CN109737825A - Guided missile rudder face mechanical zero and electrical null position while calibration tool and application method - Google Patents
Guided missile rudder face mechanical zero and electrical null position while calibration tool and application method Download PDFInfo
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- CN109737825A CN109737825A CN201910081364.XA CN201910081364A CN109737825A CN 109737825 A CN109737825 A CN 109737825A CN 201910081364 A CN201910081364 A CN 201910081364A CN 109737825 A CN109737825 A CN 109737825A
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- rudder
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- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000003780 insertion Methods 0.000 claims abstract 3
- 230000037431 insertion Effects 0.000 claims abstract 3
- 239000007787 solid Substances 0.000 claims description 2
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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Abstract
The invention discloses guided missile rudder face mechanical zero and electrical null position while calibration tool and application methods, several fixing grooves to match with rudder piece are offered on calibration tool of the invention, when in rudder piece insertion fixing groove, rudder piece is in mechanical zero, the present apparatus can the mechanical zero to rudder piece quickly positioned, and rudder pieces all on steering engine can once be positioned, be greatly improved work efficiency.
Description
Technical field
The invention belongs to guided missile fields, and in particular to a kind of guided missile rudder face mechanical zero and electrical null position calibration tool simultaneously
And application method.
Background technique
Missile flight be it is controllable, existing guided missile is typically all four rudder faces, is controlled by the steering engine in bullet.Steering engine dress
Timing can generate error, and the zero-bit of mechanical zero and potentiometer has an angular deviation.After directly shooting in this way, rudder face is mechanical
Zero-bit in zero-bit and software is not overlapped, and needs to use after matching two zero-bits.Typically used before shooting
Tooling finds out the mechanical zero of steering engine, then checks potentiometer parameter and records, the electricity set this parameter in software
Gas zero-bit.However the zeroing of each steering engine obtains and passes through two steps of machine zero and electronic zero-setting, every hair bullet has multiple steering engines,
So the relatively time consuming consumption benefit of zeroing.And the steering engine after zeroing has rigging error and generates when being again loaded into guided missile, directly
Steering engine zero-bit is caused also and then to generate error.
Summary of the invention
The purpose of the present invention is to overcome the above shortcomings and to provide a kind of guided missile rudder face mechanical zero and electrical null position while schools
Quasi- tooling and application method can quickly and effectively position steering engine, reduce because zero-bit caused by secondary assembly is missed
Difference.
In order to achieve the above object, guided missile rudder face mechanical zero and electrical null position calibration tool, including ring body simultaneously,
Several fixing grooves to match with rudder piece are offered in the axial direction of ring body, when rudder piece is inserted into fixing groove, rudder piece is in machine
Tool zero-bit.
When rudder piece is inserted into fixing groove, the wall surface of the two sides of rudder piece and two inner walls of fixing groove are in close contact.
There are four fixing groove tools.
Adjacent fixing groove is equiangularly arranged on ring body.
The application method of guided missile rudder face mechanical zero and electrical null position while calibration tool, comprising the following steps:
Step 1, by steering engine and the assembly of rudder piece on playing wall；
Rudder piece is inserted into the fixing groove on ring body by step 2, guarantees that rudder piece is in mechanical zero；
Step 3, the bullet wall position locating for the leading edge vertex of each rudder piece are marked, and make the rudder piece zero-bit of rudder piece
Label；
Step 4 removes calibration tool；
Step 5 is overlapped rudder piece leading edge vertex with rudder piece zero mark, at this moment each rudder by being finely adjusted to steering engine
The angle parameter of machine is the electrical null position of each steering engine.
In step 2, when rudder piece is inserted into the fixing groove on calibration tool, two of the wall surfaces of the two sides of rudder piece and fixing groove
Inner wall is in close contact.
Compared with prior art, several fixing grooves to match with rudder piece are offered on calibration tool of the invention, in rudder
When piece is inserted into fixing groove, rudder piece is in mechanical zero, the present apparatus can the mechanical zero to rudder piece quickly positioned, and
Rudder pieces all on steering engine can once be positioned, be greatly improved work efficiency.
Further, the wall surface of the two sides of rudder piece of the invention and two inner walls of fixing groove are in close contact, and can be made solid
Determine slot and position-limiting action is risen to rudder piece, improves the precision of the present apparatus.
Application method of the invention is that calibration tool is fixed on to rudder on piece, guarantees that rudder piece is in mechanical zero, then make rudder
Piece zero mark after removing tooling, by being finely adjusted to steering engine, is overlapped rudder piece leading edge vertex with rudder piece zero mark, this
When each steering engine angle parameter be each steering engine electrical null position.This method first assembles steering engine and returns to zero again, can be avoided because
Generated error is assembled for steering engine.
Detailed description of the invention
Fig. 1 uses schematic diagram for alignment tooling of the present invention；
Fig. 2 is the structural schematic diagram of alignment tooling of the present invention；
Wherein, 1- ring body, 2- rudder piece, 3- bullet wall, 4- rudder piece zero mark, 5- fixing groove.
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
Referring to Fig. 1 and Fig. 2, guided missile rudder face mechanical zero and electrical null position calibration tool, including ring body 1 simultaneously, ring
Several fixing grooves 5 to match with rudder piece 2 are offered in the axial direction of shape ontology 1, when rudder piece 2 is inserted into fixing groove 5, at rudder piece 2
In mechanical zero, when rudder piece 2 is inserted into fixing groove 5, the wall surface of the two sides of rudder piece 2 and two inner walls of fixing groove 5 are in close contact.
Preferably, adjacent fixing groove 5 is equiangularly arranged on ring body 1.
Referring to Fig. 1 and Fig. 2, the application method of guided missile rudder face mechanical zero and electrical null position while calibration tool, including with
Lower step:
Step 1, by steering engine and the assembly of rudder piece 2 on playing wall 3；
Calibration tool is inserted in by step 2 from missile tail, rudder piece 2 is inserted into the fixing groove 5 on calibration tool, rudder piece
The wall surface of 2 two sides and two inner walls of fixing groove 5 are in close contact, and guarantee that rudder piece 2 is in mechanical zero；
Step 3,3 position of bullet wall locating for the leading edge vertex of each rudder piece 2 are marked, and make the rudder piece zero of rudder piece 2
Position label 4；
Step 4 removes calibration tool；
Step 5 is overlapped 2 leading edge vertex of rudder piece with rudder piece zero mark 4 by being finely adjusted to steering engine, at this moment each
The angle parameter of steering engine is the electrical null position of each steering engine.
Embodiment:
There are four the tools of fixing groove 5 on calibration tool of the invention.When installation, calibration tool is inserted in from missile tail,
Rudder piece 2 is blocked with four fixing grooves 5 on calibration tool, the wall surface of 2 two sides of side wall and rudder piece of fixing groove fits closely, and protects
Card rudder piece 2 is in mechanical zero.3 position of bullet wall locating for each 2 leading edge vertex of rudder piece is marked, and makes the rudder of rudder piece 2
Piece zero mark 4.Then calibration tool is removed.It powers to flight control system, rudder piece 2 can deviate zero-bit, pass through guided missile flying-controlled box
Control steering engine is finely adjusted rudder piece 2, is overlapped 2 leading edge vertex of rudder piece and rudder piece zero mark 4 and returns to zero-bit, at this moment guided missile flies
Control software supervision to each steering engine angle parameter be exactly each steering engine electrical null position.Then it is done in guided missile flying-controlled box
Adjustment can be completed while calibrate to mechanical zero and electrical null position out.
Claims (6)
1. guided missile rudder face mechanical zero and electrical null position while calibration tool, which is characterized in that including ring body (1), annular
Several fixing grooves (5) to match with rudder piece (2) are offered in the axial direction of ontology (1), when rudder piece (2) insertion fixing groove (5) is interior,
Rudder piece (2) is in mechanical zero.
2. guided missile rudder face mechanical zero according to claim 1 and electrical null position while calibration tool, which is characterized in that rudder
When piece (2) insertion fixing groove (5) is interior, the wall surface of the two sides of rudder piece (2) and two inner walls of fixing groove (5) are in close contact.
3. guided missile rudder face mechanical zero according to claim 1 and electrical null position while calibration tool, which is characterized in that Gu
Determine there are four slot (5) tools.
4. guided missile rudder face mechanical zero according to claim 1 and electrical null position while calibration tool, which is characterized in that phase
Adjacent fixing groove (5) is equiangularly arranged on ring body (1).
5. the application method of guided missile rudder face mechanical zero described in claim 1 and electrical null position while calibration tool, feature
It is, comprising the following steps:
Steering engine and rudder piece (2) are assemblied in and play on wall (3) by step 1；
Rudder piece (2) are inserted into the fixing groove (5) on ring body (1) by step 2, guarantee that rudder piece (2) are in mechanical zero；
Step 3, bullet wall (3) position locating for the leading edge vertex of each rudder piece (2) are marked, and make the rudder piece of rudder piece (2)
Zero mark (4)；
Step 4 removes calibration tool；
Step 5 is overlapped rudder piece (2) leading edge vertex with rudder piece zero mark (4) by being finely adjusted to steering engine, at this moment each
The angle parameter of steering engine is the electrical null position of each steering engine.
6. the application method of guided missile rudder face mechanical zero according to claim 5 and electrical null position while calibration tool,
It is characterized in that, in step 2, when rudder piece (2) is inserted into fixing groove (5) on calibration tool, the wall surface of the two sides of rudder piece (2) and solid
Two inner walls for determining slot (5) are in close contact.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910081364.XA CN109737825A (en) | 2019-01-28 | 2019-01-28 | Guided missile rudder face mechanical zero and electrical null position while calibration tool and application method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910081364.XA CN109737825A (en) | 2019-01-28 | 2019-01-28 | Guided missile rudder face mechanical zero and electrical null position while calibration tool and application method |
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| Publication Number | Publication Date |
|---|---|
| CN109737825A true CN109737825A (en) | 2019-05-10 |
Family
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| CN201910081364.XA Pending CN109737825A (en) | 2019-01-28 | 2019-01-28 | Guided missile rudder face mechanical zero and electrical null position while calibration tool and application method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115164653A (en) * | 2022-06-30 | 2022-10-11 | 河北汉光重工有限责任公司 | Zero-position combined debugging device and debugging method for rudder sheet |
| CN115200426A (en) * | 2022-06-30 | 2022-10-18 | 河北汉光重工有限责任公司 | Zero-position self-adaptive debugging device and method for rudder sheet |
| CN115235298A (en) * | 2022-06-30 | 2022-10-25 | 河北汉光重工有限责任公司 | Zero debugging tool and debugging method for rudder piece |
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2019
- 2019-01-28 CN CN201910081364.XA patent/CN109737825A/en active Pending
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115164653A (en) * | 2022-06-30 | 2022-10-11 | 河北汉光重工有限责任公司 | Zero-position combined debugging device and debugging method for rudder sheet |
| CN115200426A (en) * | 2022-06-30 | 2022-10-18 | 河北汉光重工有限责任公司 | Zero-position self-adaptive debugging device and method for rudder sheet |
| CN115235298A (en) * | 2022-06-30 | 2022-10-25 | 河北汉光重工有限责任公司 | Zero debugging tool and debugging method for rudder piece |
| CN115235298B (en) * | 2022-06-30 | 2023-12-05 | 河北汉光重工有限责任公司 | Rudder sheet zero debugging tool and debugging method |
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| CN115200426B (en) * | 2022-06-30 | 2024-05-24 | 河北汉光重工有限责任公司 | Rudder sheet zero position self-adaptive debugging device and debugging method |
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Application publication date: 20190510 |
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