CN106679923B - A kind of pressure decoupling device influencing dynamometry model for high speed jet - Google Patents
A kind of pressure decoupling device influencing dynamometry model for high speed jet Download PDFInfo
- Publication number
- CN106679923B CN106679923B CN201611161925.XA CN201611161925A CN106679923B CN 106679923 B CN106679923 B CN 106679923B CN 201611161925 A CN201611161925 A CN 201611161925A CN 106679923 B CN106679923 B CN 106679923B
- Authority
- CN
- China
- Prior art keywords
- ring
- sonic nozzle
- flexible membrane
- section
- sealing ring
- Prior art date
- 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.)
- Active
Links
Classifications
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to aviation aerodynamic force wind-tunnel technique fields, are related to a kind of pressure decoupling device that dynamometry model is influenced suitable for high speed jet.It includes air inlet pipe (1), sonic nozzle (2), collection chamber (3), left flexible membrane component, right flexible membrane component, nose cone (6), measurement end (9), the 1st sealing ring (10), the 2nd sealing ring (11), the 3rd sealing ring (12), the 4th sealing ring (13), the 5th sealing ring (14), the 6th sealing ring (15), the 7th sealing ring (16), 6 jet pipes (17) and loop coil (18).The invention proposes a kind of pressure decoupling device for influencing dynamometry model suitable for high speed jet, solve the problems, such as that temperature influences balance zero.
Description
Technical field
The invention belongs to aviation aerodynamic force wind-tunnel technique fields, are related to a kind of suitable for high speed jet influence dynamometry mould
The pressure decoupling device of type.
Background technique
Thrust Vectoring Technology can significantly improve the agility, mobility, viability of modern combat aircraft and guided missile.Using thrust
The aircraft of vectoring technology, is deflected by jet pipe, is obtained additional control moment using the thrust that engine generates, is realized aircraft
Gesture stability.Its outstanding feature is that control moment is closely related with engine, without being influenced by aircraft posture itself.Therefore,
It can guarantee that aircraft makees low speed, High Angle of Attack maneuvering flight and whens a few near failures of primary control surface utilize thrust vectoring to provide is additional
Operating torque controls air maneuver.Around how effectively realizing vectored thrust, people carry out from pneumatic, mechanical etc.
A lot of research work, and have been achieved with many achievements.Wherein, model/jet pipe integrated design high speed jet influences dynamometry
Model becomes the mainstream in Now Domestic extrapolation force vector test field since the similar parameter that it can be simulated is more.Pressure decoupling
Device is to provide high pressure gas to lance system in jet efflux dynamometry model, is formed and is coupled with the balance system of model
Structure, and divide a kind of decoupling device of high-pressure air feed pipeline fixing end and measurement end simultaneously, it is that high speed jet influences dynamometry model
Core component, affect balance to a certain extent for the precise measurement of model aerodynamic force.Domestic needle is not yet inquired at present
The pressure decoupling device of dynamometry model is influenced on high speed jet is suitable for, U.S.'s nineteen ninety is by Staff of the
A User ' the s guide to the LANLEY16-foot that Propulsion Aerodynamics Branch writes
In mono- text of Transonic Tunnel Complex, a kind of pressure decoupling device is disclosed, but it is using metal material
Flexible membrane has that more serious temperature influences balance zero.
Summary of the invention
The purpose of the present invention is：It is proposed a kind of pressure decoupling device that dynamometry model is influenced suitable for high speed jet, so as to
Solve the problems, such as that temperature influences balance zero.
The technical scheme is that：A kind of pressure decoupling device influencing dynamometry model for high speed jet, feature
It is：It includes air inlet pipe 1, sonic nozzle 2, collection chamber 3, left flexible membrane component, right flexible membrane component, nose cone 6, measurement
Hold the 9, the 1st sealing ring 10, the 2nd sealing ring 11, the 3rd sealing ring 12, the 4th sealing ring 13, the 5th sealing ring 14, the 6th sealing ring 15,
7th jet pipe 17 of sealing ring 16,6 and loop coil 18；
By air inlet pipe 1, sonic nozzle 2, the 1st sealing ring 10, the 3rd sealing ring 12, the 6th sealing ring 15, the 7th sealing ring 16,
Jet pipe 17 and loop coil 18 constitute air intake assembly；
Air inlet pipe 1 is a cylinder, and the position on 1 external cylindrical surface of air inlet pipe close to left port has one to have bolt hole
Air inlet pipe flange, have an air inlet pipe end face of flange seal groove on the left side of air inlet pipe flange, the 7th sealing ring 16 is located at
In above-mentioned air inlet pipe end face of flange seal groove, there is air inlet pipe internal thread segment in the right output port of air inlet pipe 1, in air inlet pipe internal screw thread
Section the left side have one section of air inlet pipe unthreaded hole section, have on the inner cylinder face of air inlet pipe unthreaded hole section annular unthreaded hole section seal groove, the 6th
Sealing ring 15 is located in above-mentioned unthreaded hole section seal groove；
Sonic nozzle 2 is right end closing, the open cylinder in left end, has one in the middle part of 2 external cylindrical surface of sonic nozzle
A section is the outer ring boss 2e of rectangle, there is 6 be uniformly distributed along the circumference and velocity of sound on the external cylindrical surface of outer ring boss 2e
The sonic nozzle threaded hole 2f that the inner hole of nozzle 2 radially penetrates through, has an outer ring convex on the right side of outer ring boss 2e
Platform right side positions annular groove 2g, there is one section of sonic nozzle on the external cylindrical surface of sonic nozzle 2, on the right of outer ring boss 2e
Right light tube section has the right seal groove 2h of an annular sonic nozzle, the 1st sealing ring 10 on the right of the right light tube section of the sonic nozzle
It is the right external thread section of sonic nozzle on the right of the right seal groove 2h of sonic nozzle in the right seal groove 2h of above-mentioned sonic nozzle
2j；There is an outer ring boss left side positioning annular groove 2d on the left side of outer ring boss 2e, in the outer of sonic nozzle 2
On cylindrical surface, the left side of outer ring boss 2e have one section of left light tube section of sonic nozzle the 1st, in the left light tube section of sonic nozzle the 1st
On have the left seal groove 2c of an annular sonic nozzle, the 3rd sealing ring 12 is located in the left seal groove 2c of above-mentioned sonic nozzle, in sound
There is the left outside thread segment 2b of sonic nozzle on the left side of the left light tube section of fast nozzle the 1st, is on the left side of the left outside thread segment 2b of sonic nozzle
The left light tube section 2a of sonic nozzle the 2nd；The left outside thread segment 2b of sonic nozzle is screwed into the air inlet pipe internal thread segment of air inlet pipe 1, velocity of sound
In the air inlet pipe unthreaded hole section of the left light tube section 2a of nozzle the 2nd insertion air inlet pipe 1 and clearance fit is kept, loop coil 18 is screwed in sonic nozzle
On right external thread section 2j；Jet pipe 17 is with externally threaded cylinder, and the external screw thread of 6 jet pipes 17 is screwed into the 6 of sonic nozzle 2 respectively
In a sonic nozzle threaded hole 2f；
Measurement group is constituted by collection chamber 3, nose cone 6, measurement end 9, the 2nd sealing ring 11, the 4th sealing ring 13, the 5th sealing ring 14
Part；
Measurement end 9 is the cylinder that a left end has measurement end external thread section with measurement end flanges, right end, measurement end 9
The aperture of inner hole is greater than the outer diameter of 2 cylinder of sonic nozzle, is disposed with what a circle was uniformly distributed along the circumference on the inner cylinder face of measurement end 9
The outer static bole 8 of 4 waves, has a measurement end end face seal slot, the 4th sealing ring 13 is located on the right side of measurement end 9
In above-mentioned measurement end end face seal slot；Nose cone 6 is that a left end is opened wide, right output port is by a closed cylinder of circular conical surface, in head
The left end of 6 external cylindrical surfaces is bored with nose cone external thread section, there is nose cone end face seal slot, the 2nd sealing ring on the left side of nose cone 6
11 are located in above-mentioned nose cone end face seal slot, have the tapped blind hole being uniformly distributed along the circumference on the right side of measurement end flanges, in spiral shell
There is a measurement end end face of flange seal groove outside line blind hole, the 5th sealing ring 14 is located at the sealing of above-mentioned measurement end end face of flange
In slot；
Collection chamber 3 is a cylinder, and having a section in the middle part of 3 inner cylinder face of collection chamber is the annular boss of rectangle
3a has what the external cylindrical surface of 6 and collection chamber 3 being uniformly distributed along the circumference radially penetrated through to go out on the inner cylinder face of interior annular convex platform 3a
The aperture of stomata 3b, venthole 3b are greater than the outer diameter of jet pipe 17, have an annular convex on the left side of interior annular convex platform 3a
Platform left side positions annular groove 3d, there is an annular boss right side positioning annular groove on the right side of interior annular convex platform 3a
3c has left inside thread segment on the left side of interior annular convex platform 3a, has right internal thread segment on the right of interior annular convex platform 3a；Measurement end 9
The external thread section of right end is screwed into the left inside thread segment of collection chamber 3, and the nose cone external thread section of 6 left end of nose cone is screwed into collection chamber 3
In right internal thread segment；It is disposed on the inner cylinder face of each venthole 3b of collection chamber 3 in 4 waves that a circle is uniformly distributed along the circumference
Static bole 7；
Air intake assembly and measurement component pass through left flexible membrane component and right flexible membrane component formation connection relationship, Zuo Rou
Property diaphragm unit is identical with the structure of right flexible membrane component and positional symmetry；
Left flexible membrane component is made of left flexible membrane 4a, left inside pressure ring 4b and left outside pressure ring 4c；Left flexible membrane 4a
It is the annulus of light sheet manufacture, the shape of its radial section is as follows：It is divided into 3 sections from outside to inside, is outer flat segments respectively
4a1, arc section 4a3 and interior flat segments 4a4, the protrusion direction of arc section 4a3 to the left, have on the right surface of outer flat segments 4a1
Left flexible membrane outer positioning ring shape boss 4a2, has in left flexible membrane on the right surface of interior flat segments 4a4 and positions annular convex platform
4a5；Left flexible membrane 4a is fixed outside left flexible membrane between sonic nozzle 2 and collection chamber 3, the left side of outer ring boss 2e
Position annular convex platform 4a2 is located in the annular boss left side positioning annular groove 3d of collection chamber 3, positioning annular in left flexible membrane
Boss 4a5 is located in the outer ring boss left side positioning annular groove 2d of sonic nozzle 2；Left inside pressure ring 4b is an annulus, left
The left side of inner pressure ring 4b is parallel with right side, and left inside pressure ring 4b covers on the left light tube section of sonic nozzle the 1st of sonic nozzle 2 simultaneously
Clearance fit is kept, the 3rd sealing ring 12 is left inside by the clearance seal between left inside pressure ring 4b and the left light tube section of sonic nozzle the 1st
The left side of pressure ring 4b is bonded with the right side of air inlet pipe 1, and the right side of left inside pressure ring 4b is pushed down straight in left flexible membrane 4a
The left surface of section 4a4；Left outside pressure ring 4c is an annulus, and the left side of left outside pressure ring 4c is parallel with right side, left outside pressure ring 4c
External screw thread be screwed into the left inside thread segment of collection chamber 3, the outer flat segments of left flexible membrane 4a are pushed down in the right side of left outside pressure ring 4c
The left side of the left surface of 4a1, left outside pressure ring 4c is bonded with the right side of measurement end 9, and the 4th sealing ring 13 is by left outside pressure ring 4c's
Clearance seal between 9 right side of left side and measurement end；
Right flexible membrane component is made of right flexible membrane 5a, right inner pressure ring 5b and right outer press ring 5c；Right flexible membrane 5a
Material, shape and size it is identical as left flexible membrane 4a, the shape of the radial section of right flexible membrane 5a is as follows：From outside to inside
Be divided into 3 sections, be outer flat segments 5a1, arc section 5a3 and interior flat segments 5a4 respectively, the protrusion direction of arc section 5a3 to the right, outside
There is right flexible membrane outer positioning ring shape boss 5a2 on the left surface of flat segments 5a1, has the right side on the left surface of interior flat segments 5a4
Annular convex platform 5a5 is positioned in flexible membrane；Right flexible membrane 5a is between sonic nozzle 2 and collection chamber 3, outer ring boss 2e
The right, right flexible membrane outer positioning ring shape boss 5a2 be located at collection chamber 3 annular boss right side positioning annular groove 3c
Interior, positioning annular convex platform 5a5 is located in the outer ring boss right side positioning annular groove 2g of sonic nozzle 2 in right flexible membrane；
Right inner pressure ring 5b is an annulus, and the left side of right inner pressure ring 5b is parallel with right side, and right inner pressure ring 5b is covered in sonic nozzle 2
On the right light tube section of sonic nozzle and keep clearance fit, the 1st sealing ring 10 by right inner pressure ring 5b and the right light tube section of sonic nozzle it
Between clearance seal, the right surface of flat segments 5a4 in right flexible membrane 5a, right inner pressure ring 5b are pushed down in the left side of right inner pressure ring 5b
Right side by loop coil 18 left side compress, right outer press ring 5c is an annulus, the left side and right side of right outer press ring 5c
In parallel, the external screw thread of right outer press ring 5c is screwed into the right internal thread segment of collection chamber 3, and right flexibility is pushed down in the left side of right outer press ring 5c
The right surface of the outer flat segments 5a1 of diaphragm 5a, the right side of right outer press ring 5c are compressed by the left side of nose cone 6；6 jet pipes 17 are distinguished
In 6 venthole 3b of collection chamber 3, jet pipe 17 and venthole 3b keeps coaxial.
It is an advantage of the invention that：Propose a kind of pressure decoupling device that dynamometry model is influenced suitable for high speed jet, solution
The problem of temperature of having determined influence balance zero.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention.In figure, "inner" refers to by the direction of axial ray, and "outside" refers to the side far from axis
To.
Fig. 2 is the structural schematic diagram of sonic nozzle 2 in the present invention.
Fig. 3 is the structural schematic diagram of collection chamber 3 in the present invention.
Fig. 4 is the partial sectional view of left flexible membrane 4a in the present invention.
Fig. 5 is the partial sectional view of right flexible membrane 5a in the present invention.
Specific embodiment
The present invention is described in further details below.Referring to Fig. 1 to Fig. 5, one kind influencing dynamometry mould for high speed jet
The pressure decoupling device of type, it is characterised in that：It includes air inlet pipe 1, sonic nozzle 2, collection chamber 3, left flexible membrane component, the right side
Flexible membrane component, nose cone 6, measurement end 9, the 1st sealing ring 10, the 2nd sealing ring 11, the 3rd sealing ring 12, the 4th sealing ring 13,
5 sealing rings 14, the 6th sealing ring 15,16,6 jet pipes 17 of the 7th sealing ring and loop coil 18；
By air inlet pipe 1, sonic nozzle 2, the 1st sealing ring 10, the 3rd sealing ring 12, the 6th sealing ring 15, the 7th sealing ring 16,
Jet pipe 17 and loop coil 18 constitute air intake assembly；
Air inlet pipe 1 is a cylinder, and the position on 1 external cylindrical surface of air inlet pipe close to left port has one to have bolt hole
Air inlet pipe flange, have an air inlet pipe end face of flange seal groove on the left side of air inlet pipe flange, the 7th sealing ring 16 is located at
In above-mentioned air inlet pipe end face of flange seal groove, there is air inlet pipe internal thread segment in the right output port of air inlet pipe 1, in air inlet pipe internal screw thread
Section the left side have one section of air inlet pipe unthreaded hole section, have on the inner cylinder face of air inlet pipe unthreaded hole section annular unthreaded hole section seal groove, the 6th
Sealing ring 15 is located in above-mentioned unthreaded hole section seal groove；
Sonic nozzle 2 is right end closing, the open cylinder in left end, has one in the middle part of 2 external cylindrical surface of sonic nozzle
A section is the outer ring boss 2e of rectangle, there is 6 be uniformly distributed along the circumference and velocity of sound on the external cylindrical surface of outer ring boss 2e
The sonic nozzle threaded hole 2f that the inner hole of nozzle 2 radially penetrates through, has an outer ring convex on the right side of outer ring boss 2e
Platform right side positions annular groove 2g, there is one section of sonic nozzle on the external cylindrical surface of sonic nozzle 2, on the right of outer ring boss 2e
Right light tube section has the right seal groove 2h of an annular sonic nozzle, the 1st sealing ring 10 on the right of the right light tube section of the sonic nozzle
It is the right external thread section of sonic nozzle on the right of the right seal groove 2h of sonic nozzle in the right seal groove 2h of above-mentioned sonic nozzle
2j；There is an outer ring boss left side positioning annular groove 2d on the left side of outer ring boss 2e, in the outer of sonic nozzle 2
On cylindrical surface, the left side of outer ring boss 2e have one section of left light tube section of sonic nozzle the 1st, in the left light tube section of sonic nozzle the 1st
On have the left seal groove 2c of an annular sonic nozzle, the 3rd sealing ring 12 is located in the left seal groove 2c of above-mentioned sonic nozzle, in sound
There is the left outside thread segment 2b of sonic nozzle on the left side of the left light tube section of fast nozzle the 1st, is on the left side of the left outside thread segment 2b of sonic nozzle
The left light tube section 2a of sonic nozzle the 2nd；The left outside thread segment 2b of sonic nozzle is screwed into the air inlet pipe internal thread segment of air inlet pipe 1, velocity of sound
In the air inlet pipe unthreaded hole section of the left light tube section 2a of nozzle the 2nd insertion air inlet pipe 1 and clearance fit is kept, loop coil 18 is screwed in sonic nozzle
On right external thread section 2j；Jet pipe 17 is with externally threaded cylinder, and the external screw thread of 6 jet pipes 17 is screwed into the 6 of sonic nozzle 2 respectively
In a sonic nozzle threaded hole 2f；
Measurement group is constituted by collection chamber 3, nose cone 6, measurement end 9, the 2nd sealing ring 11, the 4th sealing ring 13, the 5th sealing ring 14
Part；
Measurement end 9 is the cylinder that a left end has measurement end external thread section with measurement end flanges, right end, measurement end 9
The aperture of inner hole is greater than the outer diameter of 2 cylinder of sonic nozzle, is disposed with what a circle was uniformly distributed along the circumference on the inner cylinder face of measurement end 9
The outer static bole 8 of 4 waves, has a measurement end end face seal slot, the 4th sealing ring 13 is located on the right side of measurement end 9
In above-mentioned measurement end end face seal slot；Nose cone 6 is that a left end is opened wide, right output port is by a closed cylinder of circular conical surface, in head
The left end of 6 external cylindrical surfaces is bored with nose cone external thread section, there is nose cone end face seal slot, the 2nd sealing ring on the left side of nose cone 6
11 are located in above-mentioned nose cone end face seal slot, have the tapped blind hole being uniformly distributed along the circumference on the right side of measurement end flanges, in spiral shell
There is a measurement end end face of flange seal groove outside line blind hole, the 5th sealing ring 14 is located at the sealing of above-mentioned measurement end end face of flange
In slot；
Collection chamber 3 is a cylinder, and having a section in the middle part of 3 inner cylinder face of collection chamber is the annular boss of rectangle
3a has what the external cylindrical surface of 6 and collection chamber 3 being uniformly distributed along the circumference radially penetrated through to go out on the inner cylinder face of interior annular convex platform 3a
The aperture of stomata 3b, venthole 3b are greater than the outer diameter of jet pipe 17, have an annular convex on the left side of interior annular convex platform 3a
Platform left side positions annular groove 3d, there is an annular boss right side positioning annular groove on the right side of interior annular convex platform 3a
3c has left inside thread segment on the left side of interior annular convex platform 3a, has right internal thread segment on the right of interior annular convex platform 3a；Measurement end 9
The external thread section of right end is screwed into the left inside thread segment of collection chamber 3, and the nose cone external thread section of 6 left end of nose cone is screwed into collection chamber 3
In right internal thread segment；It is disposed on the inner cylinder face of each venthole 3b of collection chamber 3 in 4 waves that a circle is uniformly distributed along the circumference
Static bole 7；
Air intake assembly and measurement component pass through left flexible membrane component and right flexible membrane component formation connection relationship, Zuo Rou
Property diaphragm unit is identical with the structure of right flexible membrane component and positional symmetry；
Left flexible membrane component is made of left flexible membrane 4a, left inside pressure ring 4b and left outside pressure ring 4c；Left flexible membrane 4a
It is the annulus of light sheet manufacture, the shape of its radial section is as follows：It is divided into 3 sections from outside to inside, is outer flat segments respectively
4a1, arc section 4a3 and interior flat segments 4a4, the protrusion direction of arc section 4a3 to the left, have on the right surface of outer flat segments 4a1
Left flexible membrane outer positioning ring shape boss 4a2, has in left flexible membrane on the right surface of interior flat segments 4a4 and positions annular convex platform
4a5；Left flexible membrane 4a is fixed outside left flexible membrane between sonic nozzle 2 and collection chamber 3, the left side of outer ring boss 2e
Position annular convex platform 4a2 is located in the annular boss left side positioning annular groove 3d of collection chamber 3, positioning annular in left flexible membrane
Boss 4a5 is located in the outer ring boss left side positioning annular groove 2d of sonic nozzle 2；Left inside pressure ring 4b is an annulus, left
The left side of inner pressure ring 4b is parallel with right side, and left inside pressure ring 4b covers on the left light tube section of sonic nozzle the 1st of sonic nozzle 2 simultaneously
Clearance fit is kept, the 3rd sealing ring 12 is left inside by the clearance seal between left inside pressure ring 4b and the left light tube section of sonic nozzle the 1st
The left side of pressure ring 4b is bonded with the right side of air inlet pipe 1, and the right side of left inside pressure ring 4b is pushed down straight in left flexible membrane 4a
The left surface of section 4a4；Left outside pressure ring 4c is an annulus, and the left side of left outside pressure ring 4c is parallel with right side, left outside pressure ring 4c
External screw thread be screwed into the left inside thread segment of collection chamber 3, the outer flat segments of left flexible membrane 4a are pushed down in the right side of left outside pressure ring 4c
The left side of the left surface of 4a1, left outside pressure ring 4c is bonded with the right side of measurement end 9, and the 4th sealing ring 13 is by left outside pressure ring 4c's
Clearance seal between 9 right side of left side and measurement end；
Right flexible membrane component is made of right flexible membrane 5a, right inner pressure ring 5b and right outer press ring 5c；Right flexible membrane 5a
Material, shape and size it is identical as left flexible membrane 4a, the shape of the radial section of right flexible membrane 5a is as follows：From outside to inside
Be divided into 3 sections, be outer flat segments 5a1, arc section 5a3 and interior flat segments 5a4 respectively, the protrusion direction of arc section 5a3 to the right, outside
There is right flexible membrane outer positioning ring shape boss 5a2 on the left surface of flat segments 5a1, has the right side on the left surface of interior flat segments 5a4
Annular convex platform 5a5 is positioned in flexible membrane；Right flexible membrane 5a is between sonic nozzle 2 and collection chamber 3, outer ring boss 2e
The right, right flexible membrane outer positioning ring shape boss 5a2 be located at collection chamber 3 annular boss right side positioning annular groove 3c
Interior, positioning annular convex platform 5a5 is located in the outer ring boss right side positioning annular groove 2g of sonic nozzle 2 in right flexible membrane；
Right inner pressure ring 5b is an annulus, and the left side of right inner pressure ring 5b is parallel with right side, and right inner pressure ring 5b is covered in sonic nozzle 2
On the right light tube section of sonic nozzle and keep clearance fit, the 1st sealing ring 10 by right inner pressure ring 5b and the right light tube section of sonic nozzle it
Between clearance seal, the right surface of flat segments 5a4 in right flexible membrane 5a, right inner pressure ring 5b are pushed down in the left side of right inner pressure ring 5b
Right side by loop coil 18 left side compress, right outer press ring 5c is an annulus, the left side and right side of right outer press ring 5c
In parallel, the external screw thread of right outer press ring 5c is screwed into the right internal thread segment of collection chamber 3, and right flexibility is pushed down in the left side of right outer press ring 5c
The right surface of the outer flat segments 5a1 of diaphragm 5a, the right side of right outer press ring 5c are compressed by the left side of nose cone 6；6 jet pipes 17 are distinguished
In 6 venthole 3b of collection chamber 3, jet pipe 17 and venthole 3b keeps coaxial.
The left flexible membrane and right flexible membrane are manufactured using canvas filler rubber, with a thickness of 0.5mm~1.5mm.
The working principle of the invention is：The canvas filler rubber flexible membrane that this pressure decoupling device uses, it is with higher to hold
Pressure energy power, up to 2.5MPa, service life is up to 10000 times.Pressure decoupling device is arranged in inside model, with balance system shape
At parallel-connection structure, aerodynamic force that model generates during the test while the gentle pressure solution coupling device in day is passed to, but due to pressure
The flexible membrane of power decoupling device uses canvas filler rubber, smaller relative to balance rigidity, therefore the model of its receiving may be implemented
Aerodynamic force is smaller, about 0.3% or so；The mechanical characteristic has fabulous stress repeatability, can be tried by pressure calibration
The aerodynamic force for being accurately obtained its receiving is tested, for the accurate amendment to balance data.This pressure decoupling device in structure,
Design has sonic nozzle, so that air-flow flow direction in the present apparatus is transferred 90 degree, liquidates entrance perpendicular to balance axis direction
The measurement end of model ensure that model entrance momentum is zero.
Embodiment
Left flexible membrane and right flexible membrane are manufactured using canvas filler rubber, with a thickness of 1mm.When test, by the one of air inlet pipe 1
End is connected by screw to high-pressure air feed pipeline, and installs sealing ring 16, is in addition connected by screw thread and sonic nozzle 2 for one section,
And sealing ring 15 is installed, the rear and front end of sonic nozzle 2 is respectively arranged front end flexible membrane and rear end flexible membrane, and front end is flexible
The inner end of diaphragm is pressed on the face 2e of sonic nozzle 2 by pressure ring 4b, and centre is equipped with sealing ring 12, rear end flexible membrane
Inner end be pressed on the face 2e of sonic nozzle 2 by pressure ring 5a, centre is equipped with sealing ring 10,4 He of front end flexible membrane
The outboard end of rear end flexible membrane 5 passes through pressure ring 4c respectively and pressure ring 5c is pressed on the end face of collection chamber 3.Nose cone 6 passes through spiral shell
Line and collection chamber 3 connect, and are fitted close with pressure ring 5c, and centre is equipped with sealing ring 11, and measurement end 9 passes through screw thread and collection chamber
3 connections, and be fitted close with pressure ring 4c, centre is equipped with sealing ring 13, and other one section of measurement end 9 is tried by screw and dynamometry
Model to be tested to be connected, centre is equipped with sealing ring 14, jet pipe 17 is finally screwed on by screw thread on the nozzle of sonic nozzle 2, so that
High pressure draught is sprayed perpendicular to axis direction, and measurement end entrance momentum is zero.Static pressure in wave is enclosed in the disposed inboard one of collection chamber 3
Measured hole 7, the measurement of realization flexible membrane inside high-pressure gas pressure, the static bole 8 outside 9 disposed inboard wave of measurement end,
Realize the dynamometry of flexible membrane outside ambient pressure.
Embodiment bearing capacity 2.5MPa, service life are that full stroke is back and forth run 10000 times, are able to satisfy most of push away
The demand of force vector test high-pressure air feed.Than controlling 0.1% or so, flexible membrane can be held for the embodiment and the rigidity of balance
The model aerodynamic force received is also 0.3% or so, and with fabulous stress repeatability, repeatability precision meets state within 2N
Army's mark requires.The example structure deft design, measurement end entrance are liquidated by sonic nozzle, guarantee that momentum is zero, and can be with
According to different operating condition of test, it being convenient for changing flexible membrane, without will affect the gap value between each system unit, being had good
Engineering application value, be successfully applied to wind tunnel test.
Claims (2)
1. a kind of pressure decoupling device for influencing dynamometry model for high speed jet, it is characterised in that：It include air inlet pipe (1),
Sonic nozzle (2), collection chamber (3), left flexible membrane component, right flexible membrane component, nose cone (6), measurement end (9), the 1st sealing
Enclose (10), the 2nd sealing ring (11), the 3rd sealing ring (12), the 4th sealing ring (13), the 5th sealing ring (14), the 6th sealing ring (15),
7th sealing ring (16), 6 jet pipes (17) and loop coil (18)；
By air inlet pipe (1), sonic nozzle (2), the 1st sealing ring (10), the 3rd sealing ring (12), the 6th sealing ring (15), the 7th sealing
It encloses (16), jet pipe (17) and loop coil (18) and constitutes air intake assembly；
Air inlet pipe (1) is a cylinder, and the position on air inlet pipe (1) external cylindrical surface close to left port has one to have bolt hole
Air inlet pipe flange, have an air inlet pipe end face of flange seal groove, the 7th sealing ring (16) position on the left side of air inlet pipe flange
In in above-mentioned air inlet pipe end face of flange seal groove, there is air inlet pipe internal thread segment in the right output port of air inlet pipe (1), in air inlet pipe
There is one section of air inlet pipe unthreaded hole section on the left side of thread segment, there is the unthreaded hole section sealing of annular on the inner cylinder face of air inlet pipe unthreaded hole section
Slot, the 6th sealing ring (15) are located in above-mentioned unthreaded hole section seal groove；
Sonic nozzle (2) is right end closing, the open cylinder in left end, has one in the middle part of sonic nozzle (2) external cylindrical surface
A section is the outer ring boss (2e) of rectangle, have on the external cylindrical surface of outer ring boss (2e) be uniformly distributed along the circumference 6 with
The sonic nozzle threaded hole (2f) that the inner hole of sonic nozzle (2) radially penetrates through, has one on the right side of outer ring boss (2e)
A outer ring boss right side positions annular groove (2g), on the external cylindrical surface of sonic nozzle (2), the right side of outer ring boss (2e)
While there is one section of right light tube section of sonic nozzle, there is the right sealing of annular sonic nozzle on the right of the right light tube section of the sonic nozzle
Slot (2h), the 1st sealing ring (10) is located in the right seal groove of above-mentioned sonic nozzle (2h), on the right side of the right seal groove of sonic nozzle (2h)
While being the right external thread section of sonic nozzle (2j)；There is an outer ring boss left side fixed on the left side of outer ring boss (2e)
Position annular groove (2d), on the external cylindrical surface of sonic nozzle (2), the left side of outer ring boss (2e) have one section of sonic nozzle the 1st
Left light tube section has the left seal groove of annular sonic nozzle (2c), the 3rd sealing ring on the left light tube section of sonic nozzle the 1st
(12) it is located in the left seal groove of above-mentioned sonic nozzle (2c), has sonic nozzle left outside on the left side of the left light tube section of sonic nozzle the 1st
Thread segment (2b) is the left light tube section (2a) of sonic nozzle the 2nd on the left side of the left outside thread segment of sonic nozzle (2b)；Sonic nozzle is left
External thread section (2b) is screwed into the air inlet pipe internal thread segment of air inlet pipe (1), and the left light tube section (2a) of sonic nozzle the 2nd is inserted into air inlet pipe
(1) in air inlet pipe unthreaded hole section and clearance fit is kept, loop coil (18) is screwed on the right external thread section of sonic nozzle (2j)；Jet pipe
It (17) is with externally threaded cylinder, the external screw thread of 6 jet pipes (17) is screwed into 6 sonic nozzle spiral shells of sonic nozzle (2) respectively
In pit (2f)；
By collection chamber (3), nose cone (6), measurement end (9), the 2nd sealing ring (11), the 4th sealing ring (13), the 5th sealing ring (14) structure
At measurement component；
Measurement end (9) is the cylinder that a left end has measurement end external thread section with measurement end flanges, right end, measurement end (9)
The aperture of inner hole is greater than the outer diameter of sonic nozzle (2) cylinder, and it is circumferentially equal that a circle is disposed on the inner cylinder face of measurement end (9)
The outer static bole (8) of 4 waves of cloth has a measurement end end face seal slot, the 4th sealing on the right side of measurement end (9)
Circle (13) is located in above-mentioned measurement end end face seal slot；Nose cone (6) is that a left end is opened wide, right output port is by a circular cone face closure
Cylinder, the left end of nose cone (6) external cylindrical surface have nose cone external thread section, have nose cone end face on the left side of nose cone (6)
Seal groove, the 2nd sealing ring (11) are located in above-mentioned nose cone end face seal slot, have on the right side of measurement end flanges circumferentially
The tapped blind hole of cloth, there is a measurement end end face of flange seal groove outside tapped blind hole, and the 5th sealing ring (14) is located at above-mentioned
In measurement end end face of flange seal groove；
Collection chamber (3) is a cylinder, and having a section in the middle part of collection chamber (3) inner cylinder face is the annular boss of rectangle
(3a), there is 6 be uniformly distributed along the circumference on the inner cylinder face of interior annular convex platform (3a) and the external cylindrical surface of collection chamber (3) radially passes through
Logical venthole (3b), the aperture of venthole (3b) is greater than the outer diameter of jet pipe (17), on the left side of interior annular convex platform (3a)
There is annular boss left side positioning annular groove (3d), has an annular convex on the right side of interior annular convex platform (3a)
Platform right side positions annular groove (3c), has left inside thread segment on the left side of interior annular convex platform (3a), in interior annular convex platform (3a)
There is right internal thread segment on the right；The external thread section of measurement end (9) right end is screwed into the left inside thread segment of collection chamber (3), and nose cone (6) is left
The nose cone external thread section at end is screwed into the right internal thread segment of collection chamber (3)；In the inner circle of each venthole (3b) of collection chamber (3)
Static bole (7) in 4 waves that a circle is uniformly distributed along the circumference is disposed on cylinder；
Air intake assembly and measurement component pass through left flexible membrane component and right flexible membrane component formation connection relationship, left flexible membrane
Piece component is identical with the structure of right flexible membrane component and positional symmetry；
Left flexible membrane component is made of left flexible membrane (4a), left inside pressure ring (4b) and left outside pressure ring (4c)；Left flexible membrane
(4a) is the annulus of light sheet manufacture, and the shape of its radial section is as follows：It is divided into 3 sections from outside to inside, is outer flat respectively
Straight section (4a1), arc section (4a3) and interior flat segments (4a4), the protrusion direction of arc section (4a3) to the left, in outer flat segments
There is left flexible membrane outer positioning ring shape boss (4a2) on the right surface of (4a1), has a left side on the right surface of interior flat segments (4a4)
Annular convex platform (4a5) is positioned in flexible membrane；Left flexible membrane (4a) is located between sonic nozzle (2) and collection chamber (3), outer ring
The left side of shape boss (2e), left flexible membrane outer positioning ring shape boss (4a2) are located at the annular boss left side of collection chamber (3)
It positions in annular groove (3d), positioning annular convex platform (4a5) is located at the outer ring boss left end of sonic nozzle (2) in left flexible membrane
Face positions in annular groove (2d)；Left inside pressure ring (4b) is an annulus, and the left side of left inside pressure ring (4b) is parallel with right side, left
Inner pressure ring (4b) covers on the left light tube section of sonic nozzle the 1st of sonic nozzle (2) and keeps clearance fit, the 3rd sealing ring (12)
By the clearance seal between left inside pressure ring (4b) and the left light tube section of sonic nozzle the 1st, the left side of left inside pressure ring (4b) and air inlet
The right side fitting of (1) is managed, the left-handed watch of left flexible membrane (4a) interior flat segments (4a4) is pushed down in the right side of left inside pressure ring (4b)
Face；Left outside pressure ring (4c) is an annulus, and the left side of left outside pressure ring (4c) is parallel with right side, the outer spiral shell of left outside pressure ring (4c)
Line is screwed into the left inside thread segment of collection chamber (3), and left flexible membrane (4a) outer flat segments are pushed down in the right side of left outside pressure ring (4c)
The left side of the left surface of (4a1), left outside pressure ring (4c) is bonded with the right side of measurement end (9), and the 4th sealing ring (13) will be left outside
Clearance seal between the left side and measurement end (9) right side of pressure ring (4c)；
Right flexible membrane component is made of right flexible membrane (5a), right inner pressure ring (5b) and right outer press ring (5c)；Right flexible membrane
Material, the shape and size of (5a) are identical as left flexible membrane (4a), and the shape of the radial section of right flexible membrane (5a) is as follows：
It is divided into 3 sections from outside to inside, is outer flat segments (5a1), arc section (5a3) and interior flat segments (5a4) respectively, arc section (5a3)
Protrusion direction to the right, has right flexible membrane outer positioning ring shape boss (5a2) on the left surface of outer flat segments (5a1), puts down inside
Have in right flexible membrane on the left surface of straight section (5a4) and positions annular convex platform (5a5)；Right flexible membrane (5a) is located at sonic nozzle
(2) between collection chamber (3), the right of outer ring boss (2e), right flexible membrane outer positioning ring shape boss (5a2) is located at gas collection
In annular boss right side positioning annular groove (3c) of room (3), positioning annular convex platform (5a5) is located at velocity of sound in right flexible membrane
In outer ring boss right side positioning annular groove (2g) of nozzle (2)；Right inner pressure ring (5b) is an annulus, right inner pressure ring (5b)
Left side it is parallel with right side, between right inner pressure ring (5b) covers on the right light tube section of sonic nozzle of sonic nozzle (2) and keeps
Gap cooperation, the 1st sealing ring (10) is by the clearance seal between right inner pressure ring (5b) and the right light tube section of sonic nozzle, right inner pressure ring
The right surface of right flexible membrane (5a) interior flat segments (5a4) is pushed down in the left side of (5b), and the right side of right inner pressure ring (5b) is by spiral shell
The left side of ring (18) compresses, and right outer press ring (5c) is an annulus, and the left side of right outer press ring (5c) is parallel with right side, right
The external screw thread of outer press ring (5c) is screwed into the right internal thread segment of collection chamber (3), and right flexibility is pushed down in the left side of right outer press ring (5c)
The right side on the right surface of diaphragm (5a) outer flat segments (5a1), right outer press ring (5c) is compressed by the left side of nose cone (6)；6 sprays
Pipe (17) is located in 6 ventholes (3b) of collection chamber (3), and jet pipe (17) keeps coaxial with venthole (3b).
2. pressure decoupling device according to claim 1, it is characterised in that：The left flexible membrane and right flexible membrane
Manufactured using canvas filler rubber, left flexible membrane and right flexible membrane with a thickness of 0.5mm~1.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161925.XA CN106679923B (en) | 2016-12-15 | 2016-12-15 | A kind of pressure decoupling device influencing dynamometry model for high speed jet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161925.XA CN106679923B (en) | 2016-12-15 | 2016-12-15 | A kind of pressure decoupling device influencing dynamometry model for high speed jet |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106679923A CN106679923A (en) | 2017-05-17 |
| CN106679923B true CN106679923B (en) | 2018-11-16 |
Family
ID=58869081
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611161925.XA Active CN106679923B (en) | 2016-12-15 | 2016-12-15 | A kind of pressure decoupling device influencing dynamometry model for high speed jet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106679923B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109387370B (en) * | 2018-11-14 | 2023-12-22 | 中国空空导弹研究院 | Direct-connection type high-altitude simulation test axial force-free air inlet system of ramjet engine |
| CN110702367B (en) * | 2019-11-01 | 2024-03-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Continuous pressure measuring device for shielding position of parallel model of hypersonic wind tunnel |
| CN110779679B (en) * | 2019-11-21 | 2021-01-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for correcting influence of pressure compensation chamber of calibration box on high-precision force measuring balance |
| CN113479343B (en) * | 2021-07-05 | 2023-12-19 | 中国航空工业集团公司沈阳空气动力研究所 | Integrated test method for air inlet channel and force measurement |
| CN115493802B (en) * | 2022-11-18 | 2023-03-10 | 中国空气动力研究与发展中心空天技术研究所 | Internal and external flow aerodynamic decoupling structure of body propulsion integrated model and working installation method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201461317U (en) * | 2009-07-17 | 2010-05-12 | 王劲 | Rectifying and vibration-absorbing device of reciprocating compressor outlet pipeline |
| CN102539053A (en) * | 2010-12-27 | 2012-07-04 | 中国航空工业第一集团公司沈阳空气动力研究所 | Ring type balance and corrugated pipe system |
| CN102828851A (en) * | 2012-08-16 | 2012-12-19 | 北京航空航天大学 | Cold flow test device for scaling linear plug type spray pipe carrier |
| CN105865742A (en) * | 2016-04-07 | 2016-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test aero-engine thrust vector jet pipe steering system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08226867A (en) * | 1995-02-22 | 1996-09-03 | Mitsubishi Heavy Ind Ltd | Piston-launching apparatus |
-
2016
- 2016-12-15 CN CN201611161925.XA patent/CN106679923B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201461317U (en) * | 2009-07-17 | 2010-05-12 | 王劲 | Rectifying and vibration-absorbing device of reciprocating compressor outlet pipeline |
| CN102539053A (en) * | 2010-12-27 | 2012-07-04 | 中国航空工业第一集团公司沈阳空气动力研究所 | Ring type balance and corrugated pipe system |
| CN102828851A (en) * | 2012-08-16 | 2012-12-19 | 北京航空航天大学 | Cold flow test device for scaling linear plug type spray pipe carrier |
| CN105865742A (en) * | 2016-04-07 | 2016-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test aero-engine thrust vector jet pipe steering system |
Non-Patent Citations (1)
| Title |
|---|
| 低速风洞推力矢量试验技术研究;贾毅;《试验流体力学》;20141231;第28卷(第6期);第92-97页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106679923A (en) | 2017-05-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106679923B (en) | A kind of pressure decoupling device influencing dynamometry model for high speed jet | |
| CN111122104A (en) | Separation wind tunnel test device for plane-symmetric hypersonic aircraft hood | |
| CN109250149B (en) | Wind tunnel test device for separation simulation of air suction type hypersonic vehicle fairing | |
| CN108254155B (en) | Rail-controlled lateral jet flow force measurement test structure for large slenderness ratio | |
| CN106840591B (en) | A kind of experimental rig directly measuring jet flow thrust | |
| CN104033279B (en) | A kind of dual vector jet pipe | |
| CN103696873A (en) | Axisymmetric vectoring nozzle with good stealth function | |
| CN110595729A (en) | Multi-jet flow interference test device for hypersonic wind tunnel surface symmetry model | |
| CN108680333B (en) | Rotary driving device for rotary aerodynamic effect wind tunnel test | |
| CN114235321B (en) | Wind tunnel force measurement experimental device integrating gas rudder and spray pipe | |
| CN114001601B (en) | Ventilation load reduction and posture adjustment device for high-speed cross-medium water inlet and adjustment method thereof | |
| CN105588702B (en) | A kind of low-speed wind tunnel model drive flight experiment dynamical system | |
| CN107218156A (en) | Hybrid rocket engine pintle formula becomes larynx footpath Effuser device | |
| CN111776199A (en) | Turbojet air supply system for jet flight control technology | |
| CN113588202B (en) | Multi-body thermal separation test simulation device and test method for high-altitude high-speed thin environment | |
| CN114486166B (en) | Model and system for control surface jet flow interference force measurement test | |
| CN211178915U (en) | Separation wind tunnel test device for plane-symmetric hypersonic aircraft hood | |
| CN201983920U (en) | Segmentation jet tube for supersonic wind tunnel | |
| CN111348169A (en) | Integrated design method for circumferential four-inlet-channel layout of conical aircraft forebody | |
| CN104033274B (en) | The axial symmetry of a kind of single actuating system is received and is expanded jet pipe | |
| CN115436009B (en) | Jet pipe thrust measurement test system with integrally designed afterbody and jet pipe | |
| CN209400562U (en) | A kind of pitot | |
| CN208947639U (en) | Flow tunnel testing device for air suction type hypersonic vehicle radome fairing separation simulation | |
| CN115931283B (en) | Accurate measurement device for thrust characteristics of double culvert spray pipe | |
| US9963999B2 (en) | Aircraft propulsion assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |