CN214174620U - Low-loss airborne weather radar servo transmission platform - Google Patents
Low-loss airborne weather radar servo transmission platform Download PDFInfo
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- CN214174620U CN214174620U CN202022949888.7U CN202022949888U CN214174620U CN 214174620 U CN214174620 U CN 214174620U CN 202022949888 U CN202022949888 U CN 202022949888U CN 214174620 U CN214174620 U CN 214174620U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
Abstract
The utility model discloses a low-loss airborne weather radar servo transmission platform. The pitching transmission unit and the azimuth transmission unit are installed on the base, and the receiving and transmitting module and the array antenna are installed on the pitching transmission unit after being in blind-mate connection. When the servo transmission platform receives the control instruction and the data signal, the pitching transmission unit and the azimuth transmission unit drive the array antenna to carry out airspace scanning in the pitching and azimuth dimensions, capture and track the target, and feed back the position angle and speed data to the inside of the base in real time to be compared and corrected with the expected value, so that the servo transmission platform forms a closed-loop control system. The utility model discloses reduced servo drive platform's volume, weight and total return difference, shortened microwave transmission path, reduced the complete machine loss, improved servo transmission precision and control performance, can be used to the airborne weather radar servo transmission control of various aircraft.
Description
Technical Field
The utility model belongs to the technical field of electronic equipment, in particular to airborne weather radar servo transmission platform can be used to the radar antenna mechanical scanning control of various aircraft.
Background
The servo transmission platform of the airborne weather radar is electromechanical integrated equipment for searching, capturing a target, tracking and measuring the position and various motion parameters of the target by the airborne weather radar, drives a radar antenna to move in a pitching and azimuth dimension according to a motion rule given by a radar system, so that the radar can realize the functions of capturing and tracking the target, and simultaneously feeds back the information of the pitching and azimuth dimension angle motion to the radar system, so that the radar system can accurately judge the position of the target.
The existing airborne weather radar servo transmission platform mostly adopts a transmission mode of adding a reduction gearbox to a motor or directly driving the motor, the reduction gearbox generally adopts multi-stage dead axle gear transmission, and the multi-stage dead axle gear reduction gearbox with a large transmission ratio has large volume, heavy weight, poor transmission precision and large total return difference. In the transmission mode of direct driving of the motor, although a middle speed reducing mechanism is omitted, a large-torque motor needs to be selected, the large-torque motor is large in size, and the motor needs a larger space to be installed. Meanwhile, the transceiver module and the radar antenna of the airborne weather radar are often used as two extensions and cannot be installed in a tight fit mode, so that the transmission path distance and the loss are increased.
Disclosure of Invention
An object of the utility model is to the not enough of above-mentioned prior art, provide a low-loss airborne weather radar servo transmission platform to reduce servo transmission platform's volume, reduce weight and total return difference, improve servo transmission precision and control performance, shorten microwave transmission path, reduce the complete machine loss.
The technical idea of the utility model is that: the radar antenna is driven to move according to a given rule in the pitching and azimuth dimensions by adopting a transmission mode of a brushless direct current servo motor, a planetary reducer and a primary reduction gear pair, and the motion parameters are accurately controlled by adopting closed-loop control; by adopting the waveguide blind plugging connection mode between the transceiver module and the radar antenna, the microwave transmission path is shortened, and the loss of the whole machine is reduced.
According to the technical idea, the utility model discloses a low-loss airborne weather radar servo transmission platform, including every single move transmission unit 1, position transmission unit 2, base 3, transceiver module 4, array antenna 5 and cushion 6, this every single move transmission unit 1 and position transmission unit 2 are installed on base 3, and this transceiver module 4 and array antenna 5 connect the back and install on every single move transmission unit 1, its characterized in that:
the pitch transmission unit 1 comprises a pitch motor 11, a pitch reducer 12, a pitch reduction gear pair 13, a pitch angle potentiometer 14 and a pitch component 15; the pitch motor 11 is a brushless dc servo motor, the pitch reducer 12 is a planetary reducer, the pitch reduction gear pair 13 is a primary gear transmission, and the pitch reducer 12 and the pitch reduction gear pair 13 together form a reduction mechanism of the pitch transmission unit 1.
The azimuth transmission unit 2 comprises an azimuth motor 21, an azimuth reducer 22, an azimuth reduction gear pair 23, an azimuth angle potentiometer 24, an azimuth component 25, a left fork arm 26, a right fork arm 27 and a driving box 28; the azimuth motor 21 is a brushless dc servo motor, the azimuth reducer 22 is a planetary reducer, the azimuth reduction gear pair 23 is a primary gear transmission, the azimuth reducer 22 and the azimuth reduction gear pair 23 together form a reduction mechanism of the azimuth transmission unit 2, and the left yoke 26, the right yoke 27 and the drive box 28 are respectively mounted on the base 3.
The transceiver module 4 is located under the array antenna 5 and is installed at the upper end of the servo transmission platform, a heat conducting medium is filled between the transceiver module and the servo transmission platform, and the transceiver module and the servo transmission platform are connected in a blind-mating mode through waveguides, so that a transmission path between the transceiver module and the servo transmission platform is shortened, and the loss of the whole machine is reduced.
Further, the pitch motor 11 and the pitch reducer 12 in the pitch transmission unit 1 are mounted on the pitch member 15 by clearance fit, one end of the pitch reduction gear pair 13 is fixed on the pitch member 15, the other end is fastened on the output shaft of the pitch reducer 12, and the rotation shaft of the pitch member 15 is concentrically connected with the rotation shaft of the pitch angle potentiometer 14.
Further, the azimuth motor 21 and the azimuth reducer 22 in the azimuth drive unit 2 are mounted on an azimuth member 25 with a clearance fit, one end of an azimuth reduction gear pair 23 is fixed to the azimuth member 25, the other end is fastened to an output shaft of the azimuth reducer 22, and a rotation shaft of the azimuth member 25 is concentrically connected to a rotation shaft of the azimuth angle potentiometer 24.
Further, the base 3 adopts an integrated structure with a circular bottom section and an elliptical upper section, and is used as a support of the whole servo transmission platform.
Furthermore, the clock, the intermediate frequency and the control signal are respectively transmitted between the transceiver module 4 and the inside of the base 3 through three cables, and the three cables enter the center holes of the rotating shaft of the azimuth component 25 and the left yoke 26 from the center hole of the rotating shaft of the pitching component 15 after being fixed and fixed, and then enter the inside of the base 3 after being fixed.
Compared with the prior art, the utility model have following advantage:
1. the utility model discloses owing to adopted the one-level gear pair to add planetary reducer's reduction gears on every single move drive unit 1 and position drive unit 2, reduced servo drive platform's volume, reduced servo drive platform's weight and total return difference, improved servo drive platform's precision and transmission efficiency.
2. The utility model discloses pitching motor 11 in pitching transmission unit 1 and position motor 21 in position transmission unit 2 all adopt brushless DC servo motor, because brushless DC servo motor has the characteristics that the response is fast, inertia is little, therefore realized servo driven closed-loop control, improved servo transmission platform's precision.
3. The utility model discloses owing to adopt the mode of waveguide blind plugging to connect between transceiver module 4 and array antenna 5, shortened microwave transmission path, reduced the complete machine loss.
4. The utility model discloses a three cables between transceiver module 4 and base 3 have improved the atress condition of cable at the platform rotation in-process owing to adopt the rotation axis centre bore from every single move component 15 to get into the line mode of walking of the rotation axis centre bore of position component 25 and left yoke 26.
Drawings
FIG. 1 is an overall block diagram of the present invention;
FIG. 2 is an overall structure diagram of the present invention;
fig. 3 is a sectional view of the pitch transmission unit of the present invention;
fig. 4 is a sectional view of the azimuth driving unit of the present invention.
Detailed Description
Examples of the present invention are described in further detail below with reference to the accompanying drawings.
Referring to fig. 1, the servo transmission platform of the present invention includes a pitching transmission unit 1, an azimuth transmission unit 2, a base 3, a transceiver module 4, an array antenna 5 and a cushion block 6; the pitching transmission unit 1 and the azimuth transmission unit 2 are installed on the base 3, the transceiver module 4 is connected with the array antenna 5 and then installed on the pitching transmission unit 1, and when the cushion block 6 is added on the contact surface of the azimuth transmission unit 2 and the base 3, the requirement of the large-size radar antenna on the rotation range can be met. When the servo transmission platform receives a control instruction and a data signal, the pitching transmission unit 1 and the azimuth transmission unit 2 drive the array antenna 5 to carry out airspace scanning in the pitching and azimuth dimensions, so that a target is captured and tracked, and meanwhile, the pitching transmission unit 1 and the azimuth transmission unit 2 feed back angle and speed data to the inside of the base 3 in real time to be compared with an expected value and corrected, so that the servo transmission platform forms a closed-loop control system.
With reference to fig. 2, the structural details of this example are described as follows:
the pitch transmission unit 1 comprises a pitch motor 11, a pitch reducer 12, a pitch reduction gear pair 13, a pitch angle potentiometer 14 and a pitch component 15; the pitching motor 11 is a brushless direct current servo motor, the pitching reducer 12 is a planetary reducer, the pitching reduction gear pair 13 is a primary gear transmission, the pitching reducer 12 and the pitching reduction gear pair 13 jointly form a reduction mechanism of the pitching transmission unit 1, the pitching motor 11 and the pitching reducer 12 are installed on a pitching member 15 in a clearance fit mode, one end of the pitching reduction gear pair 13 is fixed on the pitching member 15, the other end of the pitching reduction gear pair is fastened on an output shaft of the pitching reducer 12, and a rotating shaft of the pitching member 15 is concentrically connected with a rotating shaft of the pitching angle potentiometer 14. After the pitching motor 11 is started, the array antenna 5 is driven to move in the pitching dimension through the pitching reducer 12 and the pitching reduction gear pair 13 according to a given movement rule, and the pitching angle potentiometer 14 monitors the pitching dimension movement angle and speed in real time and feeds back the pitching angle and speed information to the inside of the base 3 to be compared with an expected value and correct the information.
The azimuth transmission unit 2 comprises an azimuth motor 21, an azimuth reducer 22, an azimuth reduction gear pair 23, an azimuth angle potentiometer 24, an azimuth component 25, a left fork arm 26, a right fork arm 27 and a driving box 28; the azimuth motor 21 is a brushless direct current servo motor, the azimuth reducer 22 is a planetary reducer, the azimuth reduction gear pair 23 is a primary gear transmission, the azimuth reducer 22 and the azimuth reduction gear pair 23 jointly form a reduction mechanism of the azimuth transmission unit 2, the azimuth motor 21 and the azimuth reducer 22 are arranged on a driving box 28 in a clearance fit manner, one end of the azimuth reduction gear pair 23 is fixed on an azimuth component 25, the other end of the azimuth reduction gear pair is fastened on an output shaft of the azimuth reducer 22, and a rotating shaft of the azimuth component 25 is concentrically connected with a rotating shaft of the azimuth angle potentiometer 24; the left fork arm 26 and the right fork arm 27 are splayed and bilaterally symmetrically across the mounting surface of the base 3 for connecting the pitch transmission unit 1 with the azimuth transmission unit 2, and the drive box 28 is mounted on the base 3. After the azimuth motor 21 is started, the array antenna 5 is driven to move in the azimuth dimension through the azimuth reducer 22 and the azimuth reduction gear pair 23 according to a given movement rule, and the azimuth angle potentiometer 24 monitors the azimuth dimension movement angle and speed in real time and feeds azimuth angle and speed information back to the inside of the base 3 to be compared with an expected value and correct the expected value.
The base 3 adopts an integrated structure with a round bottom section and an oval upper section and is used as a support of the whole servo transmission platform.
The transceiver module 4 is located right below the array antenna 5, a heat conducting medium is filled between the transceiver module and the array antenna, and the transceiver module and the elevation component 15 are installed after being connected in a blind-mating mode through waveguides, so that a transmission path between the transceiver module and the elevation component is shortened, and the loss of the whole machine is reduced.
The clock, the intermediate frequency and the control signal are respectively transmitted between the transceiver module 4 and the inside of the base 3 through three cables, and the three cables enter the center holes of the rotating shafts of the azimuth member 25 and the left yoke 26 from the center hole of the rotating shaft of the pitching member 15 after being fixed and fixed, and then enter the inside of the base 3 after being fixed.
Referring to fig. 3, the pitch reduction gear pair 13 includes a first pitch reduction gear 131 and a second pitch reduction gear 132.
The pitching member 15 comprises a pitching support 151, a first orientation support 152, a first end cover 153, a semicircular ring 154, a first angular contact bearing 155, a first baffle 156 and a first adjusting shim 157; the first angular contact bearing 155 has an inner ring which is installed on the rotation shafts at the left and right ends of the pitch bracket 151 in an interference fit manner and is connected with the first azimuth bracket 152 through the installation hole of the semicircular ring 154, a lower half portion of an outer ring thereof is installed at a corresponding semicircular position of the first azimuth bracket 152, an upper half portion thereof is installed in a fit manner with the semicircular ring 154 to limit the outer ring of the first angular contact bearing 155 through shaft shoulder contact, the first baffle 156 is installed on the inner ring of the first angular contact bearing 155 to prevent the inner ring of the first angular contact bearing 155 from axially shifting, the first adjusting shim 157 is filled between the first baffle 156 and the inner ring of the first angular contact bearing 155, and the first end cap 153 is installed on the first azimuth bracket 152 and the semicircular ring 154.
The first pitch reduction gear 131 is installed with a clearance fit with the rotation shaft of the pitch bracket 151 and fixed to the first orientation bracket 152 by a semicircular ring 154, and the second pitch reduction gear 132 is tightly fitted and connected to the output shaft of the pitch reducer 12.
Referring to fig. 4, the azimuth reduction gear pair 23 includes a first azimuth reduction gear 231 and a second azimuth reduction gear 232.
The orientation component 25 comprises a second end cover 251, a second angular contact bearing 252, a second baffle 253, a second adjusting gasket 254 and a second orientation bracket 255; the inner ring of the second angular contact bearing 252 is mounted on the left and right rotating shafts of the second azimuth support 255, the outer ring is mounted in corresponding holes of the left yoke 26 and the right yoke 27 in an interference fit manner to limit the outer ring of the second angular contact bearing 252 through shaft shoulder contact, the second baffle 253 is mounted on the inner ring of the second angular contact bearing 252 to prevent the inner ring of the second angular contact bearing 252 from axially jumping, the second adjusting gasket 254 is filled between the second baffle 253 and the inner ring of the second angular contact bearing 252, and the second end cover 251 is mounted on the left yoke 26 and the right yoke 27.
The first azimuth reducing gear 231 is mounted on the second azimuth bracket 255 after being positioned, the centers of the rotation axes of the two are overlapped, and the second azimuth reducing gear 232 is connected with the output shaft of the azimuth reducer 22 in a tight fit manner.
The above description is only a specific example of the present invention, and does not constitute any limitation to the present invention, and it is obvious to those skilled in the art that various modifications and changes in form and detail may be made without departing from the principle and structure of the present invention after understanding the content and principle of the present invention, but such modifications and changes based on the idea of the present invention are still within the scope of the claims of the present invention.
Claims (10)
1. A low-loss airborne weather radar servo transmission platform, comprising: the device comprises a pitching transmission unit (1), an azimuth transmission unit (2), a base (3), a transceiving module (4), an array antenna (5) and a cushion block (6); the pitching transmission unit (1) and the azimuth transmission unit (2) are installed on the base (3), and the receiving and transmitting module (4) is connected with the array antenna (5) and then installed on the pitching transmission unit (1), and is characterized in that:
the pitching transmission unit (1) comprises a pitching motor (11), a pitching reducer (12), a pitching reduction gear pair (13), a pitching angle potentiometer (14) and a pitching component (15); the pitching motor (11) is a brushless direct current servo motor, the pitching reducer (12) is a planetary reducer, the pitching reduction gear pair (13) is in primary gear transmission, and the pitching reducer (12) and the pitching reduction gear pair (13) jointly form a reduction mechanism of the pitching transmission unit (1);
the azimuth transmission unit (2) comprises an azimuth motor (21), an azimuth reducer (22), an azimuth reduction gear pair (23), an azimuth angle potentiometer (24), an azimuth component (25), a left fork arm (26), a right fork arm (27) and a driving box (28); the azimuth motor (21) is a brushless direct current servo motor, the azimuth reducer (22) is a planetary reducer, the azimuth reduction gear pair (23) is in primary gear transmission, the azimuth reducer (22) and the azimuth reduction gear pair (23) jointly form a reduction mechanism of the azimuth transmission unit (2), and the left fork arm (26), the right fork arm (27) and the driving box (28) are respectively installed on the base (3);
the receiving and transmitting module (4) is located under the array antenna (5) and is installed at the upper end of the servo transmission platform, a heat conducting medium is filled between the receiving and transmitting module and the servo transmission platform, and the receiving and transmitting module and the servo transmission platform are connected in a blind-mating mode through waveguides, so that a transmission path between the receiving and transmitting module and the servo transmission platform is shortened, and the loss of the whole machine is reduced.
2. The platform of claim 1, wherein: a pitching motor (11) and a pitching reducer (12) in the pitching transmission unit (1) are arranged on a pitching member (15) in a clearance fit mode, one end of a pitching reduction gear pair (13) is fixed on the pitching member (15), the other end of the pitching reduction gear pair is fastened on an output shaft of the pitching reducer (12), and a rotating shaft of the pitching member (15) is concentrically connected with a rotating shaft of a pitching angle potentiometer (14).
3. The platform of claim 1, wherein: an azimuth motor (21) and an azimuth reducer (22) in the azimuth transmission unit (2) are arranged on a driving box (28) in a clearance fit mode, one end of an azimuth reduction gear pair (23) is fixed on an azimuth component (25), the other end of the azimuth reduction gear pair is fastened on an output shaft of the azimuth reducer (22), and a rotating shaft of the azimuth component (25) is concentrically connected with a rotating shaft of an azimuth angle potentiometer (24).
4. The platform of claim 1, wherein:
-said pitch reduction gear pair (13) comprising a first pitch reduction gear (131) and a second pitch reduction gear (132);
the pitching component (15) comprises a pitching support (151), a first orientation support (152), a first end cover (153), a semicircular ring (154), a first angle contact bearing (155), a first baffle plate (156) and a first adjusting shim (157); the inner ring of the first angular contact bearing (155) is arranged on rotating shafts at the left end and the right end of the pitching support (151) in an interference fit mode and is connected with the first azimuth support (152) through a mounting hole of a semicircular ring (154), the lower half part of the outer ring of the first angular contact bearing is arranged at the corresponding semicircular position of the first azimuth support (152), the upper half part of the outer ring of the first angular contact bearing is arranged in a matched mode with the semicircular ring (154) so as to limit the outer ring of the first angular contact bearing (155) through shaft shoulder contact, the first baffle plate (156) is arranged on the inner ring of the first angular contact bearing (155) so as to prevent the inner ring of the first angular contact bearing (155) from axially moving, and the first adjusting gasket (157) is filled between the first baffle plate (156) and the inner ring of the first angular contact bearing (155); the first end cap (153) is mounted to the first azimuth bracket (152) and the semi-circular ring (154).
5. The platform according to claim 4, characterized in that said first pitch reduction gear (131) is mounted with clearance fit to the rotation axis of the pitch bracket (151) and is fixed to the first orientation bracket (152) by a semicircular ring (154); the second pitch reduction gear (132) is connected with the output shaft of the pitch reducer (12) in a tight fit mode.
6. The platform of claim 1, wherein:
the azimuth reduction gear pair (23) comprises a first azimuth reduction gear (231) and a second azimuth reduction gear (232);
the orientation component (25) comprises a second end cover (251), a second angular contact bearing (252), a second baffle plate (253), a second adjusting gasket (254) and a second orientation support (255); the inner ring of the second angular contact bearing (252) is mounted on rotating shafts at the left end and the right end of a second azimuth support (255), the outer ring is mounted in corresponding holes of a left fork arm (26) and a right fork arm (27) in an interference fit mode to limit the outer ring of the second angular contact bearing (252) through shaft shoulder contact, the second baffle (253) is mounted on the inner ring of the second angular contact bearing (252) to prevent the inner ring of the second angular contact bearing (252) from axially jumping, the second adjusting gasket (254) is filled between the second baffle (253) and the inner ring of the second angular contact bearing (252), and the second end cover (251) is mounted on the left fork arm (26) and the right fork arm (27);
the first azimuth reducing gear (231) is positioned and then installed on the third azimuth bracket (255), and the centers of the rotating shafts of the first azimuth reducing gear and the third azimuth reducing gear are superposed; the second azimuth reduction gear (232) is connected with the output shaft of the azimuth reducer (22) in a tight fit manner.
7. Platform according to claim 6, characterized in that the azimuth motor (21), the azimuth reducer (22), the second azimuth reduction gear (232) and the drive box (28) are assembled as a whole and mounted on the base (3); the left fork arm (26) and the right fork arm (27) symmetrically cross the mounting surface of the base (3) in a splayed manner, and are used for realizing the connection between the pitching transmission unit (1) and the azimuth transmission unit (2).
8. The platform of claim 1, wherein when the cushion blocks (6) are added on the contact surfaces of the left fork arm (26) and the right fork arm (27) and the base (3), the requirement of the rotation range of the large-size radar antenna can be met.
9. Platform according to claim 1, characterized in that the base (3) is a one-piece structure with a circular bottom section and an elliptical top section, which is used as a support for the whole servo drive platform.
10. Platform according to claim 1, characterized in that the clock, intermediate frequency and control signals are transmitted between the transceiver module (4) and the inside of the base (3) by means of three cables, which are routed and fixed from the center hole of the rotation axis of the pitch member (15) into the center holes of the rotation axis of the azimuth member (25) and the left yoke (26) and fixed into the inside of the base (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022949888.7U CN214174620U (en) | 2020-12-08 | 2020-12-08 | Low-loss airborne weather radar servo transmission platform |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022949888.7U CN214174620U (en) | 2020-12-08 | 2020-12-08 | Low-loss airborne weather radar servo transmission platform |
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| CN214174620U true CN214174620U (en) | 2021-09-10 |
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| CN202022949888.7U Active CN214174620U (en) | 2020-12-08 | 2020-12-08 | Low-loss airborne weather radar servo transmission platform |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117241299A (en) * | 2023-11-10 | 2023-12-15 | 中国民用航空飞行学院 | Avionic data security analysis protection method |
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2020
- 2020-12-08 CN CN202022949888.7U patent/CN214174620U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117241299A (en) * | 2023-11-10 | 2023-12-15 | 中国民用航空飞行学院 | Avionic data security analysis protection method |
| CN117241299B (en) * | 2023-11-10 | 2024-01-23 | 中国民用航空飞行学院 | Avionic data security analysis protection method |
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