CN203190886U - Installation structure for gyro muzzle - Google Patents
Installation structure for gyro muzzle Download PDFInfo
- Publication number
- CN203190886U CN203190886U CN 201320008390 CN201320008390U CN203190886U CN 203190886 U CN203190886 U CN 203190886U CN 201320008390 CN201320008390 CN 201320008390 CN 201320008390 U CN201320008390 U CN 201320008390U CN 203190886 U CN203190886 U CN 203190886U
- Authority
- CN
- China
- Prior art keywords
- dual spindle
- installation shaft
- spindle gyroscopes
- gyro
- gun
- 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 - Fee Related
Links
Images
Landscapes
- Gyroscopes (AREA)
Abstract
The utility model discloses an installation structure for a gyro muzzle. The installation structure comprises a gun barrel. A sleeve is inserted in the muzzle of the gun barrel. A locking ring is arranged on an outer ring of the muzzle of the gun barrel. One end of the locking ring is connected with the gun barrel in a threaded mode, and the other end of the locking ring is fixedly connected with the sleeve. A two-axis gyro installation shaft is arranged in the sleeve, and a bearing pack is arranged between the two-axis gyro installation shaft and the sleeve. A front limiting block and a rear limiting block of the axial limiting bearing pack are arranged in the sleeve. A check ring and a limiting protrusion of the axial limiting bearing pack are arranged on the two-axis gyro installation shaft. The check ring is located at one end of the two-axis gyro installation shaft, and a two-axis gyro is arranged at the other end of the two-axis gyro installation shaft. A non-sensitive shaft of the two-axis gyro, the two-axis gyro installation shaft, the locking ring and the gun barrel are coaxially arranged. The installation structure enables errors of parameters of a fire control system to be well controlled, and a target plate is not needed. The parameters of the fire control system can be directly used for testing after a sensor is installed, and the automation degree is high.
Description
Technical field
The utility model relates to gun muzzle field of locating technology, is specifically related to a kind of gyro gun muzzle mounting structure.
Technical background
Fire control system is the system that the control weapon is realized weapon-shooting process automation and raising fire accuracy, plays enormous function for the power of bringing into play weapon.The performance quality of gun fire control system can transfer parameters such as big gun speed, minimum pointing velocity, cannon drift velocity, cannon lasting accuracy, transient process quality to weigh by maximum.At present the more method of the testing research of these parameters there is CCD(Charge-coupled Device, charge coupled cell)+and coordinate target, laser instrument+PSD(Position Sensitive Detector, photoelectric position sensor spare) optical measurement target, CCD+ spot light.Wherein CCD+ coordinate target, laser instrument+PSD optical measurement target, CCD+ spot light all use the coordinate target, are indirect angle displacement measurement method, namely at first by to the measurement of gun muzzle straight-line displacement amount, utilize cannon that computing formula obtains and the corner of gun turret then.Advantage is that the relevant cannon fire control with existing national military standard of this several method performance parameters detection method is in full accord, easily by colleague expert and technical staff's approval.But the deficiency of said method also is apparent, and when the measured angle displacement surpassed certain limit, fire control system parameter (transferring big gun speed, minimum pointing velocity, cannon drift velocity, cannon lasting accuracy etc. as the maximum) error of being brought by computing formula was bigger.
The utility model content
The purpose of this utility model is at above-mentioned technical problem, a kind of gyro gun muzzle mounting structure is provided, this structure is installed in dual spindle gyroscopes on gun muzzle, can satisfy make under the same test precision conditions its method of testing simply be convenient to the operation, do not need to make it the professional can finish test.
For realizing this purpose, gyro gun muzzle mounting structure that the utility model is designed, comprise gun tube, it is characterized in that: be inserted with sleeve in gun muzzle of described gun tube, gun muzzle outer ring of gun tube is provided with clamp ring, be threaded between one end of described clamp ring and the gun tube, the other end of clamp ring is fixedlyed connected with sleeve, be provided with the dual spindle gyroscopes installation shaft in the described sleeve, be provided with bearing group between described dual spindle gyroscopes installation shaft and the sleeve, be provided with front limit piece and the back limited block of axial limiting bearing group in the described sleeve, described dual spindle gyroscopes installation shaft is provided with back-up ring and the spacing preiection of axial limiting bearing group, described back-up ring is positioned at an end of dual spindle gyroscopes installation shaft, the other end of described dual spindle gyroscopes installation shaft is provided with dual spindle gyroscopes, the non-sensitive axle of described dual spindle gyroscopes, the dual spindle gyroscopes installation shaft, clamp ring and gun tube are coaxial arrangement.
Described dual spindle gyroscopes installation shaft outer ring is provided with spirit level.
Described dual spindle gyroscopes end is provided with protective jacket.
First sensitive axes of described dual spindle gyroscopes is parallel to the azimuth axis of cannon, and second sensitive axes of described dual spindle gyroscopes is parallel to the pitch axis of cannon.
Be provided with pad between described sleeve and the gun tube.
By support support plate is arranged fixedly on the other end of described dual spindle gyroscopes installation shaft, on the described support plate protective jacket is set.
Described support plate is provided with gyroscope and protects the line hole.
U-shaped adjustment seat is fixedly arranged on the described sleeve, T shape footstock is fixedly arranged on the dual spindle gyroscopes installation shaft, the projection of described T shape footstock is positioned at the U-shaped opening of U-shaped adjustment seat, and the U-shaped opening both sides of described U-shaped adjustment seat are equipped with the adjustment screw that matches with the projection of T shape footstock.
One end of described clamp ring be bolted to connection after gun tube is threaded.Described bearing group comprises preceding end bearing, rear end bearing, is arranged on the spacer ring between preceding end bearing and the rear end bearing, end bearing before described front limit piece is spacing, the spacing rear end bearing of back limited block.
Second sensitive axes of described dual spindle gyroscopes is parallel with spirit level.
The utility model makes that by dual spindle gyroscopes is set at gun muzzle the error of fire control system parameter (transferring big gun speed, minimum pointing velocity, cannon drift velocity, cannon lasting accuracy etc. as maximum) can be controlled preferably, in addition, the utility model does not need target plate, the fire control system parameter just can directly be tested after sensor installs, and automaticity is higher.
Description of drawings
Fig. 1 is perspective view of the present utility model;
Fig. 2 is sectional structure schematic diagram of the present utility model;
Fig. 3 is side-looking structural representation of the present utility model;
Fig. 4 is the structural representation of the sensitive axes of dual spindle gyroscopes in the utility model.
Wherein, 1-gun tube, 2-sleeve, 3-dual spindle gyroscopes installation shaft, 4-bearing group, 4.1-preceding end bearing, 4.2-rear end bearing, 4.3-spacer ring, 5-front limit piece, 6-back limited block, 7-back-up ring, 8-spacing preiection, 9-dual spindle gyroscopes, 9.1-non-sensitive axle, 9.2-the first sensitive axes installed surface, 9.3-the second sensitive axes installed surface, 10-clamp ring, 11-spirit level, 12-protective jacket, 13-pad, 14-support, 15-support plate, 16-gyroscope protects the line hole, 17-U-shaped adjustment seat, 18-T shape footstock, 19-adjustment screw, 20-bolt.
The specific embodiment
The utility model is described in further detail below in conjunction with drawings and Examples:
Gyro gun muzzle mounting structure shown in Fig. 1 ~ 3, comprise gun tube 1, be inserted with sleeve 2 in gun muzzle of gun tube 1, gun muzzle outer ring of gun tube 1 is provided with clamp ring 10, one end of clamp ring 10 is connected by gun muzzle external screw thread with gun tube 1, the other end of clamp ring 10 is fixedlyed connected with sleeve 2, be provided with dual spindle gyroscopes installation shaft 3 in the sleeve 2, be provided with bearing group 4 between dual spindle gyroscopes installation shaft 3 and the sleeve 2, be provided with front limit piece 5 and the back limited block 6 of axial limiting bearing group 4 in the sleeve 2, dual spindle gyroscopes installation shaft 3 is provided with back-up ring 7 and the spacing preiection 8 of axial limiting bearing group 4, back-up ring 7 is positioned at an end of dual spindle gyroscopes installation shaft 3, the other end of dual spindle gyroscopes installation shaft 3 is provided with dual spindle gyroscopes 9, the non-sensitive axle 9.1 of dual spindle gyroscopes 9, dual spindle gyroscopes installation shaft 3, clamp ring 10 and gun tube 1 are coaxial arrangement.Owing to be provided with bearing group 4, above-mentioned dual spindle gyroscopes installation shaft 3 can be rotated relative to sleeve 2.
In the technique scheme, dual spindle gyroscopes installation shaft 3 outer rings are provided with spirit level 11.Described spirit level 11 is used for display unit in the axial level whether of height.
In the technique scheme, dual spindle gyroscopes 9 ends are provided with protective jacket 12.
In the technique scheme, as shown in Figure 4, first sensitive axes of dual spindle gyroscopes 9 is parallel to the azimuth axis of cannon, and second sensitive axes of dual spindle gyroscopes 9 is parallel to the pitch axis of cannon.The second sensitive axes installed surface 9.3 of described dual spindle gyroscopes 9 is parallel with spirit level 11.X and Y-axis are two sensitive axes of dual spindle gyroscopes among Fig. 4, and the Z axle is the non-sensitive axle 9.1 of dual spindle gyroscopes, and the axis of gun tube 1 is parallel with the Z axle, and azimuth axis is parallel with X-axis, and pitch axis is parallel with Y-axis.Be the azimuth axis that the first sensitive axes installed surface 9.2 of dual spindle gyroscopes 9 is parallel to cannon, the second sensitive axes installed surface 9.3 of dual spindle gyroscopes 9 is parallel to the pitch axis of cannon.
In the technique scheme, be provided with pad 13 between sleeve 2 and the gun tube 1.This pad 13 is used for making things convenient for sleeve 2 and gun tube 1 chucking.
In the technique scheme, by support 14 support plate 15 is arranged fixedly on the other end of dual spindle gyroscopes installation shaft 3, protective jacket 12 is set on the support plate 15.Described support plate 15 also is used for installing gyrostatic control circuit board.
In the technique scheme, support plate 15 is provided with gyroscope and protects line hole 16.
In the technique scheme, U-shaped adjustment seat 17 is fixedly arranged on the sleeve 2, T shape footstock 18 is fixedly arranged on the dual spindle gyroscopes installation shaft 3, the projection of T shape footstock 18 is positioned at the U-shaped opening of U-shaped adjustment seat 17, and the U-shaped opening both sides of U-shaped adjustment seat 17 are equipped with the adjustment screw 19 that matches with the projection of T shape footstock 18.During use, by control and regulation screw 19 T shape footstock 18 is moved in U-shaped adjustment seat 17, because T shape footstock 18 is fixing with dual spindle gyroscopes installation shaft 3, U-shaped adjustment seat 17 is fixing with sleeve 2, so make the bubble of spirit level 11 placed in the middle by operation adjustment screw 19, reach the purpose of accurate adjustment.
In the technique scheme, one end of clamp ring 10 is threaded with gun tube 1 and then fixedlys connected by bolt 20, described bearing group 4 comprises preceding end bearing 4.1, rear end bearing 4.2, is arranged on the spacer ring 4.3 between preceding end bearing 4.1 and the rear end bearing 4.2, described front limit piece 5 spacing preceding end bearings 4.1, back limited block 6 spacing rear end bearings 4.2.
During the utility model work: cannon is transferred to level, and making the azimuth of cannon and the angle of site is zero; Lay down the muzzle brake of gun barrel, screw with gyroscope adjusting device insertion gun muzzle and with clamp ring 10, will install fixing by the screw in the clamp ring 10.By this step, make that then gyrostatic non-sensitive axle 9.1(is space Z axle) parallel with the cannon barrel axis.Rotation dual spindle gyroscopes installation shaft 3 makes spirit level 11 in the front, and makes the bubble in the spirit level 11 roughly placed in the middle.Operate adjustment screw 19 then, make the bubble in the spirit level 11 be in the middle position, namely level(l)ing bubble maximum deviation value is no more than 1/4th scale values.By this step, make that second sensitive axes (being the space Y axle) of dual spindle gyroscopes 9 is parallel with the pitch axis of cannon.It is parallel namely to think that first sensitive axes (being the space X axle) of azimuth axis with dual spindle gyroscopes 9 of cannon is in this moment, and the cannon pitch axis is in parallel with gyrostatic space Y axle.Just can utilize dual spindle gyroscopes 9 as angular-rate sensor this moment, measures the motion of cannon on azimuth axis and pitch axis direction.After adopting dual spindle gyroscopes 9, do not need target plate, the fire control system parameter just can directly be tested after sensor installs, and has improved automaticity.
The content that this specification is not described in detail belongs to this area professional and technical personnel's known prior art.
Claims (10)
1. gyro gun muzzle mounting structure, comprise gun tube (1), it is characterized in that: be inserted with sleeve (2) in gun muzzle of described gun tube (1), gun muzzle outer ring of gun tube (1) is provided with clamp ring (10), be threaded between one end of described clamp ring (10) and the gun tube (1), the other end of clamp ring (10) is fixedlyed connected with sleeve (2), be provided with dual spindle gyroscopes installation shaft (3) in the described sleeve (2), be provided with bearing group (4) between described dual spindle gyroscopes installation shaft (3) and the sleeve (2), be provided with front limit piece (5) and the back limited block (6) of axial limiting bearing group (4) in the described sleeve (2), described dual spindle gyroscopes installation shaft (3) is provided with back-up ring (7) and the spacing preiection (8) of axial limiting bearing group (4), described back-up ring (7) is positioned at an end of dual spindle gyroscopes installation shaft (3), the other end of described dual spindle gyroscopes installation shaft (3) is provided with dual spindle gyroscopes (9), the non-sensitive axle (9.1) of described dual spindle gyroscopes (9), dual spindle gyroscopes installation shaft (3), clamp ring (10) and gun tube (1) are coaxial arrangement.
2. gyro gun muzzle mounting structure according to claim 1, it is characterized in that: described dual spindle gyroscopes installation shaft (3) outer ring is provided with spirit level (11).
3. gyro gun muzzle mounting structure according to claim 1, it is characterized in that: described dual spindle gyroscopes (9) end is provided with protective jacket (12).
4. gyro gun muzzle mounting structure according to claim 1, it is characterized in that: first sensitive axes of described dual spindle gyroscopes (9) is parallel to the azimuth axis of cannon, and second sensitive axes of described dual spindle gyroscopes (9) is parallel to the pitch axis of cannon.
5. gyro gun muzzle mounting structure according to claim 1 is characterized in that: be provided with pad (13) between described sleeve (2) and the gun tube (1).
6. gyro gun muzzle mounting structure according to claim 3 is characterized in that: by support (14) support plate (15) is arranged fixedly on the other end of described dual spindle gyroscopes installation shaft (3), protective jacket (12) is set on the described support plate (15).
7. gyro gun muzzle mounting structure according to claim 6, it is characterized in that: described support plate (15) is provided with gyroscope and protects line hole (16).
8. gyro gun muzzle mounting structure according to claim 1, it is characterized in that: described sleeve (2) is gone up fixedly U-shaped adjustment seat (17), dual spindle gyroscopes installation shaft (3) goes up fixedly T shape footstock (18), the projection of described T shape footstock (18) is positioned at the U-shaped opening of U-shaped adjustment seat (17), and the U-shaped opening both sides of described U-shaped adjustment seat (17) are equipped with the adjustment screw (19) that matches with the projection of T shape footstock (18).
9. gyro gun muzzle mounting structure according to claim 1, it is characterized in that: an end of described clamp ring (10) is threaded with gun tube (1) and then fixedlys connected by bolt (20), described bearing group (4) comprises preceding end bearing (4.1), rear end bearing (4.2), is arranged on the spacer ring (4.3) between preceding end bearing (4.1) and the rear end bearing (4.2), end bearing (4.1) before described front limit piece (5) is spacing, the spacing rear end bearing of back limited block (6) (4.2).
10. gyro gun muzzle mounting structure according to claim 4, it is characterized in that: second sensitive axes of described dual spindle gyroscopes (9) is parallel with spirit level (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320008390 CN203190886U (en) | 2013-01-08 | 2013-01-08 | Installation structure for gyro muzzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320008390 CN203190886U (en) | 2013-01-08 | 2013-01-08 | Installation structure for gyro muzzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203190886U true CN203190886U (en) | 2013-09-11 |
Family
ID=49107739
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320008390 Expired - Fee Related CN203190886U (en) | 2013-01-08 | 2013-01-08 | Installation structure for gyro muzzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203190886U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103090722A (en) * | 2013-01-08 | 2013-05-08 | 中国人民解放军海军工程大学 | Installation structure of gyroscope muzzle |
-
2013
- 2013-01-08 CN CN 201320008390 patent/CN203190886U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103090722A (en) * | 2013-01-08 | 2013-05-08 | 中国人民解放军海军工程大学 | Installation structure of gyroscope muzzle |
| CN103090722B (en) * | 2013-01-08 | 2015-03-25 | 中国人民解放军海军工程大学 | Installation structure of gyroscope muzzle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109489692B (en) | Semi-active laser guidance seeker zero adjustment method | |
| CN106705991B (en) | Strapdown is used to group and aims prism installation error test equipment | |
| WO2019007259A1 (en) | Device and method for measuring six-degree-of-freedom displacement of vehicle wheel during suspension characteristic test | |
| CN102927992A (en) | Horizontal one-observation set accuracy testing system of theodolite at extreme temperature | |
| CN105157474A (en) | Cannon pitching radius measuring method | |
| CN101614503B (en) | Multi-axis detection and correction device for 25 mm self-propelled anti-aircraft gun | |
| CN105444784A (en) | Field calibration device of plumb line displacement system | |
| CN109556459B (en) | Rocket gun inertial navigation north-seeking precision detection system and method | |
| CN109506555A (en) | The measuring device and measurement method of the U-shaped frame bearing hole concentricity of two axis | |
| CN203190886U (en) | Installation structure for gyro muzzle | |
| CN102721392B (en) | Pull-wire type angle measurement system | |
| CN103090722A (en) | Installation structure of gyroscope muzzle | |
| CN108759873A (en) | The measurement method at the pitching error of zero angle of detecting devices peculiar to vessel | |
| CN108645392A (en) | A kind of camera Installation posture calibration method and device | |
| CN101865698A (en) | Method for discriminating error source of angular instrument | |
| CN203928892U (en) | The equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems | |
| CN102087163A (en) | Method and device for leading out direction of turning spindle axis of high-precision swing bench | |
| CN105526950A (en) | Calibration detection device for optical sighting | |
| CN113701562B (en) | Gun adjustment precision detection system and detection method thereof | |
| CN201731875U (en) | Device of inclinometer for testing azimuth angle of fiber optic gyroscope | |
| CN202885836U (en) | Theodolite level one circle measurement precision testing system under extreme temperature condition | |
| CN109900156B (en) | Target correction data acquisition system and aerogun target correction method | |
| CN205449099U (en) | Automatic anping surveyor's level compensating error of compensator detecting system | |
| CN103398679B (en) | A kind of horizontal glass alignment instrument, and using method thereof | |
| CN110313237B (en) | The calibration apparatus of airplane inertial navigation device installation position based on gyroscope north searching instrument |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130911 Termination date: 20160108 |