CN111337755A - Multidirectional adjusting device and method for airplane radome in lightning current test - Google Patents

Multidirectional adjusting device and method for airplane radome in lightning current test Download PDF

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Publication number
CN111337755A
CN111337755A CN201910531243.0A CN201910531243A CN111337755A CN 111337755 A CN111337755 A CN 111337755A CN 201910531243 A CN201910531243 A CN 201910531243A CN 111337755 A CN111337755 A CN 111337755A
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adjusting
longitude
latitude
radome
gear
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CN111337755B (en
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段泽民
司晓亮
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Hefei Hangtai Electrophysics Co ltd
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Hefei Hangtai Electrophysics Co ltd
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08—Measuring electromagnetic field characteristics
    • G01R29/0807—Measuring electromagnetic field characteristics characterised by the application
    • G01R29/0814—Field measurements related to measuring influence on or from apparatus, components or humans, e.g. in ESD, EMI, EMC, EMP testing, measuring radiation leakage; detecting presence of micro- or radiowave emitters; dosimetry; testing shielding; measurements related to lightning
    • G01R29/0842—Measurements related to lightning, e.g. measuring electric disturbances, warning systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08—Measuring electromagnetic field characteristics
    • G01R29/0864—Measuring electromagnetic field characteristics characterised by constructional or functional features
    • G01R29/0871—Complete apparatus or systems; circuits, e.g. receivers or amplifiers

Abstract

The invention discloses a multidirectional adjusting device and an adjusting method for an aircraft radome in a lightning current test, wherein the device comprises the following components: the device comprises a hoisting joint, a longitude adjusting mechanism, a connecting shaft, a latitude adjusting mechanism and a radome mounting seat; one side of the longitude adjusting mechanism is connected with the hoisting joint, the longitude adjusting mechanism is connected with the latitude adjusting mechanism through a connecting shaft, and one side of the latitude adjusting mechanism is connected with the radome mounting seat. The method can quickly and accurately adjust the space position of the airplane radome required in the lightning current test process, reduces the preparation work in the early stage of the test, simultaneously shortens the time required in the lightning current test process of the radome, and reduces the cost of the whole test, thereby saving the cost of human resources in the lightning current test process of the airplane radome.

Description

Multidirectional adjusting device and method for airplane radome in lightning current test
Technical Field
The invention relates to the technical field of airplane radome lightning current tests, in particular to a multidirectional adjusting device and method for airplane radome lightning current tests.
Background
In the lightning current test process of the airplane radome, the radome needs to be adjusted to different angles to carry out lightning current tests. Among the prior art, to the angle modulation of aircraft radome, need be with the help of dedicated experimental frock, through the required spatial position when artifical the regulation in order to obtain radome lightning current test, and the outer face of special experimental frock of all passing through the radome is fixed. The prior art has the following defects:
the early preparation work of the radar cover lightning current test requires a long period and has high test cost. Because different radome profile shapes are different, and the used frock of every radome when carrying out the lightning current test is the difference, consequently before novel radome carries out the lightning current test, need redesign manufacturing this radome lightning current test in-process required special frock, this preparation process in earlier stage will consume a large amount of time, manpower resources, raw and other materials cost and manufacturing cost. And after the radar cover lightning current test is finished, the radar cover generally does not need to be repeatedly subjected to the lightning current test any more, and a special test tool used by the radar cover cannot be repeatedly utilized.
In the radar cover lightning current test process, the position adjustment of the radar cover consumes a great deal of time and human resources. In the process of adjusting the position of the radome, the radome needs to be adjusted artificially, and the space angle of the radome needs to be measured at any time in the adjustment process, so that the radome is positioned. This is a process of iterative adjustment, requiring a long adjustment period. And the position of the radome needs to be adjusted for multiple times in the lightning current test process of one radome, so that the period of the lightning current test of the airplane radome is prolonged, and simultaneously, multiple persons need to operate simultaneously in the adjusting process.
Disclosure of Invention
The invention provides a multidirectional adjusting device and an adjusting method of an aircraft radome in a lightning current test, aiming at overcoming the defects in the prior art, so that the spatial position of the aircraft radome in the lightning current test process can be quickly and accurately adjusted, the preparation work in the early stage of the test is reduced, the time required in the radar radome lightning current test process is shortened, the cost of the whole test is reduced, and the labor and resource cost of the aircraft radome in the lightning current test process is saved.
In order to achieve the purpose, the technical scheme of the invention is as follows:
the invention relates to a multidirectional adjusting device of an aircraft radome in a lightning current test, which is characterized by comprising the following components: the device comprises a hoisting joint, a longitude adjusting mechanism, a connecting shaft, a latitude adjusting mechanism, a turbine shaft, a radome mounting frame and a radome mounting seat;
the longitude adjusting mechanism includes: a longitude adjusting hemisphere, a longitude adjusting worm wheel and a longitude adjusting worm;
the latitude adjustment mechanism includes: a latitude adjusting hemisphere, a latitude adjusting worm wheel and a latitude adjusting worm;
the other side of the hoisting joint is fixedly connected with the vertex of the longitude adjusting hemisphere through a nut, and a connecting shaft is arranged on the symmetrical axis of the longitude adjusting hemisphere; the connecting shaft is installed through a deep groove ball bearing and a thrust ball bearing which are arranged on the inner side of the bottom of the longitude adjusting hemisphere; a boss is arranged on one side of the connecting shaft, and a groove is formed in the other side of the connecting shaft; the longitude adjusting turbine is sleeved on the connecting shaft; a first gear is coaxially and fixedly connected to the longitude adjusting turbine and matched with a gear on the first multi-ring potentiometer;
a groove is arranged on the longitude adjusting turbine; the boss is embedded with the groove on the longitude adjusting turbine; the longitude adjusting worm is matched with the longitude adjusting worm; a second gear is fixedly connected to one side of the longitude adjusting scroll rod; the second gear is matched with a gear of a longitude adjusting stepping motor arranged on the inner wall of the longitude adjusting hemisphere;
the groove on the connecting shaft is embedded with a boss arranged on a latitude adjusting hemisphere and is pressed tightly by a nut, so that a connecting structure of the longitude adjusting mechanism and the latitude adjusting mechanism is formed, the longitude adjusting hemisphere and the latitude adjusting hemisphere form a spherical structure, and the center of the spherical structure is positioned in the latitude adjusting hemisphere; symmetrical sliding grooves are formed in the latitude adjusting hemisphere;
the turbine shaft is arranged on a transverse shaft at the center of the latitude adjusting hemisphere through a bearing; the latitude adjusting worm wheel is fixedly connected to the middle position of the turbine shaft; a third gear is fixedly connected to the latitude adjusting worm gear and matched with a gear on a second multi-circle potentiometer;
the latitude adjusting worm wheel is matched with the latitude adjusting worm; a fourth gear is fixedly connected to one side of the latitude adjusting worm and is matched with a gear of a latitude adjusting stepping motor arranged on the inner wall of the latitude adjusting hemisphere;
the radome mounting frames are symmetrically mounted on the turbine shaft and positioned on two sides of the latitude adjusting worm wheel, the radome mounting frames are positioned in the symmetrical sliding grooves, a radome mounting seat is fixed at the bottom of each radome mounting frame, and the radome mounting seats are fixedly connected with radomes;
the radome mounting frame and the radome mounting seat are driven by the turbine shaft to rotate around the outer circumference of the latitude adjusting hemisphere.
The adjusting method of the multidirectional adjusting device is characterized by comprising the following steps of:
step 1, arranging a longitude and latitude adjusting electrical interface on the hoisting connector, wherein the longitude and latitude adjusting electrical interface is respectively connected with a first multi-turn potentiometer and a second multi-turn potentiometer;
step 2, when the position of the radome is adjusted, the longitude and latitude adjusting interface is connected with an external radome position adjuster, so that the longitude and latitude adjusting electrical interface is connected;
step 3, the first multi-turn potentiometer and the second multi-turn potentiometer respectively output a first position signal theta1And a second position signal theta2Providing the external radar cover position adjuster;
step 4, the external radar cover position regulator is used for regulating the position of the external radar cover according to the first position signal theta1And a first transmission ratio i between the first multi-turn potentiometer and the first gear1Determining an aerial longitude position θ at which the longitude-adjusted turbine is located at a current time1' and as the spatial longitude position of the radome mount, the relationship is:
Figure BDA0002099818890000031
step 5, the longitude and latitude regulator of the radome acquires the longitude to which the radome needs to be regulated
Figure BDA0002099818890000032
And according to the spatial longitude position theta of the radome mounting seat1', a third transmission ratio i of said longitude adjustment stepping motor to said longitude adjustment worm1'and a fourth gear ratio i' of the longitude adjusting worm and the longitude adjusting worm wheel1Determining the rotation angle theta of the longitude adjusting stepping motor1Thereby adjusting the position of the radome mount to a desired adjusted longitude
Figure BDA0002099818890000033
The relationship is as follows:
Figure BDA0002099818890000034
step 6, the external radome position regulator passes the second position signal theta2A second transmission ratio i between the second multi-turn potentiometer and the second gear2Determining a spatial latitudinal position θ at which the latitude-adjusted turbine is located at a current time2', and as the spatial latitude position of the radome mounting seat, the relation is
Figure BDA0002099818890000035
Step 7, the radar cover latitude and longitude regulator obtains the latitude to which the radar cover needs to be adjusted
Figure BDA0002099818890000036
According to the space latitude position theta of the radome installation seat'2The fifth transmission ratio i 'of the latitude adjusting stepping motor to the latitude adjusting worm'2And a sixth transmission ratio i' of the latitude adjusting worm and the latitude adjusting worm wheel2Determining the rotation angle theta of the latitude adjusting stepping motor (11)2Thereby adjusting the position of the radome mounting seat to the longitude and latitude required to be adjusted
Figure BDA0002099818890000037
The relationship is as follows:
Figure BDA0002099818890000038
and 8, when the radar cover mounting seat is adjusted to the required longitude and latitude position, the radar cover also reaches the appointed longitude and latitude position, and the longitude and latitude adjusting electrical interface is disconnected, so that the spatial position of the radar cover is fixed through the self-locking property of the worm gear and the worm, and the adjustment of the radar cover is completed.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, the radome mounting seat is connected with the bottom surface of the radome, so that the tool is suitable for the mounting requirements of most radomes in the lightning current test process, the time required by the earlier-stage preparation work of different radome lightning current tests is shortened, the one-time manufacture and repeated use of the tool are realized, the input cost of the tool required by the radome lightning current test is reduced, and the waste of resources is reduced. Meanwhile, the radome base is a detachable device, and can be independently adjusted to meet the installation requirement of a special radome.
2. The space position of the radome is obtained through the first multi-turn potentiometer and the second multi-turn potentiometer; the longitude adjusting stepping motor and the latitude adjusting stepping motor are controlled to adjust the radome to a specified spatial position through a position adjusting algorithm built in the radome position adjuster, so that the device can quickly and accurately adjust the radome to a required spatial position; and this adjusting device only needs alone the required space angle of input can accomplish the regulation of radome, has saved manpower resources.
3. The invention can ensure that the space position of the radome is unchanged under the condition of power failure by the self-locking performance of the worm gear and the worm, thereby ensuring that the device is not grounded in the test process and ensuring that the device does not influence a lightning current path.
Drawings
FIG. 1 is a schematic view of a multi-directional adjustment device for an aircraft radome for a lightning current test according to the invention;
FIG. 2 is a schematic structural diagram of a connecting shaft in the adjusting device of the present invention;
FIG. 3 is a schematic view of the connection between the longitude adjusting hemisphere and the latitude adjusting hemisphere according to the present invention;
reference numbers in the figures: 1. hoisting a connector; 2. a latitude and longitude adjustment electrical interface; 3. a longitude adjusting hemisphere; 4. a longitude adjusting stepping motor; 5. a longitude adjustment turbine; 6. a longitude adjusting worm; 7. a connecting shaft; 8. a thrust ball bearing; 9. a deep groove ball bearing; 10. a latitude adjusting hemisphere; 11. a latitude adjusting stepping motor; 12. a latitude adjusting scroll bar; 13. a latitude adjusting worm gear; 14. a turbine shaft; 15. a radome mounting bracket; 16. a radome mounting base; 17. a first multi-turn potentiometer; 18. a first gear; 19. a second multi-turn potentiometer; 20. a third gear.
Detailed Description
In this embodiment, as shown in fig. 1, a multi-directional adjustment device for an aircraft radome in a lightning current test includes: the device comprises a hoisting connector 1, a longitude adjusting mechanism, a connecting shaft 7, a latitude adjusting mechanism, a turbine shaft 14, a radome mounting frame 15 and a radome mounting seat 16;
the longitude adjusting mechanism comprises a longitude adjusting hemisphere 3, a longitude adjusting worm wheel 6 and a longitude adjusting worm 5;
latitude adjustment mechanism includes: a latitude adjusting hemisphere 10, a latitude adjusting worm wheel 13 and a latitude adjusting worm 12;
one side of the hoisting connector 1 is fixedly connected with an external hoisting structure to form an aerial vertical suspension state of the multidirectional adjusting device, wherein the hoisting connector 1 adopts external threads, the external hoisting structure adopts internal threads, and the threaded connection structure is stable and reliable and is easy to realize;
the other side of the hoisting connector 1 is fixedly connected with the top point of the longitude adjusting hemisphere 3 through a nut, and a connecting shaft 7 is arranged on the symmetrical axis of the longitude adjusting hemisphere 3; the connecting shaft 7 is installed through a deep groove ball bearing 9 and a thrust ball bearing 8 which are arranged on the inner side of the bottom of the longitude adjusting hemisphere 3; as shown in fig. 2, the connecting shaft 7 has a boss on one side and a groove on the other side; a longitude adjusting turbine 6 is sleeved on the connecting shaft 7; a first gear 18 is coaxially and fixedly connected to the longitude adjusting turbine 6, and the first gear 18 is matched with a gear on the first multi-circle potentiometer 17; in the present embodiment, the transmission ratio between the first gear 18 and the gear on the first multi-turn potentiometer 17 is 0.12, because a 10-turn potentiometer is relatively easy to obtain, under the condition that the longitude rotation angle of the radome reaches-180 degrees to 180 degrees, the transmission ratio is more than or equal to 0.1; and the smaller the value, the higher the angle of feedback; and considering that the stepping angle of the stepping motor is a certain value, the longitude rotation angle of the radome exceeds-180 degrees in the adjustment process, and a certain margin is required for the value of the transmission ratio.
A groove is arranged on the longitude adjusting turbine 6; the boss is embedded with the groove on the longitude adjusting turbine 6; the longitude adjusting worm wheel 6 is matched with the longitude adjusting worm 5; a second gear is fixedly connected to one side of the longitude adjusting scroll 5; the second gear is matched with a gear of a longitude adjusting stepping motor 4 arranged on the inner wall of the longitude adjusting hemisphere 3;
as shown in fig. 3, the groove on the connecting shaft 7 is embedded with the boss on the latitude adjusting hemisphere 10 and is pressed by the nut, so as to form a connecting structure of the longitude adjusting mechanism and the latitude adjusting mechanism, and the longitude adjusting hemisphere 3 and the latitude adjusting hemisphere 10 form a spherical structure, and the spherical center of the spherical structure is located in the latitude adjusting hemisphere 10; symmetrical sliding grooves are formed in the latitude adjusting hemisphere 10; the ratio of the interface of the sphere center to the longitude adjusting mechanism and the latitude adjusting mechanism to the top of the longitude adjusting hemisphere in this example is 1:1, so as to ensure that the sliding groove on the latitude adjusting hemisphere 10 can be opened to +/-120 degrees, and the larger the ratio is, the larger the latitude adjusting range is, but the maximum value is limited by the space occupied by the longitude adjusting mechanism.
A turbine shaft 14 is arranged on a horizontal shaft of the spherical center position of the latitude adjusting hemisphere 10 through a bearing; a latitude adjusting worm wheel 13 is fixedly connected at the middle position of the turbine shaft 14; a third gear 20 is fixedly connected to the latitude adjusting worm wheel 13, and the third gear 20 is matched with a gear on the second multi-circle potentiometer 19; in this embodiment, the transmission ratio between the third gear 20 and the gear on the second multi-turn potentiometer 19 is 0.12, because a 10-turn multi-turn potentiometer is easily obtained, the transmission ratio is greater than or equal to 0.067 under the condition that the longitude rotation angle of the radome reaches-120 degrees to 120 degrees; in consideration of the processing cost, the same gears as those of the first gear 18 and the first multi-turn potentiometer 17 are used.
The latitude adjusting worm wheel 13 is matched with the latitude adjusting worm 12; a fourth gear is fixedly connected to one side of the latitude adjusting worm 12 and is matched with a gear of a latitude adjusting stepping motor 11 arranged on the inner wall of the latitude adjusting hemisphere 10;
the turbine shaft 14 is symmetrically provided with radome mounting brackets 15 at two sides of the latitude adjusting worm wheel 13, the radome mounting brackets 15 are arranged in symmetrical sliding grooves, a radome mounting seat 16 is fixed at the bottom of the radome mounting bracket 15, and the radome mounting seat 16 is fixedly connected with a radome; in the embodiment, the radome mounting frame 15 and the radome mounting seat 16 are connected through bolts, and the radome mounting seat 16 and the radome are connected through bolts; the bolt connecting structure is convenient to process and disassemble.
The radome mounting bracket 15 and the radome mounting base 16 are rotated around the outer circumference of the latitude adjusting hemisphere 10 by the turbine shaft 14.
In this embodiment, an adjusting method of a multi-directional adjusting device is performed according to the following steps:
step 1, arranging a longitude and latitude adjusting electrical interface 2 on a hoisting connector 1, wherein the longitude and latitude adjusting electrical interface 2 is respectively connected with a first multi-turn potentiometer 17 and a second multi-turn potentiometer 19;
step 2, when the position of the radome is adjusted, the longitude and latitude adjusting interface 2 is connected with an external radome position adjuster, so that the longitude and latitude adjusting electrical interface 2 is connected;
step 3, the first multi-turn potentiometer 17 and the second multi-turn potentiometer 19 respectively output a first position signal theta1And a second position signal theta2For external radome position adjustmentA node device;
step 4, the external radome position regulator regulates the external radome position according to the first position signal theta1And a first transmission ratio i between the first multiturn potentiometer 17 and the first gear wheel 181Determining the spatial longitude position θ 'of the longitude-adjusted turbine 6 at the current time'1And as the spatial longitude position of radome mount 16, the relationship is:
Figure BDA0002099818890000061
step 5, the longitude and latitude adjuster of the radome acquires the longitude to which the radome needs to be adjusted
Figure BDA0002099818890000062
And according to the spatial longitude position theta 'of the radome mount 16'1Third gear ratio i 'of longitude-adjusting stepper motor 4 and longitude-adjusting worm 5'1And a fourth transmission ratio i' of the longitude adjusting worm 5 and the longitude adjusting worm wheel 61Determining the rotation angle theta' of the longitude adjusting stepping motor 41Thereby adjusting the position of radome mount 16 to the desired adjusted longitude
Figure BDA0002099818890000063
The relationship is as follows:
Figure BDA0002099818890000064
obtaining the accuracy of longitude adjustment Δ using equation (1)1：
Figure BDA0002099818890000065
In the formula (1), θsa1Adjusting the stepping angle of the stepping motor 4 for longitude;
and 6, the external radar cover position regulator passes through the second position signal theta2And a second transmission ratio i between the second multi-turn potentiometer 19 and the second gear 202Determining the spatial latitudinal position θ at which the latitude-adjusting turbine 13 is located at the present moment2', do asThe spatial latitude position of the radome mount 16 is in relation to
Figure BDA0002099818890000066
Step 7, the radar cover latitude and longitude regulator obtains the latitude to which the radar cover needs to be adjusted
Figure BDA0002099818890000067
And is based on the spatial latitude position theta 'of radome mount 16'2The fifth transmission ratio i 'of the latitude adjusting stepping motor 11 and the latitude adjusting worm 12'2And a sixth transmission ratio i' of the latitude regulating worm 12 and the latitude regulating worm wheel 132Determining the rotation angle theta' of the latitude adjusting stepping motor 112Thereby adjusting the position of the radome mount 16 to the desired longitude and latitude
Figure BDA0002099818890000068
The relationship is as follows:
Figure BDA0002099818890000069
obtaining the accuracy Delta of the latitude adjustment by using the formula (2)2：
Figure BDA00020998188900000610
In the formula (2), θsa2The step angle of the step motor 11 is adjusted for the latitude.
And 8, when the radome mounting seat 16 is adjusted to the required longitude and latitude position, the radome also reaches the appointed longitude and latitude position, and the longitude and latitude adjusting electrical interface 2 is disconnected, so that the spatial position of the radome is fixed through the self-locking property of the worm gear, and the adjustment of the radome is completed.

Claims (2)

1. A multidirectional adjusting device of aircraft radome in lightning current test, its characterized in that includes: the device comprises a hoisting connector (1), a longitude adjusting mechanism, a connecting shaft (7), a latitude adjusting mechanism, a turbine shaft (14), a radome mounting frame (15) and a radome mounting seat (16);
the longitude adjusting mechanism includes: a longitude adjusting hemisphere (3), a longitude adjusting worm wheel (6) and a longitude adjusting worm (5);
the latitude adjustment mechanism includes: a latitude adjusting hemisphere (10), a latitude adjusting worm wheel (13) and a latitude adjusting worm (12);
one side of the hoisting connector (1) is fixedly connected with an external hoisting structure so as to form an aerial vertical suspension state of the multidirectional adjusting device;
the other side of the hoisting connector (1) is fixedly connected with the top point of the longitude adjusting hemisphere (3) through a nut, and a connecting shaft (7) is arranged on the symmetrical axis of the longitude adjusting hemisphere (3); the connecting shaft (7) is installed through a deep groove ball bearing (9) and a thrust ball bearing (8) which are arranged on the inner side of the bottom of the longitude adjusting hemisphere (3); a boss is arranged on one side of the connecting shaft (7), and a groove is formed in the other side of the connecting shaft; the longitude adjusting turbine (6) is sleeved on the connecting shaft (7); a first gear (18) is coaxially and fixedly connected to the longitude adjusting turbine (6), and the first gear (18) is matched with a gear on the first multi-circle potentiometer (17);
a groove is arranged on the longitude adjusting turbine (6); the lug boss is embedded with a groove on the longitude adjusting turbine (6); the longitude adjusting worm wheel (6) is matched with the longitude adjusting worm (5); a second gear is fixedly connected to one side of the longitude adjusting scroll (5); the second gear is matched with a gear of a longitude adjusting stepping motor (4) arranged on the inner wall of the longitude adjusting hemisphere (3);
the groove on the connecting shaft (7) is embedded with a boss arranged on the latitude adjusting hemisphere (10) and is pressed tightly by a nut, so that a connecting structure of the longitude adjusting mechanism and the latitude adjusting mechanism is formed, the longitude adjusting hemisphere (3) and the latitude adjusting hemisphere (10) form a spherical structure, and the spherical center of the spherical structure is positioned in the latitude adjusting hemisphere (10); symmetrical sliding grooves are formed in the latitude adjusting hemisphere (10);
the turbine shaft (14) is arranged on a horizontal shaft of the spherical center position of the latitude adjusting hemisphere (10) through a bearing; the latitude adjusting worm wheel (13) is fixedly connected to the middle position of the turbine shaft (14); a third gear (20) is fixedly connected to the latitude adjusting worm gear (13), and the third gear (20) is matched with a gear on a second multi-circle potentiometer (19);
the latitude adjusting worm wheel (13) is matched with the latitude adjusting worm (12); a fourth gear is fixedly connected to one side of the latitude adjusting worm (12), and the fourth gear is matched with a gear of a latitude adjusting stepping motor (11) arranged on the inner wall of the latitude adjusting hemisphere (10); symmetrical sliding grooves are formed in the latitude adjusting hemisphere (10);
the two sides of the latitude adjusting worm wheel (13) on the turbine shaft (14) are symmetrically provided with the radome mounting frames (15), the radome mounting frames (15) are positioned in the symmetrical sliding grooves, the bottom of each radome mounting frame (15) is fixedly provided with a radome mounting seat (16), and the radome mounting seats (16) are fixedly connected with radomes;
the radome mounting frame (15) and the radome mounting seat (16) are driven by the turbine shaft (14) to rotate around the outer circumference of the latitude adjusting hemisphere (10).
2. An adjusting method based on the multidirectional adjusting device of claim 1, which is characterized by comprising the following steps:
step 1, a longitude and latitude adjusting electrical interface (2) is arranged on the hoisting connector (1), and the longitude and latitude adjusting electrical interface (2) is respectively connected with a first multi-turn potentiometer (17) and a second multi-turn potentiometer (19);
step 2, when the position of the radome is adjusted, the longitude and latitude adjusting interface (2) is connected with an external radome position adjuster, so that the longitude and latitude adjusting electrical interface (2) is connected;
step 3, the first multi-turn potentiometer (17) and the second multi-turn potentiometer (19) output a first position signal theta respectively1And a second position signal theta2Providing the external radar cover position adjuster;
step 4, the external radar cover position regulator is used for regulating the position of the external radar cover according to the first position signal theta1And the first multi-turn potentiometer (17) and theA first transmission ratio i between the first gears (18)1Determining a spatial longitude position theta 'at which the longitude adjustment turbine (6) is located at a current time'1And as the spatial longitude position of the radome mounting seat (16), the relation is as follows:
Figure FDA0002099818880000021
step 5, the longitude and latitude regulator of the radome acquires the longitude to which the radome needs to be regulated
Figure FDA0002099818880000022
And according to the spatial longitude position theta 'of the radome mounting seat (16)'1A third transmission ratio i 'of the longitude adjusting stepping motor (4) to the longitude adjusting worm (5)'1And a fourth transmission ratio i' of the longitude adjusting worm (5) to the longitude adjusting worm wheel (6)1Determining the rotation angle theta' of the longitude-adjusting stepping motor (4)1Thereby adjusting the position of the radome mount (16) to a desired adjusted longitude
Figure FDA0002099818880000023
The relationship is as follows:
Figure FDA0002099818880000024
step 6, the external radome position regulator passes the second position signal theta2A second transmission ratio i between the second multi-turn potentiometer (19) and the second gear (20)2Determining a spatial latitude position theta 'of the latitude adjustment turbine (13) at the current time'2And as a spatial latitude position of the radome mount (16) in relation to
Figure FDA0002099818880000025
Step 7, the radar cover latitude and longitude regulator obtains the latitude to which the radar cover needs to be adjusted
Figure FDA0002099818880000026
According to the spatial latitude position theta 'of the radome mounting seat (16)'2The fifth transmission ratio i 'of the latitude adjusting stepping motor (11) to the latitude adjusting worm (12)'2And a sixth transmission ratio i' of the latitude regulating worm (12) to the latitude regulating worm wheel (13)2Determining the rotation angle theta of the latitude adjusting stepping motor (11)2Thereby adjusting the position of the radome mount (16) to the desired longitude and latitude
Figure FDA0002099818880000027
The relationship is as follows:
Figure FDA0002099818880000028
and 8, when the radar cover mounting seat (16) is adjusted to the required longitude and latitude position, the radar cover also reaches the appointed longitude and latitude position, and the longitude and latitude adjusting electrical interface (2) is disconnected, so that the space position of the radar cover is fixed through the self-locking property of the worm gear and the worm, and the adjustment of the radar cover is completed.
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Cited By (2)

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CN113844657A (en) * 2021-10-12 2021-12-28 四川西华通用航空股份有限公司 Airborne radar hanging and flying device
CN114236299A (en) * 2022-02-24 2022-03-25 合肥航太电物理技术有限公司 Infrared temperature measurement high-speed photographic imaging integrated thunder and lightning ignition source simulation device

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