CN112483256A - Automatic opening and closing device for air inlet of ramjet engine - Google Patents
Automatic opening and closing device for air inlet of ramjet engine Download PDFInfo
- Publication number
- CN112483256A CN112483256A CN202011419994.2A CN202011419994A CN112483256A CN 112483256 A CN112483256 A CN 112483256A CN 202011419994 A CN202011419994 A CN 202011419994A CN 112483256 A CN112483256 A CN 112483256A
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- China
- Prior art keywords
- ramjet
- air inlet
- fairing
- guide rail
- closing device
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Actuator (AREA)
- Control Of Throttle Valves Provided In The Intake System Or In The Exhaust System (AREA)
Abstract
The invention provides an automatic opening and closing device for an air inlet of a ramjet, which comprises a control system and an execution mechanism, wherein the execution mechanism comprises an actuating cylinder, a connecting rod, a fairing and a guide rail, the guide rail and the actuating cylinder are fixed at the air inlet of the ramjet, the fairing is composed of a plurality of petals, each petal of fairing is arranged on the guide rail, the actuating cylinder pushes each petal of fairing to move along the guide rail through the connecting rod, when the fairing moves to the front end of the guide rail, the front end of the air inlet of the ramjet is closed to form a closed cavity, and when the fairing moves to the rear end of the guide rail, the air inlet of the ramjet is completely opened; the control system provides an ignition current to the actuator cylinder. The system is simple and reliable, does not need to carry extra energy, can reduce air resistance, and achieves the purpose of increasing voyage.
Description
Technical Field
The invention belongs to a propulsion technology and relates to a ramjet engine.
Background
The ramjet engine is an air jet engine which utilizes the speed reduction of the head-on air flow entering the engine to improve the static pressure of air. It is generally composed of three parts of air inlet channel (also called diffuser), combustion chamber and propelling nozzle. The method for compressing air by the engine is that relative airflow enters an air inlet channel of the engine to be decelerated when the aircraft flies at a high speed, and kinetic energy is converted into pressure energy. When the ramjet engine works, high-speed airflow is blown to the engine, the high-speed airflow is expanded and decelerated in the air inlet channel, the air pressure and the temperature are increased and then enter the combustion chamber to be mixed with fuel oil for combustion, and high-temperature fuel gas generated by combustion is expanded and accelerated through the propelling nozzle and is discharged from the nozzle at a high speed to generate thrust.
The ramjet has simple structure, light weight, large thrust-weight ratio and low cost, but can not be started under the static condition because of no air compressor, so the ramjet is not suitable to be used as a power device of a common airplane, is often matched with other engines to be used as a combined power device, such as a ramjet and rocket engine combination, a ramjet and turbojet engine or turbofan engine combination and the like. The aircraft provided with the combined power device starts a rocket engine, a turbojet engine or a turbofan engine during take-off, and the ramjet engine is used to close the engine which is matched with the ramjet engine to work when the flying speed is enough to ensure that the ramjet engine works normally. In the landing stage, when the flying speed of the aircraft is reduced to the point that the ramjet engine can not work normally, the engine matched with the aircraft is restarted. If the ramjet is used alone as a power plant for an aircraft, the latter must be carried in the air by other aircraft and at a certain speed before it can be started and released.
Ramjet engines are classified into subsonic, supersonic and hypersonic classes according to their application ranges. The subsonic ramjet engine uses a diffusion-shaped air inlet channel and a convergence-shaped spray pipe, generally can be started to work when the speed of an aircraft is not less than 0.5Ma, and is used for subsonic aircrafts such as subsonic target planes and the like. The supersonic ramjet adopts a supersonic air inlet (the inlet of a combustion chamber is subsonic airflow) and a convergent or convergent-divergent nozzle, the maximum propelling speed of the supersonic ramjet can reach 6Ma, and the supersonic ramjet can be used for various supersonic airplanes and missiles, such as American SR-71 black bird strategic reconnaissance aircraft, Russian SA-4 air defense missiles and the like. The hypersonic ramjet combustion is carried out at supersonic speed, the flight speed can reach 5 Ma-16 Ma by using hydrocarbon fuel or liquid hydrogen fuel, and at present, the products are in the research and test stage, for example, hypersonic aircraft X-43A is researched and developed in the United states, and the highest flight speed can reach 9.7Ma after the test.
The inherent characteristics of the ramjet determine that the ramjet cannot work in the whole flight process of the aircraft, and when the speed of the aircraft does not meet the starting requirement of the ramjet, the flight performance of the aircraft is influenced to a certain extent by the air inlet at the front end of the ramjet.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides an automatic opening and closing device for an air inlet of a ramjet engine, wherein a flap type fairing is additionally arranged on the periphery of the air inlet of the ramjet engine, and the fairing is closed before the ramjet engine works, so that the air resistance of an aircraft during starting flight is reduced; when the flying speed of the aircraft meets the working condition of the ramjet, the flap type fairing retracts backwards into the air inlet channel to ensure the ramjet to work normally; after the ramjet engine finishes working, the fairing extends forwards and is closed, so that a good pneumatic appearance is guaranteed, air resistance is reduced, and the purpose of increasing the range is achieved.
The technical scheme adopted by the invention for solving the technical problems is as follows: an automatic opening and closing device for an air inlet of a ramjet engine comprises a control system and an actuating mechanism.
The actuating mechanism comprises an actuating cylinder, a connecting rod, a fairing and a guide rail, wherein the guide rail and the actuating cylinder are fixed at an air inlet of the ramjet, the fairing is composed of a plurality of petals, each petal of fairing is arranged on the guide rail, the actuating cylinder pushes each petal of fairing to move along the guide rail through the connecting rod, when the fairing moves to the front end of the guide rail, the front end of the air inlet of the ramjet is closed to form a closed cavity, and when the fairing moves to the rear end of the guide rail, the air inlet of the ramjet is completely opened; the control system provides an ignition current to the actuator cylinder.
The actuating cylinder adopts a bidirectional working fire-working actuating cylinder, and both ends of the actuating cylinder are provided with gas producing medicaments and igniters.
The cambered surface of the inner edge of the fairing is the same as the cambered surface of the outer wall of the air inlet of the ramjet engine, so that the fairing is attached to the side wall of the air inlet after being opened.
The number of the actuating cylinders is the same as the number of the segments of the fairing, and a single actuating cylinder controls the movement of the single-segment fairing.
The guide rail is made of titanium alloy, and is provided with an inverted T-shaped groove along the axial direction for mounting the fairing.
Two ends of the connecting rod are of a fork-shaped structure and are respectively connected with the gas actuating cylinder and the fairing through pin shafts, and when the actuating cylinder works, two ends of the connecting rod rotate around the fairing and the gas actuating cylinder to realize the change of the pushing force or the pulling force in the motion direction.
The invention has the beneficial effects that: the air resistance of the aircraft is reduced when the ramjet does not work so as to achieve the purpose of increasing the range, and the characteristics are as follows:
1) the actuator cylinder is adopted to realize high thrust, and the requirement of the actuator force required by opening and closing under the condition of ultra-high speed is met;
under the condition of ultra high speed, the closing of the air inlet needs to overcome great air resistance, so that a power source is required to provide great short-time acting power, the conventional power source is difficult to realize, a gas actuating cylinder is adopted to provide great acting power (more than 105N) in a short time, the quick closing of the air inlet is realized, and the time can be controlled within 1 second.
2) The system is simple and reliable, additional energy is not required to be carried, and the weight of the system is reduced;
the gas actuating cylinder is used as a power source, only an ignition power supply is required to be provided for the aircraft, other energy devices are not required to be added, and the gas actuating cylinder with the weight of 1kg can provide the thrust of about 50000N under the normal condition. And the hydraulic pressure power supply of general need carry hydraulic pressure station, and electric putter need provide extra energy memory, and these all increase the weight of aircraft by a wide margin, are unfavorable for improving the flight efficiency of aircraft.
3) The fairing, the connecting rod and the like are made of titanium alloy, so that the specific strength is high, the high-temperature performance is good, and the weight of the system is reduced;
the structural members such as the fairing are made of titanium alloy, the titanium alloy has high specific strength and good high-temperature performance, can meet the use requirement in an ultrahigh-speed pneumatic heating environment, can greatly reduce the weight of the system compared with other materials, and improves the flight efficiency.
4) The fairing adopts an equal cambered surface design, so that the aerodynamic influence caused by carrying the fairing is reduced;
the fairing adopts an equal cambered surface design with the outer surface of the ramjet, the fairing is attached to the outer surface of the ramjet as far as possible, the influence on the aerodynamic appearance of the aircraft is reduced, the flying air resistance is reduced, and the flying efficiency is improved.
Drawings
FIG. 1 is a functional block diagram of an automatic ram engine intake port opening and closing device;
fig. 2 is a schematic structural view of an automatic ram engine intake opening/closing device, in which (a) an intake opening is closed before operation of the ram engine, (b) an intake opening is opened during operation of the ram engine, (c) an intake opening is closed after operation of the ram engine, (d) a guide rail, (e) a cowling, (f) a link, and (g) a gas cylinder;
in the figure, 1 is a fairing, 2 is a distribution position of a guide rail, 3 is a distribution position of a connecting rod, and 4 is a distribution position of a gas actuating cylinder.
Detailed Description
The present invention will be further described with reference to the following drawings and examples, which include, but are not limited to, the following examples.
The automatic opening and closing device of the ramjet air inlet mainly comprises an automatic control system and an actuating mechanism according to functional division, wherein a functional block diagram is shown in figure 1, and the automatic opening and closing device mainly comprises a bidirectional working fire working actuating cylinder, a connecting rod, a fairing, a guide rail, an ignition cable and the like according to structural division, which is shown in figure 2. The relationship and action are explained in terms of function and structural composition, respectively.
From the aspect of functional composition, the invention mainly adopts the bidirectional working fire actuating cylinder to provide power required by the opening and closing of the fairing, has the characteristics of simple structure, light weight and high working reliability, does not need to carry an additional power source compared with a hydraulic or electric device, and can be started only by providing 10 milliseconds of current of 10 amperes by an aircraft. The automatic control system can also directly adopt a control system of the aircraft, and only needs to provide a starting instruction and ensure ignition current without other changes. The actuating mechanism mainly comprises an actuating cylinder, a connecting rod, a fairing and a guide rail, and has the functions that when the actuating cylinder works, a piston rod of the actuating cylinder moves along the axial direction and drives the fairing to move back and forth along the guide rail through the motion transmission of the connecting rod, so that the automatic opening and closing function of an air inlet of an engine is realized, and the time required for opening or closing the air inlet once is less than 1 second.
From the structure composition, the actuator cylinder adopts the bidirectional type, and both ends all are equipped with and produce gas medicine and igniter, can realize preceding, back two directions respectively 1 time motion, install in the ramjet outside, and its piston rod is connected with the connecting rod through the round pin axle. One end of the connecting rod is connected with the piston rod of the actuating cylinder, the other end of the connecting rod is connected with the fairing, and the piston rod can drive the fairing to move when moving. The 4 guide rails are arranged on the outer side of the ramjet and used for fixing and moving the fairing. One end of an ignition cable of the gas actuating cylinder is connected with power supply equipment on the aircraft, and the other end of the ignition cable is respectively connected with igniters at two ends of the actuating cylinder, so that independent control of ignition at two ends of the actuating cylinder of the gas actuating cylinder is realized, and the actuating cylinder is ensured to realize front and back movement as required. A single actuator controls movement of a single fairing.
The guide rail is shown in figure 2(d) and is made of titanium alloy, the weight is reduced under the condition of ensuring the structural strength, and the axial shape of the guide rail is consistent with that of a stamping engine. An inverted T-shaped groove is formed in the middle of the guide rail and used for mounting a fairing, 1 row of 4 countersunk head screw mounting holes are formed in each of the two sides of the guide rail and are mounted on the outer surface of an air inlet channel of the ramjet engine through screws, and 4 countersunk head screw mounting holes are uniformly distributed in the circumferential direction.
The fairing is in a petal type structure, is made of alloy steel, has an inner edge cambered surface consistent with the outer cambered surface of the guide rail, is provided with an inverted T-shaped bulge in the middle, is arranged in an inverted T-shaped groove on the guide rail, and has a joint connected with the connecting rod at the tail part. The reverse T-shaped projection of the fairing can slide along the guide rail, and the fairing can move back and forth on the guide rail under the action of the gas actuating cylinder, so that the function of automatically opening and closing the air inlet of the ramjet engine is realized.
The shape of the connecting rod is shown in figure 2(f), the connecting rod is of a two-end fork structure and is respectively connected with the gas actuating cylinder and the fairing through the pin shaft, when the actuating cylinder works, the pushing force or the pulling force is transmitted through the connecting rod, and two ends of the connecting rod can rotate around the fairing and the gas actuating cylinder, so that the change of the pushing force or the pulling force in the motion direction is realized.
The shape of the gas actuating cylinder is shown in figure 2(g), and the gas actuating cylinder is an initiating explosive device and is a power source of the device, gas producing drugs are arranged at two ends in the cylinder, and two ignition plugs are arranged outside the cylinder and connected with an ignition controller on an aircraft. The middle of the engine is provided with a mounting flange which is mounted on the ramjet through 4 screws. The gas actuating cylinder is provided with a piston rod which can move forwards or backwards along the axis of the gas actuating cylinder, and the head of the gas actuating cylinder is connected with the connecting rod. When the gas actuating cylinder works, the front charging ignition is started according to an aircraft instruction, the piston rod is pushed to move backwards, the fairing is driven to be opened backwards, and the air inlet of the engine is automatically opened; when the air inlet of the engine needs to be closed, the gas actuating cylinder is started to start the rear charge to ignite according to the instruction of the aircraft, the piston rod is pushed to move forwards, the fairing is driven to move forwards, and the air inlet of the engine is automatically closed.
The working modes of the invention are as follows:
in the takeoff acceleration stage of the aircraft, the air inlet of the ramjet is in a closing state of the fairing, so that the flight resistance of the aircraft is reduced, and when the flight speed of the aircraft reaches the speed required by the work of the ramjet, the actuating cylinder is ignited for 1 time to drive the fairing to move backwards, so that the air inlet is opened and locked; when the ramjet of the aircraft stops working, the actuator cylinder is ignited again, the piston rod of the actuator cylinder moves reversely, the fairing is driven to move forwards, and the air inlet is closed and locked.
Taking an aircraft as an example, a power form of combining a solid rocket booster and a ramjet engine is adopted, the solid rocket booster works in a take-off stage, an air inlet of the ramjet engine is in a closed state, when the solid rocket booster accelerates the aircraft to 0.6Ma, a control system starts an actuating cylinder, the air inlet of the ramjet engine is opened and starts to work, the solid rocket engine stops working and is separated from the aircraft, and the ramjet engine provides power and accelerates to the maximum speed of 3Ma in the flight process. When the aircraft lands, the speed is reduced, when the speed is reduced to be below 0.6Ma, the ramjet stops working, the control system starts the actuating cylinder to move reversely again, and the air inlet of the ramjet is closed, so that the purpose of improving the voyage is achieved.
Claims (6)
1. The automatic opening and closing device for the air inlet of the ramjet comprises a control system and an execution mechanism, and is characterized in that the execution mechanism comprises an actuating cylinder, a connecting rod, a fairing and a guide rail, wherein the guide rail and the actuating cylinder are fixed at the air inlet of the ramjet; the control system provides an ignition current to the actuator cylinder.
2. The automatic ram engine air intake opening and closing device of claim 1, wherein the ram is a bi-directional working actuator cylinder with gas generating charge and igniter at both ends.
3. The automatic ramjet air inlet opening and closing device according to claim 1, wherein the arc surface of the inner edge of the fairing is the same as the arc surface of the outer wall of the ramjet air inlet, so as to ensure that the fairing is attached to the side wall of the air inlet after being opened.
4. The ramjet intake automatic opening and closing device according to claim 1, wherein the number of the actuator cylinders is the same as the number of the cowl sections, and a single actuator cylinder controls the movement of the single-section cowl.
5. The automatic ramjet engine intake port opening and closing device according to claim 1, wherein the guide rail is made of titanium alloy and has an inverted T-shaped groove formed in an axial direction thereof for mounting a cowl.
6. The automatic ram engine air inlet opening and closing device as recited in claim 1, wherein the two ends of the connecting rod are fork-shaped and are connected to the gas cylinder and the cowling respectively through the pin shafts, and when the cylinder is operated, the two ends of the connecting rod rotate around the cowling and the gas cylinder to change the pushing force or the pulling force in the moving direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419994.2A CN112483256B (en) | 2020-12-06 | 2020-12-06 | Automatic opening and closing device for air inlet of ramjet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419994.2A CN112483256B (en) | 2020-12-06 | 2020-12-06 | Automatic opening and closing device for air inlet of ramjet engine |
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| Publication Number | Publication Date |
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| CN112483256A true CN112483256A (en) | 2021-03-12 |
| CN112483256B CN112483256B (en) | 2022-08-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011419994.2A Active CN112483256B (en) | 2020-12-06 | 2020-12-06 | Automatic opening and closing device for air inlet of ramjet engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114508446A (en) * | 2021-12-30 | 2022-05-17 | 北京动力机械研究所 | Stamping range-increasing missile drag reduction control method |
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| CN110466737A (en) * | 2019-08-19 | 2019-11-19 | 西安长峰机电研究所 | A kind of composite material nose fairing |
| CN111204465A (en) * | 2020-01-21 | 2020-05-29 | 大连理工大学 | Design method of pneumatic self-separation fairing of ramjet engine air inlet |
| CN111780941A (en) * | 2020-07-23 | 2020-10-16 | 北京空天技术研究所 | Aircraft force measurement test model and method |
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2020
- 2020-12-06 CN CN202011419994.2A patent/CN112483256B/en active Active
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| EP0311514A1 (en) * | 1987-10-07 | 1989-04-12 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Fixed and centrally attached fairing for a jet engine and jet engine with this equipment |
| EP1441116A1 (en) * | 2003-01-24 | 2004-07-28 | Japan Aerospace Exploration Agency | Air intake and method for breathing air using an air intake |
| CN101497372A (en) * | 2009-02-18 | 2009-08-05 | 中国科学院力学研究所 | External cowling of scramjet engine and design method thereof |
| CN101560929A (en) * | 2009-05-22 | 2009-10-21 | 中国科学院力学研究所 | Variable incidence scramjet engine outboard cowl |
| CN102642614A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Self-adaptive adjustable low-resistance fairing |
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| CN109018382A (en) * | 2018-08-07 | 2018-12-18 | 深圳市福来过科技有限公司 | A kind of aircraft engine deformation dome structure |
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| CN110466737A (en) * | 2019-08-19 | 2019-11-19 | 西安长峰机电研究所 | A kind of composite material nose fairing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114508446A (en) * | 2021-12-30 | 2022-05-17 | 北京动力机械研究所 | Stamping range-increasing missile drag reduction control method |
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| CN112483256B (en) | 2022-08-23 |
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