CN214041746U - Missile-borne satellite navigation receiver satellite receiving test device - Google Patents
Missile-borne satellite navigation receiver satellite receiving test device Download PDFInfo
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- CN214041746U CN214041746U CN202021067622.3U CN202021067622U CN214041746U CN 214041746 U CN214041746 U CN 214041746U CN 202021067622 U CN202021067622 U CN 202021067622U CN 214041746 U CN214041746 U CN 214041746U
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Abstract
The utility model discloses a missile-borne satellite navigation receiver receives star test device, include: the base is coaxially and rotatably connected with a rotating chassis; the projectile body supporting frame is arranged on the rotating chassis, and a projectile body model is horizontally arranged on the projectile body supporting frame; the control part comprises a signal transmission component and a control component; the axis midpoint of the projectile body model is defined as a rotation center, the base is provided with a first driving assembly, a second driving assembly and a third driving assembly, the first driving assembly, the second driving assembly and the third driving assembly are respectively used for driving the projectile body model to rotate on a horizontal plane by taking the rotation center as a center point, rotate on a vertical plane by taking the rotation center as a center point and rotate around the axis of the projectile body model, the signal transmission assembly is used for transmitting satellite signals between the projectile body model and the control assembly, and the control assembly is used for analyzing the transmitted satellite signals and controlling the first driving assembly, the second driving assembly and the third driving assembly. The device can accurately verify the performance of the satellite navigation receiver in the flight state.
Description
Technical Field
The utility model relates to a guided missile test technical field especially relates to a missile-borne satellite navigation receiver receives star test device.
Background
In the process of flying of the missile, a plurality of navigation methods are adopted, wherein satellite navigation is one of the most important means, the satellite navigation receiver is likely to lose lock due to attitude changes of the missile such as yaw, roll, attack angle and the like, and the satellite receiving performance of the satellite navigation receiver is the most important index requirement of the receiver. In the process of guided missile development, a satellite receiving test of a satellite navigation receiver is required to be carried out, and the satellite receiving performance of the receiver is verified.
SUMMERY OF THE UTILITY MODEL
The utility model provides a missile-borne satellite navigation receiver receives star test device to solve the unable attitude of simulating the guided missile completely of current device in actual flight, and carry out the problem of experimental verification to the satellite navigation receiver performance of guided missile.
In order to achieve the above purpose, the utility model provides a following technical scheme: a missile-borne satellite navigation receiver satellite receiving test device comprises:
the base is coaxially and rotatably connected with a rotating chassis;
the projectile body supporting frame is mounted on the rotating chassis, and a projectile body model is horizontally mounted on the projectile body supporting frame;
a control section including a signal transmission component and a control component;
the middle point of the axis of the projectile body model is defined as a rotation center, a first driving component is arranged on the base, the first driving component is used for driving the rotating chassis to rotate, so that the bullet model rotates on a horizontal plane by taking the rotating center as a central point, the projectile body support frame is provided with a second driving assembly and a third driving assembly, the second driving assembly is used for driving the projectile body model to rotate on a vertical plane vertical to the horizontal plane by taking the rotation center as a central point, the third driving assembly is used for driving the projectile body model to rotate around the axis of the third driving assembly, and the first driving assembly, the second driving assembly and the third driving assembly can work simultaneously, the signal transmission assembly is used for satellite signal transmission between the projectile body model and the control assembly, the control assembly is used for analyzing the transmitted satellite signals and controlling the first driving assembly, the second driving assembly and the third driving assembly.
Preferably, the first driving assembly comprises a first motor and a first gear ring, the first gear ring is integrally connected to the outer side wall of the rotating chassis, the first motor is fixed on the base, a first driving gear is coaxially and fixedly connected to an output shaft of the first motor, and the first driving gear is meshed with the first gear ring.
Preferably, the second drive assembly includes second motor and second ring gear, the elastomer support frame includes supporting seat and rotating turret, the upper end of supporting seat is equipped with the arc track, the rotating turret is the arc setting, and rotating turret and arc track sliding connection, second ring gear an organic whole is connected in the lower lateral wall of rotating turret, the orbital center department of arc is seted up flutedly, the second motor is fixed on rotating the chassis, the free end of the output shaft of second motor is worn to locate in the recess, and the coaxial rigid coupling of free end of the output shaft of second motor has second drive gear, second drive gear and the meshing of second ring gear.
Preferably, the third drive assembly includes third motor and intermediate gear, the coaxial rigid coupling in axial both ends of projectile body model has the roll back shaft, just the projectile body model rotates through the roll back shaft and connects between the axial both ends of rotating turret, the coaxial rigid coupling of intermediate gear is on arbitrary roll back shaft, the tip at the rotating turret is fixed to the third motor, the coaxial rigid coupling of output shaft of third motor has third drive gear, third drive gear with the intermediate gear meshing.
Preferably, the signal transmission assembly comprises a high-frequency slip ring, a feeder line and a satellite navigation receiver, the high-frequency slip ring is fixed on any rolling support shaft, the high-frequency slip ring is electrically connected with a satellite navigation antenna on the projectile body model, the high-frequency slip ring is electrically connected with the satellite navigation receiver through the feeder line, and the satellite navigation receiver is electrically connected with the control assembly.
Compared with the prior art, the technical scheme has the following advantages:
(1) in the technical scheme, the missile model is simple, and only the actual missile is required to be intercepted and provided with the outer shell of the satellite navigation antenna cabin section;
(2) in the technical scheme, the satellite navigation receiver is connected with the antenna by adopting the slip ring, the satellite navigation receiver does not need to be fixed on a missile cabin section, the cabin section is light in weight, the supporting device can adapt to small-size to large-size missile models, and the application range is wide;
(3) in the technical scheme, the flight simulation of the projectile body model can be realistically realized, the whole flight performance of the satellite navigation receiver is tested, and the device has a simple structure and is convenient to operate;
(4) in the technical scheme, the limit condition test can be independently carried out on the azimuth, the pitch and the roll of the satellite navigation receiver.
Drawings
Fig. 1 is a schematic structural diagram of a satellite collecting test device of a missile-borne satellite navigation receiver according to the present invention;
Detailed Description
The invention will be described in further detail with reference to the following drawings and embodiments:
reference numerals in the drawings of the specification include: the device comprises a rolling supporting shaft 1, a rotating frame 2, a rotating chassis 3, a third motor 4, a high-frequency slip ring 5, a feeder line 6, a satellite navigation receiver 7, a computer 8, an elastomer model 9, a supporting seat 10, a chassis 11, a first motor 12, a second motor 13 and an intermediate gear 14.
In the embodiment, as shown in fig. 1, a satellite collecting test device for a missile-borne satellite navigation receiver 7 includes: the base is coaxially and rotatably connected with a rotating chassis 3; projectile body support frame, its frock bearing: no less than 50kg, the elastomer support frame comprises a support seat 10 and a rotating frame 2, the support seat 10 is fixedly connected to a rotating chassis 3, an arc-shaped track is arranged at the upper end of the support seat 10, the rotating frame 2 is arranged in an arc shape, the rotating frame 2 is in sliding connection with the arc-shaped track, an elastomer model 9 is horizontally installed on the elastomer support frame, the elastomer model 9 is provided with a satellite navigation antenna, two axial ends of the elastomer model 9 are coaxially and fixedly connected with a rolling support shaft 1, and the elastomer model 9 is rotatably connected between the two axial ends of the rotating frame 2 through the rolling support shaft 1; the control part comprises a signal transmission assembly and a control assembly.
The axis midpoint of the projectile body model 9 is defined as a rotation center, the rotation center and the center of the rotating chassis 3 are located on the same line perpendicular to the rotating chassis 3, a first driving assembly is arranged on the base and comprises a first motor 12 and a first gear ring, the first gear ring is integrally connected to the outer side wall of the rotating chassis 3, the first motor 12 is fixed on the base, a first driving gear is coaxially and fixedly connected to the output shaft of the first motor 12, the first driving gear is meshed with the first gear ring, and the first driving assembly is used for driving the rotating chassis 3 to rotate so that the projectile body model 9 rotates on the horizontal plane by taking the rotation center as a central point.
Be equipped with second drive assembly and third drive assembly on the projectile body support frame, second drive assembly includes second motor 13 and second ring gear, second ring gear body coupling is in the lower lateral wall of rotating turret 2, orbital center department of arc sets up flutedly, recess and arc track intercommunication, second motor 13 is fixed on rotation chassis 3, the rear end of the output shaft of second motor 13 is worn to locate in the recess, and the coaxial rigid coupling in rear end of the output shaft of second motor 13 has second drive gear, second drive gear and the meshing of second ring gear. The second driving assembly is used for driving the bullet model 9 to rotate on a vertical plane perpendicular to the horizontal plane by taking the rotation center as a center point.
The third driving component comprises a third motor 4 and a middle gear 14, the middle gear 14 is coaxially and fixedly connected to the right rolling supporting shaft 1, the third motor 4 is fixed at the right end of the rotating frame 2, an output shaft of the third motor 4 is coaxially and fixedly connected with a third driving gear, and the third driving gear is meshed with the middle gear 14. The third driving assembly is used for driving the bullet model 9 to rotate around the axis of the third driving assembly.
The high-frequency slip ring type missile body model synchronous driving mechanism comprises a first driving component, a second driving component and a third driving component, wherein the signal transmission component comprises a high-frequency slip ring 5, a feeder line 6 and a satellite navigation receiver 7, the high-frequency slip ring 5 is fixed on a right-side rolling supporting shaft 1, the high-frequency slip ring 5 is electrically connected with a satellite navigation antenna on the missile body model 9, the high-frequency slip ring 5 is electrically connected with the satellite navigation receiver 7 through the feeder line 6, the satellite navigation receiver 7 is electrically connected with a control component, the signal transmission component is used for satellite signal transmission between the missile body model 9 and the control component, the control component comprises a computer 8, a software program is stored on a storage medium of the computer 8 and used for analyzing transmitted satellite signals and controlling the first driving component, the second driving component and the third driving component.
The specific implementation process is as follows: fixing a satellite navigation antenna on the projectile body model 9, connecting the satellite navigation antenna of the projectile body model 9 with a satellite navigation receiver 7 through a high-frequency slip ring 5, and connecting the satellite navigation receiver 7 with a control resolving computer 8; the control resolving computer 8 is decomposed into three paths of output signals of azimuth (horizontal plane), pitching (vertical plane) and rolling (axis rotation) according to the flying trajectory of the missile, and controls three paths of driving components respectively; the control resolving computer 8 can receive satellite navigation signals, analyze and display satellite receiving conditions of the satellite navigation receiver 7 and evaluate satellite receiving performance; if the performance test of the satellite navigation receiver 7 is carried out, the control resolving computer 8 realizes the azimuth and pitch change ranges of the projectile body model 9 according to the test requirements: ± 45 °, azimuth, pitch change speed: no less than 10 °/s, azimuth and pitch change accuracy: no less than 0.2 °/s, rolling change speed: and 720 DEG/s, setting three output signals of a middle position (horizontal plane), a pitching (vertical plane) and a rolling (axial rotation) and respectively controlling three driving components. And the control resolving computer 8 receives the satellite navigation signal, analyzes and displays the satellite receiving condition of the satellite navigation receiver 7, and evaluates the satellite receiving performance.
The above description is only an example of the present invention, and the detailed technical solutions and/or characteristics known in the solutions are not described too much here. It should be noted that, for those skilled in the art, without departing from the technical solution of the present invention, several modifications and improvements can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (5)
1. The utility model provides a missile-borne satellite navigation receiver receives star test device which characterized in that includes:
the base is coaxially and rotatably connected with a rotating chassis;
the projectile body supporting frame is mounted on the rotating chassis, and a projectile body model is horizontally mounted on the projectile body supporting frame;
a control section including a signal transmission component and a control component;
the middle point of the axis of the projectile body model is defined as a rotation center, a first driving component is arranged on the base, the first driving component is used for driving the rotating chassis to rotate, so that the bullet model rotates on a horizontal plane by taking the rotating center as a central point, the projectile body support frame is provided with a second driving assembly and a third driving assembly, the second driving assembly is used for driving the projectile body model to rotate on a vertical plane vertical to the horizontal plane by taking the rotation center as a central point, the third driving assembly is used for driving the projectile body model to rotate around the axis of the third driving assembly, and the first driving assembly, the second driving assembly and the third driving assembly can work simultaneously, the signal transmission assembly is used for satellite signal transmission between the projectile body model and the control assembly, the control assembly is used for analyzing the transmitted satellite signals and controlling the first driving assembly, the second driving assembly and the third driving assembly.
2. The missile-borne satellite navigation receiver satellite collecting test device according to claim 1, characterized in that: first drive assembly includes first motor and first ring gear, first ring gear integrated connection is in rotating the lateral wall on chassis, first motor is fixed on the base, coaxial rigid coupling has first drive gear on the output shaft of first motor, first drive gear and the meshing of first ring gear.
3. The missile-borne satellite navigation receiver satellite collection test device according to claim 2, characterized in that: the second drive assembly includes second motor and second ring gear, the projectile body support frame includes supporting seat and rotating turret, the upper end of supporting seat is equipped with the arc track, the rotating turret is the arc setting, and rotating turret and arc track sliding connection, second ring gear an organic whole is connected in the lower lateral wall of rotating turret, orbital center department of arc is seted up flutedly, the second motor is fixed on rotating the chassis, the free end of the output shaft of second motor is worn to locate in the recess, and the coaxial rigid coupling of free end of the output shaft of second motor has second drive gear, second drive gear and the meshing of second ring gear.
4. The missile-borne satellite navigation receiver satellite collecting test device according to claim 3, characterized in that: the third drive assembly includes third motor and intermediate gear, the coaxial rigid coupling in axial both ends of projectile body model has the roll back shaft, just the projectile body model rotates through the roll back shaft and connects between the axial both ends of rotating turret, the coaxial rigid coupling of intermediate gear is on arbitrary roll back shaft, the tip at the rotating turret is fixed to the third motor, the coaxial rigid coupling of output shaft of third motor has third drive gear, third drive gear with the intermediate gear meshing.
5. The missile-borne satellite navigation receiver satellite collection test device according to claim 4, characterized in that: the signal transmission assembly comprises a high-frequency slip ring, a feeder line and a satellite navigation receiver, the high-frequency slip ring is fixed on any rolling supporting shaft and is electrically connected with a satellite navigation antenna on the projectile body model, the high-frequency slip ring is electrically connected with the satellite navigation receiver through the feeder line, and the satellite navigation receiver is electrically connected with the control assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021067622.3U CN214041746U (en) | 2020-06-11 | 2020-06-11 | Missile-borne satellite navigation receiver satellite receiving test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021067622.3U CN214041746U (en) | 2020-06-11 | 2020-06-11 | Missile-borne satellite navigation receiver satellite receiving test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214041746U true CN214041746U (en) | 2021-08-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021067622.3U Active CN214041746U (en) | 2020-06-11 | 2020-06-11 | Missile-borne satellite navigation receiver satellite receiving test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214041746U (en) |
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2020
- 2020-06-11 CN CN202021067622.3U patent/CN214041746U/en active Active
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