CN110500203A - A kind of solid rocket ramjet high speed free jet angle of attack measuring system based on weathercock - Google Patents
A kind of solid rocket ramjet high speed free jet angle of attack measuring system based on weathercock Download PDFInfo
- Publication number
- CN110500203A CN110500203A CN201910895253.2A CN201910895253A CN110500203A CN 110500203 A CN110500203 A CN 110500203A CN 201910895253 A CN201910895253 A CN 201910895253A CN 110500203 A CN110500203 A CN 110500203A
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- Prior art keywords
- weathercock
- component
- angle
- shaft
- free jet
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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
- 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
- F02K7/18—Composite ram-jet/rocket engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
The present invention proposes a kind of solid rocket ramjet high speed free jet angle of attack measuring system based on weathercock, including weathercock component, transmission component, rotating assembly, limiting device, laser displacement measurement system.Weathercock component is made of front end counterweight, connection strut and weathercock；Weathercock uses symmetrical pyramidal structure, and wherein weathercock windward side bevel angle is 53 °~62 °；Weathercock component drives shaft in rotating assembly to rotate by transmission component；Shaft uses the shaft with certain damping ratio and restoring force, smooth pivotal and system zero-bit can be voluntarily returned in no external force；Limiting device ensures that initial gas shock not will lead to weathercock component when wind-tunnel starting and transmission component occurs to deflect compared with general orientation；Laser displacement measurement system realizes the non-cpntact measurement to shaft rotational angle by laser displacement sensor and the cooperation of laser pick-off component.The present invention can satisfy the precise measurement of the angle of attack under Ducted rocket free jet test high temperature, high velocity environment.
Description
Technical field
The invention belongs to free jet test field, specially a kind of high speed free jet angle of attack based on weathercock measures system
System.
Background technique
Solid rocket ramjet belongs to airbreathing motor, and free jet test therein is Ducted rocket ground
Important tests subject in test, by the way that Ducted rocket is mounted in the equal Mach rhomboid of free jet nozzle exit,
To simulate state of the Ducted rocket in high-altitude flight.
Ducted rocket free jet test is carried out using supersonic wind tunnel at present, using air, oxygen and three groups of alcohol
Member burning can simulate Ducted rocket flight Mach number 3~4, flying height≤20km working condition, incoming flow total temperature height
Up to 600~1000K.In order to examine working performance of the Ducted rocket under different state of angle of attack, it is desirable to be able to start in Gu Chong
The change of precise measurement Ducted rocket angle of attack during free jet test under the high temperature of machine free jet test, high velocity environment
Change situation.
The angle of attack measurement of wind-tunnel is mainly realized by angle of attack sensor at present.Wherein the most widely used angle of attack passes
Sensor is broadly divided into mechanical and two class of pneumatic type from working principle, and mechanical angle of attack sensor mainly utilizes probe rotation
Angle obtains angle of attack size, including weather vane type angle of attack sensor and the differential angle of attack sensor that is zeroed；Pneumatic type angle of attack sensor
Angle of attack information, including pressure difference are obtained than incidence vane and FADS atmospheric parameter by the pressure information measured in flight course
Measurement.
In supersonic wind tunnel, pneumatic type angle of attack sensor needs to consider the shock wave of sensor aerodynamic configuration generation to the angle of attack
The influence of measurement accuracy, and sensor dynamic calibration and data processing are complex, manufacturing cost is higher.Be zeroed the differential angle of attack
Sensor because impurity, it is dirty be easily accessible air drain to influence angle of attack measurement accuracy, therefore it has measuring medium and measurement environment
Higher requirement, not can be used directly in free jet test.And traditional weather vane type angle of attack sensor mostly flies applied to low speed
Row condition, because its response speed is slow, stability is poor in high speed free jet field, and operating ambient temperature well below
600K not can be used directly in free jet test yet.
Summary of the invention
In order to solve the problems existing in the prior art, the present invention proposes that a kind of solid rocket ramjet based on weathercock is high
Fast free jet angle of attack measuring system, including weathercock component, transmission component, rotating assembly, limiting device, laser displacement measurement system
System.
The weathercock component is made of front end counterweight, connection strut and weathercock；Wherein front end counterweight is mounted on connection branch
Bar front end, for compensating influence of the gravity to weathercock position；The weathercock is arranged in connection strut rear upper, using symmetrical
Pyramidal structure, wherein weathercock windward side bevel angle is 53 °~62 °；The weathercock component is made of heat-resisting material；
Described transmission component one end is welded and fixed with the weathercock component centroid position connecting in strut, the other end with described turn
Shaft assembly cooperation；In the outer masterpiece used time, weathercock component can drive shaft in rotating assembly to rotate by transmission component；
The rotating assembly includes rotary shaft base and shaft；System zero position is marked in rotary shaft base；The shaft is adopted
With the shaft with certain damping ratio and restoring force, smooth pivotal and system zero-bit can be voluntarily returned in no external force；
There is the protrusion for cooperating with limiting device in the shaft；
The limiting device is mounted in rotary shaft base, can be with the male cooperation in the shaft, it is ensured that wind-tunnel starting
When initial gas shock not will lead to weathercock component and transmission component occurs to deflect compared with general orientation；
The laser displacement measurement system includes laser displacement sensor and laser pick-off component；The installation of laser pick-off component
In shaft, the non-cpntact measurement to shaft rotational angle is realized in laser displacement sensor and the cooperation of laser pick-off component.
Further preferred embodiment, weathercock windward side bevel angle are 60 °.
Further preferred embodiment, the weathercock component, transmission component are made using titanium alloy.
Further preferred embodiment, the connection strut use streamlined structure.
Further preferred embodiment, the laser displacement sensor use ZLDS11X high temperature displacement transducer.
Beneficial effect
The high speed free jet angle of attack measuring system based on weathercock designed herein, can satisfy Ducted rocket and freely penetrates
The precise measurement of the angle of attack under stream test high temperature, high velocity environment；Angle of attack design of measuring system is reasonable, and structure is simple, easy for installation, can
By property height, it is easy to calibrate, data processing is simple.
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Above-mentioned and/or additional aspect of the invention and advantage will become from the description of the embodiment in conjunction with the following figures
Obviously and it is readily appreciated that, in which:
Fig. 1: Ducted rocket free jet angle of attack measuring system schematic diagram；
Wherein: 1, weathercock component；2, transmission component；3, limiting device；4, system zero-bit；5, rotating assembly；6, laser connects
Receive component；7, laser displacement sensor；8, data collection system；
Fig. 2: weathercock shape face structure chart；
Pressure cloud atlas of Fig. 3: 20 ° of key groove weathercock test devices under 2 ° of operating conditions；
Pressure cloud atlas of Fig. 4: 40 ° of key groove weathercock test devices under 2 ° of operating conditions；
Pressure cloud atlas of Fig. 5: 60 ° of key groove weathercock test devices under 2 ° of operating conditions；
Pressure cloud atlas of Fig. 6: 80 ° of key groove weathercock test devices under 2 ° of operating conditions；
Difference key groove influences weather vane type device sensitivity when Fig. 7: Ma=3.
Specific embodiment
Present invention is primarily intended to develop one kind to can satisfy under Ducted rocket free jet test high temperature, high velocity environment
The angle of attack measuring system based on weathercock.
As shown in Fig. 1, system is mainly passed by weathercock component, transmission component, limiting device, rotating assembly, laser displacement
A few part compositions such as sensor.Weathercock component and transmission component are placed in FLOW FIELD IN FREE JETS by the angle of attack when measuring, and pass through weathercock group
Part perceives airflow direction, and when weathercock direction and airflow direction angle are 0 °, pressure is identical at left and right sides of weathercock, and weathercock direction is
For airflow direction；When weathercock direction and airflow direction angle are not 0 °, pressure is different at left and right sides of weathercock, and weathercock occurs inclined
Turn.Weathercock drives the angle of shaft rotation, angle signal can be converted to displacement signal with laser displacement sensor and carried out in real time
Measurement.The measurement of the angle of attack and yaw angle can be realized respectively by changing weathercock installation site.
(1) weathercock component is the sensing element for perceiving air-flow, mainly by front end counterweight, connection strut and weathercock three parts
Composition, as shown in Fig. 1.Weathercock front end increases counterweight and is used to compensate influence of the gravity to weathercock position.Connect body design at
Streamlined structure.It had not only been able to satisfy High Mach number and hot environment in this way to the rigidity requirement of weathercock, but also wind can be reduced as far as possible
Mark the influence to FLOW FIELD IN FREE JETS.To meet high temperature requirement, weathercock component is all made of titanium alloy and is made.
Weathercock is designed to symmetrical pyramidal structure, as shown in Figure 2.Applicant's analysis finds, due under the conditions of supersonic speed,
Weathercock cone angle has larger impact to the sensitivity of weathercock, therefore according to the calibration of Ducted rocket free jet test in the present invention
Operating condition, through Fluent software at free jet declared working condition condition (Mach number 3, pressure 1.0MPa, temperature 625K), respectively
Numerical simulation is carried out under different deflection angles (1 °, 2 °) operating condition to 20 °~80 ° bevel angle weathercock measuring devices, such as Fig. 3~Fig. 6.
When weathercock and air-flow have certain angle, weathercock both sides pressure difference is bigger, and weathercock changes flow-deviation angle sensitive
It spends higher (i.e. for the sensitivity of flow-deviation angle minor change).It is computed, in Ma=3, weathercock windward side bevel angle
At about 53 °~62 °, weathercock sensitivity is higher, and stability is preferable.Therefore the declared working condition of Ma=3 is directed in the present embodiment,
Weathercock windward side bevel angle is designed as 60 °, response speed and sensitivity highest, optimal stability, as shown in Figure 7.
(2) transmission component is signal transmission assembly, and main body is made of titanium alloy, and progress and wind in a welding manner
Component is marked to be connected.Weathercock deflection angle is transmitted to rotating assembly by transmission component.
(3) rotating assembly uses the shaft with certain damping ratio, should guarantee that shaft rotation smoothly without stuck, is protected again
Card weathercock in no external force can voluntarily return to system zero-bit.Weathercock deflection angle can be converted to by rotating assembly
Displacement signal measures.
(4) to guarantee that weathercock component is not started by free jet system gas shock is influenced when, in transmission component and is turned
Install limiting device between axis additional, it is ensured that when wind-tunnel starts initial gas shock not will lead to weathercock component and transmission component occur compared with
Big deflection is detached from laser optical path so as to cause laser pick-off component, leads to angle of attack measurement failure.By changing limiting device position
It sets, the measurement range of angle of attack measuring system can be changed to a certain extent.
(5) system zero-bit installs zero point as angle of attack measuring system, needs guarantee system installation zero-bit and installation during installation
Substrate axis is parallel.Simultaneously when carrying out attack angle measurement, it need to guarantee that yaw angle is placed in 0 ° of position, when carrying out sideslip angular measurement,
It need to guarantee that the angle of attack is placed in 0 ° of position.
(6) laser displacement measurement system is collectively constituted using laser displacement sensor and laser pick-off component to substitute tradition
Angle of attack sensor, to realize the No-contact Displacement Measurement of high temp objects.Laser displacement sensor be using laser technology come
It realizes the sensor of non-cpntact measurement, mainly includes the parts such as laser, laser detector and measuring circuit, it being capable of precise measurement
The change in displacement of testee.Such as the sensor of ZLDS100 type, resolution ratio is up to 0.01%；ZLDS11X high temperature displacement
Sensor can survey 500 DEG C~2200 DEG C.Flow-deviation angle degree is calculated i.e. by the displacement data that laser displacement sensor measures
For the air-flow angle of attack.
The measurement of the solid rocket ramjet high speed free jet angle of attack is carried out using above system to implement by the following method:
1, test before be respectively adopted static calibration and wind-tunnel dynamic calibration (± 45 °) to free jet angle of attack measuring system into
Row calibration；
2, angle of attack measuring system is mounted on attitude angle simulation mechanism rotatable platform, adjusting platform is placed in weathercock component
In the Mach numbers such as free jet flow field, while guaranteeing that system zero-bit is parallel with installation plate axis.
3, laser displacement sensor is installed, it is ensured that laser optical path is vertical with laser pick-off component, and records zero point, necessary
When, laser displacement sensor increase protective cover can be thermally shielded, dust-proof processing；
4, laser displacement sensor is connect with data collection system, rotates weathercock component manually to certain angle, checks
Whether measuring system output is normal；
5, after testing, Ducted rocket change in angle of attack is calculated by displacement data.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art are not departing from the principle of the present invention and objective
In the case where can make changes, modifications, alterations, and variations to the above described embodiments within the scope of the invention.
Claims (5)
1. a kind of solid rocket ramjet high speed free jet angle of attack measuring system based on weathercock, it is characterised in that: packet
Include weathercock component, transmission component, rotating assembly, limiting device, laser displacement measurement system；
The weathercock component is made of front end counterweight, connection strut and weathercock；Before wherein front end counterweight is mounted on connection strut
End, for compensating influence of the gravity to weathercock position；The weathercock is arranged in connection strut rear upper, using symmetrical taper
Structure, wherein weathercock windward side bevel angle is 53 °~62 °；The weathercock component is made of heat-resisting material；
Described transmission component one end is welded and fixed with the weathercock component centroid position connecting in strut, the other end and the shaft group
Part cooperation；In the outer masterpiece used time, weathercock component can drive shaft in rotating assembly to rotate by transmission component；
The rotating assembly includes rotary shaft base and shaft；System zero position is marked in rotary shaft base；The shaft is using tool
There is the shaft of certain damping ratio and restoring force, smooth pivotal and can voluntarily return to system zero-bit in no external force；It is described
There is the protrusion for cooperating with limiting device in shaft；
The limiting device is mounted in rotary shaft base, can be with the male cooperation in the shaft, it is ensured that at the beginning of when wind-tunnel starts
Beginning gas shock not will lead to weathercock component and transmission component occurs to deflect compared with general orientation；
The laser displacement measurement system includes laser displacement sensor and laser pick-off component；Laser pick-off component, which is mounted on, to be turned
On axis, the non-cpntact measurement to shaft rotational angle is realized in laser displacement sensor and the cooperation of laser pick-off component.
2. a kind of solid rocket ramjet high speed free jet angle of attack based on weathercock measures system according to claim 1
System, it is characterised in that: weathercock windward side bevel angle is 60 °.
3. a kind of solid rocket ramjet high speed free jet angle of attack based on weathercock measures system according to claim 1
System, it is characterised in that: the weathercock component, transmission component are made using titanium alloy.
4. a kind of solid rocket ramjet high speed free jet angle of attack based on weathercock measures system according to claim 1
System, it is characterised in that: the connection strut uses streamlined structure.
5. a kind of solid rocket ramjet high speed free jet angle of attack based on weathercock measures system according to claim 1
System, it is characterised in that: the laser displacement sensor uses ZLDS11X high temperature displacement transducer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910895253.2A CN110500203B (en) | 2019-09-20 | 2019-09-20 | High-speed free jet angle of attack measurement system of solid rocket ramjet based on weather vane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910895253.2A CN110500203B (en) | 2019-09-20 | 2019-09-20 | High-speed free jet angle of attack measurement system of solid rocket ramjet based on weather vane |
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| CN110500203A true CN110500203A (en) | 2019-11-26 |
| CN110500203B CN110500203B (en) | 2022-11-01 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114353739A (en) * | 2021-12-10 | 2022-04-15 | 武汉航空仪表有限责任公司 | Miniaturized multifunctional probe sensor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114353739A (en) * | 2021-12-10 | 2022-04-15 | 武汉航空仪表有限责任公司 | Miniaturized multifunctional probe sensor |
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