CN109612679A - Supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction - Google Patents
Supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction Download PDFInfo
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- CN109612679A CN109612679A CN201811382355.6A CN201811382355A CN109612679A CN 109612679 A CN109612679 A CN 109612679A CN 201811382355 A CN201811382355 A CN 201811382355A CN 109612679 A CN109612679 A CN 109612679A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction that this application discloses a kind of, comprising: shock tunnel, blunt body and laser energy loading system；Blunt body is contained in shock tunnel, and shock tunnel forms bowshock in blunt body front end；Optical path passes through shock tunnel, and detonation wave is generated at bowshock；Blunt body detects the pressure value at bowshock and detonation wave position.Measuring device provided by the present application, have many advantages, such as that response is fast, do not destroy flow field structure, control it is flexible.
Description
Technical field
The supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction that this application involves a kind of, belongs to master control
Flow control field.
Background technique
Hypersonic flight technology is one of the key technology that the main spacefaring nation in the world today is actively developing.When winged
When row device is with hypersonic flight, drag due to shock wave can account for more than half of aircraft drag overall, this will seriously affect aircraft
Aeroperformance increases energy consumption.Therefore from the aspect of energy conservation and improving aircraft performance two, drag reduction has been can not to avoid and must solve
Major issue certainly.
It is the Implantation Energy in the specific region of aircraft front end that energy, which deposits drag reduction, increases incoming flow pitot loss, changes and flies
The flow field structure of row device changes the pressure distribution on blunt body surface, to achieve the purpose that drag reduction, result of study shows energy
Deposition drag reduction can also reduce hot-fluid while reducing resistance.The advantages that due to directionality and good controllability, laser is considered
It is the effective energy source of drag reduction, forms plasma drag reduction, referred to as laser energy deposition drag reduction by injecting laser into flow field.
Some experimental studies have been carried out for laser energy deposition drag reduction in the world at present.The experimental study carried out is all
It is to be carried out in continuous wind-tunnel, without the sequence problem for considering to be related in pulse shock wave wind-tunnel.Due to shock tube and shock wave
Wind-tunnel using increasingly extensive, can be applied in laser energy deposition drag reduction experimental study.
Summary of the invention
According to the one aspect of the application, a kind of supersonic aircraft wave resistance based on laser energy deposition drag reduction is provided
Measuring device, the device can be used in experiment measure the wave resistance value of supersonic aircraft.
Supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction characterized by comprising shock wave wind
Hole, blunt body and laser energy loading system；
The blunt body is contained in the shock tunnel, and the shock tunnel forms arch in the blunt body front end and swashs
Wave；
The laser optical path that the laser energy loading system generates passes through the shock tunnel, and at the bowshock
Generate detonation wave；
Sensor is buried in the blunt body, for detecting the pressure at the bowshock and the detonation wave position
Value.
Optionally, the shock tunnel includes: shock tube, Laval nozzle and vacuum chamber, the connecting pin of the shock tube
It is connected with the vacuum chamber, the Laval nozzle is set in the vacuum chamber and the connecting pin with the shock tube
It is connected.
Optionally, detonation wave described in the positive face of the blunt body and bowshock interaction point are arranged.
Optionally, the supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction includes: that flow field is aobvious
Show measuring system, the optical path at the position is connect the laser energy loading system with the Flow field display and measurement system；
The laser energy loading system includes: laser and condenser lens；
The condenser lens is set in the vacuum chamber；
The laser is connect with the condenser lens optical path；
The condenser lens is connect with the position optical path.
Optionally, the Flow field display and measurement system includes: flash source and high speed camera, the flash source and the high speed
Camera is connected by schlieren light path system optical path；
The schlieren light path system is connect with the position optical path.
Optionally, the schlieren light path system includes: collimation lens, plus lens, the edge of a knife and imaging len；The flash of light
Source is connect with the collimation lens optical path；
The collimation lens is connect with the plus lens optical path；
The plus lens is connect with the edge of a knife optical path；
The edge of a knife is connected with the imaging len optical path.
Optionally, comprising: signal conditioner and capture card, the signal conditioner and the sensor power supply control connect
It connects；
The capture card is connect with the sensing data.
Optionally, the supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction includes: that timing is same
Control system is walked,
The timing synchronization control system respectively with the Flow field display and measurement system, the blunt body and the laser energy
Measure loading system control connection.
Optionally, the shock tunnel includes: shock tube, Laval nozzle and vacuum chamber, the connecting pin of the shock tube
It is connected with the vacuum chamber, the Laval nozzle is set in the vacuum chamber and the connecting pin with the shock tube
It is connected；
The supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction includes: first pressure sensing
Device, the first pressure sensor are installed on the connecting pin of the shock tube；
The timing synchronization control system is connect with the first pressure sensor signal.
Optionally, the timing synchronization control system is pulse signal generator DG645.
The beneficial effect that the application can generate includes:
1) the supersonic aircraft wave resistance measuring device provided herein based on laser energy deposition drag reduction, improves
Existing continuous wind tunnel experiment device is transformed into the lower pulse shock wave wind-tunnel of energy consumption, solves laser and go out light, shock wave
Wind-tunnel starts and the timing synchronization problem of blunt body pressure measurement.The device can push laser plasma in hypersonic flight
Active Flow Control Study on Problems in device, promotes corresponding technical level and engineering sense.
2) the supersonic aircraft wave resistance measuring device provided herein based on laser energy deposition drag reduction, using sharp
The mode of light energy deposition controls supersonic flow field, carries out display measurement using stration technique stream field, without broken
The experimental result that the structure in bad flow field itself, this non-intrusion type control and measuring technique obtain is more accurate credible, thus real
Existing non-intrusion type flow field control and Flow field display and measurement.
3) the supersonic aircraft wave resistance measuring device provided herein based on laser energy deposition drag reduction, energy consumption
It is few.Supersonic flow is generated with pulse shock wave wind-tunnel, wind-tunnel stable work time is only 5ms, and required gas storage is less, therefore phase
The energy consumption answered is less.
4) the supersonic aircraft wave resistance measuring device provided herein based on laser energy deposition drag reduction, timing are same
Step is controlled.The first pressure sensor signal rising edge that shock tube low-pressure end is installed is gone out to transmit as pulse signal generator
Number, flash source delay time is arranged according to flash source response time and flash time；It is set respectively according to the laser response time, is high
Fast capture delay time and second pressure sensor response time and the delay time of data acquisition time setting various pieces.It is logical
The internal delay time for crossing setting high speed camera, shoots the flow field evolutionary process of different moments, while measuring corresponding pressure data.
5) the supersonic aircraft wave resistance measuring device provided herein based on laser energy deposition drag reduction, flow field are aobvious
Show high resolution.Using the enhanced camera of HSFC PRO ultrahigh speed of German PCO company, Minimum Exposure Time is differentiated up to 3ns
Rate is 1280 × 1024 pixels, and 4 channels share triggering and work independently, test every channel and can record 1 photos respectively for 1 time, several
Sequential photograph need to be obtained by repeating experiment, solve the problems, such as high speed, high-resolution photography.
Detailed description of the invention
Fig. 1 is that the supersonic aircraft wave resistance in a kind of embodiment of the application based on laser energy deposition drag reduction measures dress
It sets；
Fig. 2 is schlieren light path system light path schematic diagram in a kind of embodiment of the application；
Fig. 3 is blunt body schematic diagram in a kind of embodiment of the application.
Component and reference signs list:
Specific embodiment
The application is described in detail below with reference to embodiment, but the application is not limited to these embodiments.
Referring to Fig. 1, the supersonic aircraft wave resistance measuring device provided by the present application based on laser energy deposition drag reduction, packet
Include the shock tunnel for generating supersonic flow, the blunt body 5 for simulating supersonic aircraft and laser energy load system
System
Blunt body 5 is contained in shock tunnel, and shock tunnel forms bowshock in 5 front end of blunt body；
Optical path passes through shock tunnel, and detonation wave is generated at bowshock；
Sensor is buried in blunt body 5, for detecting the pressure value at bowshock and detonation wave position.
In device provided by the present application, blunt body 5 only need by can 5 front end of blunt body formed bowshock mounting means
?.Optionally, sensor is pressure sensor.
Shock tunnel generates supersonic flow, forms bowshock in 5 front end of blunt body, while passing through acquisition second pressure
The data that sensor 7 measures；Laser breakdown air forms detonation wave, and detonation wave and bowshock interact, and reduces resistance.
It in specific example, is measured using wave resistance of the device provided by the present application to supersonic aircraft, on the one hand
Confirm the wave resistance that can reduce supersonic flight blunt body 5 based on laser energy deposition.The application offer is be provided simultaneously
Device testing result it is accurate.Device response simultaneously is fast, does not destroy flow field structure, controls flexibly.
Preferably, shock tunnel includes shock tube 1, Laval nozzle 2 and vacuum chamber 3, the connecting pin of shock tube 1 and vacuum
Cabin 3 is connected, and Laval nozzle 2 is set in vacuum chamber 3 and is connected with the connecting pin of shock tube 1.
Preferably, shock tunnel includes: first pressure sensor 4, blunt body 5 and second pressure for simulated flight device
Sensor 7, first pressure sensor 4 are installed on the connecting pin of shock tube 1；The positive face detonation wave and arch of blunt body 5
The setting of shock wave interaction point；Second pressure sensor 7 is installed on the back side of blunt body 5.
Specifically, in detonation wave and bowshock interaction point, bowshock is generated by Laval nozzle 2；Detonation
Wave is that laser breakdown air is formed.The initial position that detonation wave is in contact with bowshock, as interaction point.
Specifically, blunt body 5 can be installed in vacuum chamber 3 by bracket 6.
Preferably, laser energy loading system includes: laser 8 and condenser lens 10；Condenser lens 10 is set to vacuum
In cabin 3；Laser 8 is connect with 10 optical path of condenser lens；Condenser lens 10 is connect with position optical path.
It specifically, can be by being installed on vacuum chamber 3 in the incident vacuum chamber 3 of laser in order to enable the generation of laser 8
First optical window 9 is realized.Condenser lens 10 improves the accuracy for the detonation wave that laser generates for converging laser beam.
In one embodiment, laser 8 used is Nd:YAG laser 8 in laser energy loading system.Laser 8
Wavelength 1064nm, pulsewidth 10ns, maximum repetition rate 10Hz, maximum single pulse energy 400mJ.
The light of energy loading system is entered by vacuum tank window in experiment, and light level focuses, direction and incoming flow side
To vertical, certain specific position punctures incoming flow before laser is focused on blunt body 5 by the condenser lens 10 that focal length is 150mm, gathers
The adjusting of burnt position is realized by translating and rotating laser 8 and condenser lens 10.
Referring to Fig. 1, it is preferable that Flow field display and measurement system；Laser energy loading system and Flow field display and measurement system light
Road connection.Laser energy loading system can be attached with Flow field display and measurement system by existing all kinds of optical path connection types.
Flow field display and measurement system includes: flash source 12 and high speed camera 11, and flash source 12 and high speed camera 11 pass through line
The connection of 13 optical path of shadow light path system；Schlieren light path system 13 passes through the position of detonation wave and bowshock.
Specifically, the light that flash source 12 generates can be by the second optical window 14 for being set on 3 top surface of vacuum chamber
Into by schlieren light path system 13, and after the interaction point of detonation wave and bowshock, by vacuum chamber 3
Third optical window 15 exits into high speed camera 11.
Referring to fig. 2, the imaging plane 24 of schlieren light path system 13 and high speed camera 11 forms Flow field display and measurement system pair
Tested flow field 25 carries out display measurement.
Preferably, referring to fig. 2, schlieren light path system 13 includes: collimation lens 20, plus lens 21, the edge of a knife 22 and imaging
Lens 23；Collimation lens 20 is connect with 12 optical path of flash source；Collimation lens 20 is connect with 21 optical path of plus lens；Plus lens 21
It is connect with 22 optical path of the edge of a knife；The edge of a knife 22 is connected with 23 optical path of imaging len.Imaging plane 24, tested flow field 25 are tested in Fig. 2
Flow field schematic forms.
Because there is density level bands in the horizontal direction in the detonation wave that 5 anterior arch lambda shock wave of blunt body and laser energy deposition generate
Degree, therefore the edge of a knife 22 is selected as vertical direction in schlieren system.Using schlieren system by light by caused by behind flow perturbation area
The deviation light of different directions distinguishes, and by the light source picture of generation, falls part with the gear of the schlieren edge of a knife 22, to change the photograph in screen
Degree makes the variation of perturbing area refractive index be rendered as the schlieren image that light and shade changes on screen (or photographic negative)
In specific embodiment, schlieren light path system 13 includes xenon flash light source (flash source 12), 150mm, focal length 200mm
Schlieren mirror, the edge of a knife 22 and HSFC high speed camera 11.The enhanced camera of HSFC PRO ultrahigh speed of PCO company, used Germany
For Minimum Exposure Time up to 3ns, resolution ratio is 1280 × 1024 pixels, and 4 channels share triggering and work independently, and 1 experiment is often led to
Road can record 1 photos respectively, several sequential photographs need to be obtained by repeating experiment, solve high speed, high-resolution photography is asked
Topic.
Referring to Fig. 3, blunt body 5 includes model 51, strut 53 and second pressure sensor 7；One end of model 51 is in
Cavity is arranged in bluff nose, the other end, accommodates second pressure sensor 7；Strut 53 is connected with the other end of model 51.Pass through
Bracket 6 is convenient for by devices such as brackets 6 that blunt body 5 is fixed.Preferably, the other end side wall hollow out of model 51, convenient for the
The connecting line of two pressure sensors 7 passes through.
Preferably, blunt body 5 further include: signal conditioner 17 and capture card 18, signal conditioner 17 and second pressure pass
The connection of 7 power supply control of sensor；Capture card 18 and 7 data connection of second pressure sensor.
Preferably, blunt body 5 further includes computer 19, and computer 19 is connect with capture card eighteen data, is handled for storage
The pressure value that capture card 18 obtains.
The measurement to 5 surface stagnation pressure of blunt body in wind-tunnel may be implemented by blunt body 5.Measurement result can pass through
Second pressure sensor 7 is transmitted to computer 19 and is handled or inputted capture card 18.
In one embodiment, 5 diameter 20mm of blunt body, material are 316L stainless steel, are used between model and straight-bar
The screw thread of M6, which is installed, to be fixed, and strut 53 is fixed on the optical platform in vacuum chamber 3 by bracket 6.
5 surface stagnation pressure of blunt body is measured using the 111A24 type pressure sensor of PCB PIEZOTRONICS company,
Its principle is to convert the pressure to electric signal, inputs capture card 18, is threadedly coupled between sensor and model.
The effect of signal conditioner 17PCB482C16 be provided for second pressure sensor 7 power supply, setting test parameter and
Operating mode etc..
Signal conditioner 17PCB482C16 is connected by RS232 interface with computer 19, realizes second pressure sensor 7
Parameter setting.
In a particular embodiment, signal acquisition by section's dynamic instrument company in Chengdu PCI4712 high-speed data acquisition card
18 realize.The card supports the pci bus of 32,5V using simultaneously and concurrently designing；There is independent 40Msps in each channel
(sample per second), 12 A/D converters；With independent memory space, sampling depth reaches 4MSa
(sample)/CH；Any sample frequency synthesis of 1K~40MHz may be implemented in DDS frequency synthesizer.The input of PCI4712 hinders
Resist for 1M, the partial pressure that can ignore test equipment influences.
Preferably, comprising: timing synchronization control system 16, timing synchronization control system 16 and first pressure sensor 4 are believed
Number connection；Timing synchronization control system 16 is controlled with Flow field display and measurement system, blunt body 5 and laser energy loading system respectively
Connection.
Specifically, timing synchronization control system 16 respectively with high speed camera 11, capture card 18, flash source 12 and laser 8
Control connection.
It is realized by setting timing synchronization control system 16 and the timing synchronization of experimentation is controlled.
Preferably, timing synchronization control system 16 includes: pulse signal generator DG645；First pressure sensor 4 and arteries and veins
Rush the connection of signal generator DG645 signal；Pulse signal generator DG645 respectively with high speed camera 11, capture card 18, flash source
12 and laser 8 control connection.
Capture card 18 herein is used to obtain the data of second pressure sensor 7, and the signal with second pressure sensor 7
Adjuster 17 connects.
It is realized by timing synchronization control system 16 and each system coordination is controlled, it is orderly convenient for effectively control detection process
It carries out.
The rising edge signal that first pressure sensor 4 obtains is input to pulse signal generator DG645 as trigger source,
Different delays is arranged in pulse signal generator DG645, distinguishes laser 8, capture card 18, high speed camera 11 and flash source 12
It is controlled.By pulse signal generator DG645, so that laser 8 goes out light, Flow field display and measurement system photographs and blunt body
5 pressure measurements are carried out according to default timing, while ensuring shock tunnel steady operation.Computer 19 is for recording capture card 18
The data of acquisition.
In one embodiment, timing synchronization controlling plan design are as follows: the PCB first of 1 low-pressure end of shock tube installation is pressed
Force snesor 4 monitors incident shock, regard the rising edge input pulse signal generator DG 645 of pressure signal as trigger signal.
Incident shock reaches 3ms after low-pressure end, and shock tunnel has started and in steady-working state, xenon flash lamp flash source 12
Response time is 160s, flash time 1ms, therefore the delay time that control xenon flash lamp flash source 12 is arranged is 2.84ms；
8 response time of Nd:YAG laser is 240s, therefore the channel delay time that control YAG laser 8 is arranged is 2.76ms.At a high speed
The channel delay time of camera 11 is 3ms, so that visual field is illuminated by flash source 12 when laser breakdown air, while high speed phase
Machine 11 is opened, and different delay times can be arranged by acquisition software to record the stream of different moments in 114 channels of high speed camera
Field state.3ms, acquisition time 1ms are set by the channel delay for controlling data collecting card 18, so that entire flow field control process
The pressure data of 0 position can be recorded.
In a specific example, the design Mach number for testing shock tunnel used is respectively 5,6,7, experimental section diameter difference
For 100mm, 150mm and 200mm, observation window diameter 200mm.The basic principle of shock tunnel is the high temperature for generating shock tube 1
High pressure gas is uniform supersonic flow by 2 constant entropy expansion of Laval nozzle, it mainly includes shock tube 1, Laval nozzle 2
It is formed with 3 three parts of vacuum chamber.It can be timing synchronization control system in the PCB first pressure sensor 4 of 1 low-pressure end of shock tube installation
System 16 provides trigger signal.
1 high-low pressure segment length of this shock tube is 6m, and tube body is by circular section (internal diameter 100mm, outer diameter 130mm) stainless steel
It manages (316L) to constitute, mainly includes high pressure section, folder film section, low pressure stage and experimental section, fills air distribution system, auxiliary system, measurement system
The parts such as system.Low pressure stage is identical with high pressure section structure size, every section of 2m, and each section is connected by male and female face seam allowance with O-ring.
Wind-tunnel stable work time is in 5ms or so.Shock tube 1 drives the method for operation of air using helium in experiment, and Rupture of Membrane pressure is
1.5MPa, low pressure stage initial pressure are 0.25MPa.
2 purpose of design of Laval nozzle is to guarantee that experimental section obtains the uniform air flow of design Mach number.Devise Mach number
Respectively 5,6,7 two-dimensional axial symmetric Laval nozzle 2.Since jet pipe is longer, segmentation numerical control workshop, Zhi Houyong are used
The processing technology welded again after bolt and positioning pin connection.
3 volume 1.5m3 of vacuum chamber, has inside put the bread board for being evenly distributed with M6 internal screw thread, it is convenient to install experimental model.
Vacuum pump includes Germany Lay treasured sliding vane rotary pump SV100B and Lodz pumps WAU501, and vacuum degree can be evacuated to 10Pa magnitude by the two cooperation.
Observation window, jet pipe, data flange and blind plate have been all made of O-ring sealing when connecting with vacuum chamber 3.
More than, be only several embodiments of the application, any type of limitation not done to the application, although the application with
Preferred embodiment discloses as above, however not to limit the application, any person skilled in the art is not departing from this
In the range of applying for technical solution, a little variation or modification are made using the technology contents of the disclosure above and is equal to equivalent reality
Case is applied, is belonged in technical proposal scope.
Claims (10)
1. a kind of supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction characterized by comprising shock wave
Wind-tunnel, blunt body and laser energy loading system；
The blunt body is contained in the shock tunnel, and the shock tunnel forms bowshock in the blunt body front end；
The laser optical path that the laser energy loading system generates passes through the shock tunnel, and generates at the bowshock
Detonation wave；
Sensor is buried in the blunt body, for detecting the pressure value at the bowshock and the detonation wave position.
2. the supersonic aircraft wave resistance measuring device according to claim 1 based on laser energy deposition drag reduction, special
Sign is, the shock tunnel includes: shock tube, Laval nozzle and vacuum chamber, the connecting pin of the shock tube and described true
Empty cabin is connected, and the Laval nozzle is set in the vacuum chamber and is connected with the connecting pin of the shock tube.
3. the supersonic aircraft wave resistance measuring device according to claim 1 based on laser energy deposition drag reduction, special
Sign is that detonation wave described in the positive face of the blunt body and bowshock interaction point are arranged.
4. the supersonic aircraft wave resistance measuring device according to claim 3 based on laser energy deposition drag reduction, special
Sign is that the supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction includes: Flow field display and measurement system
System, the optical path at the position is connect the laser energy loading system with the Flow field display and measurement system；
The laser energy loading system includes: laser and condenser lens；
The condenser lens is set in the vacuum chamber；
The laser is connect with the condenser lens optical path；
The condenser lens is connect with the position optical path.
5. the supersonic aircraft wave resistance measuring device according to claim 4 based on laser energy deposition drag reduction, special
Sign is that the Flow field display and measurement system includes: flash source and high speed camera, and the flash source passes through with the high speed camera
The connection of schlieren light path system optical path；
The schlieren light path system is connect with the position optical path.
6. the supersonic aircraft wave resistance measuring device according to claim 5 based on laser energy deposition drag reduction, special
Sign is that the schlieren light path system includes: collimation lens, plus lens, the edge of a knife and imaging len；The flash source with it is described
The connection of collimation lens optical path；
The collimation lens is connect with the plus lens optical path；
The plus lens is connect with the edge of a knife optical path；
The edge of a knife is connected with the imaging len optical path.
7. the supersonic aircraft wave resistance measuring device according to claim 1 based on laser energy deposition drag reduction, special
Sign is, comprising: signal conditioner and capture card, the signal conditioner are connect with the sensor power supply control；
The capture card is connect with the sensing data.
8. the supersonic aircraft wave resistance measuring device according to claim 4 based on laser energy deposition drag reduction, special
Sign is that the supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction includes: timing synchronization control system
System,
The timing synchronization control system adds with the Flow field display and measurement system, the blunt body and the laser energy respectively
Loading system control connection.
9. the supersonic aircraft wave resistance measuring device according to claim 8 based on laser energy deposition drag reduction, special
Sign is, the shock tunnel includes: shock tube, Laval nozzle and vacuum chamber, the connecting pin of the shock tube and described true
Empty cabin is connected, and the Laval nozzle is set in the vacuum chamber and is connected with the connecting pin of the shock tube；
The supersonic aircraft wave resistance measuring device based on laser energy deposition drag reduction includes: first pressure sensor, institute
First pressure sensor is stated to be installed on the connecting pin of the shock tube；
The timing synchronization control system is connect with the first pressure sensor signal.
10. the supersonic aircraft wave resistance measuring device according to claim 8 based on laser energy deposition drag reduction, special
Sign is that the timing synchronization control system is pulse signal generator DG645.
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