CN109250073A - Hypersonic aircraft head drag reduction method based on three-electrode spark discharge thermal jet - Google Patents
Hypersonic aircraft head drag reduction method based on three-electrode spark discharge thermal jet Download PDFInfo
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- CN109250073A CN109250073A CN201811153135.6A CN201811153135A CN109250073A CN 109250073 A CN109250073 A CN 109250073A CN 201811153135 A CN201811153135 A CN 201811153135A CN 109250073 A CN109250073 A CN 109250073A
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- hypersonic aircraft
- electric discharge
- electrode spark
- hypersonic
- thermojet
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
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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
- Y02T50/10—Drag reduction
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- Aviation & Aerospace Engineering (AREA)
- Plasma Technology (AREA)
Abstract
A hypersonic speed aircraft head drag reduction method based on three-electrode spark discharge thermal jet is characterized in that a single three-electrode spark discharge thermal jet exciter is installed at the top point of the head of a hypersonic speed aircraft; in the flight process of the hypersonic aircraft, starting an exciter, and jetting high-speed gas heat jet at high speed by the exciter; under the action of the high-speed gas heat jet, the bow-shaped shock wave of the head of the hypersonic aircraft is far away from the wall surface of the head of the hypersonic aircraft, the strength of the bow-shaped shock wave is weakened, the pressure after the bow-shaped shock wave is reduced, the high-speed gas heat jet reversely flows back and is attached to the head of the hypersonic aircraft and the outer wall surface close to the head of the hypersonic aircraft under the action of high-speed free incoming flow, a backflow area is formed near a jet outlet of the exciter, the gas density in the backflow area is low, the gas pressure is small, the pressure of the head of the hypersonic aircraft and the outer wall surface close to the head of the hypersonic aircraft is reduced, and the resistance of the hypersonic.
Description
Technical field
The present invention relates to hydrodynamics to flow control field, gas discharge application field, is a kind of based on three-electrode spark
The hypersonic aircraft head drag reduction method of electric discharge thermojet.
Background technique
Hypersonic aircraft technology is the new commanding elevation of 21 century field of aerospace technology, is mankind's aerospace history
On after invention aircraft, break through sound barrier flight after third epoch-making milestone, while will also open up the mankind and entering space
New paragon.
Hypersonic aircraft has the characteristics that flying distance is remote, maneuverability is strong, penetraton probability is high, can obtain ensure into
Enter space, effective use space and the ability for controlling space, can effectively contain enemy's ground, airborne, carrier-borne early warning and weapon system
The performance of system allomeric function, effectively attack time sensitive target, shortens operational time, improves the emergentness of weapon attacking and has
Effect property.Since hypersonic aircraft is huge military and economic benefit, the world mainly make the country prosperous greatly developing it is hypersonic
Technology, and hypersonic aircraft will be developed as national strategic aim.
The key factor for determining hypersonic aircraft voyage mainly includes that engine fuel amount (dynamic) or gliding are first
The two aspects of beginning speed (unpowered), lift resistance ratio, will further increase voyage and inevitably face following two keys and ask
Topic:
1) increase of engine fuel amount or boosting vehicle are handed over to the next shift the raising of spot speed demand, this will lead to weapon system
Gross weight increases, and whole Mobile launch and survival ability reduce；
2) high lift-drag ratio design scheme is sought by aerodynamic configuration design, aircraft shape is caused to develop to " flattening ",
Aircraft interior charge space is caused to become smaller, can be small with amount of fuel, stand-alone device miniaturized pressure is big, poor universality, is developed into
A series of problems, such as this height, full aircraft manufacture, assembly process process are poor, and overall stiffness is difficult to ensure.
Therefore, the hypersonic aircraft lift resistance ratio design based on profile optimization is there are the limit, not to dynamical system or
In the case that boost motor and aircraft shape propose requirements at the higher level, explores the technical solution that resistance is effectively reduced and its realize way
Diameter is to meet one of hypersonic aircraft high lift-drag ratio technological approaches the most feasible.For cruise section, drop
Lower resistance is very significant for the gain of aircraft voyage, studies have shown that the hypersonic gliding for intercontinental range flies
The resistance that row device reduces by 10% will bring the range increment of 1000km or so；Secondly, for the Hypersonic Weapon of battle application
For pushing section, aircraft resistance, which will be effectively reduced, to push section speed requirement so that under the premise of guaranteeing to land blow speed
It is lower, bigger headroom is provided for Trajectory-terminal is motor-driven, and then effectively improve aircraft mobility.Therefore, in traditional base
In the case that profile optimization high lift-drag ratio designing technique is already close to the limit, hypersonic aircraft voyage is promoted for drag reduction
The introducing demand of new technology is very clear and urgent.
Summary of the invention
In order to overcome the shortcomings of tradition based on profile optimization high lift-drag ratio designing technique, the present invention provides a kind of based on three electricity
The hypersonic aircraft head drag reduction method of pole spark discharge thermojet, the present invention provide a kind of knot for hypersonic aircraft
Structure is simple, small light active Flow Control drag reduction technology, realizes hypersonic aircraft drag reduction and increases journey.
To realize the above-mentioned technical purpose, the technical scheme is that
A kind of hypersonic aircraft head drag reduction method based on three-electrode spark electric discharge thermojet, flies hypersonic
The cephalad apex position of row device is installed by single three-electrode spark heat discharge jet-flow excitor；In hypersonic aircraft flight course
In, three-electrode spark heat discharge jet-flow excitor is opened, generates and puts in the cavity of three-electrode spark heat discharge jet-flow excitor
Electricity generates high-speed gas thermojet so that when gases are heated, they expand and high speed ejection in driver cavity；In high-speed gas thermojet
Under the action of, the bowshock on hypersonic aircraft head far from hypersonic aircraft head wall surface, bowshock it is strong
Degree weakens, so that the pressure reduction after bowshock, and high-speed gas thermojet is reversed under the action of high speed free incoming flow
Reflow attachment is on the appearance wall surface on hypersonic aircraft head and close hypersonic aircraft head, in three electrodes fire
The jet exit of flower heat discharge jet-flow excitor is formed about recirculating zone (region that recirculating zone i.e. air-flow rotates), recirculating zone
Interior gas density is lower, air pressure is smaller, so that hypersonic aircraft head and close to hypersonic aircraft head
The pressure reduction of appearance wall surface, to reduce hypersonic aircraft resistance.
Further, the cavity volume of three-electrode spark heat discharge jet-flow excitor is less than 1500 cubic millimeters, cavity body
The excessive heating effect that will lead to electric discharge generation of product is unobvious, so that the gas energy ejected in cavity is lower, control ability
It is weaker.Three-electrode spark heat discharge jet-flow excitor impulse discharge gross energy when electric discharge gross energy is excessive, disappears less than 3.5 joules
The energy of consumption will be more than income brought by drag reduction.The frequency of three-electrode spark heat discharge jet-flow excitor electric discharge is greater than 2000 hertz
Hereby, too small will lead to of frequency can not generate continuous control effect；The jet exit of three-electrode spark heat discharge jet-flow excitor
The mass flow that diameter control will lead to thermojet at 1 to 2 millimeter, when diameter is too small is too small, and thermojet can produce when diameter is excessive
Raw biggish reaction force, has an adverse effect to drag reduction.
Further, the head of the jet exit of the three-electrode spark heat discharge jet-flow excitor and hypersonic aircraft
Portion's wall surface flushes.In this way under the premise of not changing hypersonic aircraft aerodynamic configuration, realizing reduces hypersonic aircraft
The purpose of resistance.
In the present invention the three-electrode spark electric discharge synthesizing jet-flow excitor by high-voltage pulse power source, DC power supply, put
Capacitor, driver ignitor, driver anode, driver cathode, driver cavity, jet exit composition, when work, are straight
Galvanic electricity source is discharge capacity charging, and high-voltage pulse power source spark discharge in driver cavity generates plasma, so that excitation
Breakdown voltage reduces between device anode and cathode, so that discharge capacity electric discharge is triggered, so that gas expansion is simultaneously in driver cavity
From jet exit high speed ejection, high-speed gas thermojet is formed；Then since high-speed gas thermojet sprays and driver cavity
Cooling so that driver cavity inner temperature and pressure decline, extraneous gas refills driver cavity, does for next circulation
Prepare.
Compared with the prior art, the advantages of the present invention are as follows:
(1) the passive type drag reduction technology designed compared to tradition based on profile optimization, the invention proposes a kind of high ultrasounds
Fast aircraft active Flow Control drag reduction technology can not propose higher want to dynamical system or boost motor and aircraft shape
Hypersonic aircraft resistance is effectively reduced in the case where asking, and control intensity is adjusted flexibly according to flight operating condition.
(2) compared to the non-zero mass jet stream of high-pressure air source gas supply, the present invention uses zero-net-mass-flux jet technology, has volume
Small, light-weight, structure is simple, and without complicated gas supply pipeline, and response is rapid, is easy to electrical parameter control, for strictly wanting
Ask small light, the hypersonic aircraft of fast-response control very applicable.
Detailed description of the invention
Hypersonic aircraft head flow field schematic diagram when Fig. 1 is no jet stream；
Fig. 2 is the hypersonic aircraft head flow field applied after high-speed gas thermojet；
Fig. 3 is the structural schematic diagram of single three-electrode spark electric discharge synthesizing jet-flow excitor in the embodiment of the present invention；
Fig. 4 is the reality that three-electrode spark heat discharge jet-flow excitor carries out the control of head bowshock in the embodiment of the present invention
Test schlieren figure, in which:
Fig. 4 (a) is without the flow field under control；
Fig. 4 (b) be three-electrode spark heat discharge jet-flow excitor work about 100 microseconds after apply control under flow field.
In figure:
1, the free incoming flow of high speed；2, bowshock；3, the head of hypersonic aircraft；4, high-speed gas thermojet；5,
Low pressure reflow zone；6, jet exit；7, driver anode；8, driver cavity；9, driver ignitor；10, DC power supply；
11, discharge capacity；12, high-voltage pulse power source；13, driver cathode.
Specific embodiment
With reference to the accompanying drawing 1 to Fig. 4, embodiments of the present invention are described in further detail.
Referring to Fig.1, mutual in the free incoming flow 1 of high speed and hypersonic aircraft in hypersonic aircraft flight course
Under effect, one of bowshock 2 is formd on the head of hypersonic aircraft 3, under no thermojet state of a control, arch swashs
Wave 2 and the head 3 of hypersonic aircraft are closer, and 2 intensity of bowshock is stronger, and the pressure after bowshock 2 is larger, and
And without apparent Disengagement zone between bowshock 2 and the head 3 of hypersonic aircraft, to the flight of hypersonic aircraft
Bring biggish resistance.
Referring to Fig. 2, the present invention provides the hypersonic aircraft head drag reduction side based on three-electrode spark electric discharge thermojet
Method installs three-electrode spark electric discharge synthesis thermojet driver on the head of hypersonic aircraft 3；In hypersonic aircraft
In flight course, three-electrode spark electric discharge synthesis thermojet driver is opened, discharges in three-electrode spark and synthesizes thermojet excitation
Electric discharge is generated in the cavity of device, so that when gases are heated, they expand and high speed ejection in driver cavity, generates high-speed gas thermojet
4；Under the action of high-speed gas thermojet 4, the arch on hypersonic aircraft head swashs 2 waves far from hypersonic aircraft head
Portion's wall surface, the remitted its fury of bowshock 2, so that the pressure reduction after bowshock 2, and high-speed gas thermojet is in high speed
Reverse reflux is attached to hypersonic aircraft head and close to hypersonic aircraft head under the action of free incoming flow
On appearance wall surface, it is formed about recirculating zone in the jet exit of driver, the gas density in recirculating zone is lower, air pressure is smaller,
So that the pressure reduction of hypersonic aircraft head and the appearance wall surface close to hypersonic aircraft head, to reduce
Hypersonic aircraft resistance.
In the present invention: the jet exit 6 and hypersonic flight of the three-electrode spark electric discharge synthesis thermojet driver
The head wall surface of device flushes.In this way under the premise of not changing hypersonic aircraft aerodynamic configuration, realize that reduction is hypersonic
The purpose of aircraft resistance.
Referring to Fig. 3, three-electrode spark electric discharge synthesizing jet-flow excitor in the present invention is by high-voltage pulse power source 12, straight
Galvanic electricity source 10, discharge capacity 11, driver ignitor 9, driver anode 7, driver cathode 13, driver cavity 8, jet stream
6 composition of outlet.DC power supply 10 is discharge capacity charging when driver works, and high-voltage pulse power source 12 is in driver cavity 8
Spark discharge generates plasma, so that breakdown voltage reduces between driver anode 7 and driver cathode 13, so that triggering is put
Capacitor 11 discharges, so that gas expansion and from 6 high speed ejection of jet exit in driver cavity 8, forms high-speed gas heat and penetrate
Stream.Subsequently, as high-speed gas thermojet sprays and driver cavity 8 is cooling so that in driver cavity 8 under temperature and pressure
Drop, extraneous gas refill driver cavity 8, prepare for next circulation.
Fig. 4 show the experiment line that spark discharge synthesizing jet-flow excitor in the embodiment of the present invention carries out forward shock control
Shadow figure has used single three-electrode spark electric discharge synthesizing jet-flow excitor in experiment, i.e., has pacified on the head of hypersonic aircraft
Single three-electrode spark electric discharge synthesizing jet-flow excitor is filled, about 1500 cubic millimeters of driver cavity volume, aircraft tests mould
Type diameter is about 50 millimeters.As shown in Fig. 4 (a), under no thermojet state of a control, bowshock is close to Vehicle nose's wall
Face；As shown in Fig. 4 (b), three-electrode spark is discharged after synthesizing jet-flow excitor about 100 microseconds of work, in thermojet control action
Under, bowshock is greatly increased with Vehicle nose's distance, and shock wave angle reduces, and remitted its fury leads to pressure reduction after wave.
The foregoing is merely a preferred embodiment of the present invention, are not intended to restrict the invention, for this field
For technical staff, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any
Modification, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (7)
1. a kind of hypersonic aircraft head drag reduction method based on three-electrode spark electric discharge thermojet, it is characterised in that:
The cephalad apex position of hypersonic aircraft is installed by single three-electrode spark electric discharge synthesizing jet-flow excitor；Fly hypersonic
In row device flight course, three-electrode spark electric discharge synthesizing jet-flow excitor is opened, in three-electrode spark electric discharge synthesizing jet-flow excitation
Electric discharge is generated in the cavity of device, so that when gases are heated, they expand and high speed ejection in driver cavity, generates high-speed gas thermojet；
Under the action of high-speed gas thermojet, the bowshock on hypersonic aircraft head is far from hypersonic aircraft top wall
Face, the remitted its fury of bowshock so that the pressure reduction after bowshock, and high-speed gas thermojet in high speed from origin
Reverse reflux is attached to hypersonic aircraft head and the appearance wall close to hypersonic aircraft head under the action of stream
On face, it is formed about recirculating zone in the jet exit of three-electrode spark electric discharge synthesizing jet-flow excitor, the gas in recirculating zone is close
Spend that lower, air pressure is smaller, so that hypersonic aircraft head and the appearance wall surface close to hypersonic aircraft head
Pressure reduction, to reduce hypersonic aircraft resistance.
2. the hypersonic aircraft head drag reduction side according to claim 1 based on three-electrode spark electric discharge thermojet
Method, it is characterised in that: the jet exit of three-electrode spark electric discharge synthesizing jet-flow excitor and the top wall of hypersonic aircraft
Face flushes.
3. the hypersonic aircraft head drag reduction side according to claim 1 based on three-electrode spark electric discharge thermojet
Method, it is characterised in that: the cavity volume of three-electrode spark electric discharge synthesizing jet-flow excitor is less than 1500 cubic millimeters.
4. the hypersonic aircraft head drag reduction side according to claim 1 based on three-electrode spark electric discharge thermojet
Method, it is characterised in that: the jet exit diameter of three-electrode spark electric discharge synthesizing jet-flow excitor is 1 to 2 millimeter.
5. the hypersonic aircraft head drag reduction side according to claim 1 based on three-electrode spark electric discharge thermojet
Method, it is characterised in that: three-electrode spark discharges synthesizing jet-flow excitor impulse discharge gross energy less than 3.5 joules.
6. the hypersonic aircraft head drag reduction side according to claim 1 based on three-electrode spark electric discharge thermojet
Method, it is characterised in that: the frequency of three-electrode spark electric discharge synthesizing jet-flow excitor electric discharge is greater than 2000 hertz.
7. the hypersonic aircraft head drag reduction side according to claim 1 based on three-electrode spark electric discharge thermojet
Method, it is characterised in that: the three-electrode spark electric discharge synthesizing jet-flow excitor is by high-voltage pulse power source, DC power supply, electric discharge electricity
Appearance, driver ignitor, driver anode, driver cathode, driver cavity, jet exit composition, direct current when work
Source is discharge capacity charging, and high-voltage pulse power source spark discharge in driver cavity generates plasma, so that driver is just
Breakdown voltage reduces between pole and cathode, to trigger discharge capacity electric discharge, so that gas expansion and from penetrating in driver cavity
Outflux high speed ejection forms high-speed gas thermojet；Then since high-speed gas thermojet sprays and driver cavity is cooling
So that driver cavity inner temperature and pressure decline, extraneous gas refill driver cavity, prepare for next circulation.
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| CN201811153135.6A CN109250073A (en) | 2018-09-30 | 2018-09-30 | Hypersonic aircraft head drag reduction method based on three-electrode spark discharge thermal jet |
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| CN201811153135.6A CN109250073A (en) | 2018-09-30 | 2018-09-30 | Hypersonic aircraft head drag reduction method based on three-electrode spark discharge thermal jet |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111559492A (en) * | 2020-04-26 | 2020-08-21 | 南京航空航天大学 | High-efficiency shock wave resistance reduction system of hypersonic aircraft |
| CN117864385A (en) * | 2024-03-11 | 2024-04-12 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic aircraft plasma sheath control device and flow field parameter algorithm |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111559492A (en) * | 2020-04-26 | 2020-08-21 | 南京航空航天大学 | High-efficiency shock wave resistance reduction system of hypersonic aircraft |
| CN117864385A (en) * | 2024-03-11 | 2024-04-12 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic aircraft plasma sheath control device and flow field parameter algorithm |
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Application publication date: 20190122 |