CN117906903A - Micro aerodynamic resistance measuring device and use method thereof - Google Patents
Micro aerodynamic resistance measuring device and use method thereof Download PDFInfo
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- CN117906903A CN117906903A CN202410306851.2A CN202410306851A CN117906903A CN 117906903 A CN117906903 A CN 117906903A CN 202410306851 A CN202410306851 A CN 202410306851A CN 117906903 A CN117906903 A CN 117906903A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 47
- 239000000725 suspension Substances 0.000 claims abstract description 40
- 238000005259 measurement Methods 0.000 claims abstract description 22
- 238000012360 testing method Methods 0.000 claims abstract description 14
- 238000009413 insulation Methods 0.000 claims description 13
- 238000002955 isolation Methods 0.000 claims description 12
- 239000011152 fibreglass Substances 0.000 claims description 9
- 229910052751 metal Inorganic materials 0.000 claims description 9
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- 238000002788 crimping Methods 0.000 claims description 6
- 239000000945 filler Substances 0.000 claims description 6
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention belongs to the technical field of hypersonic wind tunnel tests, and discloses a micro aerodynamic resistance measuring device and a using method thereof. The model shell of the device is of a conical hollow thin-wall structure, and a force transmission support rod, a micro-force balance and a balance support rod are sequentially fixed in the inner cavity of the model shell along the central axis from front to back; the rear section of the balance support rod is sleeved with a limiting plate, the rear end surface of the model shell is fixed with a model bottom cover, and the balance support rod penetrates through the model bottom cover to be fixedly connected with an attack angle mechanism of the hypersonic wind tunnel; and a model suspension line is fixed on the model shell and coincides with the theoretical gravity center plumb line of the force measuring model assembly. The using method comprises the steps of assembling a force measuring model assembly, suspending and leveling the force measuring model assembly, installing a force measuring balance and performing hypersonic wind tunnel force measuring test. The device and the using method solve the problem that the large model weight has serious interference to the small pneumatic load measurement, solve the problem of measuring the small pneumatic resistance of the model under the thin flow field, and have engineering popularization value.
Description
Technical Field
The invention belongs to the technical field of hypersonic wind tunnel tests, and particularly relates to a micro aerodynamic resistance measuring device and a using method thereof.
Background
With the rapid development of hypersonic aircrafts, the flying speed and the flying height of the aircrafts are continuously improved, the flying time of the aircrafts in a high-altitude thin flow area (60 km-100 km) is greatly increased, and urgent demands are put forward for accurately predicting the aerodynamic characteristics of the high-altitude thin flow area of the aircrafts.
The air in the high-altitude lean flow area is lean, and the pneumatic load is small. A9 degree blunt cone model with a length of 0.5m magnitude at a height of about 80km has an aerodynamic drag of about 0.4N at an attack angle of 0 degree, and the processing weight of the model is generally above 10N. Typically, a load cell balance is required to support the weight of the model while making model aerodynamic measurements. Under the condition of meeting the weight support requirement of the model, the sensitivity of the force measuring balance is difficult to improve, so that the accuracy of the thin flow aerodynamic force measurement is difficult to improve.
In the aspect of thin flow aerodynamic force measurement, the data disclosed at present show that the following three technical schemes are mainly available. The first is to hang the light model, through measuring the horizontal displacement that hangs the light model and produces under aerodynamic force, calculate and get the angle of suspension line and plumb line, then carry on the decomposition calculation of the force through the model weight to get the aerodynamic force of the model; the second is to support the model by magnetic suspension and measure the aerodynamic force of the model; the third is to make a small-size model (usually within 100mm scale) into a light thin shell structure, support the model by adopting a high-sensitivity force measuring balance and measure the aerodynamic force of the model. The three technical schemes have obvious defects. The first method is only suitable for a light ball model, and has large measurement error; the second technique has high threshold, large difficulty and complex equipment, and is suitable for small-size models; the third kind is only suitable for small-size light model, aerodynamic load measurement is still severely interfered by model weight, and measurement error is large.
Currently, there is a need to develop a micro aerodynamic drag measurement device and a method of using the same.
Disclosure of Invention
The invention aims to provide a micro aerodynamic resistance measuring device, and another technical problem to be solved by the invention is to provide a use method of the micro aerodynamic resistance measuring device, which is used for overcoming the defects of the prior art.
The invention relates to a micro aerodynamic resistance measuring device which is characterized by comprising a model shell, a model suspension wire, a model gravity center adjusting bolt bracket, a model bottom cover, a force transmission supporting rod, a micro-force balance, a heat insulation taper sleeve, a limiting plate and a balance supporting rod, wherein the model shell is provided with a plurality of support plates; the model shell, the model gravity center adjusting bolt bracket and the model bottom cover form a force measuring model assembly body;
The model shell is of a conical hollow thin-wall structure, and a force transmission support rod, a micro-force balance and a balance support rod are sequentially fixed from front to back along the central axis of the model shell in the inner cavity of the model shell; the rear section of the balance support rod is sleeved with a limiting plate, the rear end face of the model shell is fixed with a model bottom cover, the limiting plate is positioned in front of the model bottom cover, and an isolation gap is formed between the limiting plate and the model bottom cover; the balance support rod passes through the model bottom cover and is fixedly connected with an attack angle mechanism of the hypersonic wind tunnel, and an annular gap is formed between the balance support rod and the model bottom cover;
On a longitudinal section of the model shell, a model suspension line is arranged right above the theoretical gravity center of the model shell, and the model suspension line is coincident with a plumb line of the force measuring model assembly body; the lower end of the model suspension wire penetrates through a through hole in the model shell and is fixed by knotting, and the upper end of the model suspension wire is fixed on a suspension point of the top wall of the hypersonic wind tunnel in a crimping or binding mode;
The inner wall of the outlet of the model shell is uniformly and alternately provided with bayonets and a fixed seat along the circumferential direction, the bayonets are provided with U-shaped clamping grooves, the U-shaped clamping grooves are used for clamping a gravity center adjusting structure, and the fixed seat is provided with screw holes I; the model bottom cover is fixed on the rear end surface of the model shell through a countersunk head screw matched with the screw hole I; the gravity center adjusting structure is used for adjusting the gravity center of the force measuring model assembly body and is fixed on the U-shaped clamping groove.
Further, the force transmission support rod is a round tube I, an annular disc, a cylinder and a round tube II from front to back in sequence, the force transmission support rod is connected with the front section of the model shell through the cylindrical surface sliding fit of the round tube I, the front end surface of the annular disc is opposite to the front section end surface of the model shell, the cylinder is a force transmission section, and the round tube II is fixedly connected with the micro-force balance through cylindrical surface sliding fit screws.
Furthermore, the micro-force balance and the balance support rod are in conical surface fit through a heat insulation taper sleeve and are fixedly connected through an axial locking pin.
Further, the limiting plate consists of 2 symmetrical semicircular rings, the inner diameter of each semicircular ring is the same as the outer diameter of the rear section of the balance support rod, and the semicircular rings are installed at the rear section of the balance support rod in a clamping mode through fastening bolts; the width of the isolation gap between the rear end face of the limiting plate and the front end face of the model bottom cover is 2mm.
Further, the gravity center adjusting structure comprises 4 groups of model gravity center adjusting bolts distributed in a cross mode and corresponding model gravity center adjusting bolt supports; the model gravity center adjusting bolt bracket is provided with a fixed foot matched with the U-shaped clamping groove, the fixed foot is provided with a screw hole II, and the model gravity center adjusting bolt bracket is also provided with a screw hole matched with the model gravity center adjusting bolt; the model gravity center adjusting bolt bracket is fixed on the U-shaped clamping groove through a countersunk head screw matched with the screw hole II; the model gravity center adjusting bolt is screwed into the threaded hole from back to front, the rear end face of the bolt head of the model gravity center adjusting bolt faces the model bottom cover, and an isolation gap is arranged between the rear end face of the bolt head and the model bottom cover;
The model bottom cover is also provided with round through holes which are in one-to-one correspondence with the gravity center adjusting bolts of each model, and the front and back positions of the gravity center adjusting bolts of the model are adjusted through screwdrivers penetrating through the round through holes, so that the front and back adjustment of the gravity center position of the force measuring model assembly body is realized; the left and right adjustment of the weight center position of the force measuring model assembly is realized by installing model gravity center adjusting bolts with different masses on model gravity center adjusting bolt supports distributed left and right.
Further, the through holes are specific through holes selected by a single-point supporting method in a group of through holes; the group of through holes are positioned on a longitudinal section bus of the model shell, and a plurality of vertical through holes with the diameter phi of 0.5mm plus or minus 0.01mm are uniformly arranged along the axial direction of the model shell at equal intervals along the axial direction of the model shell;
the single-point support method comprises the steps of placing a conical support block on a horizontal tabletop, enabling a conical tip of the conical support block to vertically upwards, enabling a row of vertical through holes on a model shell to rotate to be right below the model shell, sequentially placing a group of vertical through holes on the conical support block tip, finding out two vertical through holes closest to the gravity center of a force measurement model assembly body by observing the horizontal balance position of the force measurement model assembly body under the action of gravity, and selecting the vertical through holes close to the front end of the model shell as specific through holes.
Further, the model shell and the model bottom cover are made of light metal, the light metal comprises 7075 aviation aluminum and titanium alloy, and the light metal is used for reducing the overall mass of the force measuring model assembly; the heat insulation taper sleeve is made of glass fiber reinforced plastic; the force transmission support rod is 7075 aviation aluminum or glass fiber reinforced plastic; at the temperature of 1000-2000 ℃ and high Wen Liuchang, glass fiber reinforced plastic is selected as the material of the force transmission support rod, so that the heat conduction between the model shell and the micro-force balance is reduced.
The application method of the micro aerodynamic resistance measuring device comprises the following steps:
s10, assembling a force measuring model assembly;
the method comprises the steps that 4 model gravity center adjusting bolts are respectively installed in threaded holes of corresponding model gravity center adjusting bolt supports, the positions of the model gravity center adjusting bolts are adjusted backwards, the bolt head end faces of the model gravity center adjusting bolts are closer to the fixing feet of the corresponding gravity center adjusting bolt supports, and a preset isolation gap is reserved between the bolt head end faces and the model bottom cover after the model bottom cover is installed;
clamping the fixed feet of the gravity center adjusting bolt brackets of each model on a U-shaped clamping groove of the inner wall of the outlet of the model shell, fixing the model bottom cover on the rear end surface of the model shell through a countersunk head screw matched with a screw hole I, and fixing the gravity center adjusting bolt brackets of the model on the U-shaped clamping groove through a countersunk head screw matched with a screw hole II;
S20, hanging and leveling the force measuring model assembly;
Finding out a specific through hole of the force measuring model assembly body by using a single-point support method; removing the model bottom cover, enabling the lower end of the model suspension wire to pass through the specific through hole and knotting, enabling the nodes to be positioned in the inner cavity of the model shell and not pass through the specific through hole, and installing the model bottom cover; filling the remaining vertical through holes on the model shell with removable filler comprising plasticine, and removing the redundant removable filler until the surface of the model shell is smooth and flat; the upper end of a model suspension wire is fixed on a suspension point of the top wall of the hypersonic wind tunnel in a crimping or binding mode; the length of a model suspension line is adjusted, so that a force measuring model assembly body is suspended at the center of a hypersonic wind tunnel flow field;
a screwdriver passes through a circular through hole on a bottom cover of the model, the positions of gravity center adjusting bolts of all models are adjusted, and then the gravity center position of a force measuring model assembly is adjusted, so that the force measuring model assembly is positioned at a self-balancing stable position, the gravity center of the force measuring model assembly is collinear with a suspension line of the model, the force measuring model assembly is positioned right below a suspension point of the top wall of a hypersonic wind tunnel, and meanwhile, the included angle between the central axis of the force measuring model assembly and the horizontal plane is smaller than 0.05 degrees, so that the requirement of the attitude angle installation precision of a aerodynamic test model is met;
S30, installing a force measuring balance;
Assembling a force transmission support rod, a micro-force balance, a heat insulation taper sleeve and a balance support rod to obtain an assembly body; the assembly body is arranged on an attack angle mechanism of the hypersonic wind tunnel through a cone section at the tail part of the balance support rod; the pitch angle of the attack angle mechanism is adjusted to enable the axes of the force transmission support rod, the micro-force balance and the balance support rod to be horizontal, and then the position of the attack angle mechanism in the vertical direction is adjusted to enable the axes of the force transmission support rod and the micro-force balance to be the same as the horizontal axis of the model shell;
The method comprises the steps that a limiting plate is clamped and installed on the rear section of a balance supporting rod, the distance between the rear end face of the limiting plate and the front end face of an annular disc of a force transmission supporting rod is L1, the distance between the front end face of a model shell and the front end face of an installed model bottom cover is L2, L1 is smaller than L2, and L2-L1=2mm+/-0.1 mm;
Dismantling a bottom cover of the model; the attack angle mechanism drives the assembly body to move forwards along the central axis of the force measuring model assembly body, the force transmission support rod and the micro-force balance enter the inner cavity of the model shell, the round tube I of the force transmission support rod is inserted into the cylindrical inner cavity of the front section of the model shell until the distance between the front end surface of the annular disc of the force transmission support rod and the front end surface of the front section of the model shell reaches a preset distance; restoring the model bottom cover and installing the model bottom cover on the rear end surface of the model shell;
s40, performing hypersonic wind tunnel force measurement test;
When the test is carried out, under the action of air flow, the force measuring model assembly is subjected to aerodynamic force along the axis direction and moves backwards, the front end face of the annular disc of the force transmission support rod is propped against the front end face of the model shell to realize limit, the force measuring model assembly transmits the received aerodynamic force to the micro-force balance, and the micro-force balance measures the aerodynamic resistance of the force measuring model assembly; and after the test is finished, closing the hypersonic wind tunnel, and tightly pushing the bottom cover of the model by the limiting plate to limit the forward sliding of the force measuring model assembly under the action of inertia force.
The model length of the micro aerodynamic resistance measuring device can reach 0.5m, the mass can reach 0.5kg level, and the aerodynamic resistance measuring accuracy can reach 10 -3 N.
According to the device for measuring the small aerodynamic resistance and the using method thereof, the model aerodynamic resistance is separated from the model weight, so that the force measuring balance can finish model aerodynamic resistance measurement under the condition that the model weight is not supported, the problem that the large model weight has serious interference to small aerodynamic load measurement is solved, the accuracy of measuring the small aerodynamic resistance of the model under the thin flow field is improved, the problem of measuring the small aerodynamic resistance of the model under the thin flow field is solved, and the device has engineering popularization value. An effective test method is established for measuring aerodynamic resistance of a large-size model of the hypersonic wind tunnel under the condition of 80km simulated height.
Drawings
FIG. 1 is a schematic view (perspective view) of a micro aerodynamic drag measurement device according to the present invention;
FIG. 2 is a schematic view (sectional view) showing the structure of the minute aerodynamic drag measuring device of the present invention;
FIG. 3 is a schematic view showing the installation of the gravity center adjusting structure of the micro aerodynamic drag measuring device of the present invention on a model housing;
FIG. 4a is a schematic diagram (front view) of the gravity center adjusting structure of the micro aerodynamic drag measuring device of the present invention;
FIG. 4b is a schematic diagram (perspective view) of the gravity center adjusting structure of the micro aerodynamic drag measuring device of the present invention;
FIG. 5 is a schematic view (front view) showing the installation of components such as a microbalance and a strut of the micro pneumatic resistance measuring device of the present invention;
fig. 6 is a schematic diagram (perspective view) of a limiting plate structure of the micro aerodynamic resistance measuring device of the present invention.
In the figure, 1. Model shell; 2. model suspension wires; 3. a model gravity center adjusting bolt; 4. a model gravity center adjusting bolt bracket; 5. a model bottom cover; 6. a force transmission strut; 7. a micro force balance; 8. a heat insulation taper sleeve; 9. a limiting plate; 10. balance support rod.
Detailed Description
The invention is described in detail below with reference to the drawings and examples.
Example 1:
The length of the model housing 1 of the present embodiment is 500mm; on the longitudinal section of the model shell 1, a plurality of vertical through holes with the diameter phi of 0.5mm plus or minus 0.01mm are uniformly distributed along the axial direction of the model shell 1 and at intervals of 20mm plus or minus 0.1mm in the length right above the theoretical gravity center of the model shell 1.
As shown in fig. 1 to 6, the micro aerodynamic resistance measuring device of the embodiment comprises a model shell 1, a model suspension wire 2, a model gravity center adjusting bolt 3, a model gravity center adjusting bolt bracket 4, a model bottom cover 5, a force transmission supporting rod 6, a micro force balance 7, a heat insulation taper sleeve 8, a limiting plate 9 and a balance supporting rod 10; the model shell 1, the model gravity center adjusting bolt 3, the model gravity center adjusting bolt bracket 4 and the model bottom cover 5 form a force measuring model assembly body;
The model shell 1 is of a conical hollow thin-wall structure, and a force transmission support rod 6, a micro-force balance 7 and a balance support rod 10 are sequentially fixed from front to back along the central axis of the model shell 1 in the inner cavity of the model shell 1; the rear section of the balance support rod 10 is sleeved with a limiting plate 9, the model bottom cover 5 is fixed on the rear end surface of the model shell 1, the limiting plate 9 is positioned in front of the model bottom cover 5, and an isolation gap is formed between the limiting plate 9 and the model bottom cover 5; the balance support rod 10 passes through the model bottom cover 5 and is fixedly connected with an attack angle mechanism of the hypersonic wind tunnel, and an annular gap is formed between the balance support rod 10 and the model bottom cover 5;
On the longitudinal section of the model shell 1, a model suspension line 2 is arranged right above the theoretical gravity center of the model shell 1, and the model suspension line 2 coincides with a plumb line of the force measuring model assembly body; the lower end of the model suspension wire 2 penetrates through a through hole in the model shell 1 and is fixed by knotting, and the upper end of the model suspension wire 2 is fixed on a suspension point of the top wall of the hypersonic wind tunnel in a crimping or binding mode;
The inner wall of the outlet of the model shell 1 is uniformly and alternately provided with bayonets and a fixed seat along the circumferential direction, the bayonets are provided with U-shaped clamping grooves, the U-shaped clamping grooves are used for clamping a gravity center adjusting structure, and the fixed seat is provided with screw holes I; the model bottom cover 5 is fixed on the rear end surface of the model shell 1 through a countersunk head screw matched with the screw hole I; the gravity center adjusting structure is used for adjusting the gravity center of the force measuring model assembly body and is fixed on the U-shaped clamping groove.
Further, the force transmission support rod 6 is a circular tube I, an annular disc, a cylinder and a circular tube II from front to back in sequence, the force transmission support rod 6 is connected with the front section of the model shell 1 through the cylindrical surface sliding fit of the circular tube I, the front end surface of the annular disc is opposite to the front section end surface of the model shell 1, the cylinder is a force transmission section, and the circular tube II is fixedly connected with the micro-force balance 7 through cylindrical surface sliding fit screws.
Further, the micro-force balance 7 and the balance support rod 10 are in conical surface fit through the heat insulation taper sleeve 8 and are fixedly connected through the axial locking pin.
Further, the limiting plate 9 consists of 2 symmetrical semicircular rings, the inner diameter of each semicircular ring is the same as the outer diameter of the rear section of the balance support rod 10, and the semicircular rings are installed at the rear section of the balance support rod 10 in a clamping mode through fastening bolts; the width of the isolation gap between the rear end face of the limiting plate 9 and the front end face of the mold bottom cover 5 is 2mm.
Further, the gravity center adjusting structure comprises 4 groups of model gravity center adjusting bolts 3 distributed in a cross manner and corresponding model gravity center adjusting bolt supports 4; the model gravity center adjusting bolt bracket 4 is provided with a fixed foot matched with the U-shaped clamping groove, the fixed foot is provided with a screw hole II, and the model gravity center adjusting bolt bracket 4 is also provided with a screw hole matched with the model gravity center adjusting bolt 3; the model gravity center adjusting bolt bracket 4 is fixed on the U-shaped clamping groove through a countersunk head screw matched with the screw hole II; the model gravity center adjusting bolt 3 is screwed into the threaded hole from back to front, the rear end face of the bolt head of the model gravity center adjusting bolt 3 faces the model bottom cover 5, and an isolation gap is arranged between the rear end face of the bolt head and the model bottom cover 5;
The model bottom cover 5 is also provided with circular through holes which are in one-to-one correspondence with the gravity center adjusting bolts 3 of each model, and the front and back positions of the gravity center adjusting bolts 3 of the model are adjusted through screwdrivers penetrating through the circular through holes, so that the front and back adjustment of the gravity center position of the force measuring model assembly is realized; the left and right adjustment of the weight center position of the force measuring model assembly is realized by installing model gravity center adjusting bolts 3 with different masses on model gravity center adjusting bolt supports 4 distributed left and right.
Further, the through holes are specific through holes selected by a single-point supporting method in a group of through holes; the group of through holes are positioned on a longitudinal section bus of the model shell 1, and a plurality of vertical through holes with the diameter phi of 0.5mm plus or minus 0.01mm are uniformly arranged at equal intervals along the axial direction of the model shell 1 and above the theoretical gravity center of the model shell 1;
The single-point support method comprises the steps of placing a conical support block on a horizontal tabletop, enabling a conical tip of the conical support block to vertically upwards, enabling a row of vertical through holes on a model shell 1 to rotate to be right below the model shell 1, sequentially placing a group of vertical through holes on the conical support block tip, finding out two vertical through holes closest to the gravity center of a force measurement model assembly body by observing the horizontal balance position of the force measurement model assembly body under the action of gravity, and selecting the vertical through holes close to the front end of the model shell 1 as specific through holes.
Further, the model shell 1 and the model bottom cover 5 are made of light metal, the light metal comprises 7075 aviation aluminum and titanium alloy, and the light metal is used for reducing the overall mass of the force measuring model assembly; the heat insulation taper sleeve 8 is made of glass fiber reinforced plastic; the force transmission support rod 6 is made of 7075 aviation aluminum or glass fiber reinforced plastic; at the temperature of 1000-2000 ℃ and high Wen Liuchang, glass fiber reinforced plastic is selected as the material of the force transmission support rod 6, so that the heat conduction between the model shell 1 and the micro-force balance 7 is reduced.
The application method of the micro aerodynamic resistance measuring device of the embodiment comprises the following steps:
s10, assembling a force measuring model assembly;
The method comprises the steps of installing 4 model gravity center adjusting bolts 3 in threaded holes of corresponding model gravity center adjusting bolt supports 4 respectively, and adjusting the positions of the model gravity center adjusting bolts 3 backwards, so that the bolt head end faces of the model gravity center adjusting bolts 3 are closer to the fixed feet of the corresponding gravity center adjusting bolt supports 4, and a preset isolation gap is reserved between the bolt head end faces and the model bottom covers 5 after the model bottom covers 5 are installed;
Clamping the fixed feet of each model gravity center adjusting bolt bracket 4 on a U-shaped clamping groove of the inner wall of the outlet of the model shell 1, fixing the model bottom cover 5 on the rear end surface of the model shell 1 through a countersunk screw matched with a screw hole I, and fixing the model gravity center adjusting bolt bracket 4 on the U-shaped clamping groove through a countersunk screw matched with a screw hole II;
S20, hanging and leveling the force measuring model assembly;
Finding out a specific through hole of the force measuring model assembly body by using a single-point support method; removing the model bottom cover 5, enabling the lower end of the model suspension wire 2 to pass through the specific through hole and knotting, enabling the knots to be positioned in the inner cavity of the model shell 1 and not pass through the specific through hole, and installing the model bottom cover 5; filling the remaining vertical through holes on the model shell 1 with removable filler comprising plasticine, and removing the redundant removable filler until the surface of the model shell 1 is smooth and flat; the upper end of the model suspension wire 2 is fixed on a suspension point of the top wall of the hypersonic wind tunnel in a crimping or binding mode; the length of the model suspension line 2 is adjusted, so that the force measuring model assembly body is suspended at the center of the hypersonic wind tunnel flow field;
a screwdriver passes through a circular through hole on a model bottom cover 5, the position of a gravity center adjusting bolt 3 of each model is adjusted, and then the gravity center position of a force measuring model assembly is adjusted, so that the force measuring model assembly is in a self-balancing stable position, the gravity center of the force measuring model assembly is collinear with a model suspension line 2, the force measuring model assembly is positioned right below a suspension point of the top wall of a hypersonic wind tunnel, and meanwhile, the included angle between the central axis of the force measuring model assembly and the horizontal plane is smaller than 0.05 degrees, so that the requirement of the attitude angle installation precision of a aerodynamic test model is met;
S30, installing a force measuring balance;
Assembling a force transmission support rod 6, a micro-force balance 7, a heat insulation taper sleeve 8 and a balance support rod 10 to obtain an assembly; the assembly body is arranged on an attack angle mechanism of a hypersonic wind tunnel through a cone section at the tail part of the balance support rod 10; the pitch angle of the attack angle mechanism is adjusted so that the axes of the force transmission support rod 6, the micro-force balance 7 and the balance support rod 10 are all horizontal, and then the position of the attack angle mechanism in the vertical direction is adjusted so that the axes of the force transmission support rod 6 and the micro-force balance 7 are the same as the horizontal axis of the model shell 1;
The limiting plate 9 is installed on the rear section of the balance support rod 10 in a clamping mode, the distance between the rear end face of the limiting plate 9 and the front end face of the annular disc of the force transmission support rod 6 is L1, the distance between the front end face of the model shell 1 and the front end face of the installed model bottom cover 5 is L2, L1 is less than L2, and L2-L1=2mm+/-0.1 mm;
removing the model bottom cover 5; the attack angle mechanism drives the assembly body to move forwards along the central axis of the force measuring model assembly body, the force transmission support rod 6 and the micro-force balance 7 enter the inner cavity of the model shell 1, the round tube I of the force transmission support rod 6 is inserted into the cylindrical inner cavity of the front section of the model shell 1 until the distance between the front end surface of the annular disc of the force transmission support rod 6 and the front end surface of the model shell 1 reaches a preset distance; restoring the mold bottom cover 5 and mounting on the rear end surface of the mold housing 1;
s40, performing hypersonic wind tunnel force measurement test;
when in test, under the action of air flow, the force measuring model assembly is subjected to aerodynamic force along the axial direction and moves backwards, the front end surface of the annular disc of the force transmission support rod 6 is propped against the front end surface of the model shell 1, so that limit is realized, the force measuring model assembly transmits the received aerodynamic force to the micro-force balance 7, and the micro-force balance 7 measures the aerodynamic resistance of the force measuring model assembly; and after the test is finished, closing the hypersonic wind tunnel, and tightly pushing the model bottom cover 5 by the limiting plate 9 to limit the forward sliding of the force measuring model assembly under the action of inertia force.
Although embodiments of the invention have been disclosed in the foregoing description and illustrated in the drawings, it will be understood by those skilled in the art that the present invention is not limited to the specific details and illustrations of features and steps set forth herein, and that all features of the invention disclosed, or steps of the method or process, except for mutually exclusive features and/or steps, may be combined in any manner without departing from the principles of the invention.
Claims (8)
1. The micro aerodynamic resistance measuring device is characterized by comprising a model shell (1), a model suspension wire (2), a model gravity center adjusting bolt (3), a model gravity center adjusting bolt bracket (4), a model bottom cover (5), a force transmission supporting rod (6), a micro-force balance (7), a heat insulation taper sleeve (8), a limiting plate (9) and a balance supporting rod (10); the force measuring model assembly body is formed by the model shell (1), the model gravity center adjusting bolt (3), the model gravity center adjusting bolt bracket (4) and the model bottom cover (5);
The model shell (1) is of a conical hollow thin-wall structure, and a force transmission support rod (6), a micro-force balance (7) and a balance support rod (10) are sequentially fixed from front to back along the central axis of the model shell (1) in the inner cavity of the model shell (1); the back section of the balance support rod (10) is sleeved with a limiting plate (9), the back end surface of the model shell (1) is fixed with a model bottom cover (5), the limiting plate (9) is positioned in front of the model bottom cover (5), and an isolation gap is formed between the limiting plate (9) and the model bottom cover (5); the balance support rod (10) passes through the model bottom cover (5) and is fixedly connected with an attack angle mechanism of the hypersonic wind tunnel, and an annular gap is formed between the balance support rod (10) and the model bottom cover (5);
On a longitudinal section of the model shell (1), a model suspension line (2) is arranged right above the theoretical gravity center of the model shell (1), and the model suspension line (2) coincides with a plumb line of the force measuring model assembly body; the lower end of the model suspension wire (2) penetrates through a through hole in the model shell (1) and is fixed by knotting, and the upper end of the model suspension wire (2) is fixed on a suspension point of the top wall of the hypersonic wind tunnel in a crimping or binding mode;
The inner wall of the outlet of the model shell (1) is uniformly and alternately provided with bayonets and a fixed seat along the circumferential direction, the bayonets are provided with U-shaped clamping grooves, the U-shaped clamping grooves are used for clamping a gravity center adjusting structure, and the fixed seat is provided with screw holes I; the model bottom cover (5) is fixed on the rear end surface of the model shell (1) through a countersunk head screw matched with the screw hole I; the gravity center adjusting structure is used for adjusting the gravity center of the force measuring model assembly body and is fixed on the U-shaped clamping groove.
2. The micro aerodynamic drag measuring device according to claim 1, wherein the force transmission support rod (6) is a circular tube I, an annular disc, a cylinder and a circular tube II from front to back, the force transmission support rod (6) is connected with the front section of the model shell (1) through the cylindrical surface sliding fit of the circular tube I, the front end surface of the annular disc is opposite to the front section end surface of the model shell (1), the cylinder is a force transmission section, and the circular tube II is fixedly connected with the micro-force balance (7) through cylindrical surface sliding fit screws.
3. The micro aerodynamic resistance measuring device according to claim 1, characterized in that the micro force balance (7) and the balance support rod (10) are in conical surface fit through a heat insulation taper sleeve (8) and are fixedly connected through an axial locking pin.
4. The micro aerodynamic resistance measuring device according to claim 1, characterized in that the limiting plate (9) is composed of 2 symmetrical semicircular rings, the inner diameter of each semicircular ring is the same as the outer diameter of the rear section of the balance support rod (10), and the semicircular rings are installed at the rear section of the balance support rod (10) in a clamping manner through fastening bolts; the width of the isolation gap between the rear end face of the limiting plate (9) and the front end face of the model bottom cover (5) is 2mm.
5. The micro aerodynamic drag force measuring device according to claim 1, characterized in that the gravity center adjusting structure comprises 4 groups of cross-distributed model gravity center adjusting bolts (3) and corresponding model gravity center adjusting bolt brackets (4); the model gravity center adjusting bolt bracket (4) is provided with a fixed foot matched with the U-shaped clamping groove, the fixed foot is provided with a screw hole II, and the model gravity center adjusting bolt bracket (4) is also provided with a screw hole matched with the model gravity center adjusting bolt (3); the model gravity center adjusting bolt bracket (4) is fixed on the U-shaped clamping groove through a countersunk head screw matched with the screw hole II; the model gravity center adjusting bolt (3) is screwed into the threaded hole from back to front, the rear end face of the bolt head of the model gravity center adjusting bolt (3) faces the model bottom cover (5), and an isolation gap is arranged between the rear end face of the bolt head and the model bottom cover (5);
The model bottom cover (5) is also provided with round through holes which are in one-to-one correspondence with the gravity center adjusting bolts (3) of each model, and the front and back positions of the gravity center adjusting bolts (3) of the model are adjusted through screwdrivers penetrating through the round through holes, so that the front and back adjustment of the gravity center position of the force measuring model assembly is realized; the left and right adjustment of the weight center position of the force measuring model assembly is realized by installing model gravity center adjusting bolts (3) with different masses on model gravity center adjusting bolt brackets (4) distributed left and right.
6. The micro aerodynamic drag measurement device according to claim 1, wherein the through holes are specific through holes selected by a single point support method among a group of through holes; the group of through holes are positioned on a longitudinal section bus of the model shell (1), and a plurality of vertical through holes with the diameter phi of 0.5mm plus or minus 0.01mm are uniformly arranged along the axial direction of the model shell (1) at equal intervals above the theoretical gravity center of the model shell (1);
the single-point support method comprises the steps of placing a conical support block on a horizontal tabletop, enabling a conical tip of the conical support block to vertically upwards, enabling a row of vertical through holes on a model shell (1) to rotate to the position right below the model shell (1), placing a group of vertical through holes on the conical support block tip in sequence, finding out two vertical through holes closest to the gravity center of a force measurement model assembly body by observing the horizontal balance position of the force measurement model assembly body under the action of gravity, and selecting the vertical through holes close to the front end of the model shell (1) as specific through holes.
7. The micro aerodynamic drag measuring device according to claim 1, characterized in that the materials of the model shell (1) and the model bottom cover (5) are light metals, the light metals comprise 7075 aviation aluminum and titanium alloy, and the light metals are used for reducing the overall mass of the force measuring model assembly; the heat insulation taper sleeve (8) is made of glass fiber reinforced plastic; the force transmission support rod (6) is made of 7075 aviation aluminum or glass fiber reinforced plastic; at the temperature of 1000-2000 ℃ and high Wen Liuchang, glass fiber reinforced plastic is selected as the material of the force transmission support rod (6), so that the heat conduction between the model shell (1) and the micro-force balance (7) is reduced.
8. A method of using a micro aerodynamic drag measurement device according to any one of claims 1 to 7, comprising the steps of:
s10, assembling a force measuring model assembly;
The method comprises the steps that 4 model gravity center adjusting bolts (3) are respectively arranged in threaded holes of corresponding model gravity center adjusting bolt supports (4), the positions of the model gravity center adjusting bolts (3) are adjusted backwards, the bolt head end faces of the model gravity center adjusting bolts (3) are closer to the fixed feet of the corresponding gravity center adjusting bolt supports (4), and a preset isolation gap is reserved between the bolt head end faces and the model bottom covers (5) after the model bottom covers (5) are arranged;
Clamping the fixed feet of each model gravity center adjusting bolt bracket (4) on a U-shaped clamping groove of the inner wall of the outlet of the model shell (1), fixing a model bottom cover (5) on the rear end surface of the model shell (1) through a countersunk screw matched with a screw hole I, and fixing the model gravity center adjusting bolt bracket (4) on the U-shaped clamping groove through a countersunk screw matched with a screw hole II;
S20, hanging and leveling the force measuring model assembly;
Finding out a specific through hole of the force measuring model assembly body by using a single-point support method; removing the model bottom cover (5), enabling the lower end of the model suspension wire (2) to pass through the specific through hole and knotting, enabling the knots to be positioned in the inner cavity of the model shell (1) and not pass through the specific through hole, and installing the model bottom cover (5); filling the remaining vertical through holes on the model shell (1) with removable filler comprising plasticine, and removing the redundant removable filler until the surface of the model shell (1) is smooth and flat; the upper end of a model suspension wire (2) is fixed on a suspension point of the top wall of the hypersonic wind tunnel in a crimping or binding mode; the length of a model suspension line (2) is adjusted, so that a force measuring model assembly body is suspended at the center of a hypersonic wind tunnel flow field;
A screwdriver passes through a circular through hole on a model bottom cover (5), the position of a gravity center adjusting bolt (3) of each model is adjusted, and then the gravity center position of a force measuring model assembly is adjusted, so that the force measuring model assembly is positioned at a self-balancing stable position, the gravity center of the force measuring model assembly is collinear with a model suspension line (2), the force measuring model assembly is positioned right below a suspension point of the top wall of a hypersonic wind tunnel, and meanwhile, the included angle between the central axis of the force measuring model assembly and the horizontal plane is smaller than 0.05 degrees, so that the requirement of the attitude angle installation precision of a aerodynamic test model is met;
S30, installing a force measuring balance;
Assembling a force transmission support rod (6), a micro-force balance (7), a heat insulation taper sleeve (8) and a balance support rod (10) to obtain an assembly body; the assembly body is arranged on an attack angle mechanism of a hypersonic wind tunnel through a cone section at the tail part of a balance support rod (10); the pitch angle of the attack angle mechanism is adjusted, so that the axes of the force transmission support rod (6), the micro-force balance (7) and the balance support rod (10) are all horizontal, and then the position of the attack angle mechanism in the vertical direction is adjusted, so that the axes of the force transmission support rod (6) and the micro-force balance (7) are the same height as the horizontal axis of the model shell (1);
The limiting plate (9) is installed on the rear section of the balance support rod (10) in a clamping mode, the distance between the rear end face of the limiting plate (9) and the front end face of the annular disc of the force transmission support rod (6) is L1, the distance between the front end face of the model shell (1) and the front end face of the installed model bottom cover (5) is L2, L1 is smaller than L2, and L2-L1=2mm+/-0.1 mm;
Removing the model bottom cover (5); the attack angle mechanism drives the assembly body to move forwards along the central axis of the force measuring model assembly body, the force transmission support rod (6) and the micro-force balance (7) enter the inner cavity of the model shell (1), the round tube I of the force transmission support rod (6) is inserted into the cylindrical inner cavity of the front section of the model shell (1) until the distance between the front end surface of the annular disc of the force transmission support rod (6) and the front end surface of the model shell (1) reaches a preset distance; restoring the model bottom cover (5) and installing the model bottom cover on the rear end surface of the model shell (1);
s40, performing hypersonic wind tunnel force measurement test;
When the force measuring model assembly is tested, under the action of air flow, the force measuring model assembly is subjected to aerodynamic force along the axis direction and moves backwards, the front end face of the annular disc of the force transmission support rod (6) is propped against the front end face of the model shell (1) to realize limit, the force measuring model assembly transmits the received aerodynamic force to the micro force balance (7), and the micro force balance (7) measures the aerodynamic resistance of the force measuring model assembly; and after the test is finished, closing the hypersonic wind tunnel, and tightly pushing the model bottom cover (5) by the limiting plate (9) to limit the forward sliding of the force measuring model assembly under the action of inertia force.
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