CN112894281B - Method for machining aerospace friction resistance sensor gauge head structure based on multiple machining datum planes - Google Patents
Method for machining aerospace friction resistance sensor gauge head structure based on multiple machining datum planes Download PDFInfo
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- CN112894281B CN112894281B CN202110100668.3A CN202110100668A CN112894281B CN 112894281 B CN112894281 B CN 112894281B CN 202110100668 A CN202110100668 A CN 202110100668A CN 112894281 B CN112894281 B CN 112894281B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H1/00—Electrical discharge machining, i.e. removing metal with a series of rapidly recurring electrical discharges between an electrode and a workpiece in the presence of a fluid dielectric
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- B—PERFORMING OPERATIONS; TRANSPORTING
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Abstract
The invention discloses a method for processing a head structure of an aerospace friction resistance sensor based on multiple processing reference surfaces. The processing method is suitable for a gauge head structure of an aerospace friction resistance sensor based on a K-shaped pipe differential pressure measurement principle, a gauge head base body of the gauge head structure is an eccentric round table structure with a small upper part and a large lower part, a vertical straight hole and an inclined hole which is inclined downwards are arranged on the upper surface of the gauge head structure along the airflow direction, and the inclined hole has an inclination angle alpha; the straight hole is provided with a bottom connecting straight hole I; the inclined hole is provided with a bottom connecting straight hole II. The processing method comprises the following steps: processing auxiliary fixtures, processing reference surface I, processing reference surface III, the straight hole of processing, processing reference surface II, the auxiliary fixtures is got rid of to the inclined hole of processing, and straight hole I is connected to the processing bottom and straight hole II is connected to the bottom, the type of repairing. According to the processing method, the processing of two elongated holes with smaller included angles on the same plane is realized by adopting multiple processing reference surfaces, the processing difficulty is reduced, the processing precision is improved, and the measurement precision of the aerospace friction resistance sensor is further improved.
Description
Technical Field
The method belongs to the technical field of hypersonic wind tunnel tests, and particularly relates to a method for machining a head structure of an aerospace friction resistance sensor based on multiple machining reference surfaces.
Background
Surface friction resistance, friction resistance for short, refers to the tangential force generated by a viscous fluid flowing across the surface of an object. In aerodynamics, friction resistance is an important physical quantity. In the actual engineering design, the friction resistance is an important component of the aerodynamic force of a modern hypersonic aircraft (aircraft for short), particularly, the friction resistance is greatly increased by a turbulent boundary layer, the effective range of the aircraft is directly influenced, and the performance of the aircraft is severely restricted.
Under the condition of hypersonic flight, when the boundary layer on the surface of the aircraft is twisted, the friction resistance and the heat flow of the aircraft are increased by 3-5 times, and the aerodynamic performance, the safety and the thermal protection system of the aircraft are seriously influenced. Accurate prediction of the friction resistance can provide important support for aircraft aerodynamic performance and thermal protection system design. For a near space hypersonic aircraft with the flying height of below 50-80 km, due to the fact that the local part of the aircraft has a rarefied nonequilibrium effect caused by factors such as high temperature and strong gradient, an N-S equation based on a continuous medium fails, and friction prediction is inaccurate. Local shock wave interference almost appears in all aircrafts, local high heat flow, high dynamic friction resistance and shear stress can be caused, and the local thermal environment is obviously influenced by the shock wave interference, so that the aircraft structure can be damaged. Therefore, accurate prediction of the friction drag under hypersonic flight conditions is of paramount importance for aircraft research.
At present, the research on the measurement of the friction under hypersonic Flight conditions is less, and the european EXPERT program [ light measurement technology requirements for EXPERT, the ESA in light aerotherm research project.55th International adaptive convergence, Vancouver, Canada,2004[ C ] ] has developed the research on the measurement technology of the friction based on the K-tube differential pressure measurement principle, and the aerospace friction sensor used in the research on the measurement technology of the friction has a straight hole and an inclined hole (the inclined hole is in front and behind), and the friction measurement research is carried out by the differential pressure, mainly used for the object plane flow diagnosis, suitable for the slip and thin flow area, and also suitable for the development of the laminar continuous flow area, and planning the hypersonic reentry Flight test. However, the inclined hole in the aerospace friction resistance sensor has large disturbance to the straight hole, data correction is difficult, the aerospace friction resistance sensor has large volume, and the aerospace friction resistance sensor is not suitable for being installed at a position with a large surface slope and a small installation space of an aircraft.
Inventor's group has developed a neotype space flight friction drag sensor based on K venturi tube differential pressure measurement, utilize K venturi tube differential pressure measurement principle, on the upper surface of the gauge outfit base member of gauge outfit structure, along the gas flow direction, it has straight hole and inclined hole to open in proper order, straight hole is in the front promptly, the inclined hole is after, hole centre-to-centre spacing is more than or equal to 5mm, effectively reduced the flow interference between straight hole and the inclined hole, improve the differential pressure measurement precision between straight hole and the inclined hole, and then promote and rub and hinder measuring precision. And the distribution mode that the straight hole is in the front and the inclined hole is in the back makes the hole center distance between the straight hole and the inclined hole much smaller than the distribution mode that the inclined hole is in the front and the straight hole is in the back, and the gauge head base body can be conveniently realized to be an eccentric round table structure with a small upper part and a large lower part, so that the size and the mass of the aerospace friction resistance sensor are effectively reduced, and the aerospace friction resistance sensor is favorable for flying and carrying. Meanwhile, the small eccentric round table positioned above can be conveniently arranged on the surface of the model according to the measurement requirement to carry out friction measurement, thereby effectively enlarging the measurement area.
Neotype space flight friction sensor based on K venturi tube differential pressure measurement need be at the coplanar processing two elongated holes that are less contained angle, consequently, space flight friction sensor's gauge outfit structure carries out high accuracy manufacturing and has great degree of difficulty. At present, a method for processing a multi-processing-reference-surface-based aerospace friction resistance sensor gauge head structure special for an aerospace friction resistance sensor based on K-shaped tube differential pressure measurement needs to be developed urgently.
Disclosure of Invention
The invention aims to provide a method for processing a head structure of an aerospace friction resistance sensor based on multiple processing reference surfaces.
The method for processing the spaceflight friction resistance sensor gauge outfit structure based on the multiple processing datum planes is suitable for processing the gauge outfit structure of the spaceflight friction resistance sensor based on K-shaped tube differential pressure measurement, a gauge outfit base body of the gauge outfit structure is an eccentric round table structure with a small upper part and a large lower part, a vertical straight hole is arranged on the upper surface of the gauge outfit base body along the front of an airflow direction, an inclined hole which is inclined downwards is arranged on the rear of the airflow direction, and an included angle between the inclined hole and the horizontal direction is an inclined angle alpha; a vertical bottom connecting straight hole I communicated with the straight hole is arranged below the straight hole; a vertical bottom connecting straight hole II communicated with the inclined hole is arranged below the inclined hole; the processing method comprises the following steps:
a. processing an auxiliary tool; the auxiliary tool comprises a gauge head base body and a square column body below the gauge head base body which are integrally processed;
b. processing a reference surface I; carrying out surface machining on the lower surface of a square column body of the auxiliary tool to obtain a reference surface I;
c. processing a reference surface III; taking the reference surface I as a reference, and carrying out surface machining on the upper surface of an upper circular table of the gauge head base body of the auxiliary tool to obtain a reference surface III;
d. processing a straight hole; with reference plane III as the benchmark, process vertical straight hole at the upper surface of auxiliary fixtures's gauge outfit base member, the depth-diameter ratio of straight hole is 5: 1; determining the circle center of the inclined hole on the connecting line of the circle center of the straight hole and the center of the upper round platform;
e. processing a reference surface II; setting an inclination angle alpha, cutting a square column of an auxiliary tool into an auxiliary tool I with a gauge outfit matrix and a residual auxiliary tool II in a linear cutting mode on the square column of the auxiliary tool, and performing surface machining on an inclined surface of the auxiliary tool I to obtain a reference surface II;
f. processing an inclined hole; machining an inclined hole with the diameter equal to that of the straight hole by taking the reference surface II as a reference;
g. removing the residual square column on the auxiliary tool I; removing the residual square column on the auxiliary tool I by taking the reference surface III as a reference;
h. processing a bottom connecting straight hole I and a bottom connecting straight hole II; processing a vertical bottom connecting straight hole I and a vertical bottom connecting straight hole II by taking the reference surface III as a reference;
i. modifying the model; and (3) modifying the straight hole, the inclined hole, the bottom connecting straight hole I and the bottom connecting straight hole II by utilizing linear cutting or electric sparks to finish the machining of the gauge head structure.
Further, the inclination angle α ranges from 20 ° to 30 °.
Furthermore, the hole center distance of the straight holes and the inclined holes is more than or equal to 5 mm.
Furthermore, the diameters of the straight hole and the inclined hole are both 2mm, and the depth-diameter ratio is 5: 1.
The processing datum plane I in the processing method of the aerospace friction resistance sensor gauge head structure based on the multiple processing datum planes is used as a main processing datum plane and is used for realizing processing of a gauge head substrate, a processing datum plane II and a straight hole.
The processing datum plane II in the processing method of the aerospace friction resistance sensor gauge head structure based on the multiple processing datum planes is used as a secondary processing datum plane and is used for realizing inclined hole processing.
The processing datum plane III in the processing method of the aerospace friction resistance sensor gauge head structure based on the multiple processing datum planes is used as a secondary processing datum plane for removing and processing the auxiliary tool I, and is also used for processing the bottom connecting straight hole I and processing the bottom connecting straight hole II.
According to the processing method of the aerospace friction resistance sensor gauge head structure based on the multiple processing reference surfaces, the multiple processing reference surface method is adopted, so that two elongated holes with smaller included angles are processed on the same plane, the processing difficulty of the aerospace friction resistance sensor gauge head structure is reduced, the processing precision is improved, and the measurement precision of the aerospace friction resistance sensor is further improved.
Drawings
Fig. 1 is a perspective view of a head structure of a spaceflight friction sensor of a processing object in the processing method of the head structure of the spaceflight friction sensor based on multiple processing reference surfaces;
FIG. 2 is a cross-sectional view of a head structure of a spaceflight friction resistance sensor of a processing object based on a multi-processing reference surface spaceflight friction resistance sensor head structure processing method of the invention;
FIG. 3 is a perspective view of a straight hole machining and a multi-datum plane arranged in the machining method of the aerospace friction resistance sensor gauge head structure based on the multi-datum plane;
FIG. 4 is a cross sectional view of a straight hole machining and a multi-datum plane arranged in the machining method of the aerospace friction resistance sensor gauge head structure based on the multi-datum plane;
FIG. 5 is a schematic diagram of inclined hole machining in the machining method of the aerospace friction resistance sensor gauge head structure based on multiple machining reference surfaces;
FIG. 6 is a schematic diagram of auxiliary tool removal in the method for machining a head structure of an aerospace friction resistance sensor based on multiple machining reference surfaces according to the invention;
fig. 7 is a schematic view of processing a bottom connection straight hole in the method for processing the aerospace friction resistance sensor gauge head structure based on multiple processing reference surfaces.
Fig. 8 is a schematic connection diagram of the aerospace friction resistance sensor based on K-shaped tube differential pressure measurement in embodiment 1.
In the figure, 1, a gauge head structure 2, a high-precision differential pressure micro-pressure transmitter 3, an auxiliary tool I4, an auxiliary tool II 5, a machining datum plane I6, a machining datum plane II 7, a machining datum plane III 8 and a micro pressure sensor are arranged;
101. the gauge head base body 102, the straight hole 103, the inclined hole 104, the bottom connecting straight hole I105 and the bottom connecting straight hole II.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
The method for processing the aerospace friction resistance sensor gauge outfit structure based on multiple processing reference surfaces is suitable for processing the gauge outfit structure 1 of the aerospace friction resistance sensor based on K-shaped tube differential pressure measurement as shown in figures 1 and 2, a gauge outfit base body 101 of the gauge outfit structure 1 is an eccentric circular truncated cone structure with a small upper part and a large lower part, a vertical straight hole 102 is arranged on the upper surface of the gauge outfit base body 101 along the front of an airflow direction, an inclined hole 103 which is inclined downwards is arranged on the rear of the airflow direction, and the included angle between the inclined hole 103 and the horizontal direction is an inclined angle alpha; a vertical bottom connecting straight hole I104 communicated with the straight hole 102 is arranged below the straight hole 102; a vertical bottom connecting straight hole II 105 communicated with the inclined hole 103 is arranged below the inclined hole 103; the processing method comprises the following steps:
a. processing an auxiliary tool; the auxiliary tool comprises a gauge head base body 101 and a square column body below the gauge head base body, wherein the gauge head base body 101 and the square column body are integrally machined as shown in figures 3 and 4;
b. processing a reference surface I5; carrying out surface machining on the lower surface of the square column of the auxiliary tool to obtain a reference surface I5;
c. processing a reference surface III 7; with the reference surface I5 as a reference, performing surface machining on the upper surface of the upper circular table of the gauge head base body 101 of the auxiliary tool to obtain a reference surface III 7;
d. processing a straight hole 102; with the reference surface III 7 as a reference, a vertical straight hole 102 is processed on the upper surface of a gauge head base body 101 of the auxiliary tool, and the depth-diameter ratio of the straight hole 102 is 5: 1; determining the circle center of the inclined hole 103 on the connecting line of the circle center of the straight hole 102 and the center of the upper circular truncated cone;
e. processing a reference surface II 6; setting an inclination angle alpha, cutting a square column of an auxiliary tool into an auxiliary tool I3 with a gauge outfit matrix 101 and a residual auxiliary tool II 4 by adopting a linear cutting mode on the square column of the auxiliary tool, and performing surface machining on the inclined surface of the auxiliary tool I3 to obtain a reference surface II 6;
f. machining an inclined hole 103; as shown in fig. 5, an inclined hole 103 having the same diameter as that of the straight hole 102 is formed with reference to the reference plane ii 6;
g. removing the residual square column on the auxiliary tool I3; as shown in fig. 6, the remaining square column on the auxiliary tool i 3 is removed with the reference plane iii 7 as a reference;
h. processing a bottom connecting straight hole I104 and a bottom connecting straight hole II 105; as shown in fig. 7, a vertical bottom connecting straight hole i 104 and a vertical bottom connecting straight hole ii 105 are processed by taking a reference plane iii 7 as a reference;
i. modifying the shape; and (3) modifying the straight hole 102, the inclined hole 103, the bottom connecting straight hole I104 and the bottom connecting straight hole II 105 by utilizing linear cutting or electric sparks to finish the machining of the gauge outfit structure 1.
Further, the inclination angle α ranges from 20 ° to 30 °.
Furthermore, the hole center distance between the straight hole 102 and the inclined hole 103 is more than or equal to 5 mm.
Furthermore, the diameters of the straight hole 102 and the inclined hole 103 are both 2mm, and the depth-diameter ratio is 5: 1.
Example 1
The gauge outfit structure 1 diameter of the space flight friction resistance sensor of this embodiment is 30mm, highly is 17mm, and gauge outfit structure 1's little boss diameter is 20mm, highly is 3mm, and straight hole 102 and inclined hole 103 diameter are 2mm, depth-diameter ratio is 5: 1. the center distance between the two holes is 5mm, the inclination angle of the inclined hole 103 is 30 degrees, the differential pressure measuring range of the adopted high-precision differential pressure micro-pressure transmitter 2 is 0-100 Pa, the measuring precision is 0.07 percent, and the absolute pressure measuring range of the adopted micro-pressure sensor 8 is 0-5000 Pa, and the measuring precision is 0.5 percent.
The installation process is as follows:
as shown in fig. 8, a straight hole 102 of a gauge head structure 1 of the aerospace friction resistance sensor based on K-shaped tube differential pressure measurement is connected to an inlet end of a three-way joint through a connecting tube i and a pressure measuring hose i in sequence, one outlet end of the three-way joint is connected to a measurement port i of a high-precision differential pressure micro 2-pressure transmitter through a pressure measuring hose ii, and the other outlet end of the three-way joint is connected to a micro pressure sensor 8; the inclined hole 103 is connected to a measurement port II of the high-precision differential pressure micro-pressure transmitter 2 sequentially through a connecting pipe II and a pressure measuring hose III.
Before the test, the sensitivity coefficient curve of the aerospace friction resistance sensor is determined by the following steps:
a. selecting typical friction test state parameters and the appearance and the size of a test model;
b. developing numerical simulation, and establishing a correlation mathematical model between the pressure difference and the friction resistance of the aerospace friction resistance sensor;
c. selecting a high-precision MEMS friction resistance sensor to carry out a contrast wind tunnel test, correcting the correlation mathematical model according to the contrast test result, and determining the sensitivity coefficient curve of the aerospace friction resistance sensor.
During testing, holes are formed in the surface of the wind tunnel test model according to the size of the small boss of the gauge outfit structure 1, the aerospace friction resistance sensor is placed in the inner cavity of the wind tunnel test model, the small boss of the gauge outfit structure 1 is clamped in the holes from inside to outside, and the surface of the small boss is in smooth transition with the surface of the wind tunnel test model.
Although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, but it can be applied to various fields suitable for the present invention. It will be apparent to those skilled in the art that additional modifications and adaptations can be readily made thereto without departing from the principles of the invention, and it is therefore intended that the invention not be limited to the specific details and illustrations contained herein, except insofar as they are within the scope of the appended claims and their equivalents.
Claims (4)
1. The method for processing the aerospace friction resistance sensor gauge head structure based on multiple processing reference surfaces is characterized in that the method is suitable for processing the gauge head structure (1) of the aerospace friction resistance sensor based on K-shaped tube differential pressure measurement, a gauge head base body (101) of the gauge head structure (1) is an eccentric circular truncated cone structure with a small top and a large bottom, a vertical straight hole (102) is formed in the upper surface of the gauge head base body (101) in the front of an airflow direction, an inclined hole (103) which is inclined downwards is formed in the rear of the airflow direction, and the included angle between the inclined hole (103) and the horizontal direction is an inclined angle alpha; a vertical bottom connecting straight hole I (104) communicated with the straight hole (102) is arranged below the straight hole (102); a vertical bottom connecting straight hole II (105) communicated with the inclined hole (103) is arranged below the inclined hole (103); the processing method comprises the following steps:
a. processing an auxiliary tool; the auxiliary tool comprises a gauge head base body (101) and a square column body below the gauge head base body, wherein the gauge head base body and the square column body are integrally machined;
b. machining a reference surface I (5); carrying out surface machining on the lower surface of the square column body of the auxiliary tool to obtain a reference surface I (5);
c. a machining reference surface III (7); with the reference surface I (5) as a reference, performing surface machining on the upper surface of an upper circular table of a gauge head base body (101) of the auxiliary tool to obtain a reference surface III (7);
d. machining a straight hole (102); with the reference surface III (7) as a reference, processing a vertical straight hole (102) on the upper surface of a gauge outfit base body (101) of the auxiliary tool, wherein the depth-diameter ratio of the straight hole (102) is 5: 1; determining the circle center of the inclined hole (103) on the connecting line of the circle center of the straight hole (102) and the center of the upper round platform;
e. processing a reference surface II (6); setting an inclination angle alpha, cutting a square column into an auxiliary tool I (3) with a gauge head base body (101) and a residual auxiliary tool II (4) by adopting a linear cutting mode on the square column of the auxiliary tool, and performing surface machining on the inclined surface of the auxiliary tool I (3) to obtain a reference surface II (6);
f. machining an inclined hole (103); machining an inclined hole (103) with the diameter equal to that of the straight hole (102) by taking the reference surface II (6) as a reference;
g. removing the residual square columns on the auxiliary tool I (3); removing the residual square column on the auxiliary tool I (3) by taking the reference surface III (7) as a reference;
h. processing a bottom connecting straight hole I (104) and a bottom connecting straight hole II (105); processing a vertical bottom connecting straight hole I (104) and a vertical bottom connecting straight hole II (105) by taking a reference surface III (7) as a reference;
i. modifying the model; performing shape modification on a straight hole (102), an inclined hole (103), a bottom connecting straight hole I (104) and a bottom connecting straight hole II (105) by utilizing linear cutting or electric sparks to complete machining of the gauge head structure (1);
the machining datum plane I (5) is used as a main machining datum plane and is used for machining the gauge head base body, the machining datum plane II (6) and the straight hole; the machining reference surface II (6) is used as a secondary machining reference surface for realizing inclined hole machining; and the machining datum plane III (7) is used as a secondary machining datum plane for realizing the removal machining of the auxiliary tool I and also used for machining the bottom connecting straight hole I and machining the bottom connecting straight hole II.
2. The method for processing the aerospace friction resistance sensor gauge outfit structure based on multiple processing datum planes according to claim 1, wherein: the inclination angle alpha ranges from 20 degrees to 30 degrees.
3. The method for processing the aerospace friction resistance sensor gauge outfit structure based on multiple processing datum planes according to claim 1, wherein: the hole center distance of the straight hole (102) and the inclined hole (103) is more than or equal to 5 mm.
4. The method for processing the aerospace friction resistance sensor gauge outfit structure based on multiple processing datum planes according to claim 1, wherein: the diameters of the straight hole (102) and the inclined hole (103) are both 2mm, and the depth-diameter ratio of the inclined hole (103) is 5: 1.
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