CN106842151A - Based on the Passive Positioning method of testing that guinea pig system interference source azimuth angle is constant - Google Patents

Abstract

The invention provides based on the constant Passive Positioning method of testing of guinea pig system interference source azimuth angle, it is characterised in that step is as follows：1) laboratory simulation interference source signal bugle is placed on the position that radar system azimuth is α, α is between ± 10 °~± 55 °；2) airborne sensor parameter value initial setting up, carrier aircraft ground velocity Ve, inertia height He, carrier aircraft original heading angle beta are carried out on avionics system simulator₀, the initial longitude Lon of carrier aircraft₀, latitude Lat₀, carrier aircraft angle of climb θ, interference source speed Vj, interference source height Hj, interference source longitude Lonj, latitude Latj, carrier aircraft is with interference source starting GPS apart from R₀；3) after radar enters the working method of Passive Positioning interference source, start carrier aircraft course angle β and press avionics system simulator update cycle dt automatic Iteratives and calculate, to ensure the radar system azimuth angle alpha of interference source after each data update cycle in assigned error range delta₀Within keep constant, azimuth angle error Δ is.

Description

Based on the Passive Positioning method of testing that guinea pig system interference source azimuth angle is constant

Technical field

The invention belongs to airborne fire control radar field, it is related to the test of radar Passive Positioning interference source working method to verify.

Background technology

The purpose of Passive Positioning is the angle measurement data that is received using radar and carrier aircraft navigation data will be by by nonlinear filtering Target or interference source kinematic parameter such as position, speed, the acceleration estimation of tracking are out.

Airborne radar when being positioned to ground/sea clutter jamming source using Passive Positioning interference source function, in carrier aircraft flight course, Ground/sea is static or slow motion interference source is usually what is be continually changing relative to the Department of Geography azimuth of carrier aircraft radar.Laboratory is tested Can realize simulating by two ways in environment：One is that the electromagnetic horn that will simulate interference source echo passes through programme-control in two dimension Motion in plane or ball surface；Two is the programmed rotation on turntable of radar frame.But both approaches are required on a large scale Mechanical device, and it is very high for the requirement in place, and the laboratory typically taken a flight test in outfield cannot be realized.

The content of the invention

The purpose of the present invention is：The correctness and precision of checking radar Passive Positioning algorithm and Project Realization are tested by ground simulation Level, so as to reach the purpose for shortening the cycle of taking a flight test and reducing funds expenditure.

The technical scheme is that：

1) laboratory simulation interference source signal bugle is placed on the position that radar system azimuth is α, α is at ± 10 °~± 55 ° Between；

2) airborne sensor parameter value initial setting up, carrier aircraft ground velocity Ve, inertia height He, carrier aircraft are carried out on avionics system simulator Original heading angle beta₀, the initial longitude Lon of carrier aircraft₀, latitude Lat₀, carrier aircraft angle of climb θ, interference source speed Vj, interference source are high Degree Hj, interference source longitude Lonj, latitude Latj, carrier aircraft is with interference source starting GPS apart from R₀；

3) after radar enters the working method of Passive Positioning interference source, start carrier aircraft course angle β and press the avionics system simulator update cycle Dt automatic Iteratives are calculated, to ensure the radar system azimuth angle alpha of interference source after each data update cycle in assigned error range delta₀ Within keep constant, azimuth angle error Δ is：

If Δ >=Δ₀, then：

β_i+1=β_i+Δ₁ (2)

If Δ<Δ₀, then：

β_i+1=β_i (3)

Flag_V wherein in (1) formula_iAnd flag_H_iWhen respectively avionics system simulator updated for i-th (i=0,1 ... ...) individual cycle GPS between carrier aircraft and interference source is apart from R_iVertically to horizontal direction component；

flag_V_i+1=flag_V_i-Ve×dt×cosβ_i+1 (4)

flag_H_i+1=flag_H_i-Ve×dt×sinβ_i+1 (5)

As i=0：

4) by the iteration of course angle β, the longitude and latitude degrees of data of carrier aircraft is automatically updated, it is public according to the carrier aircraft longitude and latitude that course angle updates Formula is as follows：

Wherein:

RR=6378137/sqrt (1-0.00669449 × sin (Lat_i)×sin(Lon_i)) (10)

5) Radar Intercept interference source, after being transferred to the mode of Passive Positioning interference source, radar is by the distance of real-time output tracking interference source Rj_i, the real time GPS distance between the carrier aircraft and interference source of avionics system simulator simulation is R_i, by Rj_iWith R_iContrasted, realized Test checking to the correctness and precision level of radar Passive Positioning interference source Passive Positioning algorithm and Project Realization.

The advantage and purposes of the invention：The large-scale mechanical device of original ground simulation method of testing needs, and for The requirement in place is very high, and existing outfield experiment in flight test room cannot meet these requirements substantially.Radar to sea, calculate over the ground by Passive Positioning The correctness and precision of method, can only take a flight test to be confirmed, to verify that the function generally requires the adjustment of 3~5 sorties by adjustment Take a flight test work, this consumes human and material resources, financial resources significantly.

This method determines whether the precision of analogue data disclosure satisfy that the requirement of Passive Positioning algorithm by emulating, and can tentatively quantify Judge that the convergence time and positioning precision of Passive Positioning change with time situation, then precision can be carried out by record data Analysis.

The more and more a kind of antijamming measures having as various airborne fire control radar of Passive Positioning interference source, by being based on The constant Passive Positioning interference source ground test method of guinea pig system interference source azimuth angle, can be quick in routine experimentation room environmental Checking Passive Positioning algorithm and Project Realization correctness and precision level, so as to reach shortening take a flight test the cycle and reduce funds expenditure Purpose.

Brief description of the drawings

Fig. 1 is that, based on the constant interference source Passive Positioning carrier aircraft course angle more new diagram of radar system azimuth angle alpha, β is load in figure Machine course angle, α is the radar system azimuth of interference source, R_iIt is carrier aircraft and the GPS distances of interference source, flag_V_iAnd flag_H_i Respectively R_iVertically to horizontal direction component.

Fig. 2 automatically updates iteration changing trend diagram for carrier aircraft course angle β, and abscissa is bus update cycle number, and ordinate is load Machine course angle, unit degree；

Fig. 3 is that carrier aircraft longitude and latitude updates changing trend diagram with course angle β iteration, and lines are carrier aircraft longitude and latitude variation track, circle It is interference source longitude and latitude.

Specific embodiment

The present invention is described in further details below.Based on the Passive Positioning test side that guinea pig system interference source azimuth angle is constant Method, it is characterised in that step is as follows：

1) laboratory simulation interference source signal bugle is placed on the position that radar system azimuth is α, if α=27.26 °；

2) airborne sensor parameter value initial setting up, carrier aircraft ground velocity Ve=400 meter per seconds, inertia height are carried out on avionics system simulator He=3000 meters, carrier aircraft original heading angle beta₀=0 °, the initial longitude Lon of carrier aircraft₀=110.5 °, latitude Lat₀=18 °, carrier aircraft Angle of climb θ=5.1 °, interference source starting is apart from R₀=200000 meters, interference source speed Vj=0, Hj=10 meters of source height of interference, Interference source longitude is 111.37 °, and latitude is 19.6 °；

3) after radar enters the working method of Passive Positioning interference source, start carrier aircraft course angle β and press the avionics system simulator update cycle Dt=50ms automatic Iteratives are calculated, to ensure the radar system azimuth angle alpha of interference source after each data update cycle in assigned error Range delta₀Keep constant within=1e-4, azimuth angle error Δ is：

If Δ >=1e-4,：

β_i+1=β_i+1e-8 (2)

If Δ<1e-4, then：

β_i+1=β_i (3)

It is as shown in Figure 2 that carrier aircraft course angle β automatically updates iteration variation tendency.

Flag_V wherein in (1) formula_iAnd flag_H_iWhen respectively avionics system simulator updated for i-th (i=0,1 ... ...) individual cycle GPS between carrier aircraft and interference source is apart from R_iVertically to horizontal direction component.

flag_V_i+1=flag_V_i-Ve×dt×cosβ_i+1 (4)

flag_H_i+1=flag_H_i-Ve×dt×sinβ_i+1 (5)

As i=0：

4) by the iteration of course angle β, the longitude and latitude degrees of data of carrier aircraft is automatically updated, it is public according to the carrier aircraft longitude and latitude that course angle updates Formula is as follows：

Wherein:

RR=6378137/sqrt (1-0.00669449 × sin (Lat_i)×sin(Lon_i)) (10)

It is as shown in Figure 3 that carrier aircraft longitude and latitude updates variation tendency with course angle β iteration.

Real time GPS between the carrier aircraft and interference source of avionics system simulator simulation is apart from R_iKeep constant with radar bearing angle α in theory GPS distance versus between the carrier aircraft and interference source that are calculated under state obtain the error of the two 0.4% or so, meet radar passive The requirement of correctness and precision level the test checking of location interference source Passive Positioning algorithm and Project Realization；

5) Radar Intercept interference source, after being transferred to the mode of Passive Positioning interference source, radar by real-time output tracking interference source away from From Rj_i, the real time GPS distance between the carrier aircraft and interference source of avionics system simulator simulation is R_i, by Rj_iWith R_iContrasted, Realize the test checking to the correctness and precision level of radar Passive Positioning interference source Passive Positioning algorithm and Project Realization.

Claims (1)

1. based on the Passive Positioning method of testing that guinea pig system interference source azimuth angle is constant, it is characterised in that step is as follows：

1) laboratory simulation interference source signal bugle is placed on the position that radar system azimuth is α, α is at ± 10 °~± 55 ° Between；

2) airborne sensor parameter value initial setting up, carrier aircraft ground velocity Ve, inertia height He, carrier aircraft are carried out on avionics system simulator Original heading angle beta₀, the initial longitude Lon of carrier aircraft₀, latitude Lat₀, carrier aircraft angle of climb θ, interference source speed Vj, interference source are high Degree Hj, interference source longitude Lonj, latitude Latj, carrier aircraft is with interference source starting GPS apart from R₀；

3) after radar enters the working method of Passive Positioning interference source, start carrier aircraft course angle β and press the avionics system simulator update cycle Dt automatic Iteratives are calculated, to ensure the radar system azimuth angle alpha of interference source after each data update cycle in assigned error range delta₀ Within keep constant, azimuth angle error Δ is：

$\mathrm{\&Delta;}=\frac{\mathrm{\&pi;}}{2}-arctan\left(\frac{flag\_V_{i+1}}{flag\_H_{i+1}}\right)-{\mathrm{\&beta;}}_i-\mathrm{\&alpha;}---\left(1\right)$

If △ >=△₀, then：

β_i+1=β_i+△₁ (2)

If △<△₀, then：

β_i+1=β_i (3)

Flag_V wherein in (1) formula_iAnd flag_H_iWhen respectively avionics system simulator updated for i-th (i=0,1 ... ...) individual cycle GPS between carrier aircraft and interference source is apart from R_iVertically to horizontal direction component；

flag_V_i+1=flag_V_i-Ve×dt×cosβ_i+1 (4)

flag_H_i+1=flag_H_i-Ve×dt×sinβ_i+1 (5)

As i=0：

$flag\_V_0=R_0\&times;cos(\frac{\mathrm{\&pi;}}{2}-{\mathrm{\&beta;}}_0-\mathrm{\&alpha;})---\left(6\right)$

$flag\_H_0=R_0\&times;sin(\frac{\mathrm{\&pi;}}{2}-{\mathrm{\&beta;}}_0-\mathrm{\&alpha;})---\left(7\right)$

4) by the iteration of course angle β, the longitude and latitude degrees of data of carrier aircraft is automatically updated, it is public according to the carrier aircraft longitude and latitude that course angle updates Formula is as follows：

${\mathrm{Lat}}_{i+1}={\mathrm{Lat}}_i+\frac{Ve\&times;cos\mathrm{\&theta;}\&times;{\mathrm{cos\&beta;}}_i\&times;dt}{RR}---\left(8\right)$

${\mathrm{Lon}}_{i+1}={\mathrm{Lon}}_i+\frac{Ve\&times;cos\mathrm{\&theta;}\&times;{\mathrm{sin\&beta;}}_i\&times;dt}{RR\&times;cos\left({\mathrm{Lat}}_i\right)}---\left(9\right)$

Wherein:

RR=6378137/sqrt (1-0.00669449 × sin (Lat_i)×sin(Lon_i)) (10)

5) Radar Intercept interference source, after being transferred to the mode of Passive Positioning interference source, radar is by the distance of real-time output tracking interference source Rj_i, the real time GPS distance between the carrier aircraft and interference source of avionics system simulator simulation is R_i, by Rj_iWith R_iContrasted, realized Test checking to the correctness and precision level of radar Passive Positioning interference source Passive Positioning algorithm and Project Realization.