CN111577465A - Hypersonic inlet lip rotating device and test method - Google Patents
Hypersonic inlet lip rotating device and test method Download PDFInfo
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- CN111577465A CN111577465A CN202010320138.5A CN202010320138A CN111577465A CN 111577465 A CN111577465 A CN 111577465A CN 202010320138 A CN202010320138 A CN 202010320138A CN 111577465 A CN111577465 A CN 111577465A
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- 238000010998 test method Methods 0.000 title claims abstract description 8
- 238000012360 testing method Methods 0.000 claims description 29
- 238000000034 method Methods 0.000 abstract description 11
- 230000008602 contraction Effects 0.000 abstract description 5
- YAFQFNOUYXZVPZ-UHFFFAOYSA-N liproxstatin-1 Chemical compound ClC1=CC=CC(CNC=2C3(CCNCC3)NC3=CC=CC=C3N=2)=C1 YAFQFNOUYXZVPZ-UHFFFAOYSA-N 0.000 description 34
- 238000013461 design Methods 0.000 description 5
- 238000011160 research Methods 0.000 description 5
- 238000013459 approach Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000013519 translation Methods 0.000 description 2
- 108091053398 TRIM/RBCC family Proteins 0.000 description 1
- 102000011408 Tripartite Motif Proteins Human genes 0.000 description 1
- 102100040255 Tubulin-specific chaperone C Human genes 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 108010093459 tubulin-specific chaperone C Proteins 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to the technical field of flow control of an air inlet, and discloses a lip rotating device of a hypersonic air inlet and a test method, wherein the lip rotating device comprises side walls which are fixed on the upper parts of the front ends of two sides of an air inlet model and are provided with shaft holes, and lip covers are arranged at the upper edges between the side walls; a rotary lip with a rocker arm and a shaft hole is arranged at the front edge of the lip cover, and the rotary lip is movably connected between the side walls through a rotary shaft, a rotary shaft gasket and a rotary shaft nut; a linear motor is fixed at the top of the lip cover, and a push rod is installed at the front end of a rotating shaft of the linear motor; the push rod is connected with the rocker arm on the rotary lip through a pin shaft, a pin shaft gasket and a pin shaft nut. According to the invention, the linear motor is controlled to drive the push rod to stretch, so that the rocker arm drives the rotary lip to rotate around the rotary shaft, and the opening or closing of the air inlet channel is realized; and a variable geometry process with variable contraction ratio of the air inlet is realized, so that the maximum self-starting angle of the rotary lip and the minimum starting angle of the rotary lip are obtained.
Description
Technical Field
The invention relates to the technical field of flow control of an air inlet, in particular to a lip rotating device of a hypersonic speed air inlet and a test method.
Background
The air-breathing hypersonic propulsion technology is a hotspot of current domestic and foreign research, a hypersonic air inlet channel is used as a key component of a propulsion system, the hypersonic air inlet channel mainly has the main functions of reducing and pressurizing free incoming flow, providing stable air flow for combustion in a combustion chamber, and the performance of the hypersonic propulsion system is directly influenced by the advantages and disadvantages of the aerodynamic performance of the air inlet channel. The working range of the hypersonic inlet is wide, for example, the working range of Mach number is often between Ma4 and Ma6+, and some working ranges are even as high as Ma 12. It is not possible to maintain high aerodynamic performance for a fixed geometry inlet over such a wide range, and using a variable geometry approach allows the inlet to maintain high aerodynamic performance at all times. Therefore, variable geometry air inlets are widely used in the field of foreign TBCC and RBCC combined power research. On the other hand, in a wind tunnel test, when a fixed geometry air inlet is used, when the shrinkage in the air inlet is large, the situation that the air inlet cannot be started often occurs, so that the test fails, and at the moment, the variable geometry air inlet is used, so that the air inlet can be kept started or restarted, and the smooth test is ensured.
Therefore, the use of variable geometry air inlets, or the realization of variable geometry air inlets, is an important technical measure. Meanwhile, the realization of the variable geometry of the air inlet channel is also an effective way for researching the contraction ratio distribution in the air inlet channel and developing the interference of the shock wave boundary layer of the air inlet channel. There are many schemes for realizing the variable geometry of the air inlet at home and abroad, and the common schemes are a translation lip and a rotation lip. The U.S. adopts a translation scheme in the GTX project and a rotation scheme in the X-43A aircraft, the latter is successfully realized in flight tests, but the related specific design is not disclosed for confidentiality reasons. The variable geometry of the air inlet in China is limited to ground research, and the lip is mainly changed statically (namely the angle and the position of the lip are changed before the test, the lip is kept unchanged during the test, and the angle and the position of the lip are changed again after the test and the test is continued).
In conclusion, the lip of the air inlet cannot be adjusted in real time in the test process and cannot meet the requirement of real-time variable geometry control, so that the pneumatic performance of the air inlet cannot be improved in the test process.
Disclosure of Invention
Based on the problems, the hypersonic inlet lip rotating device and the test method provided by the invention have the advantages that the linear motor is controlled to drive the push rod to stretch, so that the rocker arm drives the rotating lip to rotate around the rotating shaft, and the opening or closing of the inlet is realized; and a variable geometry process with variable contraction ratio of the air inlet is realized, so that the maximum self-starting angle of the rotary lip and the minimum starting angle of the rotary lip are obtained.
In order to solve the technical problem, the invention provides a hypersonic inlet lip rotating device which comprises side walls fixed on two sides of an inlet model, wherein a lip cover is arranged at the upper edge between the two side walls; a rotary lip with a shaft hole is arranged at the front edge of the lip cover and is movably connected between the side walls through a rotary shaft; a linear motor is fixed at the top of the lip cover, and a push rod is installed at the front end of a rotating shaft of the linear motor; and a rocker arm is fixed on the rotary lip and is in driving connection with the push rod.
Furthermore, the rotary lip is fixed between the side walls through a rotary shaft, a rotary shaft gasket and a rotary shaft nut, and the shaft end of the rotary shaft is provided with a locking nut.
Furthermore, the top of the rocker arm of the rotating lip is provided with a sliding groove, and the push rod is connected with the sliding groove of the rocker arm of the rotating lip through a pin shaft, a pin shaft gasket and a pin shaft nut.
In order to solve the technical problem, the invention also provides a test method of the hypersonic inlet lip rotating device, which comprises the following steps:
s1, before the first vehicle test, controlling a linear motor, rotating a rotating lip to a position where the inner wall surface of the rotating lip forms an angle of 10 degrees with the horizontal plane, and then performing a wind tunnel driving test, wherein an air inlet channel is not started in the state;
s2, when the air inlet channel is not started in the S1 state, the air is continuously blown without stopping, the linear motor is controlled to gradually push the rotary lip to rotate until the air inlet channel is in a closed state, and before the air inlet channel is closed, the air inlet channel is observed to be started again; determining an included angle between the inner wall surface of the lip and the horizontal plane when the air inlet duct is restarted, wherein the included angle is the maximum self-starting angle of the rotary lip;
s3, continuously controlling the linear motor in the same train number, pulling the rotary lip until the inner wall surface of the rotary lip forms an angle of 10 degrees with the horizontal plane again, enabling the air inlet channel to be in a starting state all the time, and stopping the wind tunnel at the moment;
s4, before a second vehicle test, controlling the linear motor to rotate the rotary lip to an air inlet closed state, then starting the wind tunnel, and after the flow field is stabilized, controlling the linear motor to pull the rotary lip to an angle of 10 degrees between the inner wall surface of the rotary lip and the horizontal plane, wherein the air inlet is smoothly started;
and S5, in the same train number in S4, continuously controlling the motor to pull the rotary lip until the air inlet enters an un-starting state, and determining the angle between the inner wall surface of the rotary lip and the horizontal plane at the moment, thereby obtaining the minimum startable angle.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, the linear motor is controlled to drive the push rod to stretch, so that the rocker arm drives the rotary lip to rotate around the rotary shaft, and the opening or closing of the air inlet channel is realized; and a variable geometry process with variable contraction ratio of the air inlet is realized, so that the maximum self-starting angle of the rotary lip and the minimum starting angle of the rotary lip are obtained.
2. The angle of the rotary lip is adjusted by controlling the linear motor, so that the air inlet which is not started is restarted.
Drawings
FIG. 1 is a schematic structural diagram of a hypersonic inlet lip rotating device in the embodiment 1 and 2;
FIG. 2 is a disassembled view of the components of the hypersonic inlet lip rotating device in embodiments 1 and 2;
FIG. 3 is a schematic structural view of an intake duct in a closed state according to embodiment 2;
FIG. 4 is a schematic structural view of an intake duct in a design state according to embodiment 2;
FIG. 5 is a schematic structural view of an intake duct in a maximum flare angle state in embodiment 2;
wherein: 1. rotating the lip; 2. a rotating shaft; 3. a rotating shaft spacer; 4. rotating the spindle nut; 5. a pin shaft; 6. a pin shaft gasket; 7. a pin nut; 8. a push rod; 9. a linear motor; 10. an air inlet channel model; 11. a lip cover; 12. a side wall; 13. a rocker arm.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1:
referring to fig. 1 and 2, the hypersonic inlet lip rotating device comprises side walls 12 fixed on two sides of an inlet model 10, and a lip cover 11 is arranged at the upper edge position between the two side walls 12; a rotary lip 1 with a shaft hole is arranged at the front edge of the lip cover 11, and the rotary lip 1 is movably connected between the side walls 12 through a rotary shaft 2; a linear motor 9 is fixed at the top of the lip cover 11, and a push rod 8 is installed at the front end of a rotating shaft of the linear motor 9; a rocker arm 13 is fixed on the rotary lip 1, and the rocker arm 13 is in driving connection with the push rod 8.
The requirements of the wind tunnel test on the hypersonic inlet channel lip rotating device are as follows: the rotary lip 1 runs stably without jamming; the lip opening 1 is rotated to act quickly; the rotary lip 1 has no idle return and no step loss and has a self-locking function. In this embodiment, the components of the hypersonic inlet lip rotating device are shown in fig. 2, and include: the device comprises a rotary lip 1, a rotary shaft 2, a rotary shaft gasket 3, a rotary shaft nut 4, a pin shaft 5, a pin shaft gasket 6, a pin shaft nut 7, a push rod 8, a linear motor 9, an air inlet channel model 10, a lip cover 11 and a side wall 12; in order to control the rotation of the rotating lip 1, in this embodiment, a rocker arm 13 is disposed on the rotating lip 1, and the rocker arm 13 is provided with a sliding slot and connected with a push rod 8 of an external linear stepping motor through a pin 5. The rotary lip 1 with the rocker arm 13 is fixed between the side walls 12 of the lip cover 11 through the rotary shaft 2, the rotary shaft gasket 3 and the rotary shaft nut 4, the rotary lip 1 comprises a shaft hole and can rotate around the rotary shaft 2 after being inserted into the rotary shaft 2, and two ends of the rotary shaft 2 are connected with the side walls 12 of the inlet lip cover 11, so that the rotary lip 1 is connected with the inlet lip cover 11; one end of a push rod 8 is connected with a rocker arm 13 of the rotary lip 1 through a pin shaft 5, a pin shaft gasket 6 and a pin shaft nut 7, the other end of the push rod 8 is connected with a linear motor 9, and a base of the linear motor 9 is fixed on a lip cover 11 of the air inlet channel model 10. The rotary lip 1 can rotate around the rotary shaft 2, so that the opening and closing of the air inlet channel can be realized, and the variable geometry process with the variable contraction ratio of the air inlet channel can be realized.
In order to prevent the rotation shaft 2 from slipping out, the rotation shaft 2 is provided with a lock nut at the shaft end in the present embodiment.
Example 2:
referring to fig. 1-5, a test method of a hypersonic inlet lip rotating device:
three typical states of a hypersonic inlet:
fig. 3-5 are schematic diagrams showing typical states of the lip rotating device in the dynamic operation process of the hypersonic inlet. The linear motor 9 is controlled, the rotating lip 1 of the hypersonic inlet channel can be adjusted through the rotating lip 1, and the hypersonic inlet channel is in three typical states:
the air inlet channel is in a closed state, as shown in FIG. 3;
the air inlet channel is in a design state, as shown in FIG. 4;
the inlet duct is in a maximum flare angle state as shown in fig. 5.
The incoming flow parameters of the wind tunnel in the embodiment are as follows: the nominal Mach number of the incoming flow is 4.0, the total pressure is 6.25atm, and the total temperature is 288K. The specific test steps are as follows:
s1, before the first vehicle test, controlling the linear motor 9, rotating the rotating lip 1 until the inner wall surface of the rotating lip forms an angle of 10 degrees with the horizontal plane (as shown in figure 4), and then performing a wind tunnel driving test, wherein the air inlet channel is not started in the state;
s2, when the air inlet channel is not started in the S1 state, the air is continuously blown without stopping, the linear motor 9 is controlled to gradually push the rotary lip 1 to rotate until the air inlet channel is in a closed state, and before the air inlet channel is closed, the air inlet channel is observed to be started again; determining an included angle between the inner wall surface of the lip and the horizontal plane when the air inlet channel is restarted, wherein the included angle is the maximum automatic starting angle of the rotary lip 1;
in the embodiment, before the air inlet is closed, an included angle of 13 degrees between the inner wall surface of the lip and the horizontal plane when the air inlet is restarted can be observed; it can be seen that the rotary lip 1 of the present invention obtained the maximum self-starting angle of the rotary lip 1 during the test.
S3, continuously controlling the linear motor 9 in the same train number, and pulling and rotating the lip 1 until the inner wall surface of the lip forms an angle of 10 degrees with the horizontal plane again, wherein the air inlet channel is always in a starting state; compared with the step S1, when the wind tunnel is not started and the inner wall surface of the rotary lip 1 forms an angle of 10 degrees with the horizontal plane, the air duct is in an un-started state after the wind tunnel is started; in the continuous blowing process of the wind tunnel, the linear motor 9 controls the rotary lip 1 to be in a starting state after the inner wall and the horizontal plane are in a design state, a closing state and a design state; this procedure indicates that the rotary lip 1 can restart the intake duct that is not started;
s4, before a second vehicle test, controlling the linear motor 9 to rotate the rotary lip 1 to an air inlet closed state (as shown in figure 3), then starting the wind tunnel, and after a flow field is stabilized, controlling the linear motor 9 to pull the rotary lip 1 until the inner wall surface of the rotary lip 1 forms an angle of 10 degrees with the horizontal plane (as shown in figure 4), and at the moment, smoothly starting the air inlet; this step actually successfully simulated the motion of the U.S. X-43A flight demonstration;
and S5, in the same train number in S4, continuously controlling the motor to pull the rotary lip 1 until the air inlet enters an un-starting state, and determining the angle between the inner wall surface of the rotary lip 1 and the horizontal plane at the moment, thereby obtaining the minimum startable angle. In the embodiment, the air inlet enters an un-starting state until the angle between the inner wall surface and the horizontal plane is reduced to 4 degrees; it follows that the rotary lip 1 according to the invention makes it possible to obtain a minimum possible starting angle in tests.
Summarizing, hypersonic inlet lip rotary device's functional characteristics:
(1) the angle of the rotary lip 1 is adjusted by controlling the linear motor 9, so that the air inlet which is not started is restarted;
(2) the lip rotating device can obtain the maximum automatic starting angle of the rotating lip 1 in the test process;
(3) the lip rotating apparatus can obtain the minimum startable angle of the rotating lip 1 during the test.
The lip rotating device is fully verified and applied in a ground test, is particularly suitable for experimental research of a hypersonic inlet channel with the Mach number of 4-6 +, and provides an operable technical approach for an inlet channel/engine matching test and experimental research of an integrated hypersonic aircraft. Preliminary tests also prove that the motor can bear high-temperature impact by carrying out thermal protection (such as water cooling and the like), the rotary lip 1 can be completely used in a high-enthalpy temporary flushing wind tunnel, the test result can directly simulate the actual situation of flight demonstration, and considerable benefits are obtained.
Other parts in this embodiment are the same as embodiment 1, and are not described herein again. The above is an embodiment of the present invention. The embodiments and specific parameters in the embodiments are only for the purpose of clearly illustrating the verification process of the invention and are not intended to limit the scope of the invention, which is defined by the claims, and all equivalent structural changes made by using the contents of the specification and the drawings of the present invention should be covered by the scope of the present invention.
Claims (4)
1. Hypersonic inlet duct lip rotary device, its characterized in that: comprises side walls (12) fixed on two sides of an air inlet channel model (10), and a lip cover (11) is arranged at the upper edge between the two side walls (12); a rotary lip (1) with a shaft hole is arranged at the front edge of the lip cover (11), and the rotary lip (1) is movably connected between the side walls (12) through a rotary shaft (2); a linear motor (9) is fixed at the top of the lip cover (11), and a push rod (8) is installed at the front end of a rotating shaft of the linear motor (9); a rocker arm (13) is fixed on the rotary lip (1), and the rocker arm (13) is in driving connection with the push rod (8).
2. The hypersonic inlet lip rotation device of claim 1, wherein: the rotary lip (1) is fixed between the side walls (12) through the rotary shaft (2), the rotary shaft gasket (3) and the rotary shaft nut (4), and the rotary shaft (2) is provided with a locking nut at the shaft end.
3. The hypersonic inlet lip rotation device of claim 1, wherein: the top of the rocker arm (13) of the rotary lip (1) is provided with a sliding groove, and the push rod (8) is connected with the sliding groove of the rocker arm (13) of the rotary lip (1) through the pin shaft (5), the pin shaft gasket (6) and the pin shaft nut (7).
4. A test method of a hypersonic inlet lip rotating device is based on any one of claims 1 to 3, and is characterized by comprising the following steps:
s1, before the first vehicle test, controlling a linear motor (9), rotating a rotating lip (1) until the inner wall surface of the rotating lip forms an angle of 10 degrees with the horizontal plane, and then performing a wind tunnel driving test, wherein an air inlet channel is not started in the state;
s2, when the air inlet channel is not started in the S1 state, the air is continuously blown without stopping, the linear motor (9) is controlled to gradually push the rotary lip (1) to rotate until the air inlet channel is in a closed state, and before the air inlet channel is closed, the air inlet channel is observed to be started again; determining an included angle between the inner wall surface of the lip and the horizontal plane when the air inlet channel is restarted, wherein the included angle is the maximum automatic starting angle of the rotary lip (1);
s3, continuously controlling the linear motor (9) in the same train number, pulling the rotary lip (1) until the inner wall surface of the rotary lip forms an angle of 10 degrees with the horizontal plane again, enabling the air inlet channel to be in a starting state all the time, and stopping the wind tunnel at the moment;
s4, before a second vehicle test, controlling the linear motor (9), rotating the rotary lip (1) to an air inlet closed state, then starting the wind tunnel, and after a flow field is stabilized, controlling the linear motor (9) to pull the rotary lip (1) until the inner wall surface of the rotary lip (1) forms an angle of 10 degrees with the horizontal plane, and at the moment, smoothly starting the air inlet;
s5, in the same train number in S4, the motor is continuously controlled to pull the rotary lip (1) until the air inlet enters an un-starting state, and at the moment, the angle between the inner wall surface of the rotary lip (1) and the horizontal plane is determined, so that the minimum starting angle is obtained.
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| CN202010320138.5A CN111577465A (en) | 2020-04-22 | 2020-04-22 | Hypersonic inlet lip rotating device and test method |
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| CN202010320138.5A CN111577465A (en) | 2020-04-22 | 2020-04-22 | Hypersonic inlet lip rotating device and test method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461494A (en) * | 2020-11-09 | 2021-03-09 | 中国空气动力研究与发展中心 | Pulse combustion wind tunnel model support-balance integrated force measuring device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461494A (en) * | 2020-11-09 | 2021-03-09 | 中国空气动力研究与发展中心 | Pulse combustion wind tunnel model support-balance integrated force measuring device |
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