CN103076331B - A kind of wiring method of composites gas cylinder monitoring optical fiber - Google Patents

Abstract

The present invention relates to the wiring method of a kind of composites gas cylinder monitoring optical fiber, comprising: step (1), gas cylinder inside lining filling is stuck on numerical control winding machine main shaft, (2), optical fiber is arranged at gas cylinder inner lining surface, (3), the Wrapping formed and solidification of gas cylinder composite layer, (4), hydraulic pressure self-tightening is tested, the present invention is according to the design feature of column composites gas cylinder, the geodesic line of analog composite material cylinder or Non-geodesic winding Alignment Design planning mode, adopt the optical fiber wiring method of geodesic line or the non-geodesic curve changing wiring direction gradually first, achieve the stress of any angular orientation, strain, the measuring optical fiber gradual change track wiring of temperature, Wrapping formed at gas cylinder after avoiding Fibre Optical Sensor to implant, in gas cylinder solidification process and hydraulic testing process, cause optical fiber to damage because there is larger stress difference between winding layer fiber and optical fiber to lose efficacy, substantially increase the survival rate that optical fiber is implanted at gas cylinder interlayer.

Description

A kind of wiring method of composites gas cylinder monitoring optical fiber

Technical field

The present invention relates to the wiring method of a kind of composites gas cylinder monitoring optical fiber, belong to composite material process planning technical field.

Background technology

For the requirement of aerospacecraft engine system by composite material pressure container Service Environment: weight, helium leak rate, pressure, reusable number of times, volume, displacement, clean cavity degree, assembly precision etc., be necessary to adopt helium leak test technology, acoustic emission, high-precision deformation measuring technique, optical fiber health monitoring technique etc., set up a set of meet that aerospacecraft Service Environment requires containing super thin metal inner lining lightweight composite material pressure container use limits method, for the engineer applied of super thin metal inner lining lightweight composite material pressure container provides relevant supporting technology, ensure its reliability applied on aerospacecraft and security.

Traditional nondestructiving detecting means as Ultrasonic Detection, ray detection can only be passive, static certain detection is carried out to material, acoustic emission can carry out carrying out dynamic monitoring in gas cylinder hydraulic pressure reception test, but has certain limitation.Optical fiber sensing technology is in recent years along with a kind of brand-new monitoring means that smart material and structure rises in the widespread use of all trades and professions.By Fibre Optical Sensor being pasted onto gas cylinder surface or imbedding in material, the procedure parameters such as temperature in solidification process, strain, degree of cure can be monitored, the important information of relation product quality is provided; The parameters such as the temperature of gas cylinder in process of the test, strain can be monitored; The Service Environment temperature etc. of gas cylinder can be monitored.

Current domestic Duo Jia unit has carried out correlative study work in optical fiber health monitoring field, but, Fibre Optical Sensor is also at the experimental stage at present to the health monitoring technique of composites gas cylinder, the Problem of Failure of fiber grating in observation process is serious, optical fiber survival rate is lower, have and lost efficacy in the fabrication process close to half optical fiber, affect the coverage rate of test monitoring, therefore the aspect such as optimization, performance monitoring evaluation of Fibre Optical Sensor arrangement also needs further further investigation.

Summary of the invention

The object of the invention is to the above-mentioned deficiency overcoming prior art, a kind of composites gas cylinder is provided to monitor the wiring method of optical fiber, the method substantially reduces that Fibre Optical Sensor is Wrapping formed at implantation process, gas cylinder, crash rate in gas cylinder solidification process, improves the technology stability of optical fiber wiring and the coverage rate of Fibre Optical Sensor monitoring.

Above-mentioned purpose of the present invention is mainly achieved by following technical solution:

A wiring method for composites gas cylinder monitoring optical fiber, comprises the steps:

(1), gas cylinder inside lining filling is stuck on numerical control winding machine main shaft;

(2), will be connected with the fiber arrangement of Fibre Optical Sensor at gas cylinder inner lining surface, and be adhesively fixed with gas cylinder inner lining surface, wherein optical fiber is determined according to following formula at the angle of lay α of gas cylinder inner lining surface:

$\sin \mathrm{\α}=\frac{r_0}{r}$

Wherein: α is the angle of optical fiber and end socket curved surface upper branch of meridian;

R ₀for end socket pole hole circle radius,

R is optical fiber and end socket curved surface upper branch of meridian point of intersection parallel circle radius;

(3), carry out the Wrapping formed of gas cylinder composite layer, in an oven heating cure is carried out to gas cylinder composite layer afterwards;

(4), by the composites gas cylinder after solidification carry out hydraulic pressure self-tightening, gas cylinder liner and gas cylinder composite layer are fitted tightly.

A wiring method for composites gas cylinder monitoring optical fiber, comprises the steps:

(1), gas cylinder inside lining filling is stuck on numerical control winding machine main shaft;

(2), will be connected with the fiber arrangement of Fibre Optical Sensor at gas cylinder inner lining surface, and be adhesively fixed with gas cylinder inner lining surface, wherein optical fiber is determined according to following formula at the angle of lay α ' of gas cylinder inner lining surface:

$\begin{array}{c}\frac{\mathrm{d\φ}}{\mathrm{dz}}=\frac{-\tan {\mathrm{\α}}^{\′}\sqrt{1+{\left(R^{\′}\left(z\right)\right)}^2}}{R\left(z\right)}\\ \frac{d{\mathrm{\α}}^{\′}}{\mathrm{dz}}=\frac{\mathrm{\λ}[(1+{\left(R^{\′}\left(z\right)\right)}^2){\sin }^2{\mathrm{\α}}^{\′}-R\left(z\right)R^{\′\′}\left(z\right){\cos }^2{\mathrm{\α}}^{\′}}{R\left(z\right)(1+{\left(R^{\′}\left(z\right)\right)}^2)\cos {\mathrm{\α}}^{\′}}]-\frac{(1+{\left(R^{\′}\left(z\right)\right)}^2)R^{\′}\left(z\right)\sin {\mathrm{\α}}^{\′}}{R\left(z\right)(1+{\left(R^{\′}\left(z\right)\right)}^2){\mathrm{\α}}^{\′}}\end{array}$

Set up three-dimensional cartesian coordinate system OXYZ, Z axis is revolving shaft, and according to right-hand rule determination X-axis and Y-axis, then solid of revolution surface equation is:

$\stackrel{\→}{r}(z,)=\{R\left(z\right)\cos \mathrm{\φ},R\left(z\right)\sin \mathrm{\φ},z\}$ ；

Wherein: z is the bent line coordinate of warp direction;

R (z) is solid of revolution bus equation;

Angle parameter centered by φ;

λ is slip coefficient;

(3), carry out the Wrapping formed of gas cylinder composite layer, in an oven heating cure is carried out to gas cylinder composite layer afterwards;

(4), by the composites gas cylinder after solidification carry out hydraulic pressure self-tightening, gas cylinder liner and gas cylinder composite layer are fitted tightly.

In the wiring method of above-mentioned composites gas cylinder monitoring optical fiber, in step (2), optical fiber is in the wiring of gas cylinder inner lining surface, can realize optical fiber to the ess-strain of any direction between gas cylinder liner and composite layer and the monitoring of temperature variation.

In the wiring method of above-mentioned composites gas cylinder monitoring optical fiber, in step (2), optical fiber is in the wiring of gas cylinder inner lining surface, and two line ends of optical fiber stretch out from two of gas cylinder liner ports respectively, or stretches out from a port of gas cylinder liner simultaneously.

In the wiring method of above-mentioned composites gas cylinder monitoring optical fiber, when two line ends of optical fiber stretch out from two of gas cylinder liner ports respectively, optical fiber is symmetric relative to the central point of gas cylinder liner in the wiring of gas cylinder inner lining surface.

In the wiring method of above-mentioned composites gas cylinder monitoring optical fiber, in step (2), optical fiber adopts spiralling wire laying mode in the port of gas cylinder liner.

In the wiring method of above-mentioned composites gas cylinder monitoring optical fiber, gas cylinder composite layer is carbon fiber, glass fibre or aramid fiber.

In the wiring method of above-mentioned composites gas cylinder monitoring optical fiber, gas cylinder liner is metal material, can be aluminium alloy, titanium alloy or stainless steel.

The present invention compared with prior art has following beneficial effect:

(1), the present invention is according to the design feature of column composites gas cylinder, the geodesic line of analog composite material cylinder or Non-geodesic winding Alignment Design planning mode, adopt the optical fiber wiring method of geodesic line or the non-geodesic curve changing wiring direction gradually first, achieve the stress of any angular orientation, strain, the measuring optical fiber gradual change track wiring of temperature, Wrapping formed at gas cylinder after avoiding Fibre Optical Sensor to implant, in gas cylinder solidification process and hydraulic testing process, cause optical fiber to damage because there is larger stress difference between winding layer fiber and optical fiber to lose efficacy, substantially increase the survival rate that optical fiber is implanted at gas cylinder interlayer,

(2), the present invention is because composites gas cylinder many employings high strength, high modulus fibre are as composite layer reinforcing material, its breaking strain is far below the breaking strain of fiber-optic signal conductive glass fiber, therefore when intracellular signaling optical fiber and high strength, high modulus fibre keep close linear track, can ensure under same strain condition, composite layer preferential destruction, optical fiber can not be destroyed, ensure that optical fiber is in the survival rate manufactured and in process of the test, make it can destroy in overall process in the explosion of gas cylinder composite layer and monitor;

(3), the present invention adopts the wire laying mode of geodesic line or non-geodesic curve due to optical fiber, avoiding partially laterally shearing force concentrates the optical fiber caused to lose efficacy, thus ensure that the coverage rate that Fibre Optical Sensor is monitored, test proves that the optical fiber survival rate of the optical fiber wiring adopting the inventive method to carry out rises to more than 80% by existing 50%, substantially increases the technology stability of optical fiber wiring.

Accompanying drawing explanation

Fig. 1 is the composites gas cylinder structural representation of the pre-buried optical fiber of the present invention;

Fig. 2 is geodesic line track schematic diagram;

Fig. 3 is space of the present invention solid of revolution curved surface schematic diagram;

Fig. 4 a is the single-ended wire laying mode front view of gas cylinder hoop optical fiber of the present invention;

Fig. 4 b is the single-ended wire laying mode side view of gas cylinder hoop optical fiber of the present invention;

Fig. 5 a is the single-ended wire laying mode front view of gas cylinder axial optical fiber of the present invention;

Fig. 5 b is the single-ended wire laying mode side view of gas cylinder axial optical fiber of the present invention;

Fig. 6 is the wiring method process flow diagram of composites gas cylinder of the present invention monitoring optical fiber.

Embodiment

Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail:

Be illustrated in figure 1 the composites gas cylinder structural representation of the pre-buried optical fiber of the present invention, composites gas cylinder is generally column construction, be made up of gas cylinder liner 1 and the coated composite layer 4 of outside surface, the wiring of composites gas cylinder monitoring optical fiber 2 is implanted between composite layer 4 and gas cylinder liner 1.Interlayer is implanted gas cylinder monitoring optical fiber 2 and is made up of Fibre Optical Sensor and signal transmission fiber two parts.Wherein, Fibre Optical Sensor is used for measuring, and signal transmission fiber is used for signal conveying.But because signal transmission fiber is in implantation process, wire laying mode is unreasonable is easily causing stress to concentrate in local, causing that optical fiber is Wrapping formed at gas cylinder, stress is too high and lost efficacy in gas cylinder solidification process and hydraulic testing process.

The geodesic line of analog composite material cylinder of the present invention or Non-geodesic winding Alignment Design planning mode, adopt the optical fiber wiring method of geodesic line or the non-geodesic curve changing wiring direction gradually first, achieve the measuring optical fiber gradual change track wiring of the stress of any angular orientation, strain, temperature, cause optical fiber to damage because there is larger stress difference between winding layer fiber and optical fiber in, gas cylinder solidification process Wrapping formed at gas cylinder and hydraulic testing process after avoiding Fibre Optical Sensor to implant to lose efficacy, and substantially increased the survival rate that optical fiber is implanted at gas cylinder interlayer.The wiring method of composites gas cylinder monitoring optical fiber of the present invention is specific as follows:

Step one, gas cylinder liner detect qualified after, with clamping tooling just gas cylinder liner 1 be installed on numerical control winding machine main shaft.

Step 2, the optical fiber 2 being connected with Fibre Optical Sensor is arranged in gas cylinder liner 1 surface, and be adhesively fixed with gas cylinder liner 1 surface, wherein the angle of lay α of optical fiber 2 on gas cylinder liner 1 surface determines (adopt geodesic line mode to connect up, be illustrated in figure 2 geodesic line track schematic diagram) according to following formula:

$\sin \mathrm{\α}=\frac{r_0}{r}---\left(1\right)$

Wherein: α is the angle of optical fiber 2 and end socket 3 curved surface upper branch of meridian;

R ₀for end socket 3 pole hole circle radius,

R is optical fiber 2 and end socket 3 curved surface upper branch of meridian point of intersection parallel circle radius.

In addition the wiring method of composites gas cylinder monitoring optical fiber also can be non-geodesic curve method, be illustrated in figure 3 space of the present invention solid of revolution curved surface schematic diagram, revolving shaft is the Z axis of three-dimensional cartesian coordinate system, sets up three-dimensional cartesian coordinate system according to the right-hand rule, then solid of revolution surface equation is:

$\stackrel{\→}{r}(z,)=\{R\left(z\right)\cos \mathrm{\φ},R\left(z\right)\sin \mathrm{\φ},z\}---\left(2\right)$

Wherein: z is the bent line coordinate of warp direction;

R (z) is solid of revolution bus equation;

φ is the central angle parameter of parametric equation;

The angle of lay α ' of optical fiber 2 on gas cylinder liner 1 surface determines according to following formula (3):

$\begin{array}{c}\frac{\mathrm{d\φ}}{\mathrm{dz}}=\frac{-\tan {\mathrm{\α}}^{\′}\sqrt{1+{\left(R^{\′}\left(z\right)\right)}^2}}{R\left(z\right)}\\ \frac{d{\mathrm{\α}}^{\′}}{\mathrm{dz}}=\frac{[(1+{\left(R^{\′}\left(z\right)\right)}^2){\sin }^2{\mathrm{\α}}^{\′}-R\left(z\right)R^{\′\′}\left(z\right){\cos }^2{\mathrm{\α}}^{\′}}{R\left(z\right)(1+{\left(R^{\′}\left(z\right)\right)}^2)\cos {\mathrm{\α}}^{\′}}]-\frac{(1+{\left(R^{\′}\left(z\right)\right)}^2)R^{\′}\left(z\right)\sin {\mathrm{\α}}^{\′}}{R\left(z\right)(1+{\left(R^{\′}\left(z\right)\right)}^2){\mathrm{\α}}^{\′}}\end{array}---\left(3\right)$

Wherein: λ is slip coefficient;

α ' is winding angle.

Step 3, carry out the Wrapping formed of gas cylinder composite layer 4, namely according to the ply stacking-sequence determined, winding tension, speed of wrap etc., utilize fiber winding machine, carry out the Wrapping formed of each laying of composites gas cylinder successively, in an oven heating cure is carried out to gas cylinder composite layer 4 afterwards.

The winding, molding method of each laying of composites gas cylinder comprises geodesic line mode or non-geodesic curve mode, and two kinds of modes can be used alone or cross-reference in Wrapping formed process, and wherein the detailed process of geodesic line mode is as follows:

Compound substance is at the winding angle α on gas cylinder liner 1 surface ₁determine according to following formula:

$\sin {\mathrm{\α}}_1=\frac{r_0}{r_1}---\left(4\right)$

Wherein: α ₁for geodesic line and end socket curved surface upper branch of meridian angle;

R ₀for end socket pole hole circle radius;

R ₁for geodesic line and meridian point of intersection parallel circle radius.

The detailed process of the Wrapping formed employing non-geodesic curve mode of each laying of composites gas cylinder is as follows:

As shown in Figure 3, revolving shaft is the Z axis of three-dimensional cartesian coordinate system, sets up three-dimensional cartesian coordinate system according to the right-hand rule, then solid of revolution surface equation is formula (2).

Compound substance is at the winding angle α on gas cylinder liner 1 surface ₂determine according to following formula:

$\begin{array}{c}\frac{\mathrm{d\φ}}{\mathrm{dz}}=\frac{-\tan {\mathrm{\α}}_2\sqrt{1+{\left(R^{\′}\left(z\right)\right)}^2}}{R\left(z\right)}\\ \frac{d{\mathrm{\α}}_2}{\mathrm{dz}}=\frac{\mathrm{\λ}[(1+{\left(R^{\′}\left(z\right)\right)}^2){\sin }^2{\mathrm{\α}}_2-R\left(z\right)R^{\′\′}\left(z\right){\cos }^2{\mathrm{\α}}_2]}{R\left(z\right)(1+{\left(R^{\′}\left(z\right)\right)}^2)\cos {\mathrm{\α}}_2}-\frac{(1+{\left(R^{\′}\left(z\right)\right)}^2)R^{\′}\left(z\right)\sin {\mathrm{\α}}_2}{R\left(z\right)(1+{\left(R^{\′}\left(z\right)\right)}^2)\cos {\mathrm{\α}}_2}\end{array}---\left(5\right)$

Wherein: λ slip coefficient;

α ₂for winding angle.

Step 4, the composites gas cylinder after solidification is carried out the test of hydraulic pressure self-tightening, gas cylinder liner 1 and gas cylinder composite layer 4 are fitted tightly.

Step 5, afterwards employing fiber-optic monitoring gas cylinder ess-strain in use and the situation of change of temperature.

Be illustrated in figure 6 the wiring method process flow diagram of composites gas cylinder of the present invention monitoring optical fiber.In the wiring method of optical fiber of the present invention, two line ends of optical fiber 2 stretch out from two of gas cylinder liner 1 ports respectively, or stretch out from a port of gas cylinder liner 1 simultaneously.When two line ends of optical fiber 2 stretch out from two of gas cylinder liner 1 ports respectively, optical fiber 2 is symmetric relative to the central point of gas cylinder liner 1 in the wiring on gas cylinder liner 1 surface.And optical fiber 2 adopts spiralling wire laying mode at port 5 place of gas cylinder liner 1.As shown in Fig. 4 a and Fig. 5 a.

In the present invention, gas cylinder composite layer 4 is carbon fiber, glass fibre or aramid fiber.Gas cylinder liner 1 is metal material, can be aluminium alloy, titanium alloy or stainless steel.

The single-ended wire laying mode front view of gas cylinder hoop optical fiber of the present invention as shown in Figure 4 a, Fig. 4 b is depicted as the single-ended wire laying mode side view of gas cylinder hoop optical fiber of the present invention, gas cylinder composite layer 4 is carbon fiber in the present embodiment, gas cylinder liner 1 is aluminium alloy, optical fiber 2 adopts non-geodesic curve mode to connect up, for hoop wire laying mode, two line ends of optical fiber 2 stretch out from two of gas cylinder liner 1 ports respectively, only give the wiring diagram of optical fiber one end in figure, optical fiber 2 is symmetric relative to the central point of gas cylinder liner 1 in the wiring on gas cylinder liner 1 surface.And optical fiber 2 adopts spiralling wire laying mode at port 5 place of gas cylinder liner 1.

Be the single-ended wire laying mode front view of gas cylinder axial optical fiber of the present invention as shown in Figure 5 a, Fig. 5 b is the single-ended wire laying mode side view of gas cylinder axial optical fiber of the present invention, gas cylinder composite layer 4 is carbon fiber in the present embodiment, gas cylinder liner 1 is titanium alloy, optical fiber 2 adopts geodesic line mode to connect up in end socket region 3, adopt non-geodesic curve mode to connect up in all the other regions, for axial wire laying mode, two line ends of optical fiber 2 stretch out from two of gas cylinder liner 1 ports respectively, the wiring diagram of optical fiber one end is only gived in figure, optical fiber 2 is symmetric relative to the central point of gas cylinder liner 1 in the wiring on gas cylinder liner 1 surface.And optical fiber 2 adopts spiralling wire laying mode at port 5 place of gas cylinder liner 1.

Except above-mentioned two kinds of modes, the present invention can realize the measuring optical fiber gradual change track wiring of the stress of any angular orientation, strain and temperature.

The above; be only the embodiment of the best of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.

The content be not described in detail in instructions of the present invention belongs to the known technology of professional and technical personnel in the field.

Claims (7)

1. a wiring method for composites gas cylinder monitoring optical fiber, is characterized in that comprising the steps:

(1), gas cylinder liner (1) is installed on numerical control winding machine main shaft;

(2), the optical fiber (2) being connected with Fibre Optical Sensor is arranged in gas cylinder liner (1) surface, and be adhesively fixed with gas cylinder liner (1) surface, wherein optical fiber (2) is determined according to following formula at the angle of lay α on gas cylinder liner (1) surface:

$\sin \mathrm{\α}=\frac{r_0}{r}$

Wherein: α is the angle of optical fiber (2) and end socket (3) curved surface upper branch of meridian;

R ₀for end socket (3) pole hole circle radius,

R is optical fiber (2) and end socket (3) curved surface upper branch of meridian point of intersection parallel circle radius;

Wherein optical fiber (2) is in the wiring on gas cylinder liner (1) surface, two line ends of optical fiber (2) stretch out from two ports (5) of gas cylinder liner (1) respectively, or stretch out from a port (5) of gas cylinder liner (1) simultaneously;

(3), carry out the Wrapping formed of gas cylinder composite layer (4), in an oven heating cure is carried out to gas cylinder composite layer (4) afterwards;

(4), by the composites gas cylinder after solidification carry out hydraulic pressure self-tightening, gas cylinder liner (1) and gas cylinder composite layer (4) are fitted tightly.

2. a wiring method for composites gas cylinder monitoring optical fiber, is characterized in that comprising the steps:

(1), gas cylinder liner (1) is installed on numerical control winding machine main shaft;

(2), the optical fiber (2) being connected with Fibre Optical Sensor is arranged in gas cylinder liner (1) surface, and be adhesively fixed with gas cylinder liner (1) surface, wherein optical fiber (2) is determined according to following formula at the angle of lay α ' on gas cylinder liner (1) surface:

$\frac{\mathrm{d\φ}}{\mathrm{dz}}=\frac{-\tan {\mathrm{\α}}^{\′}\sqrt{1+{\left(R^{\′}\left(z\right)\right)}^2}}{R\left(z\right)}$

$\frac{d{\mathrm{\α}}^{\′}}{\mathrm{dz}}=\frac{\mathrm{\λ}[(1+{\left(R^{\′}\left(z\right)\right)}^2){\sin }^2{\mathrm{\α}}^{\′}-R\left(z\right)R^{\′\′}\left(z\right){\cos }^2{\mathrm{\α}}^{\′}]}{R\left(z\right)(1+{\left(R^{\′}\left(z\right)\right)}^2)\cos {\mathrm{\α}}^{\′}}-\frac{(1+{\left(R^{\′}\left(z\right)\right)}^2)R^{\′}\left(z\right)\sin {\mathrm{\α}}^{\′}}{R\left(z\right)(1+{\left(R^{\′}\left(z\right)\right)}^2)\cos {\mathrm{\α}}^{\′}}$

Wherein: α ' is winding angle;

Set up three-dimensional cartesian coordinate system OXYZ, Z axis is revolving shaft, and according to right-hand rule determination X-axis and Y-axis, then solid of revolution surface equation is:

$\stackrel{\→}{r}(z,\mathrm{\φ})=\{R\left(z\right)\cos \mathrm{\φ},R\left(z\right)\sin \mathrm{\φ},z\};$

Wherein: z is the bent line coordinate of warp direction;

R (z) is solid of revolution bus equation;

Angle parameter centered by φ;

λ is slip coefficient;

Wherein optical fiber (2) is in the wiring on gas cylinder liner (1) surface, two line ends of optical fiber (2) stretch out from two ports (5) of gas cylinder liner (1) respectively, or stretch out from a port (5) of gas cylinder liner (1) simultaneously;

(3), carry out the Wrapping formed of gas cylinder composite layer (4), in an oven heating cure is carried out to gas cylinder composite layer (4) afterwards;

(4), by the composites gas cylinder after solidification carry out hydraulic pressure self-tightening, gas cylinder liner (1) and gas cylinder composite layer (4) are fitted tightly.

3. the wiring method of a kind of composites gas cylinder monitoring optical fiber according to claim 1 and 2, it is characterized in that: in described step (2), optical fiber (2) is in the wiring on gas cylinder liner (1) surface, can realize optical fiber (2) to the ess-strain of any direction and the monitoring of temperature variation between gas cylinder liner (1) and composite layer (4).

4. the wiring method of a kind of composites gas cylinder monitoring optical fiber according to claim 1 and 2, it is characterized in that: when two line ends of described optical fiber (2) stretch out from two ports of gas cylinder liner (1) respectively, optical fiber (2) is symmetric relative to the central point of gas cylinder liner (1) in the wiring on gas cylinder liner (1) surface.

5. the wiring method of a kind of composites gas cylinder monitoring optical fiber according to claim 1 and 2, is characterized in that: in described step (2), optical fiber (2) adopts spiralling wire laying mode at port (5) place of gas cylinder liner (1).

6. the wiring method of a kind of composites gas cylinder monitoring optical fiber according to claim 1 and 2, is characterized in that: described gas cylinder composite layer (4) is carbon fiber, glass fibre or aramid fiber.

7. the wiring method of a kind of composites gas cylinder monitoring optical fiber according to claim 1 and 2, is characterized in that: described gas cylinder liner (1) is metal material, is specially aluminium alloy, titanium alloy or stainless steel.