CN102176546A - Method for resetting reflecting surface of antenna based on laser tracker - Google Patents

Abstract

The invention discloses a method for resetting a reflecting surface of an antenna based on a laser tracker, comprising the following steps: 1, establishment of a scene resetting coordinate system: searching a benchmark horizontally and vertically and establishing the scene resetting coordinate system by taking the ground level as a benchmark and a design coordinate of the reflecting surface as an original point, wherein the scene resetting coordinate system is coordinated with a scene; 2, adjustment for rough positioning of four points: measuring index points under the scene resetting coordinate system, calculating a first adjusted quantity to adjust the index points and ensuring an adjustment error to be less than or equal to +/-2mm; 3, optimal even gaps at edges: calculating a second adjusted quantity by edge best fit to adjust the edges, and ensuring the error of the index points to be less than or equal to +/-0.5mm and gap widths to be less than or equal to (0.1+/-0.05) lambda; and 4, singly accurate adjustment of molded surfaces for each reflecting surface: calculating a third adjusted quantity to adjust the molded surfaces by limiting the best fit of three-degree-of-freedom molded surfaces, and ensuring an adjustment error to be less than or equal to +/-0.02mm. The method can be utilized to improve the resetting efficiency of the reflecting surface of the antenna, shorten the resetting period and ensure the resetting quality; and in addition, the method is applied to resetting large antennas which are formed by assembling the multiple reflecting surfaces.

Description

Antenna reflective face based on laser tracker is debug method

Technical field

The present invention relates to a kind of method that antenna reflective face is debug, be particularly suitable for debuging by the scene of the assembled large-scale antenna of polylith reflecting surface.

Background technology

Along with the development of the communication technology, advanced radar, survey of deep space, remote sensing and stealth technology, various countries are increasing to the demand of big dead zone, ultrabroad band, millimeter wave large-scale antenna.Reflecting surface, back of the body frame, centerbody and antenna base have constituted the basic structure of large-scale antenna.Antenna-reflected panel adjustment technology is meant and utilizes specific panel adjusting mechanism, changes the locus of aerial panel, makes each target point on it be tending towards corresponding points on the ideally-reflecting face to greatest extent, and the high more reflector precision that shows of convergence degree is high more.Because low cost of manufacture, characteristics such as maintainability is good, present large-scale reflector antenna adopts the polylith reflecting surface assembled mostly, and the antenna reflective face overall precision directly influences its maximum operating frequency simultaneously, becomes the key that guarantees to tighten a quality so reflecting surface detects to debug.

In the volume the 1st phase " marine charting " " application of electronic theodolite multi-theodolite intersection system in the large-scale antenna precision installs and measures " by name disclosed January the 25th in 2005.This system is made up of two to four T3000A electronic theodolites.The control net is made of 6 high measurement piers of 9～16m.Adopt T3000A angle measurement, TC2003 to survey the limit, after the data processing positional accuracy of triangulateration network can reach ± the 0.3mm warp in.The dimensional accuracy that 3 instruments are set up system is better than 10 ^-5Measure in 772 time spent 4h, the intersection precision is better than 0.3mm (RMS).

Large-scale reflector antenna belongs to typical nonstandard single products, and it debugs process is not a simple measurement and an orientation problem, especially the technology based on a cover complexity of reflector antenna being debug each reflecting surface profound understanding.For guaranteeing the final profile precision of reflecting surface, just must formulation reasonably debug technology, in the shortest time shape of entire emission face and ideally-reflecting face are matched as far as possible, could guarantee the electricity function index of antenna like this.

Summary of the invention

The objective of the invention is to propose a kind of antenna reflective face and debug method based on laser tracker, this method is calculated the reflecting surface adjustment amount by nonlinear least square method, by 4 points-edge-profile three phases reflecting surface is adjusted to position with ideally-reflecting face optimum Match successively then.The present invention debugs method and has improved antenna reflective face and debug efficient, shortens and debugs the duration, guarantees to debug quality, is particularly suitable for debuging by the assembled large-scale antenna of polylith reflecting surface.

A kind of antenna reflective face based on laser tracker of the present invention is debug method, and a required laser tracker carries out the index point measurement of coordinates, stores in the computer control system and debugs processing unit, and this method of debuging in the processing unit of debuging includes:

Step 1: set up antenna coordinate system o is installed ^*-x ^*y ^*z ^*Step;

Step 2: regulate the coarse positioning step at 4;

Step 3: best even slit, edge step;

Step 4: monolithic accurate adjustment typing face step.

The advantage that the antenna reflective face that the present invention is based on laser tracker is debug method is:

1. set up laser tracker and debug antenna installation coordinate system o ^*-x ^*y ^*z ^*, make coordinate system o be installed ^*-x ^*y ^*z ^*With earth coordinates o ^w-x ^wy ^wz ^wParallel, coordinate mutually with the antenna general structure design, consistent with reflecting surface design coordinate o-xyz, thereby guarantee the precision measuring and debug.

2. adopt 4 points-three adjusting stages of edge-profile, progressively heighten the adjustment precision, reflecting surface is adjusted to best match position with its design, guarantee continuity and feasibility that adjusting process is implemented.

3. adopt the simplex optimized Algorithm of going down the hill, calculate second stage and phase III adjustment amount, improve and adjust efficient, shorten and debug the duration.

4. in the phase III adjustment process, limit the three degree of freedom that reflecting surface is adjusted, guaranteed the reflection line position precision, and avoided the mutual interference between the reflecting surface, guaranteed the safety and the stability of the process of debuging, guaranteed to debug quality.

5. adopt a laser tracker as measuring equipment, edge, index point and profile to the alignment target point at scene, axial index point and reflecting surface are measured, the measurement range is big, the precision height, simple to operate, and can monitor the coordinate figure of index point in real time, guarantee to debug quality, improve and debug efficient.

Description of drawings

Fig. 1 is that laser tracker of a kind of usefulness of the present invention carries out the structure schematic diagram of antenna reflective face when debuging.

Figure 1A is the flow chart that the present invention debugs processing unit.

Fig. 2 is the graph of a relation that the present invention debugs multi-coordinate in the processing unit.

Fig. 2 A is that the present invention debugs antenna installation coordinate system corner schematic diagram in the processing unit.

Fig. 3 is that NJD2025 tightens a reflecting surface piecemeal and layout.

Fig. 4 is 4 adjustment type surface accuracies of NJD2025-08 figure.

Fig. 5 is NJD2025-08 edge optimum adjustment profile precision figure.

Fig. 6 is NJD2025-08 profile optimum adjustment profile precision figure.

Fig. 7 is that NJD2025 tightens a monolithic devices surface accuracy figure.

Embodiment

The present invention is described in further detail below in conjunction with accompanying drawing and application example.

Referring to shown in Figure 1, in the present invention, form tetragonal index point peg model by first supporting bracket, second supporting bracket, the 3rd supporting bracket and the 4th supporting bracket are end to end.This index point peg model is used to install a plurality of index points.The material of four supporting brackets can be glass plate, plank etc.

In the present invention, applying electronic theodolite (or level meter) carries out adjustment in same horizontal plane (promptly being mapped to the demarcation horizontal plane in the computer control system) face to being arranged on part index point in a plurality of index points on four supporting brackets, remains in the same horizontal plane with four or more the index point at least that guarantees to be arranged on four supporting brackets.

In the present invention, use a laser tracker (can select Leica at901-b for use) coordinate of a plurality of index points on four supporting brackets is measured, measure the period coordinate figure that obtains and be transferred in the computer control system.

In the present invention, computer control system comprises a PC and the processing unit of debuging that is installed in the PC processor; Shown in Figure 1A, debug processing unit and coordinate system o is installed by setting up antenna ^*-x ^*y ^*z ^*Module, 4 adjusting coarse positioning modules, the best even slit module in edge and monolithic accurate adjustment typing face mould pieces constitute; Debug processing unit and adopt vb 6.0 language developments.

PC is a kind ofly can carry out the modernized intelligent electronic device of massive values computation and various information processings automatically, at high speed according to prior program stored.Minimalist configuration is CPU 2GHz, internal memory 2GB, hard disk 40GB; Operating system is windows 2000/2003/XP.

A kind of large-scale antenna reflecting plane assistant resetting method based on laser tracker of the present invention is by approaching, divide three different adjusting stages that reflecting surface is adjusted to position with its ideally-reflecting face optimum Match one by one.

Shown in Figure 1A, a kind of antenna reflective face based on laser tracker of the present invention is debug method, includes to set up antenna installation coordinate system o ^*-x ^*y ^*z ^*Step, 4 adjusting coarse positioning steps, the best even slit step in edge and monolithic accurate adjustment typing face steps.

(1) antenna is installed coordinate system o ^*-x ^*y ^*z ^*Step

Because the installation of reflector antenna generally will be considered installation site relations such as reflecting surface and scanning support, feed, erecting bed, back of the body frame, supporting construction, measurement target, in order to guarantee to debug the accuracy of benchmark, the present invention must set up before adjusting based on the antenna of debuging of laser tracker coordinate system o is installed ^*-x ^*y ^*z ^*, guarantee to install coordinate system o ^*-x ^*y ^*z ^*With earth coordinates o ^w-x ^wy ^wz ^wParallel, coordinate mutually with the antenna general structure design, consistent with reflecting surface design coordinate o-xyz.

Antenna is installed coordinate system o ^*-x ^*y ^*z ^*Foundation include following implementation step:

Step 1-1:(A) around the reflector antenna erecting bed, four supporting brackets are set, and the head and the tail of four supporting brackets is connected to form quadrangle; Then laser tracker is arranged on described tetragonal outside, the coordinate system of described laser tracker is designated as o ^Lt-x ^Lty ^Ltz ^Lt

In the present invention, described quadrangle is mapped to debug and is demarcation horizontal plane (referring to shown in Figure 2) in the processing unit, and four supporting brackets are for demarcating four limits of horizontal plane, be that AB limit and CD limit are the axial direction limit, AB is parallel to CD, and AC limit and BD limit are the horizontal direction limit, and AC is parallel to BD;

(B) the alignment target point is set respectively on four supporting brackets, and in debuging processing unit, writes down period;

In the present invention, the index point of layout on each supporting bracket adopts level meter (or electronic theodolite) to assist layout when mounted, with the alignment target point that guarantees to be provided with on each supporting bracket at same horizontal plane.

(C) measure each period at o according to period with laser tracker ^Lt-x ^Lty ^Ltz ^LtUnder coordinate figure;

Wherein, the coordinate figure of the index point on the AB limit is designated as Q (x _Qi, y _Qi, z _Qi) i=1,2 ..., m (abbreviates first group of axial coordinate value Q (x as _Qi, y _Qi, z _Qi) i=1,2 ..., m);

Wherein, the coordinate figure of the index point on the CD limit is designated as R (x _Rj, y _Rj, z _Rj) j=1,2 ..., s (abbreviates second group of axial coordinate value R (x as _Rj, y _Rj, z _Rj) j=1,2 ..., s); M=s wherein, m represents the mark mark (perhaps number) of first group of axial index point (index point on the AB limit), s represents the mark mark (perhaps number) of second group of axial index point (index point on the CD limit);

Wherein, the coordinate figure of the alignment target point on the AC limit is designated as P (x _Pk, y _Pk, z _Pk) k=1,2 ..., n (abbreviates horizontal period coordinate figure P (x as _Pk, y _Pk, z _Pk) k=1,2 ..., n); Owing to four supporting brackets are carried out match according to parallelogram,, only gather the coordinate figure of period on one side when then the alignment target point on these two limits is measured with laser tracker so the BD limit is parallel with the AC limit.N represents the mark mark (perhaps number) of alignment target point (index point on the AC limit).

Referring to shown in Figure 2, the p on the AB limit of demarcation horizontal plane ₁The coordinate of period is p ₁(x ₁, y ₁, z ₁), p _nThe coordinate of period is p _n(x _n, y _n, z _n), p _N-1The coordinate of period is p _N-1(x _N-1, y _N-1, z _N-1); P on the AC limit ₂The coordinate of period is p ₂(x ₂, y ₂, z ₂), p ₃The coordinate of period is p ₃(x ₃, y ₃, z ₃); P on the CD limit ₄The coordinate of period is p ₄(x ₄, y ₄, z ₄), p ₅The coordinate of period is p ₅(x ₅, y ₅, z ₅); P on the DB limit _kThe coordinate of period is p _k(x _k, y _k, z _k).

In the present invention, the laser tracker adjustment is according to the minimum principle of measure error, and the vibrations of laser tracker position are set to less than 0.01mm.

Step 1-2: determine to demarcate coordinate system

(A) adopt the coordinate figure P (x of least square method to obtaining among the step 1-1 _Pk, y _Pk, z _Pk) k=1,2 ..., n carries out match, obtains demarcating horizontal plane A x+By+Cz=0, and this demarcation horizontal plane flatness need reach 00 grade; Wherein, A represents to demarcate in the horizontal plane x method of principal axes to vector, and B represents to demarcate that the y method of principal axes is to vector in the horizontal plane, and C represents to demarcate z method of principal axes vector in the horizontal plane;

(B) extract the vector of demarcating A, B, C among the horizontal plane A x+By+Cz=0, be designated as

Normalization

Promptly obtain earth coordinates o ^w-x ^wy ^wz ^wThe vector of vertical

, promptly

$\stackrel{\→}{N}=(\frac{A}{\sqrt{A^2+B^2+C^2}},\frac{B}{\sqrt{A^2+B^2+C^2}},\frac{C}{\sqrt{A^2+B^2+C^2}});$

(C) with Q (x _Qi, y _Qi, z _Qi) i=1,2 ..., m projects to and demarcates on the horizontal plane A x+By+Cz=0, and the coordinate figure that obtains after the projection is designated as q (x _Qi, y _Qi, z _Qi) i=1,2 ..., m; Adopt least square method to q (x _Qi, y _Qi, z _Qi) i=1,2 ..., m carries out match, and the straight line that obtains the first group echo point is designated as L ₁(being the AB sideline), L ₁Linear equation be expressed as c ₁+ n ₁X+n ₂Y=0;

(D) with R (x _Rj, y _Rj, z _Rj) j=1,2 ..., s projects to and demarcates on the horizontal plane A x+By+Cz=0, and the coordinate figure that obtains after the projection is designated as r (x _Rj, y _Rj, z _Rj) j=1,2 ..., s; Adopt least square method to r (x _Rj, y _Rj, z _Rj) j=1,2 ..., s carries out match, and the straight line that obtains the second group echo point is designated as L ₂(being the CD sideline), L ₂Linear equation be expressed as c ₂+ n ₃X+n ₄Y=0;

In the present invention, c ₁Expression L ₁Constant offset in the linear equation, c ₂Expression L ₂Constant offset in the linear equation, n ₁Expression straight line L ₁At o ^Lt-x ^Lty ^Ltz ^LtThe vector of the x direction under the coordinate system, n ₂Expression straight line L ₁At o ^Lt-x ^Lty ^Ltz ^LtThe vector of the y direction under the coordinate system, n ₃Expression straight line L ₂At o ^Lt-x ^Lty ^Ltz ^LtThe vector of the x direction under the coordinate system, n ₄Expression straight line L ₂At o ^Lt-x ^Lty ^Ltz ^LtThe vector of the y direction under the coordinate system;

Make n ₁=n ₃, n ₂=n ₄, and

So straight line L ₁With straight line L ₂Parallel (L ₁//L ₂); Extract straight line L ₁Direction vector be designated as

(E) will

As demarcating coordinate system o ^Xc-x ^Xcy ^Xcz ^XcMiddle y ^XcThe direction of principal axis vector,

As demarcating coordinate system o ^Xc-x ^Xcy ^Xcz ^XcMiddle z ^XcThe direction of principal axis vector, and with P (x _Pk, y _Pk, z _Pk) k=1,2 ..., certain among the n obtains being presented at the demarcation coordinate system o on the display in the computer control system a bit as initial point according to the right-handed coordinate system rule ^Xc-x ^Xcy ^Xcz ^Xc

Step 1-3: determine antenna installation coordinate system o ^*-x ^*y ^*z ^*

To demarcate coordinate system o ^Xc-x ^Xcy ^Xcz ^Xcformerly press side-play amount { Δ z} translation obtain antenna coordinate system o is installed for Δ x, Δ y ^*-x ^*y ^*z ^*In, wherein

$\mathrm{\Δx}=\frac{1}{t}(\underset{a=1}{\overset{t}{\mathrm{\Σ}}}{x_a}^{\mathrm{xc}}-\underset{a=1}{\overset{t}{\mathrm{\Σ}}}{x}_a^{\′})$

$\mathrm{\Δy}=\frac{1}{t}(\underset{a=1}{\overset{t}{\mathrm{\Σ}}}{y}_a-\underset{a=1}{\overset{t}{\mathrm{\Σ}}}{y}_a^{\′})$

$\mathrm{\Δz}=\frac{1}{t}(\underset{a=1}{\overset{t}{\mathrm{\Σ}}}{z}_a-\underset{a=1}{\overset{t}{\mathrm{\Σ}}}{z}_a^{\′})$

Indicator sign point is being demarcated coordinate system o ^Xc-x ^Xcy ^Xcz ^XcUnder the measurement coordinate figure;

(x ' _a, y ' _a, z ' _a), a=1,2 ... the coordinate figure of t indicator sign point under theory design coordinate system o '-x ' y ' z ';

The number of t indicator sign point.

Regulate coarse positioning step (being to adjust the phase I) at (two) four

Determined antenna installation coordinate system o ^*-x ^*y ^*z ^*After, whole V piece antenna reflective faces are mounted on the supporting construction, this moment, the reflection line position error ratio was bigger;

In the present invention, distance was generally greater than 10mm between the reflecting surface edge when phase I, the reflecting surface in adjusting mounted, and step also clearly before and after the inhomogeneous and slit, slit.

In adjusting in the phase I, be adjusted on its Design Theory coordinate system o '-x ' y ' z ', make the reflecting surface Primary Location making W index point on the every reflecting surface in advance; V represents the piece number of antenna reflective face among the present invention, and W represents the number of index point on the every reflecting surface.

In the present invention, the phase I is adjusted and includes following set-up procedure:

Step 2-1: coordinate system o is installed at antenna ^*-x ^*y ^*z ^*Down, with the 1st reflecting surface according to first adjustment amount { Δ xD1 _B1, Δ yD1 _B1, Δ zD1 _B1Adjust, wherein:

$\mathrm{\&Delta;x}{D1}_{b1}=x_{\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">b</figure-callout>}1}^{\mathrm{dian}}-x_{b1}^{\mathrm{<figure-callout\; id="1"\; label="d"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">d</figure-callout>}1}$

$\mathrm{\&Delta;y}{D1}_{b1}={\mathrm{<figure-callout\; id="1"\; label="y\; b"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">y</figure-callout>}}_b^1-x_{b1}^{\mathrm{<figure-callout\; id="1"\; label="d"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">d</figure-callout>}1}$

$\mathrm{\&Delta;z}{D1}_{b1}={\mathrm{<figure-callout\; id="1"\; label="z\; b"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">z</figure-callout>}}_b^1-x_{b1}^{\mathrm{<figure-callout\; id="1"\; label="d"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">d</figure-callout>}1}$

Subscript b represents b index point, b=1,2 ... W, the 1st reflecting surface of subscript 1 expression,

The Design Theory coordinate figure of representing the 1st b index point of antenna reflective face, W are represented the number of each piece antenna reflective face index point.

Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*B index point of following the 1st antenna reflective face measured coordinate figure; In like manner the Design Theory coordinate figure of the 2nd antenna reflective face is expressed as

, the measurement coordinate figure of the 2nd antenna reflective face is expressed as Adopt the laser tracker monitoring coordinate figure of sign in real time in the adjustment process

, if the adjustment error of index point then enters step 2-2 smaller or equal to ± 2mm;

$\mathrm{\&Delta;x}{D1}_{b1}=|x_{\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">b</figure-callout>}1}^{\mathrm{dian}}-x_{b1}^{\mathrm{<figure-callout\; id="1"\; label="d"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">d</figure-callout>}1}|\&le;2\mathrm{mm}$

Promptly $\mathrm{\&Delta;y}{D1}_{b1}=|{\mathrm{<figure-callout\; id="1"\; label="y\; b"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">y</figure-callout>}}_b^1-x_{b1}^{\mathrm{<figure-callout\; id="1"\; label="d"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">d</figure-callout>}1}|\&le;2\mathrm{mm};$

$\mathrm{\&Delta;z}{D1}_{b1}=|{\mathrm{<figure-callout\; id="1"\; label="z\; b"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">z</figure-callout>}}_b^1-x_{b1}^{\mathrm{<figure-callout\; id="1"\; label="d"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">d</figure-callout>}1}|\&le;2\mathrm{mm}$

Step 2-2: one by one the 2nd～V piece reflecting surface is adjusted according to the described method of step 2-1;

Step 2-3: one by one the 1st～V piece reflecting surface is checked, if the adjustment error of index point then enters step 3 smaller or equal to ± 2mm;

$\mathrm{\&Delta;x}{D1}_{b1}=|x_{\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">b</figure-callout>}1}^{\mathrm{dian}}-x_{b1}^{\mathrm{<figure-callout\; id="1"\; label="d"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">d</figure-callout>}1}|\&le;2\mathrm{mm}$

Otherwise continue execution in step 2-1, satisfied until the adjustment error of index point $\mathrm{\&Delta;y}{D1}_{b1}=|{\mathrm{<figure-callout\; id="1"\; label="y\; b"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">y</figure-callout>}}_b^1-x_{b1}^{\mathrm{<figure-callout\; id="1"\; label="d"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">d</figure-callout>}1}|\&le;2\mathrm{mm};$

$\mathrm{\&Delta;z}{D1}_{b1}=|{\mathrm{<figure-callout\; id="1"\; label="z\; b"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">z</figure-callout>}}_b^1-x_{b1}^{\mathrm{<figure-callout\; id="1"\; label="d"\; filenames="HSA00000430813900031.png"\; state="\{\{state\}\}">d</figure-callout>}1}|\&le;2\mathrm{mm}$

(3) the best even slit step (being the second stage adjustment) in edge

Large-scale antenna is generally assembled by the polylith reflecting surface, for avoiding the interference between the reflecting surface edge and reducing the interference of slit to electromagnetic field, be installed to the theoretical position of its design so must guarantee reflecting surface, and guarantee horizontal vertically flat and slit, edge evenly, make antenna reflective face position the best.

The concrete enforcement of the adjustment of second stage is as follows:

Step 3-1: adopt the simplex down-hill method to find the solution unconfinement six parametrical nonlinearity equations

Spatial alternation parameter (α, beta, gamma, x ₀, y ₀, z ₀), with (α, beta, gamma, x ₀, y ₀, z ₀) be designated as τ, τ=(α, beta, gamma, x ₀, y ₀, z ₀); f ₁(x, y z)=0 are the edge theoretical equation of the 1st reflecting surface, and α, β and γ are respectively at antenna coordinate system o is installed ^*-x ^*y ^*z ^*Down around x ^*, y ^*And z ^*Three the anglec of rotation (shown in Fig. 2 A), x ₀, y ₀And z ₀Be respectively at antenna coordinate system o is installed ^*-x ^*y ^*z ^*Lower edge x ^*, y ^*And z ^*Three translational movement, NE represent to adopt laser tracker that coordinate system o is being installed ^*-x ^*y ^*z ^*The number of following static measurement marginal point,

Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*Following the 1st antenna reflective face edge metering coordinate figure, subscript e are represented e edge metering point, the 1st reflecting surface of subscript 1 expression.In like manner the 2nd reflecting surface can be expressed as

, the 2nd antenna reflective face edge metering coordinate figure is expressed as

Step 3-2: coordinate system 0 is installed at antenna ^*-x ^*y ^*z ^*Down, with the 1st reflecting surface according to second adjustment amount { Δ xD2 _B1, Δ yD2 _B1, Δ zD2 _B1Adjust, wherein:

$\mathrm{\&Delta;x}{D2}_{b1}=x_{b1}^{d2p}-x_{b1}^{d2}$

$\mathrm{\&Delta;y}{D2}_{b1}=y_{b1}^{d2p}-y_{b1}^{d2}$

$\mathrm{\&Delta;z}{D2}_{b1}=z_{b1}^{d2p}-z_{b1}^{d2}$

Represent the edge best fit optimization coordinate figure of the 1st b index point of antenna reflective face, W represents the number of each piece antenna reflective face index point,

Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*B index point of following the 1st antenna reflective face measured coordinate figure, and subscript b represents b index point, the 1st reflecting surface of subscript 1 expression; The coordinate representation of b index point measurement of the 2nd antenna reflective face in like manner is

The edge best fit of the 2nd b index point of antenna reflective face is optimized coordinate figure and is expressed as

, and have

$\left(\begin{array}{c}{x}_{b1}^{d2p}\\ y_{b1}^{d2p}\\ z_{b1}^{d2p}\end{array}\right)=R_{\mathrm{\&gamma;}}\&CenterDot;R_{\mathrm{\&beta;}}\&CenterDot;R_{\mathrm{\&alpha;}}\&CenterDot;\left[\begin{array}{c}{x}_{b1}^{d2}-x_0\\ y_{b1}^{d2}-y_0\\ z_{b1}^{d2}-{\mathrm{<figure-callout\; id="0"\; label="z"\; filenames="HSA00000430813900032.png,HSA00000430813900051.png"\; state="\{\{state\}\}">z</figure-callout>}}_0\end{array}\right]$

α, β, γ, x ₀, y ₀And z ₀Be the spatial alternation parameter of calculating among the step 3-1, R _α, R _βAnd R _γBe respectively the spin matrix of corresponding α, β, γ, wherein

$R_{\mathrm{\&alpha;}}=\left[\begin{array}{ccc}1& 0& 0\\ 0& \cos \mathrm{\&alpha;}& \sin \mathrm{\&alpha;}\\ 0& -\sin \mathrm{\&alpha;}& \cos \mathrm{\&alpha;}\end{array}\right],$ $R_{\mathrm{\&beta;}}=\left[\begin{array}{ccc}\cos \mathrm{\&beta;}& 0& -\sin \mathrm{\&beta;}\\ 0& 1& 0\\ \sin \mathrm{\&beta;}& 0& \cos \mathrm{\&beta;}\end{array}\right],$ $R_{\mathrm{\&gamma;}}=\left[\begin{array}{ccc}\cos \mathrm{\&gamma;}& \sin \mathrm{\&gamma;}& 0\\ -\sin \mathrm{\&gamma;}& \cos \mathrm{\&gamma;}& 0\\ 0& 0& 1\end{array}\right].$

Adopt the real-time coordinate of laser tracker monitoring index point in the adjustment process

If all reflecting surface index points are at x ^*Axle and y ^*Axle two directions are adjusted error smaller or equal to ± 0.5mm, promptly satisfy

$\mathrm{\&Delta;x}{D2}_{b1}=|x_{b1}^{d2p}-x_{b1}^{d2}|\&le;0.5\mathrm{mm}$

$\mathrm{\&Delta;y}{D2}_{b1}=|y_{b1}^{d2p}-y_{b1}^{d2}|\&le;0.5\mathrm{mm}$

$\mathrm{\&Delta;z}{D2}_{b1}=|z_{b1}^{d2p}-z_{b1}^{d2}|\&le;0.5\mathrm{mm}$

And the slit is more even, and gap width≤(0.1 ± 0.05) λ (λ is the minimum operation wavelength of antenna) then enters step 3-3; Otherwise continue step 3-1.

Step 3-3: one by one the 2nd～V piece reflecting surface is adjusted according to step 3-1 and the described method of step 3-2;

Step 3-4: one by one the 1st～V piece reflecting surface is checked, if all reflecting surface index points are at x ^*Axle and y ^*Axle two directions are adjusted error smaller or equal to ± 0.5mm, promptly satisfy

$\mathrm{\&Delta;x}{D2}_{b1}=|x_{b1}^{d2p}-x_{b1}^{d2}|\&le;0.5\mathrm{mm}$

$\mathrm{\&Delta;y}{D2}_{b1}=|y_{b1}^{d2p}-y_{b1}^{d2}|\&le;0.5\mathrm{mm}$

$\mathrm{\&Delta;z}{D2}_{b1}=|z_{b1}^{d2p}-z_{b1}^{d2}|\&le;0.5\mathrm{mm}$

And the slit is more even, and gap width≤(0.1 ± 0.05) λ (λ is the minimum operation wavelength of antenna) then enters step 4; Otherwise continue step 3-1.

(4) monolithic accurate adjustment typing face step (being to adjust the phase III)

Because the reflecting surface foozle accumulates on edge, by step 3 with the edge adjust to horizontal flat vertically after, reflecting surface is at x ^*, y ^*Two direction of principal axis are limited on its theoretical position, and for guaranteeing the positional precision of monolithic reflecting surface in the phase III adjustment process, the adjustment process restriction reflecting surface of adjusting in the phase III is along x ^*, y ^*The translation of two direction of principal axis reaches around z ^*The three degree of freedom of axle rotation makes reflecting surface profile the best, the adjustment of phase III is concrete implement as follows:

Step 4-1: adopt the simplex down-hill method to find the solution belt restraining three parametrical nonlinearity equations

The spatial alternation parameter (α ', β ', z ' ₀), (α ', β ', z ' ₀) be designated as τ ', τ '=(α ', β ', z ' ₀); The profile theoretical equation of expression reflecting surface, α ' and β ' are respectively at antenna coordinate system o are installed ^*-x ^*y ^*z ^*Down around x ^*And y ^*The anglec of rotation of diaxon, z ' ₀Be illustrated in antenna coordinate system o is installed ^*-x ^*y ^*z ^*Lower edge z ^*The translational movement of axle, NS represent to adopt laser tracker that coordinate system o is being installed ^*-x ^*y ^*z ^*The number of following kinetic measurement profile point, Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*Following the 1st antenna reflective face profile measurement coordinate figure, subscript g are represented g edge metering point, the 1st reflecting surface of subscript 1 expression.In like manner the measurement coordinate figure of the 2nd reflecting surface is expressed as $(x_{g2}^{\mathrm{mian}},y_{g2}^{\mathrm{mian}},z_{g2}^{\mathrm{mian}}),g=\mathrm{1,2},...,\mathrm{NS}.$

Step 4-2: coordinate system o is installed at antenna ^*-x ^*y ^*z ^*Down, with the 1st reflecting surface according to the 3rd adjustment amount { Δ xD3 _B1, Δ yD3 _B1, Δ zD3 _B1Adjust, wherein:

$\mathrm{\&Delta;x}{D3}_{b1}=x_{b1}^{d3p}-x_{b1}^{d3}$

$\mathrm{\&Delta;y}{D3}_{b1}=y_{b1}^{d3p}-y_{b1}^{d3}$

$\mathrm{\&Delta;z}{D3}_{b1}=z_{b1}^{d3p}-z_{b1}^{d3}$

Represent the profile best fit optimization coordinate figure of the 1st b index point of antenna reflective face, W represents the number of each piece antenna reflective face index point,

Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*B index point of following the 1st antenna reflective face measured coordinate figure, and subscript b represents b index point, the 1st reflecting surface of subscript 1 expression; In like manner, the measurement coordinate figure of the 2nd b index point of antenna reflective face is expressed as

The profile best fit of the 2nd b index point of antenna reflective face is optimized coordinate figure and is expressed as

And have

$\left(\begin{array}{c}{x}_{b1}^{d3p}\\ y_{b1}^{d3p}\\ z_{b1}^{d3p}\end{array}\right)=R_{{\mathrm{\&beta;}}^{\&prime;}}^{\&prime;}\&CenterDot;R_{{\mathrm{\&alpha;}}^{\&prime;}}^{\&prime;}\&CenterDot;\left[\begin{array}{c}{x}_{b1}^{d3}\\ y_{b1}^{d3}\\ z_{b1}^{d3}-{\mathrm{<figure-callout\; id="0"\; label="z"\; filenames="HSA00000430813900032.png,HSA00000430813900051.png"\; state="\{\{state\}\}">z</figure-callout>}}_0^{\&prime;}\end{array}\right],$

α ', β ' and z ' ₀Be the spatial alternation parameter of the belt restraining that calculates among the step 4-1, R ' _{α '}And R ' _{β '}Be respectively the spin matrix of corresponding α ' and β ', wherein

$R_{{\mathrm{\&alpha;}}^{\&prime;}}^{\&prime;}=\left[\begin{array}{ccc}1& 0& 0\\ 0& \cos {\mathrm{\&alpha;}}^{\&prime;}& \sin {\mathrm{\&alpha;}}^{\&prime;}\\ 0& -\sin {\mathrm{\&alpha;}}^{\&prime;}& \cos {\mathrm{\&alpha;}}^{\&prime;}\end{array}\right],$ $R_{{\mathrm{\&beta;}}^{\&prime;}}^{\&prime;}=\left[\begin{array}{ccc}\cos {\mathrm{\&beta;}}^{\&prime;}& 0& -\sin {\mathrm{\&beta;}}^{\&prime;}\\ 0& 1& 0\\ \sin {\mathrm{\&beta;}}^{\&prime;}& 0& \cos {\mathrm{\&beta;}}^{\&prime;}\end{array}\right].$

Adopt the real-time coordinate of laser tracker monitoring index point in the adjustment process , if all reflecting surface index points are at z ^*Direction of principal axis is adjusted error smaller or equal to ± 0.02mm, promptly satisfies:

$\mathrm{\&Delta;x}{D3}_{b1}=|x_{b1}^{d3p}-x_{b1}^{d3}|\&le;0.02\mathrm{mm}$

$\mathrm{\&Delta;y}{D3}_{b1}=|y_{b1}^{d3p}-y_{b1}^{d3}|\&le;0.02\mathrm{mm}$

$\mathrm{\&Delta;z}{D3}_{b1}=|z_{b1}^{d3p}-z_{b1}^{d3}|\&le;0.02\mathrm{mm}$

And reflecting surface is in course of adjustment and be out of shape by restraining force, then changes step 4-3 over to, otherwise changes step 4-1 over to.

Step 4-3: one by one the 2nd～V piece reflecting surface is adjusted according to step 4-1 and the described method of step 4-2.

Step 4-4: one by one the 1st～V piece reflecting surface is checked, if all reflecting surface index points are at z ^*Direction of principal axis is adjusted error smaller or equal to ± 0.02mm, promptly satisfies:

$\mathrm{\&Delta;x}{D3}_{b1}=|x_{b1}^{d3p}-x_{b1}^{d3}|\&le;0.02\mathrm{mm}$

$\mathrm{\&Delta;y}{D3}_{b1}=|y_{b1}^{d3p}-y_{b1}^{d3}|\&le;0.02\mathrm{mm}$

$\mathrm{\&Delta;z}{D3}_{b1}=|z_{b1}^{d3p}-z_{b1}^{d3}|\&le;0.02\mathrm{mm}$

And reflecting surface is in course of adjustment and be out of shape by restraining force, then finishes antenna reflective face and debugs, otherwise changes step 4-1 over to.

The antenna reflective face that the present invention is based on laser tracker is debug method, adopt a laser tracker as measuring equipment, adopt the simplex down-hill method to calculate adjustment amount, by the horizontal flat benchmark of vertically looking for, regulate coarse positioning at 4, best even slit, edge, four set-up procedures of monolithic accurate adjustment typing face, progressively heighten adjust precision the most at last antenna reflective face adjust to and the best position that coincide of design reflectivity face, guarantee the final profile precision of antenna reflective face, guarantee that antenna satisfies electricity function index, can improve antenna reflective face and debug efficient, shorten and debug the duration, quality is debug in assurance, is particularly suitable for debuging by the assembled large-scale antenna of polylith reflecting surface.

Application example

Tighten antenna test site CATR (Compact Antenna Test Range) and be called for short the deflation field, the spherical wave that it will send from point source is at inner conversion plane wave closely, thereby allow in the indoor measurement of carrying out under the far field condition, to satisfy the far field condition requirement of antenna pattern and RCS RCS (Radar Cross-Section) test.For outfield and indoor near field, tightening the field has following advantage: tighten a plane wave that produces and focus in the collimated beam of sound, the dead zone ambient level is low; Tighten the field and be installed in microwave dark room, not only have confidentiality, and be not subjected to weather and seasonal effect fully, improved test condition, improved the precision and the efficient of rcs measurement; The working band that tightens the field is wide, can satisfy the test request of millimeter wave and submillimeter wave from hundreds of MHz to hundreds of GHz.At present, tighten the growing maturation of field technology, progressively become stealthy research, target RCS test, advanced capabilities radar antenna measurement, satellite and put in order the necessaries to the various measurements of plane wave environmental requirement strictness such as star test, millimeter wave antenna and millimeter-wave systems performance test.

As shown in Figure 3, a certain reflector antenna is divided into 9 little reflecting surface manufacturings, and the monolithic reflecting surface adopts honeycomb sandwich construction, is shaped through flexible multi-point mould negative pressure of vacuum, and monolithic reflecting surface profile precision RMS is all below 40 μ m.Wherein reflecting surface NJD2025-08 is positioned at and tightens a center, dead zone, its final precision has the greatest impact to tightening an overall performance, this reflecting surface can be used as the benchmark of other reflecting surface adjustment location simultaneously, so be example with NJD2025-08 reflective face, implement this and debugs technology.

1, the horizontal flat benchmark of vertically looking for

According to following position shown in Figure 1, fixed installation LEACIA AT901-B laser tracker, adopt the YGLP210 theodolite evenly to arrange 10 alignment target points on supporting bracket, arrange 5 points on the supporting bracket of north and south respectively, wherein alignment target point is at laser tracker coordinate system o ^Lt-x ^Lty ^Ltz ^LtUnder measurement coordinate figure such as following table 1:

Table 1 horizontal plane index point

The index point period	x lt(mm)	y lt(mm)	z lt(mm)
				1	5188.923	-1095.411	14.314
2	5138.325	567.188	-13.41
				3	5277.668	4070.779	-71.298
4	5241.315	5861.93	-100.791
				5	2261.185	6883.654	-127.677
6	406.097	7002.648	-135.267
				7	-1494.697	7116.303	-143.492
8	-7503.723	4588.312	-121.507
				9	-4298.291	-7312.309	85.639
10	-3745.632	-7778.765	95.123

Calculating is tried to achieve at laser tracker coordinate system o ^Lt-x ^Lty ^Ltz ^LtDown, its normal vector is $\stackrel{\&RightArrow;}{N}=(-\mathrm{0.00329,0.016519,0.999858});$

Try to achieve the parallel lines direction equally

With position P (139.430 ,-2179.819,14.511) is initial point, and calculating and being tied to the coordinate conversion parameter of demarcating coordinate system from individual laser tracker coordinate is τ=(270.9333,0.2458,3.5009,5.996,21.042 ,-2184.21) after, set up antenna coordinate system o has been installed ^*-x ^*y ^*z ^*

Last four theoretical coordinates of adjusting point of reflecting surface NJD2025-08 are in the middle of known again:

Table 2NJD2025-08 adjusts some theoretical coordinate value

Period	x′(mm)	y′(mm)	z′(mm)
				1	-509.787	3309.640	346.940
2	-509.791	4386.301	596.648
				3	509.791	4386.301	596.648
4	509.787	3309.640	346.940

Reflecting surface is installed coordinate system o at antenna after mounting on the back of the body frame ^*-x ^*y ^*z ^*Last four of reflecting surface NJD2025-8 adjusts the point coordinates value in the middle of the following measurement:

Table 3NJD2025-08 demarcates coordinate system o ^Xc-x ^Xcy ^Xcz ^XcUnder measure coordinate figure

Period	x xc(mm)	y xc(mm)	z xc(mm)
				1	-516.985	3193.768	-8521.652
2	-516.334	4269.296	-8268.505
				3	504.248	4270.053	-8272.962
4	503.885	3194.409	-8526.235

Calculate from demarcating coordinate system o according to (4) ^Xc-x ^Xcy ^Xcz ^XcTo antenna coordinate system o is installed ^*-x ^*y ^*z ^*Translational movement:

$\mathrm{\&Delta;x}=\frac{1}{4}(\underset{a=1}{\overset{4}{\mathrm{\&Sigma;}}}{x_a}^{\mathrm{xc}}-\underset{a=1}{\overset{4}{\mathrm{\&Sigma;}}}{x}_a^{\&prime;})=-6.2965$

$\mathrm{\&Delta;y}=\frac{1}{4}(\underset{a=1}{\overset{4}{\mathrm{\&Sigma;}}}{y}_a-\underset{a=1}{\overset{4}{\mathrm{\&Sigma;}}}{y}_a^{\&prime;})=-116.0889$

$\mathrm{\&Delta;z}=\frac{1}{4}(\underset{a=1}{\overset{4}{\mathrm{\&Sigma;}}}{z}_a-\underset{a=1}{\overset{4}{\mathrm{\&Sigma;}}}{z}_a^{\&prime;})=-8869.1327$

Obtain laser tracker coordinate system o ^Lt-x ^Lty ^Ltz ^Lt, demarcate coordinate system o ^Xc-x ^Xcy ^Xcz ^XcWith antenna coordinate system o is installed ^*-x ^*y ^*z ^*Transformational relation between three coordinate systems is as shown in table 4 below:

Table 4 coordinate system conversion parameter table

So antenna is installed coordinate system o ^*-x ^*y ^*z ^*Foundation is finished.

2, regulate coarse positioning at 4

Reflecting surface NJD2025-8 is positioned at and tightens a center, dead zone, requirement has the highest precision, known NJD2025-8 reflecting surface profile accuracy of manufacture RMS is 32.8 μ m before debuging, NJD2025-8 is in the center simultaneously, other reflectings surface all are in contact with it, so NJD2025-8 can be used as the benchmark of other reflecting surface location, it are numbered 1, with NJD2025-8 reflective face is example, and it is as follows to implement index point location coarse adjustment:

Measure last four of reflecting surface NJD2025-8 and adjust point at antenna installation coordinate system o ^*-x ^*y ^*z ^*Middle coordinate figure is:

Table 5NJD2025-08 debugs coordinate figure under the coordinate system

Period	x *(mm)	y *(mm)	z *(mm)
				1	-508.260	3325.599	340.542
2	-507.609	4401.127	593.689
				3	512.973	4401.884	589.232
4	512.611	3326.240	335.960

Then can get adjustment amount according to (5) calculating is:

4 adjustment amounts of table 6

Period	ΔxD1 b1(mm)	ΔyD1 b1(mm)	?ΔzD1 b1(mm)
				1	-1.527	-15.959	?6.398
2	-2.182	-14.826	?2.959
				3	-3.182	-15.583	?7.416
4	-2.824	-16.600	?10.980

According to above-mentioned adjustment amount, adjust point with four and adjust to upper/lower positions:

Position coordinate value after 4 adjustment of table 7

Period	x *(mm)	y *(mm)	z *(mm)
				1	-509.663	3308.864	346.732
2	-511.260	4384.986	597.310
				3	509.388	4386.738	597.423
4	511.408	3310.607	346.693

Adjusting the mistake residual error this moment is:

4 in table 8 is adjusted error

Period	ΔxD1 b1(mm)	ΔyD1 b1(mm)	ΔzD1 b1(mm)
				1	-0.124	0.776	0.208
2	1.469	1.315	-0.662
				3	0.403	-0.437	-0.775
4	-1.621	-0.967	0.247

After the phase I adjustment, the profile precision RMS of NJD2025-08 reflecting surface is 236.8 μ m, and the profile error profile is seen Fig. 4.Other reflectings surface are all according to NJD2025-08 reflecting surface adjustment process, block-by-block adjustment.

3, best even slit, edge

Put in place by 9 reflecting surface coarse adjustment of previous step, adjust error substantially all to be controlled at ± 2mm in, be example with the NJD2025-8 reflecting surface equally again, implement the edge best located and put as follows:

Adopt a little on NJD2025-8 reflecting surface four edges edge according to the 90mm spacing, antenna is installed coordinate system o ^*-x ^*y ^*z ^*Following measurement point coordinate such as following table 9:

Table 9 edge metering point coordinates value

Period	x *(mm)	y *(mm)	z *(mm)
				1	-823.014	4789.118	708.673
2	-704.737	4789.062	703.216
				3	-608.249	4789.002	699.429
4	-495.786	4789.152	695.631
				5	-362.874	4789.065	692.269
6	-251.627	4789.44	690.201
				7	-144.409	4789.095	688.959
8	-35.73	4788.469	688.405
				9	11.602	4788.189	688.494
10	68.533	4788.197	688.633
				...	...	...	...

80	44.494	2914.482	254.055
				81	-79.417	2914.271	254.07
82	-203.461	2914.4	255.153
				83	-330.315	2914.483	257.246
84	-444.971	2914.511	259.894
				85	-500.08	2914.548	261.445
86	-598.332	2914.573	264.713
				87	-745.223	2914.568	270.584
88	-832.585	2914.613	274.664
				89	-905.156	2914.958	278.635

Can obtain following transformation parameter τ by the edge optimum Match:

α(°)	-0.0191
		β(°)	0.0137
γ(°)	-0.0032
		x 0(mm)	0.0001
y 0(mm)	0.2690
		z 0(mm)	1.2212

Then can get adjustment amount according to (table 6, table 8) calculating is:

The best adjustment amount in table 10 edge

Period	?ΔxD2 b1(mm)	ΔyD2 b1(mm)	ΔzD2 b1(mm)
				1	?0.0849	-0.1013	-0.0247
2	?0.1464	-0.1847	0.3336
				3	?0.1464	-0.1846	0.0833

4

?0.0848

-0.1012

-0.2751

This step just four adjustment points is adjusted to upper/lower positions:

The best position of adjusting, table 11 edge

Period	x *(mm)	y *(mm)	z *(mm)
				1	-510.511	3309.958	347.040
2	-509.831	4386.440	596.289
				3	510.811	4385.929	596.636
4	510.516	3309.465	347.188

Adjusting the mistake residual error this moment is:

The best error of adjusting in table 12 edge

Period	ΔxD2 b1(mm)	ΔyD2 b1(mm)	ΔzD2 b1(mm)
				1	0.0849	-0.1013	-0.0247
2	0.1464	-0.1847	0.3336
				3	0.1464	-0.1846	0.0833
4	0.0848	-0.1012	-0.2751

The edge is best should to guarantee to adjust residual error after adjusting in ± 0.5mm, and the slit is even substantially.

Precision RMS is 56.3 μ m after the edge adjustment of NJD2025-8 reflecting surface, and error profile is seen Fig. 5.

After the adjustment, the slit is even.

4, monolithic accurate adjustment typing face

The slit adjustment finishes, and in order to guarantee the precision in reflecting surface edge and slit, in the process of adjusting profile, must limit it at X, and the translation of Y direction reaches the rotation around the Z axle.Set 90mm * 90mm spacing and evenly dynamically adopt some measurement point coordinate such as following table 13 at reflecting surface:

Table 13 profile measurement point coordinates value

Period	x *(mm)	y *(mm)	z *(mm)
				1	-852.419	4745.734	719.998
2	-809.874	4745.385	717.807

3	-719.860	4762.097	718.435
				4	-629.648	4744.718	709.778
5	-539.982	4736.977	704.384
				6	-449.627	4733.247	700.603
7	-359.805	4734.209	698.710
				8	-269.863	4721.535	693.392
9	-179.638	4738.776	697.125
				10	-89.918	4728.844	693.532
...	...	...	...
				267	-0.304	2941.272	280.024
268	-90.269	2934.599	279.029
				269	-180.187	2936.544	280.184
270	-270.147	2928.106	279.910
				271	-360.135	2937.576	283.329
272	-450.242	2934.340	284.944
				273	-540.058	2955.723	291.407
274	-630.079	2951.548	293.877
				275	-720.089	2945.622	296.469
276	-810.123	2932.953	298.362

Can obtain following transformation parameter τ ' by profile non-linear least square optimum Match:

α′(°)	-0.0037
		β′(°)	-0.0007
γ′(°)	0

x′ 0(mm)	0
		y′ 0(mm)	0
z′ 0(mm)	0.2446

Then can get adjustment amount according to (table 9) calculating is:

Table 14 phase III adjustment amount

Period	?ΔxD3 b1(mm)	?ΔyD3 b1(mm)	ΔzD3 b1(mm)
				1	?0.0053	?0.0344	-0.0310
2	?0.0053	?0.0182	0.0384
				3	?0.0053	?0.0152	0.0515
4	?0.0053	?0.0314	-0.0180

This step just four adjustment points is adjusted to upper/lower positions:

Table 15 profile coupling is adjusted the position

Period	x *(mm)	y *(mm)	z *(mm)
				1	-510.545	3309.819	347.033
2	-509.8502	4386.26	596.345
				3	510.774	4385.905	596.688
4	510.504	3309.478	347.199

Adjusting the mistake residual error this moment is:

Table 16 profile coupling is adjusted error

Period	?ΔxD3 b1(mm)	?ΔyD3 b1(mm)	ΔzD3 b1(mm)
				1	?0.0393	?0.1734	-0.024
2	?0.0245	?0.1982	-0.0176
				3	?0.0423	?0.0392	-0.0005
4	?0.0173	?0.0184	-0.029

As above shown in the table 16, adjust back NJD2025-08 reflecting surface by the phase III and adjust ERROR CONTROL in ± 0.02mm scope, it is 38.5 μ m that final NJD2025-08 reflecting surface is adjusted precision RMS, has reached the accuracy of manufacture 32.8 μ m (referring to shown in Figure 6) of this reflecting surface substantially.

According to the method for adjustment of above-mentioned 4 points-edge-profile, every reflecting surface is all adjusted to position with its theoretical position optimum Match, intact whole debuging of tightening, final precision reaches 57.0 μ m, satisfies the application requirements of the highest 40GHz.Overall precision is referring to shown in Figure 7.

Claims (6)

1. the antenna reflective face based on laser tracker is debug method, and a required laser tracker carries out the index point measurement of coordinates, stores in the computer control system and debugs processing unit, it is characterized in that the described method of debuging in the processing unit of debuging includes:

Step 1: set up antenna coordinate system o is installed ^*-x ^*y ^*z ^*Step;

Step 2: regulate the coarse positioning step at 4;

Step 3: best even slit, edge step;

Step 4: monolithic accurate adjustment typing face step.

2. the antenna reflective face based on laser tracker according to claim 1 is debug method, it is characterized in that setting up antenna coordinate system o is installed ^*-x ^*y ^*z ^*Step includes following implementation step:

Step 1-1:(A) around the reflector antenna erecting bed, four supporting brackets are set, and the head and the tail of four supporting brackets is connected to form quadrangle; Then laser tracker is arranged on described tetragonal outside, the coordinate system of described laser tracker is designated as o ^Lt-x ^Lty ^Ltz ^Lt

(B) the alignment target point is set respectively on four supporting brackets, and in debuging processing unit, writes down period;

(C) measure each period at o according to period with laser tracker ^Lt-x ^Lty ^Ltz ^LtUnder coordinate figure;

Wherein, first group of axial coordinate value Q (x _Qi, y _Qi, z _Qi) i=1,2 ..., m;

Wherein, second group of axial coordinate value R (x _Rj, y _Rj, z _Rj) j=1,2 ..., s; M=s wherein, m represents the mark mark of first group of axial index point, s represents the mark mark of second group of axial index point;

Wherein, the coordinate figure P (x of alignment target point _Pk, y _Pk, z _Pk) k=1,2 ..., n;

Step 1-2: determine to demarcate coordinate system

(A) adopt the coordinate figure P (x of least square method to obtaining among the step 1-1 _Pk, y _Pk, z _Pk) k=1,2 ..., n carries out match, obtains demarcating horizontal plane A x+By+Cy=0, and this demarcation horizontal plane flatness need reach 00 grade; Wherein, A represents to demarcate in the horizontal plane x method of principal axes to vector, and B represents to demarcate that the y method of principal axes is to vector in the horizontal plane, and C represents to demarcate z method of principal axes vector in the horizontal plane;

(B) extract the vector of demarcating A, B, C among the horizontal plane A x+By+Cz=0, be designated as

Normalization

Promptly obtain earth coordinates o ^w-x ^wy ^wz ^wThe vector of vertical

Promptly

$\stackrel{\&RightArrow;}{N}=(\frac{A}{\sqrt{A^2+B^2+C^2}},\frac{B}{\sqrt{A^2+B^2+C^2}},\frac{C}{\sqrt{A^2+B^2+C^2}});$

(C) with Q (x _Qi, y _Qi, z _Qi) i=1,2 ..., m projects to the demarcation horizontal plane

On, the coordinate figure that obtains after the projection is designated as q (x _Qi, y _Qi, z _Qi) i=1,2 ..., m; Adopt least square method to q (x _Qi, y _Qi, z _Qi) i=1,2 ..., m carries out match, and the straight line that obtains the first group echo point is designated as L ₁, L ₁Linear equation be expressed as c ₁+ n ₁X+n ₂Y=0;

(D) with R (x _Rj, y _Rj, z _Rj) j=1,2 ..., s projects to and demarcates on the horizontal plane A x+By+Cz=0, and the coordinate figure that obtains after the projection is designated as r (x _Rj, y _Rj, z _Rj) j=1,2 ..., s; Adopt least square method to r (x _Rj, y _Rj, z _Rj) j=1,2 ..., s carries out match, and the straight line that obtains the second group echo point is designated as L ₂, L ₂Linear equation be expressed as c ₂+ n ₃X+n ₄Y=0;

Make n ₁=n ₃, n ₂=n ₄, and So straight line L ₁With straight line L ₂Parallel (L ₁//L ₂); Extract straight line L ₁Direction vector be designated as

(E) with the vertical vector As demarcating coordinate system o ^Xc-x ^Xcy ^Xcz ^XcMiddle y ^XcThe direction of principal axis vector,

As demarcating coordinate system o ^Xc-x ^Xcy ^Xcz ^XcMiddle z ^XcThe direction of principal axis vector, and with P (x _Pk, y _Pk, z _Pk) k=1,2 ..., certain among the n obtains being presented at the demarcation coordinate system o on the display in the computer control system a bit as initial point according to the right-handed coordinate system rule ^Xc-x ^Xcy ^Xcz ^Xc

Step 1-3: determine antenna installation coordinate system o ^*-x ^*y ^*z ^*

To demarcate coordinate system o ^Xc-x ^Xcy ^Xcz ^Xcformerly press side-play amount { Δ z} translation obtain antenna coordinate system o is installed for Δ x, Δ y ^*-x ^*y ^*z ^*In, wherein

$\mathrm{\&Delta;x}=\frac{1}{t}(\underset{a=1}{\overset{t}{\mathrm{\&Sigma;}}}{x_a}^{\mathrm{xc}}-\underset{a=1}{\overset{t}{\mathrm{\&Sigma;}}}{x}_a^{\&prime;})$

$\mathrm{\&Delta;y}=\frac{1}{t}(\underset{a=1}{\overset{t}{\mathrm{\&Sigma;}}}{y}_a-\underset{a=1}{\overset{t}{\mathrm{\&Sigma;}}}{y}_a^{\&prime;})$

$\mathrm{\&Delta;z}=\frac{1}{t}(\underset{a=1}{\overset{t}{\mathrm{\&Sigma;}}}{z}_a-\underset{a=1}{\overset{t}{\mathrm{\&Sigma;}}}{z}_a^{\&prime;})$

Indicator sign point is being demarcated coordinate system o ^Xc-x ^Xcy ^Xcz ^XcUnder the measurement coordinate figure;

(x ' _a, y ' _a, z ' _a), a=1,2 ... the coordinate figure of t indicator sign point under theory design coordinate system o '-x ' y ' z ';

The number of t indicator sign point.

3. the antenna reflective face based on laser tracker according to claim 1 is debug method, it is characterized in that: the laser tracker adjustment is according to the minimum principle of measure error, and the vibrations of laser tracker position are set to less than 0.01mm.

4. the antenna reflective face based on laser tracker according to claim 1 is debug method, it is characterized in that: determined antenna installation coordinate system o ^*-x ^*y ^*z ^*After, whole V piece antenna reflective faces are mounted on the supporting construction, this moment, the reflection line position error ratio was bigger; Regulate the coarse positioning step at 4 set-up procedure arranged:

Step 2-1: coordinate system o is installed at antenna ^*-x ^*y ^*z ^*Down, with the 1st reflecting surface according to first adjustment amount { Δ xD1 _B1, Δ yD1 _B1, Δ zD1 _B1Adjust, wherein:

$\mathrm{\&Delta;x}{D1}_{b1}=x_{b1}^{\mathrm{dian}}-x_{b1}^{d1}$

$\mathrm{\&Delta;y}{D1}_{b1}=y_{b1}^{\mathrm{dian}}-x_{b1}^{d1}$

$\mathrm{\&Delta;z}{D1}_{b1}=z_{b1}^{\mathrm{dian}}-x_{b1}^{d1}$

Subscript b represents b index point, b=1,2 ... W, the 1st reflecting surface of subscript 1 expression, The Design Theory coordinate figure of representing the 1st b index point of antenna reflective face, W are represented the number of each piece antenna reflective face index point;

Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*B index point of following the 1st antenna reflective face measured coordinate figure; In like manner the Design Theory coordinate figure of the 2nd antenna reflective face is expressed as

, the measurement coordinate figure of the 2nd antenna reflective face is expressed as

Adopt the laser tracker monitoring coordinate figure of sign in real time in the adjustment process If the adjustment error of index point then enters step 2-2 smaller or equal to ± 2mm;

$\mathrm{\&Delta;x}{D1}_{b1}=|x_{b1}^{\mathrm{dian}}-x_{b1}^{d1}|\&le;2\mathrm{mm}$

Promptly $\mathrm{\&Delta;y}{D1}_{b1}=|y_{b1}^{\mathrm{dian}}-x_{b1}^{d1}|\&le;2\mathrm{mm};$

$\mathrm{\&Delta;z}{D1}_{b1}=|z_{b1}^{\mathrm{dian}}-x_{b1}^{d1}|\&le;2\mathrm{mm}$

Step 2-2: one by one the 2nd～V piece reflecting surface is adjusted according to the described method of step 2-1;

Step 2-3: one by one the 1st～V piece reflecting surface is checked, if the adjustment error of index point then enters step 3 smaller or equal to ± 2mm;

$\mathrm{\&Delta;x}{D1}_{b1}=|x_{b1}^{\mathrm{dian}}-x_{b1}^{d1}|\&le;2\mathrm{mm}$

Otherwise continue execution in step 2-1, satisfied until the adjustment error of index point $\mathrm{\&Delta;y}{D1}_{b1}=|y_{b1}^{\mathrm{dian}}-x_{b1}^{d1}|\&le;2\mathrm{mm}.$

$\mathrm{\&Delta;z}{D1}_{b1}=|z_{b1}^{\mathrm{dian}}-x_{b1}^{d1}|\&le;2\mathrm{mm}$

5. the antenna reflective face based on laser tracker according to claim 1 is debug method, it is characterized in that: large-scale antenna is generally assembled by the polylith reflecting surface, for avoiding the interference between the reflecting surface edge and reducing the interference of slit to electromagnetic field, be installed to the theoretical position of its design so must guarantee reflecting surface, and guarantee horizontal flat the even of slit that vertically reach in edge;

The concrete enforcement of adjustment of best even slit, edge step is as follows:

Step 3-1: adopt the simplex down-hill method to find the solution unconfinement six parametrical nonlinearity equations

Spatial alternation parameter (α, beta, gamma, x ₀, y ₀, z ₀), with (α, beta, gamma, x ₀, y ₀, z ₀) be designated as τ, τ=(α, beta, gamma, x ₀, y ₀, z ₀); f ₁(x, y z)=0 are the edge theoretical equation of the 1st reflecting surface, and α, β and γ are respectively at antenna coordinate system o is installed ^*-x ^*y ^*z ^*Down around x ^*, y ^*And z ^*Three the anglec of rotation (shown in Fig. 2 A), x ₀, y ₀And z ₀Be respectively at antenna coordinate system o is installed ^*-x ^*y ^*z ^*Lower edge x ^*, y ^*And z ^*Three translational movement, NE represent to adopt laser tracker that coordinate system o is being installed ^*-x ^*y ^*z ^*The number of following static measurement marginal point,

Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*Following the 1st antenna reflective face edge metering coordinate figure, subscript e are represented e edge metering point, the 1st reflecting surface of subscript 1 expression; In like manner the 2nd reflecting surface can be expressed as

The 2nd antenna reflective face edge metering coordinate figure is expressed as

Step 3-2: coordinate system o is installed at antenna ^*-x ^*y ^*z ^*Down, with the 1st reflecting surface according to second adjustment amount { Δ xD2 _B1, Δ yD2 _B1, Δ zD2 _B1Adjust, wherein:

$\mathrm{\&Delta;x}{D2}_{b1}=x_{b1}^{d2p}-x_{b1}^{d2}$

$\mathrm{\&Delta;y}{D2}_{b1}=y_{b1}^{d2p}-y_{b1}^{d2}$

$\mathrm{\&Delta;z}{D2}_{b1}=z_{b1}^{d2p}-z_{b1}^{d2}$

Represent the edge best fit optimization coordinate figure of the 1st b index point of antenna reflective face, W represents the number of each piece antenna reflective face index point,

Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*B index point of following the 1st antenna reflective face measured coordinate figure, and subscript b represents b index point, the 1st reflecting surface of subscript 1 expression; The coordinate representation of b index point measurement of the 2nd antenna reflective face in like manner is

, the edge best fit of the 2nd b index point of antenna reflective face is optimized coordinate figure and is expressed as

, and have

$\left(\begin{array}{c}{x}_{b1}^{d2p}\\ y_{b1}^{d2p}\\ z_{b1}^{d2p}\end{array}\right)=R_{\mathrm{\&gamma;}}\&CenterDot;R_{\mathrm{\&beta;}}\&CenterDot;R_{\mathrm{\&alpha;}}\&CenterDot;\left[\begin{array}{c}{x}_{b1}^{d2}-x_0\\ y_{b1}^{d2}-y_0\\ z_{b1}^{d2}-z_0\end{array}\right]$

α, β, γ, x ₀, y ₀And z ₀Be the spatial alternation parameter of calculating among the step 3-1, R _α, R _βAnd R _γBe respectively the spin matrix of corresponding α, β, γ, wherein

$R_{\mathrm{\&alpha;}}=\left[\begin{array}{ccc}1& 0& 0\\ 0& \cos \mathrm{\&alpha;}& \sin \mathrm{\&alpha;}\\ 0& -\sin \mathrm{\&alpha;}& \cos \mathrm{\&alpha;}\end{array}\right],$ $R_{\mathrm{\&beta;}}=\left[\begin{array}{ccc}\cos \mathrm{\&beta;}& 0& -\sin \mathrm{\&beta;}\\ 0& 1& 0\\ \sin \mathrm{\&beta;}& 0& \cos \mathrm{\&beta;}\end{array}\right],$ $R_{\mathrm{\&gamma;}}=\left[\begin{array}{ccc}\cos \mathrm{\&gamma;}& \sin \mathrm{\&gamma;}& 0\\ -\sin \mathrm{\&gamma;}& \cos \mathrm{\&gamma;}& 0\\ 0& 0& 1\end{array}\right].$

Adopt the real-time coordinate of laser tracker monitoring index point in the adjustment process , if all reflecting surface index points are at x ^*Axle and y ^*Axle two directions are adjusted error smaller or equal to ± 0.5mm, promptly satisfy

$\mathrm{\&Delta;x}{D2}_{b1}=|x_{b1}^{d2p}-x_{b1}^{d2}|\&le;0.5\mathrm{mm}$

$\mathrm{\&Delta;y}{D2}_{b1}=|y_{b1}^{d2p}-y_{b1}^{d2}|\&le;0.5\mathrm{mm}$

$\mathrm{\&Delta;z}{D2}_{b1}=|z_{b1}^{d2p}-z_{b1}^{d2}|\&le;0.5\mathrm{mm}$

And the slit is more even, gap width≤(0.1 ± 0.05) λ, and λ is the minimum operation wavelength of antenna, then enters step 3-3; Otherwise continue step 3-1;

Step 3-3: one by one the 2nd～V piece reflecting surface is adjusted according to step 3-1 and the described method of step 3-2;

Step 3-4: one by one the 1st～V piece reflecting surface is checked, if all reflecting surface index points are at x ^*Axle and y ^*Axle two directions are adjusted error smaller or equal to ± 0.5mm, promptly satisfy

$\mathrm{\&Delta;x}{D2}_{b1}=|x_{b1}^{d2p}-x_{b1}^{d2}|\&le;0.5\mathrm{mm}$

$\mathrm{\&Delta;y}{D2}_{b1}=|y_{b1}^{d2p}-y_{b1}^{d2}|\&le;0.5\mathrm{mm}$

$\mathrm{\&Delta;z}{D2}_{b1}=|z_{b1}^{d2p}-z_{b1}^{d2}|\&le;0.5\mathrm{mm}$

And the slit is more even, and gap width≤(0.1 ± 0.05) λ then enters step 4; Otherwise continue step 3-1.

6. the antenna reflective face based on laser tracker according to claim 1 is debug method, it is characterized in that the concrete enforcement of adjustment of monolithic accurate adjustment typing face step is as follows:

Step 4-1: adopt the simplex down-hill method to find the solution belt restraining three parametrical nonlinearity equations

The spatial alternation parameter (α ', β ', z ' ₀), (α ', β ', z ' ₀) be designated as τ ', τ '=(α ', β ', z ' ₀);

The profile theoretical equation of expression reflecting surface, α ' and β ' are respectively at antenna coordinate system o are installed ^*-x ^*y ^*z ^*Down around x ^*And y ^*The anglec of rotation of diaxon, z ' ₀Be illustrated in antenna coordinate system o is installed ^*-x ^*y ^*z ^*Lower edge z ^*The translational movement of axle, NS represent to adopt laser tracker that coordinate system o is being installed ^*-x ^*y ^*z ^*The number of following kinetic measurement profile point,

Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*Following the 1st antenna reflective face profile measurement coordinate figure, subscript g are represented g edge metering point, the 1st reflecting surface of subscript 1 expression; In like manner the measurement coordinate figure of the 2nd reflecting surface is expressed as $(x_{g2}^{\mathrm{mian}},y_{g2}^{\mathrm{mian}},z_{g2}^{\mathrm{mian}}),g=\mathrm{1,2},...,\mathrm{NS};$

Step 4-2: coordinate system o is installed at antenna ^*-x ^*y ^*z ^*Down, with the 1st reflecting surface according to the 3rd adjustment amount { Δ xD3 _B1, Δ yD3 _B1, Δ zD3 _B1Adjust, wherein:

$\mathrm{\&Delta;x}{D3}_{b1}=x_{b1}^{d3p}-x_{b1}^{d3}$

$\mathrm{\&Delta;y}{D3}_{b1}=y_{b1}^{d3p}-y_{b1}^{d3}$

$\mathrm{\&Delta;z}{D3}_{b1}=z_{b1}^{d3p}-z_{b1}^{d3}$

Represent the profile best fit optimization coordinate figure of the 1st b index point of antenna reflective face, W represents the number of each piece antenna reflective face index point,

Expression utilizes laser tracker at antenna coordinate system o to be installed ^*-x ^*y ^*z ^*B index point of following the 1st antenna reflective face measured coordinate figure, and subscript b represents b index point, the 1st reflecting surface of subscript 1 expression; In like manner, the measurement coordinate figure of the 2nd b index point of antenna reflective face is expressed as The profile best fit of the 2nd b index point of antenna reflective face is optimized coordinate figure and is expressed as

And have

$\left(\begin{array}{c}{x}_{b1}^{d3p}\\ y_{b1}^{d3p}\\ z_{b1}^{d3p}\end{array}\right)=R_{{\mathrm{\&beta;}}^{\&prime;}}^{\&prime;}\&CenterDot;R_{{\mathrm{\&alpha;}}^{\&prime;}}^{\&prime;}\&CenterDot;\left[\begin{array}{c}{x}_{b1}^{d3}\\ y_{b1}^{d3}\\ z_{b1}^{d3}-z_0^{\&prime;}\end{array}\right],$

α ', β ' and z ' ₀Be the spatial alternation parameter of the belt restraining that calculates among the step 4-1, R ' _{α '}And R ' _{β '}Be respectively the spin matrix of corresponding α ' and β ', wherein

$R_{{\mathrm{\&alpha;}}^{\&prime;}}^{\&prime;}=\left[\begin{array}{ccc}1& 0& 0\\ 0& \cos {\mathrm{\&alpha;}}^{\&prime;}& \sin {\mathrm{\&alpha;}}^{\&prime;}\\ 0& -\sin {\mathrm{\&alpha;}}^{\&prime;}& \cos {\mathrm{\&alpha;}}^{\&prime;}\end{array}\right],$ $R_{{\mathrm{\&beta;}}^{\&prime;}}^{\&prime;}=\left[\begin{array}{ccc}\cos {\mathrm{\&beta;}}^{\&prime;}& 0& -\sin {\mathrm{\&beta;}}^{\&prime;}\\ 0& 1& 0\\ \sin {\mathrm{\&beta;}}^{\&prime;}& 0& \cos {\mathrm{\&beta;}}^{\&prime;}\end{array}\right];$

Adopt the real-time coordinate of laser tracker monitoring index point in the adjustment process

, if all reflecting surface index points are at z ^*Direction of principal axis is adjusted error smaller or equal to ± 0.02mm, promptly satisfies:

$\mathrm{\&Delta;x}{D3}_{b1}=|x_{b1}^{d3p}-x_{b1}^{d3}|\&le;0.02\mathrm{mm}$

$\mathrm{\&Delta;y}{D3}_{b1}=|y_{b1}^{d3p}-y_{b1}^{d3}|\&le;0.02\mathrm{mm}$

$\mathrm{\&Delta;z}{D3}_{b1}=|z_{b1}^{d3p}-z_{b1}^{d3}|\&le;0.02\mathrm{mm}$

And reflecting surface is in course of adjustment and be out of shape by restraining force, then changes step 4-3 over to, otherwise changes step 4-1 over to;

Step 4-3: one by one the 2nd～V piece reflecting surface is adjusted according to step 4-1 and the described method of step 4-2;

Step 4-4: one by one the 1st～V piece reflecting surface is checked, if all reflecting surface index points are at z ^*Direction of principal axis is adjusted error smaller or equal to ± 0.02mm, promptly satisfies:

$\mathrm{\&Delta;x}{D3}_{b1}=|x_{b1}^{d3p}-x_{b1}^{d3}|\&le;0.02\mathrm{mm}$

$\mathrm{\&Delta;y}{D3}_{b1}=|y_{b1}^{d3p}-y_{b1}^{d3}|\&le;0.02\mathrm{mm}$

$\mathrm{\&Delta;z}{D3}_{b1}=|z_{b1}^{d3p}-z_{b1}^{d3}|\&le;0.02\mathrm{mm}$

And reflecting surface is in course of adjustment and be out of shape by restraining force, then finishes antenna reflective face and debugs, otherwise changes step 4-1 over to.

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