CN104535974A - Boresight device of airplane radar system and using method of boresight device - Google Patents

Abstract

The invention relates to a boresight device of an airplane radar system and a using method of the boresight device, belonging to the field of airplane radars. The boresight device comprises a computer, a laser tracker, an electronic level meter, a servo mechanism and a target device, wherein the computer is connected with the laser tracker and the servo mechanism via cables, the laser tracker is mounted on the servo mechanism, the servo mechanism is mounted on the electronic level meter, and the target device receives signals of the laser tracker. The laser tracker emits laser measuring signals to the target device, a photoelectric sensor of the target device feedback target position signals to the laser tracker, the computer controls the laser tracker via the servo mechanism, and thus, the laser tracker aligning reference points of the target. The boresight method and using method thereof do not damage a radar, the measurement area is greatly reduced, it is not required to place the target, the labor cost is reduced, the production period of an airplane is shortened, and the fighting performance of the airplane is improved.

Description

A kind of rebecca system calibration device and using method thereof

Technical field

The present invention relates to rebecca field, relate to a kind of rebecca system calibration device and using method thereof specifically.

Background technology

Existing boresight utilizes level meter, target plate in kind and boresight fixture assembly to carry out, target plate is placed far away, general 22 meters (see accompanying drawing 1), occupy hall space, and be manual working pattern, homogeneity of product is poor, when every airplane is measured, measuring equipment is debugged repeatedly, and manual measurement exists certain personal error, measures out of true.Boresight fixture must be arranged on radar antenna, easily causes the scuffing of radar antenna.

Utility model content

The object of the invention is to solve the problem, a kind of rebecca system calibration device and using method thereof are provided.

In order to realize object of the present invention, the technical solution used in the present invention is:

A kind of rebecca system calibration device, comprise computer, laser tracker, electrolevel, servo control mechanism, target apparatus, computer is connected with laser tracker and servo control mechanism respectively by cable, laser tracker is arranged on servo control mechanism, servo control mechanism is arranged on electrolevel, and target apparatus receives laser tracker signal.

Described target apparatus comprises photoelectric sensor, target, bubble, target stand, rebound, radar, radar frame, target and bubble, photoelectric sensor is installed on target stand, and target stand is arranged on rebound, rebound to be arranged on radar frame and to be positioned at above radar, and radar is fixed on radar frame.

Use a method for above-mentioned rebecca system calibration device, its step is as follows: 1) by aircraft level-off, makes the surving coordinate system of laser tracker and the assembling coordinate system one of aircraft general assembly (GA) erect-position, and the bubble on adjustment radar boresight fixture assembly is placed in the middle; 2) selected two reference points 2 can determining the aircraft axis of symmetry ^#, 12 ^#in computing machine, construct the aircraft axis of symmetry, laser tracker sends laser measurement signal to boresight fixture assembly, and the position signalling of boresight fixture assembly feeds back to laser tracker, computing machine is controlled laser tracker by servo control mechanism, realizes laser tracker to 2 of target ^#, 12 ^#reference point is aimed at; 3) calculate also figure by computer construction and show the deviation of the relative aircraft system surface level of radar mounting direction and the axis of symmetry, make operating personnel according to the TipWizard of graphic, the reading of aircraft axis of symmetry data, the measurement of target point automatic or manual, the calculating of radar pitch deviation, the calculating of radar bearing deviation can be realized successively; 4) according to the proposition site error of computing machine, artificial adjustment radar points to, and after adjustment, repeats step 3, until reach boresight requirement.

Beneficial effect of the present invention is: 1, during calibration, and discord radar antenna directly contacts, and therefore can not damage radar.2, virtual target plate can be utilized to replace original target plate in kind, and greatly reduce measurement area, what eliminate target plate puts work simultaneously, reduces labour cost, shortens the production cycle of aircraft.3, adopt high-precision laser measuring equipment, improve the degree of accuracy of measurement and the consistance of duplicate measurements, increase substantially the pointing accuracy of aircraft, thus promote the operational performance of aircraft.

Accompanying drawing explanation

Fig. 1 is the radar system boresight fixture assembly do not improved,

Fig. 2 is structural representation of the present invention,

Fig. 3 is target apparatus structural representation of the present invention.

Embodiment

Below in conjunction with drawings and Examples, the present invention is further described:

Embodiment: see Fig. 1, Fig. 2, Fig. 3.

A kind of rebecca system calibration device, comprise computer 1, laser tracker 2, electrolevel 5, servo control mechanism 3, target apparatus 4, computer 1 is connected with laser tracker 2 and servo control mechanism 3 respectively by cable, laser tracker 2 is arranged on servo control mechanism 3, servo control mechanism 3 is arranged on electrolevel 5, and target apparatus 4 receives laser tracker 2 signal.

Described target apparatus 4 comprises photoelectric sensor 43, target 41, bubble 42, target stand 44, rebound 47, radar 45, radar frame 46, target 41, bubble 42, photoelectric sensor 43 are installed on target stand 44, target stand 44 is arranged on rebound 47, rebound 47 to be arranged on radar frame 46 and to be positioned at above radar 45, and radar 45 is fixed on radar frame 46.

A using method for above-mentioned rebecca system calibration, its step is as follows: 1) by aircraft level-off, makes the surving coordinate system of laser tracker and the assembling coordinate system one of aircraft general assembly (GA) erect-position, and the bubble on adjustment radar boresight fixture assembly is placed in the middle; 2) selected two reference points 2 can determining the aircraft axis of symmetry ^#, 12 ^#in computing machine, construct the aircraft axis of symmetry, laser tracker sends laser measurement signal to boresight fixture assembly, and the position signalling of boresight fixture assembly feeds back to laser tracker, computing machine is controlled laser tracker by servo control mechanism, realizes laser tracker to 2 of target ^#, 12 ^#reference point is aimed at; 3) calculate also figure by computer construction and show the deviation of the relative aircraft system surface level of radar mounting direction and the axis of symmetry, make operating personnel according to the TipWizard of graphic, the reading of aircraft axis of symmetry data, the measurement of target point automatic or manual, the calculating of radar pitch deviation, the calculating of radar bearing deviation can be realized successively; 4) according to the proposition site error of computing machine, artificial adjustment radar points to, and after adjustment, repeats step 3, until reach boresight requirement.

The described laser tracker that utilizes measures 2#, 12# reference point, and the step of the computer construction aircraft axis of symmetry is as follows:

1) laser tracker is utilized to measure 2#, 12# two reference point P _2#, P _12#:

P _2#＝(x _2#,y _2#,z _2#),P _12#＝(x _12#,y _12#,z _12#)；

2) by P _2#, P _12#be projected to XOZ plane, obtain subpoint P ⊥ XOZ 2#, P ⊥ XOZ 12#:

P⊥XOZ 2#＝(x _2#,0,z _2#),P⊥XOZ 12#＝(x _12#,0,z _12#)；

3) then namely P ⊥ XOZ 2#P ⊥ XOZ 12# determines aircraft axis of symmetry L;

$L\left(x\right)=P_{12\#}^{\⊥\mathrm{xoz}}+x\·d,$ Wherein $d=\frac{P_{12\#}^{\⊥\mathrm{XOZ}}{P}_{2\#}^{\⊥\mathrm{XOZ}}}{\left|\right|P_{12\#}^{\⊥\mathrm{XOZ}}{P}_{2\#}^{\⊥\mathrm{XOZ}}\left|\right|},$ Characterize the direction of aircraft axis of symmetry L.

Described calculating the figure display relative aircraft system surface level of radar mounting direction and the deviation step of the axis of symmetry comprise:

1) laser tracker is utilized to measure 2 target point P _m1, P _m2:

P _M1＝(x _M1,y _M1,z _M1),P _M2＝(x _M2,y _M2,z _M2)；

2) according to P _m1=(x _m1, y _m1, z _m1), P _m2=(x _m2, y _m2, z _m2), by it to XOZ plane projection, the azimuthal error θ of radar can be calculated _yaw:

${\mathrm{\θ}}_{\mathrm{yaw}}=\arctan \frac{z_{M2}-z_{M1}}{x_{M2}-x_{M1}}$

3) according to P _m1=(x _m1, y _m1, z _m1), P _m2=(x _m2, y _m2, z _m2), it is projected to XOY plane, the pitch error θ of radar can be calculated _pitch:

${\mathrm{\θ}}_{\mathrm{pitch}}=\arctan \frac{y_{M1}-y_{M2}}{x_{M2}-x_{M1}}$

4) position of the aiming point of radar on simulation target plate is calculated

----target point P _m1subpoint on simulation target,

----target point P _mAsubpoint on simulation target,

Dev=D × tan Ф---- relatively side-play amount, wherein,

D----target point P _m1to the distance of actual target plate,

Ф---the drift angle, space of the relative aircraft axis of symmetry of-radar, it is calculated as follows

First, direction, radar course is calculated:

$d_{\mathrm{racours}}=\frac{P_{M1}{P}_{M2}}{\left|\right|P_{M1}{P}_{M2}\left|\right|}$

Then, $\mathrm{\φ}=\arccos \frac{d\·d_{\mathrm{racours}}}{\left|\right|d\left|\right|\·\left|\right|d_{\mathrm{racours}}\left|\right|}=\arccos (d\·d_{\mathrm{racours}}),$

if(Ф﹥π/2),Ф＝π-Ф；

Aiming point computation process as follows:

By P _m1p _m2determine straight line L _r

L _R(x)＝P _M1+x·d _R

Wherein characterize straight line L _rdirection,

Then, P _mA=L _r(t ')=P _m1+ t ' d _r, wherein,

According to $P_{\mathrm{MA}}^{\⊥}=(0,y_{\mathrm{MA}},Z_{\mathrm{MA}}),$ Namely aiming point position is tried to achieve

When measuring target spot, the error of laser tracker is mainly derived from: the measuring error of laser tracker, the positioning error of target mount pad, laser tracker turns station error and ground vibrations error, and the source of error reducing laser tracker can improve precision further.Radar install after orientation, pitch error output control is in ± 1 ' scope.

One of preferred embodiment that what embodiments of the invention were announced is also, but to be not limited thereto, those of ordinary skill in the art, very easily according to above-described embodiment, to understand spirit of the present invention, and make different

Amplification and change, but only otherwise depart from spirit of the present invention, all in protection scope of the present invention.

Claims (3)

1. a rebecca system calibration device, comprise computer, laser tracker, electrolevel, servo control mechanism, target apparatus, it is characterized in that: computer is connected with laser tracker and servo control mechanism respectively by cable, laser tracker is arranged on servo control mechanism, servo control mechanism is arranged on electrolevel, and target apparatus receives laser tracker signal.

2. a kind of rebecca system calibration device according to claim 1, it is characterized in that: described target apparatus comprises photoelectric sensor, target, bubble, target stand, rebound, radar, radar frame, target, bubble, photoelectric sensor are installed on target stand, target stand is arranged on rebound, rebound to be arranged on radar frame and to be positioned at above radar, and radar is fixed on radar frame.

3. the using method with rebecca system calibration device according to claim 1, its characterization step is as follows: 1) by aircraft level-off, make the surving coordinate system of laser tracker and the assembling coordinate system one of aircraft general assembly (GA) erect-position, the bubble on adjustment radar boresight fixture assembly is placed in the middle; 2) selected two reference points can determining the aircraft axis of symmetry, the aircraft axis of symmetry is constructed in computing machine, laser tracker sends laser measurement signal to boresight fixture assembly, the position signalling of boresight fixture assembly feeds back to laser tracker, computing machine is controlled laser tracker by servo control mechanism, realizes laser tracker and aims at two of target reference points; 3) calculate also figure by computer construction and show the deviation of the relative aircraft system surface level of radar mounting direction and the axis of symmetry, make operating personnel according to the TipWizard of graphic, the reading of aircraft axis of symmetry data, the measurement of target point automatic or manual, the calculating of radar pitch deviation, the calculating of radar bearing deviation can be realized successively; 4) according to the proposition site error of computing machine, artificial adjustment radar points to, and after adjustment, repeats step 3, until reach boresight requirement.