CN218765327U - Testing device for inertial navigation - Google Patents
Testing device for inertial navigation Download PDFInfo
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- CN218765327U CN218765327U CN202223180795.8U CN202223180795U CN218765327U CN 218765327 U CN218765327 U CN 218765327U CN 202223180795 U CN202223180795 U CN 202223180795U CN 218765327 U CN218765327 U CN 218765327U
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- inertial navigation
- adapter plate
- adjusting
- test device
- zero point
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Abstract
The utility model discloses a be used to lead and use test device, including biax revolving stage and keysets, be equipped with on the keysets be used for with be used to lead the coupling mechanism who is connected, be equipped with many fitting pins on the keysets, correspond every fitting pin and all be equipped with the zero point locator that is used for locking and unclamps the fitting pin on the stage body of biax revolving stage. The inertial navigation testing device has the advantages of being capable of being quickly disassembled and assembled, reducing labor intensity, improving testing efficiency, being easy to implement, having good application prospect and the like.
Description
Technical Field
The utility model relates to a be used to lead technical field, concretely relates to be used to lead and use test device.
Background
Inertial navigation requires the use of a fixture mounted on a dual-axis turntable to perform various tests. Because the inertial navigation models are various and the difference between the inertial navigation appearance and the installation size is large, a corresponding installation positioning clamp needs to be designed for each model of inertial navigation, and the required clamps are various. In the traditional test device, screws penetrate through mounting through holes of inertial navigation self-belts to be mounted on a patch board, and then the patch board is directly mounted and fixed on a double-shaft turntable by the screws, so that different patch boards corresponding to the distribution positions of threaded holes are required to be designed when inertial navigation tests of different models are carried out due to different mounting through holes of the inertial navigation self-belts of different models, the number of patch boards required to be equipped is large, and the cost is high; meanwhile, when the inertial navigation is disassembled and assembled, the screw is disassembled and assembled by a tester by using an inner hexagon wrench or a torque wrench, so that the fixed connection and the disassembly of the mounting and positioning clamp and the rotary table are realized, the tester is led to bear a large amount of clamp mounting and disassembling operations every day, and the labor intensity is high and the efficiency is low. In addition, because the inertial navigation is indirectly installed on the table body of the double-shaft rotary table through the adapter plate, the adapter plate inevitably has precision limitation and certain errors during processing, connection and assembly, so that the inertial navigation cannot meet the test requirement relative to the posture of the table body after being installed on the table body through the adapter plate, and the requirement on processing, manufacturing and assembly is high.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to overcome the not enough that prior art exists, but provide a quick assembly disassembly, reduce intensity of labour, improve test efficiency, easy to carry out, application prospect is good is used to lead and uses test device.
In order to solve the technical problem, the utility model discloses a following technical scheme:
the utility model provides a test device for inertial navigation, includes biax revolving stage and keysets, be equipped with on the keysets and be used for being connected with the coupling mechanism that is used for inertial navigation, be equipped with many check pins on the keysets, it all is equipped with the zero point locator that is used for locking and unclamping the check pin to correspond every check pin on the stage body of biax revolving stage.
As a further improvement of the above technical solution:
all the zero point positioners are arranged on a bottom plate, and the bottom plate is arranged on the table body through a fastening piece.
The bottom plate is provided with an air inlet channel used for ventilating each zero point locator and an air pipe plug connector connected with the air inlet channel, and the zero point locator is used for ventilating, opening and locking.
The connecting mechanism comprises a plurality of connecting units which are arranged on the adapter plate and are respectively used for connecting different models of inertial navigation.
The connection unit comprises a plurality of threaded connection holes arranged on the adapter plate.
And the adapter plate is provided with an attitude adjusting assembly for adjusting the relative inclination angle of the inertial navigation relative to the adapter plate.
The attitude adjusting assembly comprises more than three adjusting studs for supporting inertial navigation and separation from the adapter plate, each adjusting stud on the adapter plate is provided with a thread adjusting hole corresponding to each adjusting stud, and the adjusting studs are in thread fit connection in the corresponding thread adjusting holes and can be adjusted in mounting height on the adapter plate by screwing.
And one end of the adjusting stud, which is far away from the adapter plate, is provided with a spherical surface for supporting inertial navigation.
Compared with the prior art, the utility model has the advantages of:
the utility model discloses a be used to lead and use test device adopts the zero point locator of setting on the stage body of biax revolving stage and sets up the fitting pin cooperation on the keysets, and accessible control zero point locator realizes quick locking and loosens the fitting pin to realize that the keysets is automatic to be connected and dismantlement fast, but greatly reduced intensity of labour improves test efficiency, and its easy to carry out, application prospect are good.
Drawings
Fig. 1 is a schematic perspective view of a test apparatus for inertial navigation.
FIG. 2 is a schematic diagram of a split three-dimensional structure of the inertial navigation testing device.
Fig. 3 is a schematic perspective view of the bottom plate.
Fig. 4 is a schematic top view of the interposer.
Fig. 5 is a schematic front view of the adjusting stud connected to the adapter plate.
FIG. 6 is a front view of the adjusting stud.
Illustration of the drawings:
1. a double-shaft turntable; 11. a table body; 2. an adapter plate; 21. connecting a threaded hole; 22. a threaded adjustment hole; 3. a locking pin; 4. a zero locator; 5. a base plate; 51. an air intake passage; 6. adjusting the stud; 61. a spherical surface; 100. and (5) inertial navigation.
Detailed Description
The present invention will be described in further detail with reference to the following drawings and specific embodiments.
As shown in fig. 1 and fig. 2, the inertial navigation testing apparatus of this embodiment includes a dual-axis turntable 1 and an adapter plate 2, a connecting mechanism for connecting with an inertial navigation device (denoted by 100 in the drawings) is disposed on the adapter plate 2, a plurality of locking pins 3 are disposed on the adapter plate 2, and a zero point locator 4 for locking and releasing the locking pins 3 is disposed on a table body 11 of the dual-axis turntable 1 corresponding to each locking pin 3. This be used to lead and use test device adopts zero point locator 4 and the fitting pin 3 of setting on keysets 2 of setting on the stage body 11 of biax revolving stage 1 to cooperate, and accessible control zero point locator 4 realizes quick locking and unclamps fitting pin 3 to realize that keysets 2 is automatic to be connected and dismantles fast, but greatly reduced intensity of labour, improvement test efficiency, and its easy to carry out, application prospect are good.
In this embodiment, all the zero point positioners 4 are mounted on a base plate 5, and the base plate 5 is mounted on the stage body 11 by fasteners. The structure of the complex installation zero point positioner 4 does not need to be arranged on the table body 11, and the existing table body 11 does not need to be modified.
In the present embodiment, as shown in fig. 3, the bottom plate 5 is provided with an air inlet passage 51 for ventilating each zero point positioner 4 and an air pipe connector (not shown) connected to the air inlet passage 51, and the zero point positioner 4 performs an opening operation for ventilation and a locking operation for air shutoff. Because be used to lead when installing on stage 11 and test, stage 11 can take and be used to lead the motion, can make zero point locator 4 and control pressure air supply convenient, swift dismouting of carrying on through the trachea bayonet joint, can realize when the installation is used to lead, the trachea of connection control pressure air supply, the trachea of control pressure air supply is pulled out fast after the installation is accomplished to avoid influencing the test. Meanwhile, the zero positioner is matched with ventilation to execute opening action and air cut-off to execute locking action, so that the locking pin 3 can be locked after the air pipe for controlling the pressure air source is pulled out, the test requirement of inertial navigation can be completely met, and the convenience in use is ensured.
In this embodiment, as shown in fig. 4, the connection mechanism includes a plurality of connection units respectively arranged on the adapter plate 2 and used for connecting different models of inertial navigations. The adapter plate 2 can be used for connecting inertial navigations of various different models, the adapter plate 2 does not need to be replaced when the inertial navigations of different models are tested, the number of the required adapter plates 2 is small, and the cost can be reduced.
In this embodiment, the connection unit includes a plurality of threaded connection holes 21 arranged on the adapter plate 2, so that the inertial navigation device can conveniently adopt screws to penetrate through the installation through holes of the inertial navigation device to be connected with the threaded connection holes 21 in a matched manner, thereby fixing the inertial navigation device and the adapter plate 2. The connecting device is simple in structure, easy to process and manufacture and convenient for connecting and disassembling the inertial navigation and the adapter plate 2.
In this embodiment, as shown in fig. 4 to 6, the adaptor plate 2 is provided with a posture adjustment assembly for adjusting a relative inclination angle of inertial navigation with respect to the adaptor plate 2. Manufacturing and assembling errors exist in all parts of the test device for inertial navigation, and the relative inclination angle of the inertial navigation relative to the adapter plate 2 can be adjusted through the posture adjusting assembly, so that after the inertial navigation is installed on the table body 11, the inclination angle relative to the table body 11 meets the test installation requirements.
In this embodiment, the attitude adjustment assembly includes more than three adjustment studs 6 for supporting the inertial navigation and disengaging from the adapter plate 2, a threaded adjustment hole 22 is provided on the adapter plate 2 corresponding to each adjustment stud 6, and the adjustment studs 6 are in threaded fit connection with the corresponding threaded adjustment holes 22 and can be adjusted in mounting height on the adapter plate 2 by screwing. Because the inertial navigation is supported on the adjusting stud 6, the inclination angle of the inertial navigation relative to the adapter plate 2 can be adjusted by adjusting the installation height of the adjusting stud 6 on the adapter plate 2. The posture adjusting assembly has the advantages of simple structure, low cost, easiness in processing and manufacturing and simplicity and convenience in adjustment.
In this embodiment, the end of the adjusting stud 6 away from the adapter plate 2 is provided with a spherical surface 61 for supporting inertial navigation. The inertial navigation support forms point contact on the spherical surface 61, so that the influence of the contact surface of the adjusting stud 6 on the inclination angle adjustment of the adapter plate 2 caused by the surface contact between the adjusting stud 6 and the inertial navigation support can be avoided.
The above description is only the preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments. To those skilled in the art, the modifications and changes that can be made without departing from the scope of the present invention shall be considered as the protection scope of the present invention.
Claims (8)
1. The utility model provides a test device for inertial navigation, includes biax revolving stage (1) and keysets (2), be equipped with on keysets (2) be used for with be used for the coupling mechanism who is connected of inertial navigation, its characterized in that: be equipped with many fitting pins (3) on keysets (2), correspond every fitting pin (3) on stage body (11) of biax revolving stage (1) and all be equipped with zero point locator (4) that are used for locking and unclamp fitting pin (3).
2. The inertial navigation test device according to claim 1, wherein: all the zero point locators (4) are mounted on a bottom plate (5), and the bottom plate (5) is mounted on the table body (11) through fasteners.
3. The inertial navigation test device according to claim 2, wherein: the bottom plate (5) is provided with an air inlet channel (51) used for ventilating each zero point positioner (4) and an air pipe plug connector connected with the air inlet channel (51), and the zero point positioner (4) is used for performing opening action for ventilation and locking action for air cutoff.
4. The inertial navigation test device according to claim 1, wherein: the connecting mechanism comprises a plurality of connecting units which are arranged on the adapter plate (2) and are respectively used for connecting different models of inertial navigation.
5. The inertial navigation test device according to claim 4, wherein: the connection unit comprises a plurality of threaded connection holes (21) arranged on the adapter plate (2).
6. The inertial navigation test apparatus according to claim 1, wherein: and the adapter plate (2) is provided with a posture adjusting assembly for adjusting the relative inclination angle of inertial navigation relative to the adapter plate (2).
7. The inertial navigation test device according to claim 6, wherein: the posture adjusting assembly comprises more than three adjusting studs (6) used for supporting inertial navigation and separating from the adapter plate (2), each adjusting stud (6) corresponding to the adapter plate (2) is provided with a thread adjusting hole (22), and the adjusting studs (6) are in thread fit connection in the corresponding thread adjusting holes (22) and can be adjusted in mounting height on the adapter plate (2) through screwing.
8. The inertial navigation test apparatus according to claim 7, wherein: and a spherical surface (61) for supporting inertial navigation is arranged at one end of the adjusting stud (6) far away from the adapter plate (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223180795.8U CN218765327U (en) | 2022-11-29 | 2022-11-29 | Testing device for inertial navigation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223180795.8U CN218765327U (en) | 2022-11-29 | 2022-11-29 | Testing device for inertial navigation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218765327U true CN218765327U (en) | 2023-03-28 |
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ID=85678257
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223180795.8U Active CN218765327U (en) | 2022-11-29 | 2022-11-29 | Testing device for inertial navigation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218765327U (en) |
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2022
- 2022-11-29 CN CN202223180795.8U patent/CN218765327U/en active Active
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