CN203638101U - Aviation inertial navigation bracket based on support nails - Google Patents
Aviation inertial navigation bracket based on support nails Download PDFInfo
- Publication number
- CN203638101U CN203638101U CN201320848179.7U CN201320848179U CN203638101U CN 203638101 U CN203638101 U CN 203638101U CN 201320848179 U CN201320848179 U CN 201320848179U CN 203638101 U CN203638101 U CN 203638101U
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- CN
- China
- Prior art keywords
- bracket
- inertial navigation
- aviation
- support nail
- pallet base
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 238000009434 installation Methods 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims description 11
- 239000000463 material Substances 0.000 claims description 7
- 239000010935 stainless steel Substances 0.000 claims description 7
- 229910001220 stainless steel Inorganic materials 0.000 claims description 4
- 229910000989 Alclad Inorganic materials 0.000 claims description 3
- 230000006978 adaptation Effects 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims description 3
- 229920000647 polyepoxide Polymers 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 abstract description 3
- 230000007774 longterm Effects 0.000 abstract description 2
- 238000005299 abrasion Methods 0.000 abstract 1
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 239000000758 substrate Substances 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 239000011435 rock Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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Abstract
Provided is an aviation inertial navigation bracket based on support nails. The bracket comprises the bracket support nails, a bracket substrate and bracket pins. Installation of a current aviation inertial navigation is achieved via cooperation of three pins on a bracket and three pin holes in the bottom of the aviation inertial navigation, and in order to achieve rapid disassembly, the pins are in clearance fit with the pin holes, so it is difficult to firmly combine the aviation inertial navigation and the bracket. In order to overcome minimal gaps and shaking between an aviation inertial navigation and a bracket, two support nails are installed on the bracket provided by the utility model. During installation, there is small interference in sizes between the support nails and two support blocks at the bottom of the aviation inertial navigation, so installation gaps between the pins and the pin holes are counteracted when the support nails are installed in the bracket. Thus, an inertial navigation part is firmly installed on the bracket, precision of dynamic using of a gyro of the inertial navigation part is increased, abrasion caused by long-term usage of pins and pin holes is reduced, service lifetime of devices is prolonged, and maintenance cost is reduced.
Description
Technical field
The utility model belongs to Electromechanical Control field, and particularly a kind of aviation inertial navigation bracket based on support nail is more fastening reliable after can making aviation inertial navigation equipment and bracket install.
Background technology
The market demand and competition are to pursue development in a scientific way and the power of technological advance, along with advancing by leaps and bounds that laser inertial technical elements is obtained, and laser is used to group, and in the widespread use, particularly airborne of the every field such as space flight, aviation and navigation, the quick-detachment to laser inertial, maintainability and commonality propose high requirement.Therefore, necessary research and development laser inertial equipment quick-detachment and the design of general interchange structure.
Prior art scheme is to adopt inertial navigation parts and bracket split design, and bracket is fixed on carrier aircraft base plate by three screws, and bracket has three pins that stretch out, three pin-and-holes are arranged at inertial navigation bottom, push after bracket, pin coordinates with pin-and-hole, then by the locking of national military standard Type B handle.Due to for convenient disassembly, pin and pin-and-hole are to adopt free-running fit, in the time that inertial navigation is used, particularly, in vibration processes, between inertial navigation parts and bracket, just may exist and rock, and inertial navigation inside sensing instrument navigation accuracy is exerted an influence.
Utility model content
The technical problems to be solved in the utility model is: overcome the deficiencies in the prior art, provide a kind of simple in structure, easily manufactured, can make the more reliable fastening bracket that packs into of aviation class inertial navigation equipment improve equipment in-use performance.
Technical solution of the present utility model is: a kind of aviation inertial navigation bracket based on support nail, comprise bracket support nail, pallet base and bracket pin, totally three of bracket pins, one of them bracket pin is fixedly connected on center position on the side of pallet base, two other bracket pin is fixedly connected on the two ends of the side of pallet base, and three bracket pin directions are consistent; Totally 2 of support nails, screw thread is fixed on the surface of pallet base; Respectively there is a groove type slide rail upper surface both sides of pallet base, and described pallet base has the first hollow square structure and the second hollow square structure and the 3rd hollow square structure, and has a strength beam in the 3rd hollow square structure.
Described bracket support nail adopts corrosion-resistant steel M5 outer-hexagonal bolts, be fitted into after the repair of bracket ad-hoc location, ensure and inertial navigation equipment bottom matching allowance 0.05-0.1mm, and it is good when for the first time with inertial navigation adaptation procedure, can to carry out micro-height adjustment with spanner as required, and use epoxide-resin glue fix tightly.
Pallet base adopts Alclad material, and bracket pin adopts stainless steel material, and itself and inertial navigation bottom respective pin hole are to take free-running fit, and in use procedure, bracket support nail is offset gap, with fastening installation.
The utility model beneficial effect is compared with prior art:
(1) the utility model is realized inertial navigation and bracket is realized rigid fit, avoids wobble effects Gyro Precision in dynamic use procedure.
(2) in the utility model, bracket support nail has been offset pin-and-hole and pin-hole clearance, reduces Dynamic wear, in the extension device life-span, reduces maintenance cost.
(3) the utility model bracket installation support nail can form with common outer-hexagonal stainless steel screw transformation, and material is easily found, and is easy to realize, and in the time using for the first time, is easy to adjust adaptive in processing.
Brief description of the drawings
Fig. 1 is the utility model bracket schematic diagram;
Fig. 2 is that the utility model bracket support is followed closely local enlarged diagram;
Fig. 3 is the utility model bracket and inertial navigation equipment assembling schematic diagram.
Detailed description of the invention
Basic ideas of the present utility model are: have minim gap and rock for aviation inertial navigation and bracket installation, take to install two support nails on bracket, when installation and in inertial navigation feature bottom two back-up block sizes, there is slight interference, while packing into, offset pin and pin-and-hole assemblage gap, make the fastening installation of inertial navigation parts and bracket, improve the dynamic service precision of inertial navigation equipment gyroscope, improve the long-term pin pin-and-hole wearing and tearing that use, extension device service life, reduce maintenance cost, be a kind of preferred embodiment below.
As shown in Figure 1, a kind of aviation inertial navigation bracket based on support nail, comprise bracket support nail 1, pallet base 2 and bracket pin 3, totally three of bracket pins 3, one of them bracket pin is fixedly connected on center position on the side 201 of pallet base 2, two other bracket pin is fixedly connected on the two ends of the side 205 of pallet base 2, and three bracket pin directions are consistent; Totally 2 of support nails 1, screw thread is fixed on the surface 206 of pallet base 2; Respectively there is a groove type slide rail 202 the upper surface both sides of pallet base 2, and described pallet base 2 has the first hollow square structure 203 and the second hollow square structure 204 and the 3rd hollow square structure 208, and in the 3rd hollow square structure 208, have a strength beam 207.
As shown in Figure 2, described bracket support nail 1 adopts corrosion-resistant steel M5 outer-hexagonal bolts, be fitted into after the repair of bracket ad-hoc location, ensure and inertial navigation equipment bottom matching allowance 0.05-0.1mm, and it is good when for the first time with inertial navigation adaptation procedure, can to carry out micro-height adjustment with spanner as required, and use epoxide-resin glue fix tightly.
As shown in Figure 3, Fig. 3 is that inertial navigation equipment is assemblied in the state on inertial navigation bracket of the present utility model; In order to ensure conveniently quick-detachment on bracket of inertial navigation parts, its bracket pin 3 and inertial navigation bottom respective pin hole have certain interval, likely have gap after causing thus inertial navigation parts to pack bracket into, in carrier aircraft dynamically or when serious offense carrying is moving, there will be and rock, affect gyroscope precision.Therefore increase bracket support nail 1, and ensure that its and inertial navigation ground are combined with 0.05-0.1mm interference man-hour adding, when installation, push by handle leverage, increase and retrain, realized location, realize inertial navigation and bracket is fastenedly connected.
Be arranged in the use procedure of this bracket at inertial navigation equipment, can carry out random vibration test, add up its gyro pulse mean effective value, checking support nail result of use, as shown in the table:
Can be found out by upper table, install after support nail at bracket, vibration processes gyro pulse mean effective value obviously reduces, and very large limit reduces inertial navigation to be affected in use procedure Gyro Precision.
Certainly, to each constituent elements of the present utility model, position relationship and connection mode, in the situation that not changing its function, the equivalent transformation carrying out or alternative, also falls into protection domain of the present utility model.
The unspecified part of the utility model belongs to general knowledge as well known to those skilled in the art.
Claims (5)
1. the aviation inertial navigation bracket based on support nail, it is characterized in that: comprise bracket support nail (1), pallet base (2) and bracket pin (3), totally three of bracket pins (3), one of them bracket pin is fixedly connected on the upper center position in side (201) of pallet base (2), two other bracket pin is fixedly connected on the two ends of the side (205) of pallet base (2), and three bracket pin directions are consistent; Totally 2 of support nails (1), screw thread is fixed on the surface (206) of pallet base (2); Respectively there is a groove type slide rail (202) the upper surface both sides of pallet base (2).
2. a kind of aviation inertial navigation bracket based on support nail according to claim 1, it is characterized in that: described pallet base (2) has the first hollow square structure (203) and the second hollow square structure (204) and the 3rd hollow square structure (208), and has a strength beam (207) in the 3rd hollow square structure (208).
3. a kind of aviation inertial navigation bracket based on support nail according to claim 1, it is characterized in that: described bracket support nail (1) adopts corrosion-resistant steel M5 outer-hexagonal bolts, be fitted into after the repair of bracket ad-hoc location, ensure and inertial navigation equipment bottom matching allowance 0.05-0.1mm, and it is good when for the first time with inertial navigation adaptation procedure, can to carry out micro-height adjustment with spanner as required, and use epoxide-resin glue fix tightly.
4. a kind of aviation inertial navigation bracket based on support nail according to claim 1, is characterized in that: pallet base (2) adopts Alclad material.
5. a kind of aviation inertial navigation bracket based on support nail according to claim 1, it is characterized in that: described bracket pin (3) adopts stainless steel material, itself and inertial navigation bottom respective pin hole are to take free-running fit, and in use procedure, bracket support nail is offset gap, with fastening installation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320848179.7U CN203638101U (en) | 2013-12-19 | 2013-12-19 | Aviation inertial navigation bracket based on support nails |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320848179.7U CN203638101U (en) | 2013-12-19 | 2013-12-19 | Aviation inertial navigation bracket based on support nails |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203638101U true CN203638101U (en) | 2014-06-11 |
Family
ID=50869368
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320848179.7U Expired - Lifetime CN203638101U (en) | 2013-12-19 | 2013-12-19 | Aviation inertial navigation bracket based on support nails |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203638101U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104493773A (en) * | 2014-12-16 | 2015-04-08 | 北京航天新风机械设备有限责任公司 | Mounting precision adjusting tool for inertial navigation unit |
| CN115649476A (en) * | 2022-09-30 | 2023-01-31 | 成都飞机工业（集团）有限责任公司 | Pin type finished product bottom plate installation method based on vibration environment |
-
2013
- 2013-12-19 CN CN201320848179.7U patent/CN203638101U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104493773A (en) * | 2014-12-16 | 2015-04-08 | 北京航天新风机械设备有限责任公司 | Mounting precision adjusting tool for inertial navigation unit |
| CN104493773B (en) * | 2014-12-16 | 2016-05-25 | 北京航天新风机械设备有限责任公司 | A kind of inertial nevigation apparatus installation accuracy is adjusted frock |
| CN115649476A (en) * | 2022-09-30 | 2023-01-31 | 成都飞机工业（集团）有限责任公司 | Pin type finished product bottom plate installation method based on vibration environment |
| CN115649476B (en) * | 2022-09-30 | 2024-05-14 | 成都飞机工业（集团）有限责任公司 | Bolt finished product bottom plate mounting method based on vibration environment |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140611 |