CN115265999A - Horizontal double-engine layout air inlet duct wind tunnel test device - Google Patents
Horizontal double-engine layout air inlet duct wind tunnel test device Download PDFInfo
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- CN115265999A CN115265999A CN202211186700.5A CN202211186700A CN115265999A CN 115265999 A CN115265999 A CN 115265999A CN 202211186700 A CN202211186700 A CN 202211186700A CN 115265999 A CN115265999 A CN 115265999A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention belongs to the technical field of wind tunnel tests and discloses a horizontal double-engine layout air inlet duct wind tunnel test device. The test device comprises a fixed support system, a rotary support system and a sideslip angle positioning system; the rotary supporting system rotates relative to the fixed supporting system, and the sideslip angle of the horizontal double-engine layout air inlet channel test model is changed; and locking the sideslip angle of the horizontal double-engine layout air inlet test model by the sideslip angle positioning system. The wind tunnel test device installs two flowmeters on the rotation support system horizontally side by side, a reliable test support scheme is provided for the wind tunnel test of the horizontal twin engine layout aircraft inlet duct, the rotation of the rotation support system solves the problem of coupling of the attack angle and the sideslip angle operation range in the wind tunnel test in the double-rotating-shaft variable sideslip mode, the test attack angle envelope is expanded, the support position adjustment requirements of different horizontal twin engine layout inlet duct test models are met, the convenience of variable sideslip angles is enhanced, and the wind tunnel test efficiency of the horizontal twin engine layout inlet duct is improved.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to a horizontal double-engine layout air inlet duct wind tunnel test device.
Background
In a wind tunnel test, the change of the attack angle and the sideslip angle of a test model is often required to be realized so as to obtain the aerodynamic characteristic parameters of the test model under the condition of different attitude angle combinations. In general, the change of the attack angle of the test model is a head raising or lowering motion in the vertical plane, and the change of the sideslip angle of the test model is a head swinging motion in the plane perpendicular to the vertical plane (such as the horizontal plane).
At present, the change of the attack angle of a test model is realized by the motion of an attack angle mechanism connected with the test model on a vertical plane, the attack angle mechanism consists of a driving system, a curved knife and an auxiliary system, the curved knife generally adopts a sectional design and mainly consists of an upper curved knife, a middle bracket and a lower curved knife, the middle bracket is mainly used for supporting the test model and can be designed and replaced according to the specific test type. The connection between the test model and the attack angle mechanism has two modes: one mode is that the test model is directly connected with an attack angle mechanism through a straight supporting rod; the other mode is that the test model is firstly connected with the double-rotating-shaft mechanism through the straight supporting rod, and then the double-rotating-shaft mechanism is arranged on the attack angle mechanism. The double-rotating-shaft mechanism comprises a front shaft system and a rear shaft system, a certain included angle is formed between the front shaft and the rear shaft, the two shafts can rotate and be fixed around respective axes, the rear shaft needs to be combined with relevant parts of the middle support, and the double-rotating-shaft mechanism can realize certain pre-deflection of an attack angle and certain change of a sideslip angle. There are three common ways to test model sideslip angle changes: one way is to directly replace the middle bracket with a certain sideslip angle pre-deflection; the other mode is realized by adopting double rotating shafts, after the rear shaft of the double rotating shafts rotates, an included angle, namely a sideslip angle, is formed between a test model arranged on the front shaft and a vertical plane, and the test model is leveled through the front shaft of the double rotating shafts; the third mode is to realize the change of the sideslip angle through a multi-degree-of-freedom motion mechanism. The main disadvantages of the above three ways of changing the sideslip angle are: the first mode is complex, needs to disassemble and assemble a test model, is mainly suitable for a wind tunnel with a 0.5 meter-level caliber, is used as a middle support of the wind tunnel with the magnitude of 1 meter and above in a main battlefield, is heavy and is difficult to replace, so the mode is gradually eliminated; the second mode has the problem of coupling of the operation ranges of the attack angle and the sideslip angle, and can change the test operation envelope, for example, the operation range of an attack angle mechanism is-18 degrees, if a double-rotating-shaft mechanism with a front-rear-shaft included angle of 10 degrees is installed, when the sideslip angle is 0 degree, the test attack angle range is-8-28 degrees, when the sideslip angle is 10 degrees, the test attack angle range is-18 degrees, and when the transverse pneumatic load is large, the condition that the front shaft of the double-rotating-shaft mechanism fails (rotates) is easily caused; in the third mode, because the angle-of-attack mechanism is supported in only one direction, the bearing capacity is limited, and particularly, the transverse (sideslip angle direction) bearing capacity is relatively low, and the application range is relatively narrow.
With the development of aircraft development, horizontal twin-engine layouts, combined-power layouts and even multi-engine layouts have become an important layout research direction. The air inlet channel is an important component of an aircraft power system and is used for providing high-quality air for an engine; horizontal twin engine layout aircraft often take the form of a horizontal layout of "2 inlet ducts +2 engines", one inlet duct providing the required air for only one turbine engine. The wind tunnel test is an important means for obtaining performance parameters of the air inlet channel, and in the wind tunnel test, the performance of the air inlet channel of the horizontal twin-engine layout aircraft can be well tested only by arranging two flow meters and related auxiliary equipment horizontally; meanwhile, the flight incidence angle/sideslip angle envelope line of the novel aircraft is relatively wide, and higher requirements are provided for original air inlet channel wind tunnel test technical equipment.
At present, a horizontal double-engine layout air inlet duct wind tunnel test device needs to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a horizontal double-engine layout air inlet channel wind tunnel test device.
The invention relates to a wind tunnel test device for a horizontal double-engine layout air inlet channel, which is characterized by comprising a fixed support system, a rotary support system and a sideslip angle positioning system; the rotary supporting system rotates relative to the fixed supporting system, and the sideslip angle of the horizontal double-engine layout air inlet channel test model is changed; the sideslip angle positioning system locks the sideslip angle of the horizontal double-engine layout air inlet channel test model; the central axes of the two flowmeters of the horizontal double-engine air inlet passage test model are parallel and are distributed in bilateral symmetry.
Furthermore, the fixed support system comprises a sideslip angle rotating upper base, a sideslip angle rotating lower base, an upper connection lug of the angle of attack mechanism and a lower connection lug of the angle of attack mechanism; the mechanism is divided into an upper group and a lower group, wherein one group is a sideslip angle rotating upper base and an upper connecting lug of an angle of attack mechanism, and the other group is a sideslip angle rotating lower base and a lower connecting lug of the angle of attack mechanism;
the top of a connecting lug piece on the angle-of-attack mechanism is fixedly connected with an upper curved knife interface of the wind tunnel angle-of-attack mechanism above a horizontal symmetrical plane of the wind tunnel, and the bottom of the connecting lug piece on the angle-of-attack mechanism is fixedly connected with the top of the sideslip angle rotating upper base; the bottom of a lower connecting lug of the angle-of-attack mechanism is fixedly connected with a lower bent knife interface of the wind tunnel angle-of-attack mechanism below a horizontal symmetry plane of the wind tunnel, and the top of the lower connecting lug of the angle-of-attack mechanism is fixedly connected with the bottom of the sideslip angle rotating lower base;
a circular boss is arranged at the front end of the bottom of the sideslip angular rotation upper base, a rotation groove is arranged at the rear end of the bottom, and a positioning clamping groove is arranged above the rotation groove; the front end of the top of the side sliding angle rotating lower base is provided with a circular groove, the rear end of the bottom of the side sliding angle rotating lower base is a fan-shaped flat plate, and a side sliding angle bayonet is arranged on the fan-shaped flat plate; the axes of the circular boss, the rotary groove and the circular groove are overlapped.
Furthermore, the rotary support system comprises a sideslip angle rotary upper support, a flowmeter front support, a flowmeter rear support, a sideslip angle rotary lower support, a flowmeter front section sleeve support and a flowmeter rear section fixed support;
the rotary support system is sequentially sleeved with a sideslip angle rotary lower support, a flowmeter front support and a sideslip angle rotary upper support from bottom to top, the flowmeter front support is connected with a flowmeter rear support in a front-back mode, a flowmeter front section sleeve support is installed on the flowmeter front support, and a flowmeter rear section fixed support is installed on the flowmeter rear support; the rear-section fixed support of the flowmeter is X-shaped and is provided with bayonets which are symmetrical left and right;
the front end of the top of the sideslip angle rotating upper support is provided with a circular groove matched with a circular boss at the front end of the bottom of the sideslip angle rotating upper base, the rear end of the top of the sideslip angle rotating upper support is provided with a fan-shaped flat plate matched with a rotating groove at the rear end of the bottom of the sideslip angle rotating upper base, and a sideslip angle bayonet is arranged on the fan-shaped flat plate; the front end of the bottom of the sideslip angle rotating lower support is provided with a circular boss matched with a circular groove at the front end of the top of the sideslip angle rotating lower base, the rear end of the bottom of the sideslip angle rotating lower support is provided with a rotating groove matched with a fan-shaped flat plate at the rear end of the bottom of the sideslip angle rotating lower support, and a positioning clamping groove is formed above the rotating groove;
the two flowmeters are horizontally arranged side by side and are symmetrically installed in the left and right directions, the front end of each flowmeter is connected with an inlet channel outlet and related test parts corresponding to the horizontal double-engine layout inlet channel test model, the front section of each flowmeter is sleeved in a sleeve of a sleeve support at the front section of each flowmeter, and the rear section of each flowmeter is clamped on a bayonet corresponding to a fixed support at the rear section of the X-shaped flowmeter;
the main structures of the sideslip angle rotating upper base and the sideslip angle rotating lower support are similar, and the main structures of the sideslip angle rotating upper support and the sideslip angle rotating lower base are similar; the circular bosses, the circular grooves and the sector flat plates of the sideslip angle rotating upper bracket and the sideslip angle rotating lower bracket are superposed with the circular bosses, the circular grooves and the circular grooves of the sideslip angle rotating upper base and the sideslip angle rotating lower base; the rotary supporting system is connected with the sideslip angle rotary upper base through the sideslip angle rotary upper support, is connected with the sideslip angle rotary lower base through the sideslip angle rotary lower support, and rotates around an axis.
Further, the sideslip angle positioning system comprises a sideslip angle upper variable angle block and a sideslip angle lower variable angle block; the outline of the sideslip angle upper variable angle block and the outline of the sideslip angle lower variable angle block are consistent with the positioning clamping groove.
When the rotary support system rotates to a specified side-slip angle position: inserting the sideslip angle upper angle-changing block from a positioning clamping groove above a rotating groove of the sideslip angle rotating upper base, wherein the upper end and the lower end of the sideslip angle upper angle-changing block are respectively positioned in a positioning clamping groove above the rotating groove of the sideslip angle rotating upper base and a sideslip angle bayonet on a sector flat plate of the sideslip angle rotating upper bracket; inserting a sideslip angle lower variable angle block from a positioning clamping groove above a rotating groove of a sideslip angle rotating lower support, wherein the upper end and the lower end of the sideslip angle lower variable angle block are respectively positioned in a positioning clamping groove above the rotating groove of the sideslip angle rotating lower support and a sideslip angle bayonet on a sideslip angle rotating lower base fan-shaped flat plate; positioning of the sideslip angle of the horizontal double-engine layout air inlet test model is achieved through the sideslip angle upper angle changing block and the sideslip angle lower angle changing block.
Furthermore, the upper connection lug of the angle of attack mechanism and the lower connection lug of the angle of attack mechanism set a pre-deflection angle according to the requirement of an aircraft air inlet channel test angle of attack envelope, and the angle of attack range of the horizontal double-engine layout air inlet channel test model is changed.
Furthermore, the fixed support system is connected with the upper and lower bent blades of the wind tunnel angle-of-attack mechanism, the fixed support system and the rotary support system, and the upper and lower components in the fixed support system and the rotary support system through parallel threaded bolt assemblies which are arranged at equal intervals; the relative adjustment of the position of the horizontal double-engine layout air inlet test model in the wind tunnel test section is realized by changing the connection position.
Furthermore, a side slip angle scale mark and a marking line are carved on a circular groove at the front end of the top of the side slip angle rotating upper bracket; the round boss at the front end of the bottom of the sideslip angle rotating lower support is carved with sideslip angle scale lines and marking lines; the angles positioned by the angle changing block on the sideslip angle and the angle positioning by the angle changing block under the sideslip angle are mutually verified through the relative rotating angle of the marked line.
Further, when the sideslip angle upper angle-changing block and the sideslip angle lower angle-changing block are installed in the forward direction, the sideslip angle upper angle-changing block and the sideslip angle lower angle-changing block correspond to the sideslip angle positive angle of the horizontal double-engine layout air inlet test model, and when the sideslip angle upper angle-changing block and the sideslip angle lower angle-changing block are installed in the reverse direction, the sideslip angle upper angle-changing block and the sideslip angle lower angle-changing block correspond to the sideslip angle negative angle of the horizontal double-engine layout air inlet test model; the installation directions of the variable angle blocks at the upper side slip angle and the variable angle blocks at the lower side slip angle are synchronously changed, so that the side slip angle direction of the horizontal double-engine layout air inlet test model is changed.
The installation process and the test process of the horizontal double-engine layout air inlet channel wind tunnel test device are as follows:
s1, connecting and installing a lower connection lug of an angle-of-attack mechanism, a sideslip angle rotating lower base, a sideslip angle rotating lower support, a flowmeter front support, a sideslip angle rotating upper base and an upper connection lug of the angle-of-attack mechanism from bottom to top in sequence; the rear bracket of the flowmeter is arranged behind the front bracket of the flowmeter;
s2, horizontally and parallelly installing two flowmeters on a front flowmeter support and a rear flowmeter support through a front section sleeve support and a rear section fixed support of the flowmeters;
s3, fixedly connecting an upper connecting lug of the angle-of-attack mechanism with an upper curved knife of the angle-of-attack mechanism, and fixedly connecting a lower connecting lug of the angle-of-attack mechanism with a lower curved knife of the angle-of-attack mechanism;
s4, during testing, synchronously rotating the sideslip angle rotating upper support, the flowmeter front support, the flowmeter rear support and the sideslip angle rotating lower support to a preset sideslip angle around a rotating shaft, installing a corresponding sideslip angle upper angle changing block and a corresponding sideslip angle lower angle changing block, realizing positioning of the sideslip angle of the horizontal double-engine layout air inlet channel test model, and connecting and tensioning through a series of bolt threads between the sideslip angle rotating upper support and the sideslip angle rotating upper base and between the sideslip angle rotating lower base and the sideslip angle rotating lower support; and finally, after the horizontal double-engine layout air inlet test model is confirmed to reach a preset test state, carrying out an air blowing test.
The horizontal double-engine layout air inlet tunnel test device adopts a split design and building block splicing mode, has reasonable layout and simple structure, and has the following specific characteristics:
a. two flowmeters are horizontally arranged on a rotary supporting system side by side, the rotary supporting system rotates relative to a fixed supporting system to change a sideslip angle, and a sideslip angle positioning system locks the sideslip angle.
b. The form that the rotary supporting system rotates around a rotating shaft to change a sideslip angle and the variable angle block locks the sideslip angle is adopted, the problem that the operation ranges of an attack angle and the sideslip angle are coupled in a double-rotating-shaft sideslip changing mode of a wind tunnel test is solved, according to different test requirements, an upper connection lug piece of an attack angle mechanism with an attack angle pre-deflection angle and a lower connection lug piece of the attack angle mechanism are designed, and an attack angle envelope line of a horizontal double-engine layout air inlet channel test is expanded.
c. The connecting position between the fixed supporting system and the wind tunnel bent knife (or between the fixed supporting system and the rotary supporting system, or between the upper part and the lower part of the fixed supporting system and the rotary supporting system) is synchronously changed, the position of the horizontal double-distribution air inlet channel test model in the wind tunnel test section can be adjusted, and the requirements of the air inlet channel test on the schlieren area are met.
d. The upper base and the lower support are rotated by the sideslip angle, so that the rotating groove not only provides a running space for the fan-shaped flat plate when the sideslip angle rotates, but also plays roles in longitudinal positioning and structural strength enhancement.
e. The installation positions of the sideslip angle upper variable angle block and the sideslip angle lower variable angle block are designed at the rotating grooves of the sideslip angle rotating upper base and the sideslip angle rotating lower support, the force arm is long, and large transverse load can be borne.
f. The flow meter front support and the flow meter rear support are independently designed, so that the flow meter is convenient to mount; through processing the sleeve support at the front section of the flowmeter and the fixed support at the rear section of the flowmeter with different wheelbases, the requirement of an air inlet channel test on the distance between the central axes of the two flowmeters is conveniently met, and the development cost is reduced.
g. The upper variable angle block of the sideslip angle and the lower variable angle block of the sideslip angle are replaced by operating from the upper surface of the corresponding rotary groove, so that the operation is convenient and fast, and after the sideslip angle is replaced, the test can be continuously carried out without leveling the test model of the double-engine layout air inlet channel, the test preparation time is saved, and the test efficiency is improved.
According to the horizontal double-engine layout air inlet duct wind tunnel test device, two flowmeters are horizontally arranged on a rotary supporting system side by side, the rotary supporting system rotates relative to a fixed supporting system to change a sideslip angle, and a sideslip angle positioning system locks a sideslip angle mode, so that a reliable test supporting scheme is provided for a horizontal double-engine layout aircraft air inlet duct wind tunnel test.
Drawings
FIG. 1 is a schematic structural diagram of a horizontal double-engine layout air inlet duct wind tunnel test device.
In the figure, 1, the upper base is rotated by a sideslip angle; 2. the upper bracket is rotated by a sideslip angle; 3. an upper variable angle block of a sideslip angle; 4. a flow meter front support; 5. a flow meter rear bracket; 6. the lower bracket is rotated by a sideslip angle; 7. the lower base is rotated by a sideslip angle; 8. a sideslip angle lower angle changing block; 9. a flow meter; 10. the attack angle mechanism is connected with a lug; 11. the lower part of the attack angle mechanism is connected with a lug; 12. a sleeve support at the front section of the flowmeter; 13. a rear section fixed support of the flowmeter; 14. a wind tunnel test section.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
The horizontal double-engine layout air inlet channel wind tunnel test device comprises a fixed support system, a rotary support system and a sideslip angle positioning system; the rotary supporting system rotates relative to the fixed supporting system, and the sideslip angle of the horizontal double-engine layout air inlet channel test model is changed; the sideslip angle positioning system locks the sideslip angle of the horizontal double-engine layout air inlet channel test model; the central axes of the two flowmeters 9 of the horizontal double-engine layout air inlet channel test model are parallel and are distributed in bilateral symmetry.
Further, the fixed support system comprises a sideslip angle rotating upper base 1, a sideslip angle rotating lower base 7, an angle-of-attack mechanism upper connecting lug 10 and an angle-of-attack mechanism lower connecting lug 11; the mechanism is divided into an upper group and a lower group, wherein one group comprises a sideslip angle rotating upper base 1 and an attack angle mechanism upper connecting lug 10, and the other group comprises a sideslip angle rotating lower base 7 and an attack angle mechanism lower connecting lug 11;
the top of a connecting lug piece 10 on the angle-of-attack mechanism is fixedly connected with an upper curved knife interface of the wind tunnel angle-of-attack mechanism above a horizontal symmetrical plane of the wind tunnel, and the bottom of the connecting lug piece 10 on the angle-of-attack mechanism is fixedly connected with the top of the sideslip angle rotating upper base 1; the bottom of a lower connecting lug 11 of the angle-of-attack mechanism is fixedly connected with a lower bent blade interface of the wind tunnel angle-of-attack mechanism below a horizontal symmetrical plane of the wind tunnel, and the top of the lower connecting lug 11 of the angle-of-attack mechanism is fixedly connected with the bottom of the sideslip angle rotating lower base 7;
the front end of the bottom of the sideslip angular rotation upper base 1 is provided with a circular boss, the rear end of the bottom is provided with a rotation groove, and a positioning clamping groove is arranged above the rotation groove; a circular groove is formed in the front end of the top of the sideslip angle rotating lower base 7, a fan-shaped flat plate is arranged at the rear end of the bottom of the sideslip angle rotating lower base, and a sideslip angle bayonet is formed in the fan-shaped flat plate; the axes of the circular boss, the rotary groove and the circular groove are overlapped.
Further, the rotary support system comprises a sideslip angle rotary upper support 2, a flowmeter front support 4, a flowmeter rear support 5, a sideslip angle rotary lower support 6, a flowmeter front section sleeve support 12 and a flowmeter rear section fixed support 13;
the rotary supporting system is sequentially sleeved with a sideslip angle rotary lower support 6, a flowmeter front support 4 and a sideslip angle rotary upper support 2 from bottom to top, the flowmeter front support 4 is connected with a flowmeter rear support 5 in a front-back mode, a flowmeter front section sleeve support 12 is installed on the flowmeter front support 4, and a flowmeter rear section fixed support 13 is installed on the flowmeter rear support 5; the rear-section fixed support 13 of the flowmeter is X-shaped and is provided with bayonets which are symmetrical left and right;
the front end of the top of the sideslip angular rotation upper bracket 2 is provided with a circular groove matched with a circular boss at the front end of the bottom of the sideslip angular rotation upper base 1, the rear end of the top of the sideslip angular rotation upper bracket 2 is provided with a fan-shaped flat plate matched with a rotary groove at the rear end of the bottom of the sideslip angular rotation upper base 1, and a sideslip angular bayonet is arranged on the fan-shaped flat plate; a circular boss matched with a circular groove at the front end of the top of the sideslip angular rotation lower base 7 is arranged at the front end of the bottom of the sideslip angular rotation lower support 6, a rotating groove matched with a fan-shaped flat plate at the rear end of the bottom of the sideslip angular rotation lower support 6 is arranged at the rear end of the bottom of the sideslip angular rotation lower support 6, and a positioning clamping groove is arranged above the rotating groove;
the two flowmeters 9 are horizontally arranged side by side and are symmetrically installed in the left and right directions, the front end of each flowmeter 9 is connected with an inlet outlet and related test parts corresponding to the horizontal double-engine layout inlet test model, the front section of each flowmeter is sleeved in a sleeve of a sleeve support 12 at the front section of each flowmeter, and the rear section of each flowmeter is clamped on a bayonet corresponding to a fixed support 13 at the rear section of each X-shaped flowmeter;
the main structures of the sideslip angle rotating upper base 1 and the sideslip angle rotating lower support 6 are similar, and the main structures of the sideslip angle rotating upper support 2 and the sideslip angle rotating lower base 7 are similar; the circular bosses, the circular grooves and the sector flat plates of the sideslip angular rotation upper bracket 2 and the sideslip angular rotation lower bracket 6 are superposed with the circular bosses, the circular grooves and the circular grooves of the sideslip angular rotation upper base 1 and the sideslip angular rotation lower base 7; the rotary supporting system is connected with the sideslip angle rotary upper base 1 through the sideslip angle rotary upper support 2, is connected with the sideslip angle rotary lower base 7 through the sideslip angle rotary lower support 6, and rotates around an axis.
Further, the sideslip angle positioning system comprises a sideslip angle upper angle changing block 3 and a sideslip angle lower angle changing block 8; the outline of the sideslip angle upper variable angle block 3 and the outline of the sideslip angle lower variable angle block 8 are consistent with the outline of the positioning clamping groove;
when the rotary support system is rotated to a specified side-slip angle position: inserting the sideslip angle upper angle-changing block 3 from a positioning clamping groove above a rotating groove of the sideslip angle rotating upper base 1, and respectively positioning the upper end and the lower end of the sideslip angle upper angle-changing block 3 at the positioning clamping groove above the rotating groove of the sideslip angle rotating upper base 1 and a sideslip angle bayonet on a fan-shaped flat plate of the sideslip angle rotating upper bracket 2; inserting a sideslip angle lower variable angle block 8 from a positioning clamping groove above a rotating groove of a sideslip angle rotating lower support 6, wherein the upper end and the lower end of the sideslip angle lower variable angle block 8 are respectively positioned in a positioning clamping groove above the rotating groove of the sideslip angle rotating lower support 6 and a sideslip angle bayonet on a sector flat plate of a sideslip angle rotating lower base 7; the positioning of the sideslip angle of the horizontal double-engine layout air inlet test model is realized through the sideslip angle upper angle changing block 3 and the sideslip angle lower angle changing block 8.
Furthermore, the upper connection lug 10 of the angle of attack mechanism and the lower connection lug 11 of the angle of attack mechanism set a pre-deflection angle according to the requirement of the test angle of attack envelope of the aircraft air inlet channel, and the angle of attack range of the horizontal double-engine layout air inlet channel test model is changed.
Furthermore, the fixed support system is connected with the upper and lower bent blades of the wind tunnel angle-of-attack mechanism, the fixed support system and the rotary support system, and the upper and lower components in the fixed support system and the rotary support system through parallel threaded bolt assemblies which are arranged at equal intervals; the relative adjustment of the position of the horizontal double-engine layout air inlet channel test model in the wind tunnel test section is realized by changing the connection position.
Furthermore, a round groove at the front end of the top of the sideslip angle rotating upper bracket 2 is carved with sideslip angle scale lines and marking lines; the round boss at the front end of the bottom of the sideslip angle rotating lower bracket 6 is carved with sideslip angle scale lines and marking lines; the angles positioned by the side slip angle upper angle changing block 3 and the side slip angle lower angle changing block 8 are mutually verified through the relative rotation angle of the marked lines.
Further, when the sideslip angle upper angle-changing block 3 and the sideslip angle lower angle-changing block 8 are installed in the forward direction, the sideslip angle upper angle-changing block corresponds to the sideslip angle positive angle of the horizontal double-engine layout air inlet test model, and when the sideslip angle upper angle-changing block 3 and the sideslip angle lower angle-changing block 8 are installed in the reverse direction, the sideslip angle lower angle-changing block corresponds to the sideslip angle negative angle of the horizontal double-engine layout air inlet test model; the sideslip angle direction of the horizontal double-engine layout air inlet channel test model is changed by synchronously changing the installation directions of the sideslip angle upper angle-changing block 3 and the sideslip angle lower angle-changing block 8.
Example 1
As shown in fig. 1, the horizontal double-engine air inlet duct wind tunnel test device of the present embodiment is installed on the upper curved blade and the lower curved blade of the angle-of-attack mechanism of the wind tunnel test section 14.
In the present embodiment, the distance between the center axes of the two flow meters 9 is 187.5mm.
In this embodiment, the angle of attack operation range of the wind tunnel angle of attack mechanism itself is-18 to 18 degrees, the variation range of the sideslip angle of the air inlet tunnel test device is-12 to 12 degrees, the angle of attack pre-deflection angle of the upper connection lug 10 of the angle of attack mechanism and the lower connection lug 11 of the angle of attack mechanism is 10 degrees, and the test envelope that the air inlet tunnel test device can realize is: the angle of attack ranges from-8 degrees to 28 degrees, the angle of attack envelope of the sideslip angle ranges from-12 degrees to 12 degrees, namely the test angle of attack ranges from-8 degrees to 28 degrees in the whole variation range of the sideslip angle; if other attack angle ranges need to be realized, only the upper connection lug 10 of the attack angle mechanism and the lower connection lug 11 of the attack angle mechanism with corresponding pre-deflection angles need to be processed.
In the embodiment, the left and right sides of the circular groove at the front end of the top of the upper sideslip angle rotating bracket 2 and the lower sideslip angle rotating base 7 are respectively provided with 6 threaded holes, and the included angle between the two adjacent threaded holes and the connecting line of the rotating centers on the rotating shaft is 12 degrees; 3 kidney holes are respectively arranged on the left side and the right side above the circular bosses at the front ends of the bottoms of the sideslip angle rotating upper base 1 and the sideslip angle rotating lower support 6, the included angle between the connecting line of the circular arc centers at the two ends of the kidney holes and the rotating center is 12 degrees, and each kidney hole corresponds to 2 threaded holes. After the sideslip angle is rotated to the position, the rotating supporting system and the fixed supporting system are tensioned through 6 screw rods, and the connection strength is further enhanced.
In this embodiment, the connection distance between the bolt thread combinations between the angle-of-attack mechanism upper connection lug 10 and the sideslip angle rotation upper base 1 as well as between the angle-of-attack mechanism lower connection lug 11 and the sideslip angle rotation lower base 7 is 40mm, the connection distance between the bolt thread combinations between the flow meter front support 4 and the flow meter rear support 5 as well as between the sideslip angle rotation upper support 2 and between the angle-of-attack mechanism lower support 6 is also 40mm, and the positions of the flow meter front support 4 and the flow meter rear support 5 as well as the positions of the sideslip angle rotation upper support 2 and between the angle-of-attack mechanism lower connection lug 11 and the sideslip angle rotation lower base 7 are synchronously adjusted by and independently adjusting the relative positions of the angle-of-attack mechanism upper connection lug 10 and the sideslip angle rotation upper base 1 as well as between the angle-of-attack mechanism lower connection lug 11 and the sideslip angle rotation lower base 7, or by synchronously adjusting the relative positions of the flow meter front support 4 and the flow meter rear support 5 as well as between the sideslip angle rotation upper support 2 and the sideslip angle rotation lower support 6, thereby changing the position of the horizontal double-hair layout air inlet duct test model in the wind tunnel.
The present invention is not limited to the above-described embodiments, and those skilled in the art will be able to make various modifications without creative efforts from the above-described conception, and fall within the scope of the present invention.
Claims (8)
1. A wind tunnel test device for a horizontal double-engine layout air inlet passage is characterized by comprising a fixed support system, a rotary support system and a sideslip angle positioning system; the rotary supporting system rotates relative to the fixed supporting system, and the sideslip angle of the horizontal double-engine layout air inlet test model is changed; the sideslip angle positioning system locks the sideslip angle of the horizontal double-engine layout air inlet channel test model; the central axes of the two flowmeters (9) of the horizontal double-engine layout air inlet channel test model are parallel and are distributed in bilateral symmetry.
2. The air inlet channel wind tunnel test device with the horizontal double-engine layout as claimed in claim 1, wherein the fixed support system comprises a sideslip angle rotating upper base (1), a sideslip angle rotating lower base (7), an angle-of-attack mechanism upper connecting lug (10) and an angle-of-attack mechanism lower connecting lug (11); the mechanism is divided into an upper group and a lower group, wherein one group is a sideslip angle rotating upper base (1) and an upper connecting lug (10) of an angle-of-attack mechanism, and the other group is a sideslip angle rotating lower base (7) and a lower connecting lug (11) of the angle-of-attack mechanism;
the top of a connecting lug piece (10) on the angle-of-attack mechanism is fixedly connected with an upper curved knife interface of the wind tunnel angle-of-attack mechanism above a horizontal symmetrical plane of the wind tunnel, and the bottom of the connecting lug piece (10) on the angle-of-attack mechanism is fixedly connected with the top of the sideslip angle rotating upper base (1); the bottom of a lower connecting lug (11) of the angle-of-attack mechanism is fixedly connected with a lower bent blade interface of the wind tunnel angle-of-attack mechanism below a horizontal symmetry plane of the wind tunnel, and the top of the lower connecting lug (11) of the angle-of-attack mechanism is fixedly connected with the bottom of the sideslip angle rotating lower base (7);
a round boss is arranged at the front end of the bottom of the sideslip angular rotation upper base (1), a rotation groove is arranged at the rear end of the bottom, and a positioning clamping groove is arranged above the rotation groove; a circular groove is formed in the front end of the top of the sideslip angle rotating lower base (7), a fan-shaped flat plate is arranged at the rear end of the bottom of the sideslip angle rotating lower base, and a sideslip angle bayonet is formed in the fan-shaped flat plate; the axes of the circular boss, the rotary groove and the circular groove are overlapped.
3. The air inlet channel wind tunnel test device with the horizontal double-engine layout as claimed in claim 2, wherein the rotary supporting system comprises a sideslip angle rotary upper support (2), a flowmeter front support (4), a flowmeter rear support (5), a sideslip angle rotary lower support (6), a flowmeter front section sleeve support (12) and a flowmeter rear section fixed support (13);
the rotary supporting system is sequentially sleeved with a sideslip angle rotary lower support (6), a flowmeter front support (4) and a sideslip angle rotary upper support (2) from bottom to top, the flowmeter front support (4) is connected with a flowmeter rear support (5) in a front-back mode, a flowmeter front section sleeve support (12) is installed on the flowmeter front support (4), and a flowmeter rear section fixed support (13) is installed on the flowmeter rear support (5); the rear section fixed support (13) of the flowmeter is X-shaped and is provided with bayonets which are symmetrical left and right;
the front end of the top of the sideslip angle rotating upper support (2) is provided with a circular groove matched with a circular boss at the front end of the bottom of the sideslip angle rotating upper base (1), the rear end of the top of the sideslip angle rotating upper support (2) is provided with a fan-shaped flat plate matched with a rotating groove at the rear end of the bottom of the sideslip angle rotating upper base (1), and a sideslip angle bayonet is arranged on the fan-shaped flat plate; a circular boss matched with a circular groove at the front end of the top of the sideslip angular rotation lower base (7) is arranged at the front end of the bottom of the sideslip angular rotation lower support (6), a rotating groove matched with a fan-shaped flat plate at the rear end of the bottom of the sideslip angular rotation lower support (6) is arranged at the rear end of the bottom of the sideslip angular rotation lower support (6), and a positioning clamping groove is arranged above the rotating groove;
the two flowmeters (9) are horizontally arranged side by side and are symmetrically installed in the left and right directions, the front end of each flowmeter (9) is connected with an inlet channel outlet and related test parts corresponding to the horizontal double-engine layout inlet channel test model, the front section of each flowmeter is sleeved in a sleeve of a sleeve support (12) at the front section of each flowmeter, and the rear section of each flowmeter is clamped on a bayonet corresponding to a fixed support (13) at the rear section of the X-shaped flowmeter;
the circular bosses, the circular grooves and the sector flat plates of the sideslip angle rotating upper bracket (2) and the sideslip angle rotating lower bracket (6) are superposed with the axes of the circular bosses, the circular grooves and the circular grooves of the sideslip angle rotating upper base (1) and the sideslip angle rotating lower base (7); the rotary supporting system is connected with the sideslip angle rotary upper base (1) through the sideslip angle rotary upper support (2), is connected with the sideslip angle rotary lower base (7) through the sideslip angle rotary lower support (6), and rotates around an axis.
4. The horizontal double-engine layout air inlet channel wind tunnel test device according to claim 3, wherein the sideslip angle positioning system comprises a sideslip angle upper variable angle block (3) and a sideslip angle lower variable angle block (8); the outline of the side slip angle upper angle-changing block (3) and the outline of the side slip angle lower angle-changing block (8) are consistent with the positioning clamping groove;
when the rotary support system rotates to a specified side-slip angle position: inserting a sideslip angle upper angle-changing block (3) into a positioning clamping groove above a rotating groove of a sideslip angle rotating upper base (1), wherein the upper end and the lower end of the sideslip angle upper angle-changing block (3) are respectively positioned in the positioning clamping groove above the rotating groove of the sideslip angle rotating upper base (1) and a sideslip angle bayonet on a sector flat plate of a sideslip angle rotating upper bracket (2); inserting a sideslip angle lower variable angle block (8) into a positioning clamping groove above a rotating groove of a sideslip angle rotating lower support (6), wherein the upper end and the lower end of the sideslip angle lower variable angle block (8) are respectively positioned in a positioning clamping groove above the rotating groove of the sideslip angle rotating lower support (6) and a sideslip angle bayonet on a sector flat plate of a sideslip angle rotating lower base (7); the positioning of the sideslip angle of the horizontal double-engine layout air inlet test model is realized through the sideslip angle upper angle-changing block (3) and the sideslip angle lower angle-changing block (8).
5. The wind tunnel test device for the horizontal double-engine layout air inlet passage according to claim 4 is characterized in that a pre-deflection angle is set by an upper connection lug (10) of the angle-of-attack mechanism and a lower connection lug (11) of the angle-of-attack mechanism according to the requirement of an aircraft air inlet passage test angle-of-attack envelope, and the angle-of-attack range of a horizontal double-engine layout air inlet passage test model is changed.
6. The horizontal double-engine layout air inlet channel wind tunnel test device according to claim 4, wherein the fixed support system is connected with the upper and lower bent blades of the wind tunnel angle-of-attack mechanism, the fixed support system is connected with the rotary support system, and the upper and lower components inside the fixed support system and the rotary support system are connected through parallel threaded bolt assemblies arranged at equal intervals; the relative adjustment of the position of the horizontal double-engine layout air inlet test model in the wind tunnel test section is realized by changing the connection position.
7. The horizontal double-engine layout air inlet channel wind tunnel test device according to claim 4, characterized in that a side slip angle scale mark and a marking line are engraved on a circular groove at the front end of the top of the side slip angle rotating upper bracket (2); the round boss at the front end of the bottom of the sideslip angle rotating lower bracket (6) is carved with sideslip angle scale lines and marking lines; the relative rotation angle of the marked line is mutually verified with the positioning angles of the sideslip angle upper angle-changing block (3) and the sideslip angle lower angle-changing block (8).
8. The horizontal double-engine layout air inlet channel wind tunnel test device according to claim 4, characterized in that when the sideslip angle up-changing block (3) and the sideslip angle down-changing block (8) are installed in the forward direction, the sideslip angle up-changing block corresponds to the sideslip angle of the horizontal double-engine layout air inlet channel test model, and when the sideslip angle up-changing block (3) and the sideslip angle down-changing block (8) are installed in the reverse direction, the sideslip angle up-changing block corresponds to the sideslip angle negative angle of the horizontal double-engine layout air inlet channel test model; the sideslip angle direction of the horizontal double-engine layout air inlet test model is changed by synchronously changing the installation directions of the sideslip angle upper variable angle block (3) and the sideslip angle lower variable angle block (8).
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