonic inlet closure as described above, the retraction actuator is a powder actuator configured to be energized after an engine revolution such that the powder actuator retracts.

Optionally, in the actuated flow-guiding supersonic inlet blocking cover, one end of the retracting actuator cylinder is connected to the wall surface of the exhaust port through a hinge, and the blocking cover body can be driven to rotate through the hinge during the retracting process of the retracting actuator cylinder.

An embodiment of the present invention further provides an aircraft, including: the actuating type flow guide supersonic speed blocking device comprises an oil tank and a combustion chamber communicated with the blocking device through an engine air inlet.

The embodiment of the invention provides an actuating type diversion supersonic inlet blocking cover and an aircraft, wherein the inlet blocking cover comprises: the plug cover comprises a plug cover body, a rotating shaft, a contraction actuating cylinder, an engine air inlet, an air inlet stepped sealing port, an air outlet of an air inlet channel and an air outlet stepped sealing port; the rotating shaft is arranged at one end of the plugging cover body, one end of the contraction actuating cylinder is connected to the wall surface of the exhaust port, and the other end of the contraction actuating cylinder is connected to the middle part of the plugging cover body; and the contraction actuator cylinder is configured to contract to drive the plugging cover body to rotate along the rotating shaft and rotate from the position of the air inlet stepped sealing port to the position of the air outlet stepped sealing port. The air inlet blocking cover provided by the embodiment of the invention has the advantages of simple structure, convenience in installation, small flight resistance in a boosting stage, low difficulty in throwing and releasing the transition blocking cover and the like.

Drawings

The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.

Fig. 1 is a schematic structural diagram of an actuated flow guiding supersonic inlet blocking cover according to an embodiment of the present invention;

FIG. 2 is a schematic structural view of a cap body of the actuated supersonic flow guiding inlet cap according to an embodiment of the present invention;

FIG. 3 is a schematic diagram of a retractable actuator cylinder in the actuated supersonic flow guide inlet blanking cap according to an embodiment of the present invention;

FIG. 4 is a schematic structural view of a Y-shaped flow passage of an aircraft;

FIGS. 5 and 6 are schematic views illustrating the operation of the actuated supersonic diversion inlet cap in the boost stage according to the embodiment of the present invention;

fig. 7 is a schematic view of the working process of the actuated diversion supersonic inlet blocking cover provided in the embodiment of the present invention after the transition.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.

The technical solution provided by the present invention is explained in detail by several specific examples below. The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.

Fig. 1 is a schematic structural view of an actuated flow-guiding supersonic inlet flow cap according to an embodiment of the present invention, fig. 2 is a schematic structural view of a cap body in the actuated flow-guiding supersonic inlet flow cap according to an embodiment of the present invention, and fig. 3 is a schematic structural view of a retracting actuator cylinder in the actuated flow-guiding supersonic inlet flow cap according to an embodiment of the present invention.

The actuated guiding supersonic inlet cap provided in this embodiment may include: the engine comprises a blanking cover body 5, a rotating shaft 6, a contraction actuating cylinder 4, an engine air inlet 2, an air inlet stepped sealing port 1, an air outlet 7 of an air inlet channel and an air outlet stepped sealing port 3.

The mechanical plug cover in the embodiment of the invention is specifically arranged at the position of the air inlet 2 at the rear part of the air inlet channel. Wherein, the moving shaft 6 is arranged at one end of the blanking cover body 1, one end of the contraction actuating cylinder 4 is connected to the wall surface of the exhaust port, and the other end is connected to the middle part of the blanking cover body 5; in practice, one end of the retraction actuator 4 may be hinged to the wall of the exhaust port.

The retracting cylinder 4 is configured to be retracted to rotate the plug body 5 along the rotating shaft 6 from the position of the intake step seal port 1 to the position of the exhaust step seal port 3.

In the intake passage of the embodiment of the present invention, the inner passage, the intake port 2 and the exhaust port 7 form a Y-shaped flow passage structure. Fig. 4 is a schematic structural diagram of a Y-shaped flow passage of an aircraft. Referring to fig. 1, the air inlet blocking cover is specifically disposed at a diversion position in a Y-shaped flow channel structure of the air inlet. The air inlet blocking cover needs to be correspondingly matched with an air outlet 7.

The air inlet blocking cover provided by the embodiment of the invention is configured in such a way that in the boosting stage, the blocking cover body 5 is positioned at the position of the air inlet stepped sealing opening 1, and the air flow passing through the compression surface, the air inlet lip and the air inlet inner channel is discharged to the outside of an aircraft through the air outlet 7.

The air inlet blocking cover provided by the embodiment of the invention is also configured in such a way that after the engine is in a stage change state, the blocking cover body 5 is positioned at the position 3 of the exhaust stepped sealing opening, and air flow passing through the compression surface, the air inlet lip and the air inlet channel is supplied to the engine through the air inlet 2 of the engine.

It can be seen that the plug body 5 can simultaneously play a role in sealing and guiding when respectively matching with the air inlet stepped sealing port 1 and the air outlet stepped sealing port 3.

The retraction ram 4 in the present embodiment is, for example, a powder ram and is configured to be energized after an engine revolution so that the powder ram is retracted.

The actuating type diversion supersonic inlet blocking cover disclosed by the embodiment of the invention is designed relative to an inlet and an outlet of an inlet system, and has the advantages of simple structure and convenience in installation; in the boosting stage of the engine, the blocking cover is matched with the air inlet of the engine, the air outlet is opened, the air inlet channel is in a through-flow state, the resistance of the aircraft is reduced, and the surge phenomenon caused by opening of the air inlet channel is effectively prevented; when the engine changes the stage, under the effect of actuator cylinder, the blanking cover revolves the axis of rotation and rotates, and blanking cover and gas vent cooperation, engine inlet are opened, and the intake duct provides compressed air for the engine, and this kind of working method can effectively prevent the phenomenon that intake duct surge is led to the instantaneous high pressure of intake duct export gas when changing the stage, has promoted intake duct change reliability, has reduced the blanking cover and has thrown the control degree of difficulty.

Fig. 5 and fig. 6 are schematic diagrams illustrating a working process of the actuating type diversion supersonic inlet blocking cover provided by the embodiment of the invention in a boosting stage. As shown in fig. 5 and 6, before the transition, the cap body 5 of the actuating type diversion supersonic inlet cap is matched with the stepped sealing port 1 at the inlet 2 of the engine, and the air flow passing through the compression surface 11, the inlet lip 12 and the inlet inner channel 13 is discharged to the outside of the projectile body through the exhaust port 7.

Fig. 7 is a schematic view illustrating a working process of the actuated supersonic flow guiding inlet blocking cover according to an embodiment of the present invention after the transition. As shown in fig. 5 and 7, after the engine step command is issued, the rocket booster 10 is disengaged. Meanwhile, the contraction actuator cylinder 4 contracts to drive the blanking cover body 5 to rotate around the rotating shaft 6 until the blanking cover body 5 is matched with the exhaust port stepped sealing port 3, and air flow passing through the compression surface 11, the air inlet lip 12 and the air inlet channel 13 is guided to the engine combustion chamber 9. The airflow is mixed with fuel ejected by the ejection opening 8 for combustion, and the engine 14 provides thrust for the supersonic aircraft.

The actuating type flow guide supersonic air inlet blocking cover in the embodiment of the invention is a mechanical blocking cover, and has the advantages of simple structure, convenience in installation, small flight resistance in a boosting stage, low difficulty in throwing and placing control of a transition blocking cover and the like.

Based on the actuated diversion supersonic inlet blocking cover provided by the embodiment of the invention, the embodiment of the invention also provides an aircraft, which comprises: the actuating type flow guide supersonic speed blocking device in any one of the embodiments and the engine comprise an oil tank and a combustion chamber communicated with the blocking device through an air inlet of the engine. The position relationship of the mechanical blanking cap in the aircraft, the fuel tank, the intake duct and the combustion chamber in the engine, and the compression surface 11, the intake duct lip 12, the passage 13 in the intake duct and the exhaust port 7 of the aircraft is shown with reference to fig. 6 and 7.

Although the embodiments of the present invention have been described above, the present invention is not limited to the embodiments described above. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.