?? jave-ppp.txt
字號:
if(tsec >= allBC[prn][mxrow].gBCjts()){ return mxrow; } //*** last row
//*** increment until upper point passes the given time
for(int i=1; i<=mxrow-1; ++i) {
if(allBC[prn][i+1].gBCjts() >= tsec){
if(Math.abs(tsec-allBC[prn][i ].gBCjts()) <
Math.abs(tsec-allBC[prn][i+1].gBCjts())) { return i; }
else { return i+1; }
}
}
//*** fell thru loop -- not allowed
System.err.println("Loop prob in locBC() " + prn + " " + tsec);
System.exit(1);
return -1;
}
}
//************************************************************************
class BCstuf {
//*** broadcast orbit object
private static final double gm = 3.986005e14;
private static final double we = 7.2921151467e-5; //*** rad/sec
private static final double gpspi = 3.1415926535898e0;
private static final double bigf = -4.442807633e-10;
private int id; //* my id (just a serial number)
private double jts; //* my time for lookup index
private int prn; //* prn id
//*** clock parameters
private double t0c; //* clock corrector reference epoch (s)
private double af0; //* clock offset (s)
private double af1; //* clock error rate (s/s)
private double af2; //* clock error accelleration (s/(s*s))
//*** kepler elements
private double t0e; //* reference epoch of ephemeris (sow)
private double sqrta; //* square root of semimajor axis sqrt(m)
private double e; //* eccentricity
private double eye0; //* inclination at ref. epoch (r)
private double omg0; //* right ascension of asc. node at ref. epoch (r)
private double w; //* argument of perigee (r)
private double em0; //* mean anomaly at ref. epoch (r)
//*** perturbation parameters
private double deln; //* mean motion difference from computed value (r/s)
private double eyedot; //* rate of change of inclination (r/s)
private double omgdot; //* rate of change of right ascension (r/s)
private double cuc; //* cosine harmonic correction to arg. of lat. (r)
private double cus; //* sine harmonic correction to arg. of lat. (r)
private double crc; //* cosine harmonic correction to radius (m)
private double crs; //* sine harmonic correction to radius (m)
private double cic; //* cosine harmonic correction to inclination (r)
private double cis; //* sine harmonic correction to inclination (r)
//*** other data
private double iode; //* issue of data ephemeris
private double l2cd; //* codes on l2 channel (binary, 01-p, 10-c/a)
private double wkno; //* gps week # (to go with toe) (wk)
private double l2pd; //* l2 p data flag (binary, 0-norm, 1-set off)
private double svac; //* URA index (converted) (m)
private double svhl; //* sv health (6 bits, 0-ok, 1-not)
private double tgd; //* est. group delay (tsv-tgd) (s)
private double iodc; //* issue of data clock
private double tot; //* transmission time of message (sow)
//*****
//***** methods
//*****
public BCstuf(int myid) {id=myid;}
public int getBC() {return id;}
public double gBCjts() {return jts;}
public String toString() {return "" + id;}
public int gBCprn() {return prn;}
public double gBCt0c() {return t0c;}
public double gBCt0e() {return t0e;}
public double gBCwkno() {return wkno;}
public double gBCsvac() {return svac;}
public double gBCsvhl() {return svhl;}
public double gBCtot() {return tot;}
//*****
//***** load methods
//*****
public void put0BC(String myString, int myid, Gtime tStuf) {
//*** load record (epoch and clock)
//*** y2k code fails after 2079
//*** clock parameters
String subField;
int iyr,imo,idy,ihr,imn;
double sec,tsec;
subField = myString.substring( 0, 2);
prn = Integer.parseInt(subField.trim());
subField = myString.substring( 2, 5);
iyr = Integer.parseInt(subField.trim());
if (iyr < 80) {iyr=iyr+2000;} //*** y2k
else if(iyr <= 99) {iyr=iyr+1900;} //*** fail 2080
subField = myString.substring( 5, 8);
imo = Integer.parseInt(subField.trim());
subField = myString.substring( 8, 11);
idy = Integer.parseInt(subField.trim());
subField = myString.substring(11, 14);
ihr = Integer.parseInt(subField.trim());
subField = myString.substring(14, 17);
imn = Integer.parseInt(subField.trim());
subField = myString.substring(17, 22);
sec = Double.valueOf(subField.trim()).doubleValue();
//*** if first epoch, check to establish time offset
if(myid <= 1){
if(tStuf.getMjd0() <= -1){
System.err.println("Time was set in nav file -- check obs file");
tStuf.setjd0(iyr, imo, idy);
}
}
jts = tStuf.civjts(iyr,imo,idy,ihr,imn,sec); //*** also used for index
t0c = tStuf.jtssow(jts);
subField = myString.substring(22, 41).replace('D','e');
af0 = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(41, 60).replace('D','e');
af1 = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(60, 79).replace('D','e');
af2 = Double.valueOf(subField.trim()).doubleValue();
}
public void put1BC(String myString) {
//*** load record (BC Orbit 1)
String subField;
subField = myString.substring( 3, 22).replace('D','e');
iode = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(22, 41).replace('D','e');
crs = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(41, 60).replace('D','e');
deln = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(60, 79).replace('D','e');
em0 = Double.valueOf(subField.trim()).doubleValue();
}
public void put2BC(String myString) {
//*** load record (BC Orbit 2)
String subField;
subField = myString.substring( 3, 22).replace('D','e');
cuc = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(22, 41).replace('D','e');
e = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(41, 60).replace('D','e');
cus = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(60, 79).replace('D','e');
sqrta = Double.valueOf(subField.trim()).doubleValue();
}
public void put3BC(String myString) {
//*** load record (BC Orbit 3)
String subField;
subField = myString.substring( 3, 22).replace('D','e');
t0e = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(22, 41).replace('D','e');
cic = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(41, 60).replace('D','e');
omg0 = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(60, 79).replace('D','e');
cis = Double.valueOf(subField.trim()).doubleValue();
}
public void put4BC(String myString) {
//*** load record (BC Orbit 4)
String subField;
subField = myString.substring( 3, 22).replace('D','e');
eye0 = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(22, 41).replace('D','e');
crc = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(41, 60).replace('D','e');
w = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(60, 79).replace('D','e');
omgdot = Double.valueOf(subField.trim()).doubleValue();
}
public void put5BC(String myString) {
//*** load record (BC Orbit 5)
String subField;
subField = myString.substring( 3, 22).replace('D','e');
eyedot = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(22, 41).replace('D','e');
l2cd = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(41, 60).replace('D','e');
wkno = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(60, 79).replace('D','e');
l2pd = Double.valueOf(subField.trim()).doubleValue();
}
public void put6BC(String myString) {
//*** load record (BC Orbit 6)
String subField;
subField = myString.substring( 3, 22).replace('D','e');
//*** troublesome field in gait nav file
try {
svac = Double.valueOf(subField.trim()).doubleValue();
}
catch (NumberFormatException e) {
//****System.err.println("Reset acc. for " + subField.trim());
svac = 384.0;
}
subField = myString.substring(22, 41).replace('D','e');
svhl = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(41, 60).replace('D','e');
tgd = Double.valueOf(subField.trim()).doubleValue();
subField = myString.substring(60, 79).replace('D','e');
iodc = Double.valueOf(subField.trim()).doubleValue();
}
public void put7BC(String myString) {
//*** load record (BC Orbit 7)
String subField;
subField = myString.substring( 3, 22).replace('D','e');
tot = Double.valueOf(subField.trim()).doubleValue();
}
//*****
//***** compute methods
//*****
public PosT bcxyzt (double tsv, Modes myModes) {
//*** compute pos of broadcast orbit (BC) for a single time
//*** sense of the corrector (with relativity) is: t=tsv-dt-dtr
//*** BC is in GPS system time (use clock corr, time in sec.of.week)
double dt, dtr, bcclok;
//*** correct satellite time
dt = bcclok1(tsv); //*** icd-200 20.3.3.3.3.1
dtr = bcclok2(tsv,dt);
bcclok = dt+dtr;
//*** icd-200 20.3.3.3.3.2 (not dual and not b-cast iono)
if( (!myModes.isdFreq()) && (!myModes.isbIon())) bcclok = bcclok - tgd;
//*** compute broadcast position at corrected time
return bcxyz(tsv-bcclok, bcclok, dtr);
}
public double bcclok1 (double t) {
//*** compute satellite clock correction (non-relativity term)
//*** sense of the corrector is: t=tsv-dt
double dt;
if( (t-t0c) > 302400.0 ) t=t-604800.0; //*** handle week rollover
if( (t-t0c) <-302400.0 ) t=t+604800.0; //*** valid icd200
dt=af0+af1*(t-t0c)+af2*(t-t0c)*(t-t0c); //*** valid icd200
return dt;
}
public double bcclok2 (double t, double dt) {
//*** compute satellite clock correction (relativity term)
//*** sense of the corrector is: t=tsv-dt-dtr
double dtr; //*** relativity term
double ek;
if( (t-t0c) > 302400.0 ) t=t-604800.0; //*** handle week rollover
if( (t-t0c) <-302400.0 ) t=t+604800.0; //*** valid icd200
//*** relativity term
ek=eccano(t-dt);
dtr=bigf*e*sqrta*Math.sin(ek); //*** valid icd200
return dtr;
}
public PosT bcxyz(double t, double bcclok, double dtr) {
//*** compute ECBF XYZ at time t from broadcast elements
//*** units: seconds, meters, radians
//*** note: t corrected for SV clock error, also passed in bcclok
//*** note: also passing relativitistic correction
double a,en0,tk,en,emk,ek,sinek,cosek,f,u,cu2,su2,duk,drk,dik;
double uk,rk,eyek,ceyek,xpk,ypk,omgk,comgk,somgk,xk,yk,zk;
if( (t-t0e) > 302400.0 ) t=t-604800.0; //*** handle week rollover
if( (t-t0e) <-302400.0 ) t=t+604800.0; //*** valid icd200
//*** mean motion
a = sqrta*sqrta;
en0 = Math.sqrt(gm/(a*a*a));
//*** time since orbit reference epoch
tk = t-t0e;
//*** corrected mean motion
en = en0+deln;
//*** mean anomaly, M
emk = em0+en*tk;
//*** solve kepler's equation for eccentric anomaly, E
ek = kepEQ(emk);
sinek = Math.sin(ek);
cosek = Math.cos(ek);
//*** true anomaly, f
f = Math.atan2( Math.sqrt(1.0-e*e)*sinek, cosek-e);
//*** argument of latitude, u
u = f+w;
cu2 = Math.cos(u+u);
su2 = Math.sin(u+u);
//*** corrections to the arg. of lat., radius, and inclination
duk = cuc*cu2+cus*su2;
drk = crc*cu2+crs*su2;
dik = cic*cu2+cis*su2;
//*** correct the arg. of lat., radius, and inclination
uk = u + duk;
rk = a*(1.0-e*cosek) + drk;
eyek = eye0+eyedot*tk + dik;
ceyek = Math.cos(eyek);
//*** position in the orbital plane
xpk = rk*Math.cos(uk);
ypk = rk*Math.sin(uk);
//*** correct the longitude of the ascending node
omgk = omg0+(omgdot-we)*tk-we*t0e;
comgk = Math.cos(omgk);
somgk = Math.sin(omgk);
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