Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft
阅读说明：本技术 一种定几何宽速域超音速进气道及其工作方法和飞行器 (Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft ) 是由 万丽颖 肖毅 高骏冬 王天绥 卢杰 刘涛 安平 陈尊敬 赵政衡 王春利 万志明 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定几何宽速域超音速进气道及其工作方法和飞行器,包括：进气道唇罩,由进气道唇罩和外压缩段形成的内通道,设置于进气道的收缩段的放气腔和气流调节装置；其中,气流调节装置设置于放气腔的放气口位置,被配置为根据对飞行马赫数的要求,调节通过放气口的气流流量；放气腔,被配置为以气流调节装置调节后的气流流量,对进气道的来流进行放气。本发明实施例解决了现有定几何超音速进气道,存在高马赫数状态性能与低马赫数状态起动不兼容的问题。(The embodiment of the invention discloses a fixed-geometry wide-speed-range supersonic air inlet, a working method thereof and an aircraft, wherein the fixed-geometry wide-speed-range supersonic air inlet comprises the following steps: the air inlet channel lip cover is an inner channel formed by the air inlet channel lip cover and an outer compression section, and an air discharge cavity and an air flow adjusting device are arranged at the compression section of the air inlet channel; the air flow adjusting device is arranged at the air discharge port of the air discharge cavity and is configured to adjust the air flow passing through the air discharge port according to the requirement on the flight Mach number; and the air discharge cavity is configured to discharge the incoming flow of the air inlet channel by the flow of the air flow regulated by the air flow regulating device. The embodiment of the invention solves the problem that the conventional fixed-geometry supersonic inlet is incompatible in starting at a high-Mach-number state and a low-Mach-number state.)
1. A fixed geometry wide velocity range supersonic inlet, comprising: the air inlet channel lip cover, an inner channel formed by the air inlet channel lip cover and the outer compression section, an air discharging cavity arranged at the compression section of the air inlet channel and an air flow adjusting device;
the air flow adjusting device is arranged at the air discharge port of the air discharge cavity and is configured to adjust the air flow passing through the air discharge port according to the requirement on the flight Mach number;
the air discharge cavity is configured to discharge the incoming flow of the air inlet channel at the air flow rate regulated by the air flow regulating device.
2. The fixed-geometry wide-velocity-range supersonic inlet according to claim 1, wherein said flow modulation device is an electromagnetic fluid modulation device;
the electromagnetic fluid regulating device is configured to regulate the flow of gas through the relief port by regulating electromagnetic energy.
3. The fixed-geometry wide-velocity-range supersonic inlet according to claim 2, wherein said solenoid fluid adjusting means comprises a plurality of solenoid plates disposed on said bleed cavity, and a bleed slot formed through said solenoid plates;
the electromagnetic fluid adjusting device is further configured to increase or decrease the air flow speed through the air release port by adjusting the electromagnetic performance of the electromagnetic sheet, so as to adjust the air flow rate of the air release port.
4. The fixed-geometry wide-velocity-range supersonic inlet of claim 2, wherein said solenoid fluid modulation device modulates the flow rate of air through said bleed port, comprising:
the solenoid fluid regulator is further configured to increase airflow at the bleed port to increase airflow capacity of the inlet port when the aircraft is flying at a low mach number, such that the inlet port is enabled to start at the low mach number.
5. The fixed-geometry wide-velocity-range supersonic inlet of claim 4, wherein said solenoid fluid modulation device modulates the flow rate of air through said bleed port, further comprising:
the solenoid fluid regulator is further configured to reduce the airflow at the bleed port to increase the internal contraction ratio of the inlet duct when the aircraft is flying at a high mach number.
6. A fixed-geometry wide-velocity-range supersonic inlet according to any one of claims 1 to 5, wherein the working envelope corresponding to said bleed air volume is a envelope matching said flight Mach number.
7. A working method of a fixed-geometry wide-velocity-range supersonic inlet is characterized in that the working method is executed by the fixed-geometry wide-velocity-range supersonic inlet according to any one of claims 1 to 6, and the working method comprises the following steps:
according to the requirement on the flight Mach number, the airflow flow passing through the air relief port is adjusted through an airflow adjusting device;
and the air flow quantity adjusted by the air flow adjusting device is used for deflating the incoming flow of the air inlet channel through the air bleeding cavity.
8. The method of claim 7, wherein said adjusting the flow rate of gas through said bleed port comprises:
when the aircraft flies at a low Mach number, the airflow flow of the air outlet is increased to increase the airflow circulation capacity of the air inlet channel, so that the air inlet channel is started at the low Mach number;
when the aircraft flies at a high Mach number, the airflow rate of the air outlet is reduced to increase the internal contraction ratio of the air inlet channel.
9. An aircraft, characterized in that it comprises: the fixed-geometry wide-velocity-range supersonic inlet according to any one of claims 1 to 6;
the inlet duct set up in the side of aircraft, perhaps, the lower surface of aircraft and the lip cover of inlet duct form the inner channel.
Technical Field
The application relates to the technical field of aircraft air inlets, in particular to a fixed-geometry wide-speed-range supersonic air inlet, a working method thereof and an aircraft.
Background
Supersonic inlets are a very important aerodynamic component of supersonic air-breathing aircraft (e.g., missiles), and their performance has a great influence on the engine's operational capacity and performance.
The active supersonic air inlet is basically in a fixed geometric form due to the space limitation of an aircraft, the fixed geometric supersonic air inlet generally takes a missile cruise state as a design point and has a high Mach number in the missile cruise state, and in order to ensure the performance of the air inlet when incoming flow of the high Mach number flows, the contraction ratio in the air inlet cannot be too small. At the moment, the internal contraction ratio of the air inlet channel is larger than that required by self-starting of the air inlet channel under the low incoming flow Mach number, the capture flow of the air inlet channel is larger than the through-flow capacity of the air inlet channel, and the air inlet channel easy to bleed does not start. That is, a fixed geometry supersonic inlet presents the problem of incompatible performance at high mach number conditions and start-up at low mach number conditions.
Disclosure of Invention
In order to solve the technical problems, embodiments of the present invention provide a fixed-geometry wide-speed-range supersonic inlet, a working method thereof, and an aircraft, so as to solve the problem that the existing fixed-geometry supersonic inlet is incompatible in performance at a high mach number state and starting at a low mach number state.
The embodiment of the invention provides a fixed-geometry wide-speed-range supersonic air inlet, which comprises: the air inlet channel lip cover, an inner channel formed by the air inlet channel lip cover and the outer compression section, an air discharging cavity arranged at the compression section of the air inlet channel and an air flow adjusting device;
the air flow adjusting device is arranged at the air discharge port of the air discharge cavity and is configured to adjust the air flow passing through the air discharge port according to the requirement on the flight Mach number;
the air discharge cavity is configured to discharge the incoming flow of the air inlet channel at the air flow rate regulated by the air flow regulating device.
Optionally, in the fixed-geometry wide-velocity-range supersonic inlet as described above, the airflow adjusting device is an electromagnetic fluid adjusting device;
the electromagnetic fluid regulating device is configured to regulate the flow of gas through the relief port by regulating electromagnetic energy.
Optionally, in the fixed-geometry wide-velocity-range supersonic inlet as described above, the electromagnetic fluid regulating device includes a plurality of electromagnetic sheets disposed on the air bleeding cavity, and an air bleeding slit formed by the electromagnetic sheets;
the electromagnetic fluid adjusting device is further configured to increase or decrease the air flow speed through the air release port by adjusting the electromagnetic performance of the electromagnetic sheet, so as to adjust the air flow rate of the air release port.
Optionally, in the fixed-geometry wide-velocity-range supersonic inlet as described above, the electromagnetic fluid regulating device regulates an airflow passing through the relief port, and includes:
the solenoid fluid regulator is further configured to increase airflow at the bleed port to increase airflow capacity of the inlet port when the aircraft is flying at a low mach number, such that the inlet port is enabled to start at the low mach number.
Optionally, in the fixed-geometry wide-velocity-range supersonic inlet as described above, the electromagnetic fluid regulating device regulates an airflow passing through the relief port, and further includes:
the solenoid fluid regulator is further configured to reduce the airflow at the bleed port to increase the internal contraction ratio of the inlet duct when the aircraft is flying at a high mach number.
Optionally, in the fixed-geometry wide-velocity-range supersonic inlet as described above, the working envelope corresponding to the purge amount is an envelope matched with the flight mach number.
The embodiment of the invention also provides a working method of the fixed-geometry wide-speed-range supersonic inlet, which is implemented by adopting any one of the fixed-geometry wide-speed-range supersonic inlets, and comprises the following steps:
according to the requirement on the flight Mach number, the airflow flow passing through the air relief port is adjusted through an airflow adjusting device;
and the air flow quantity adjusted by the air flow adjusting device is used for deflating the incoming flow of the air inlet channel through the air bleeding cavity.
Optionally, in the method for operating a fixed-geometry wide-velocity-range supersonic inlet as described above, the adjusting of the flow rate of the gas through the relief port includes:
when the aircraft flies at a low Mach number, the airflow flow of the air outlet is increased to increase the airflow circulation capacity of the air inlet channel, so that the air inlet channel is started at the low Mach number;
when the aircraft flies at a high Mach number, the airflow rate of the air outlet is reduced to increase the internal contraction ratio of the air inlet channel.
An embodiment of the present invention further provides an aircraft, including: a fixed geometry wide velocity range supersonic inlet as claimed in any one of the preceding claims;
the inlet duct set up in the side of aircraft, perhaps, the lower surface of aircraft and the lip cover of inlet duct form the inner channel.
According to the fixed-geometry wide-speed-range supersonic air inlet, the working method thereof and the aircraft provided by the embodiment of the invention, the air outlet cavity and the electromagnetic fluid adjusting device are additionally arranged, the air outlet cavity is arranged at the contraction section of the air inlet, the electromagnetic fluid adjusting device is additionally arranged between the air inlet and the air outlet cavity, the device can adjust the air outlet amount according to the flight state, and the problem that the air inlet in a low-Mach number state is difficult to start under a high-Mach point design state of the fixed-geometry supersonic air inlet or the air inlet in a high-Mach number state is poor in performance under a low-Mach point design state can be effectively solved; the fixed-geometry supersonic air inlet provided with the air discharge cavity and the electromagnetic fluid control device skillfully utilizes the gap between the air discharge cavity and the compression surface, is provided with the electromagnetic acceleration and deceleration device, and accelerates and decelerates the air discharge flow through the electromagnetic acceleration and deceleration device so as to adjust the air discharge amount. By adopting the air inlet provided with the air discharging cavity and the electromagnetic fluid control device, the electromagnetic fluid adjusting device is additionally arranged on the compression surfaces of the air discharging cavity and the air inlet, when the aircraft is in low Mach relay, the air flow is accelerated to be discharged, the air discharge amount is increased, the through flow capacity of the air inlet channel is increased, the starting of the air inlet channel under low Mach is ensured, the relay of the aircraft is successful, when the aircraft flies at high Mach number, the reverse acceleration is provided for the bleed air flow, the bleed amount is reduced, which is equal to the increase of the contraction ratio in the air inlet channel and the increase of the performance of the air inlet channel when the aircraft flies at high Mach number, therefore, the problem that the inlet in the low-Mach state is difficult to start under the high-Mach point design state of the fixed-geometry supersonic inlet or the problem that the inlet in the high-Mach state is poor in performance under the low-Mach point design state can be effectively solved, the speed range of the fixed-geometry supersonic inlet is improved, and the fixed-geometry supersonic inlet has a good engineering application value.
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 a fixed-geometry wide-velocity-range supersonic inlet according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of a fixed geometry wide velocity range supersonic inlet provided in the embodiment of FIG. 1.
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 above background art has shown that the existing fixed-geometry supersonic inlet generally uses the missile cruise state as the design point, that is, the design is based on the high mach number state, and in practical application, the aircraft inevitably experiences low mach number relay in the flight process, so that the risk of the inlet not starting exists under the low mach number. That is to say, the existing fixed-geometry wide-speed-range supersonic inlet has the problem that the performance in a high-Mach-number state is incompatible with the starting in a low-Mach-number state.
Therefore, a new air inlet structure is proposed at present, which can realize the starting under the state of compatible performance under the high mach number and the low mach number.
The embodiment of the invention provides a fixed geometry supersonic air inlet with an air discharge cavity and an electromagnetic fluid control device and an aircraft using the same, aiming at the problems that the air inlet in a low-Mach state is difficult to start under the high-Mach point design state of the current fixed geometry supersonic air inlet or the air inlet in a high-Mach state is poor in performance under the low-Mach point design state.
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 diagram of a fixed-geometry wide-velocity-range supersonic inlet according to an embodiment of the present invention, and fig. 2 is a cross-sectional view of the fixed-geometry wide-velocity-range supersonic inlet according to the embodiment of fig. 1. Referring to fig. 1 and fig. 2, the fixed-geometry wide-velocity-range supersonic inlet provided in this embodiment may include: intake
The air flow adjusting device is arranged at the air outlet position of the
and the
The air flow regulating device in the embodiment of the invention is, for example, an electromagnetic fluid regulating device;
an electromagnetic fluid regulating device configured to regulate the flow of gas through the
Referring to fig. 1 and 2, the electromagnetic fluid regulating device includes a plurality of
and the electromagnetic fluid adjusting device is also configured to increase or decrease the air flow speed passing through the air release port by adjusting the electromagnetic performance of the
In practical applications, the implementation of the electromagnetic fluid regulating device for regulating the flow rate of the air passing through the
first, the solenoid fluid operated device is configured to increase the airflow at the
Secondly, the solenoid fluid regulator is configured to reduce the air flow at the
It should be noted that, in the embodiment of the present invention, in the process of performing deflation through the electromagnetic fluid adjusting device, the working envelope corresponding to the
As shown in fig. 1 and fig. 2, when the aircraft is in low-speed relay, the
According to the constant-geometry wide-speed-range supersonic air inlet provided by the embodiment of the invention, the air outlet cavity is arranged at the contraction section of the air inlet by adding the air outlet cavity and the electromagnetic fluid adjusting device, the electromagnetic fluid adjusting device is additionally arranged between the air inlet cavity and the air outlet cavity, the device can adjust the air outlet quantity according to the flight state, and the problem that the air inlet in a low-Mach-number state is difficult to start under a high-Mach-number point design state of the constant-geometry supersonic air inlet or the air inlet in a high-Mach-number state is poor in performance under a low-Mach-number point design state can be; the fixed-geometry supersonic air inlet provided with the air discharge cavity and the electromagnetic fluid control device skillfully utilizes the gap between the air discharge cavity and the compression surface, is provided with the electromagnetic acceleration and deceleration device, and accelerates and decelerates the air discharge flow through the electromagnetic acceleration and deceleration device so as to adjust the air discharge amount. By adopting the air inlet provided with the air discharging cavity and the electromagnetic fluid control device, the electromagnetic fluid adjusting device is additionally arranged on the compression surfaces of the air discharging cavity and the air inlet, when the aircraft is in low Mach relay, the air flow is accelerated to be discharged, the air discharge amount is increased, the through flow capacity of the air inlet channel is increased, the starting of the air inlet channel under low Mach is ensured, the relay of the aircraft is successful, when the aircraft flies at high Mach number, the reverse acceleration is provided for the bleed air flow, the bleed amount is reduced, which is equal to the increase of the contraction ratio in the air inlet channel and the increase of the performance of the air inlet channel when the aircraft flies at high Mach number, therefore, the problem that the inlet in the low-Mach state is difficult to start under the high-Mach point design state of the fixed-geometry supersonic inlet or the problem that the inlet in the high-Mach state is poor in performance under the low-Mach point design state can be effectively solved, the speed range of the fixed-geometry supersonic inlet is improved, and the fixed-geometry supersonic inlet has a good engineering application value.
Based on the fixed-geometry wide-speed-range supersonic inlet provided by the embodiment of the invention, the embodiment of the invention also provides a working method of the fixed-geometry wide-speed-range supersonic inlet, which comprises the following steps:
and 2, deflating the incoming flow of the air inlet channel through the air bleeding cavity by using the airflow adjusted by the airflow adjusting device.
In practical applications, the implementation manner of adjusting the flow rate of the air passing through the air release port by the air flow adjusting device in
first, when the aircraft flies at a low Mach number, the airflow of the air release port is increased to increase the airflow capacity of the air inlet channel, so that the air inlet channel starts at the low Mach number;
second, when the aircraft is flying at a high mach number, the airflow rate at the bleed port is reduced to increase the internal contraction ratio of the inlet duct.
Based on the fixed-geometry wide-speed-range supersonic inlet provided by the embodiment of the invention, the embodiment of the invention also provides an aircraft, which comprises: a fixed geometry wide velocity range supersonic inlet as provided in any one of the embodiments of the present invention;
in one implementation of the embodiments of the invention, the air inlet may be provided at a side of the aircraft.
In another implementation of an embodiment of the invention, the lower surface of the aircraft forms an internal channel with the lip of the inlet duct, which implementation may refer to the structure of the inlet duct shown in fig. 1 and 2.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. 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.
- 上一篇：一种医用注射器针头装配设备
- 下一篇：航空发动机风扇叶片脱落事件降载装置