下面是一段matlab生成的读取导航电文的代码：function navData = readRinexNav(filename)
% 检查文件存在性
if ~exist(filename, 'file')
error('文件不存在: %s', filename);
end
% 打开文件
fid = fopen(filename, 'r');
if fid == -1
error('无法打开文件: %s', filename);
end
% 初始化输出结构
navData = struct();
navData.Header = struct();
navData.Ephemeris = struct();
try
% ========== 读取文件头信息 ==========
line = fgetl(fid);
rinexVersion = 2.0; % 默认版本
while ischar(line)
if contains(line, 'END OF HEADER')
break;
end
% 解析RINEX版本
if contains(line, 'RINEX VERSION / TYPE')
rinexVersion = sscanf(line(1:9), '%f');
navData.Header.Version = rinexVersion;
navData.Header.FileType = strtrim(line(21:40));
end
% 解析文件创建信息
if contains(line, 'PGM / RUN BY / DATE')
navData.Header.Program = strtrim(line(1:20));
navData.Header.Creator = strtrim(line(21:40));
navData.Header.Date = strtrim(line(41:60));
end
% 解析电离层参数 (RINEX 2)
if contains(line, 'ION ALPHA') && rinexVersion < 3
ionAlpha = sscanf(line(3:end), '%f %f %f %f');
navData.Header.IonAlpha = ionAlpha;
end
% 解析电离层参数 (RINEX 3)
if contains(line, 'IONOSPHERIC CORR') && rinexVersion >= 3
system = line(1:4);
params = sscanf(line(6:end), '%f %f %f %f');
navData.Header.IonosphericCorr.(system) = params;
end
% 解析时间系统参数
if contains(line, 'TIME SYSTEM CORR')
system = line(1:4);
params = sscanf(line(6:end), '%f %f %f %f');
navData.Header.TimeSystemCorr.(system) = params;
end
% 解析跳秒
if contains(line, 'LEAP SECONDS')
navData.Header.LeapSeconds = sscanf(line(1:6), '%d');
end
line = fgetl(fid);
end
% ========== 读取卫星轨道数据 ==========
% 预分配内存
maxEntries = 10000; % 初始分配大小
navData.Ephemeris.SatelliteID = cell(maxEntries, 1);
navData.Ephemeris.Epoch = zeros(maxEntries, 6); % [年, 月, 日, 时, 分, 秒]
navData.Ephemeris.ClockBias = zeros(maxEntries, 1);
navData.Ephemeris.ClockDrift = zeros(maxEntries, 1);
navData.Ephemeris.ClockDriftRate = zeros(maxEntries, 1);
navData.Ephemeris.IODE = zeros(maxEntries, 1);
navData.Ephemeris.Crs = zeros(maxEntries, 1);
navData.Ephemeris.DeltaN = zeros(maxEntries, 1);
navData.Ephemeris.M0 = zeros(maxEntries, 1);
navData.Ephemeris.Cuc = zeros(maxEntries, 1);
navData.Ephemeris.e = zeros(maxEntries, 1);
navData.Ephemeris.Cus = zeros(maxEntries, 1);
navData.Ephemeris.sqrtA = zeros(maxEntries, 1);
navData.Ephemeris.Toe = zeros(maxEntries, 1);
navData.Ephemeris.Cic = zeros(maxEntries, 1);
navData.Ephemeris.Omega0 = zeros(maxEntries, 1);
navData.Ephemeris.Cis = zeros(maxEntries, 1);
navData.Ephemeris.i0 = zeros(maxEntries, 1);
navData.Ephemeris.Crc = zeros(maxEntries, 1);
navData.Ephemeris.omega = zeros(maxEntries, 1);
navData.Ephemeris.OmegaDot = zeros(maxEntries, 1);
navData.Ephemeris.IDOT = zeros(maxEntries, 1);
navData.Ephemeris.CodesL2 = zeros(maxEntries, 1);
navData.Ephemeris.GPSWeek = zeros(maxEntries, 1);
navData.Ephemeris.L2PFlag = zeros(maxEntries, 1);
navData.Ephemeris.SVAccuracy = zeros(maxEntries, 1);
navData.Ephemeris.SVHealth = zeros(maxEntries, 1);
navData.Ephemeris.TGD = zeros(maxEntries, 1);
navData.Ephemeris.IODC = zeros(maxEntries, 1);
navData.Ephemeris.TransmissionTime = zeros(maxEntries, 1);
navData.Ephemeris.FitInterval = zeros(maxEntries, 1);
entryCounter = 0;
% 读取导航电文体
while ~feof(fid)
line = fgetl(fid);
if ~ischar(line), break; end
% 跳过空行
if isempty(strtrim(line)), continue; end
entryCounter = entryCounter + 1;
if entryCounter > maxEntries
% 动态扩展数组大小
maxEntries = maxEntries * 2;
navData.Ephemeris.SatelliteID{maxEntries} = [];
navData.Ephemeris.Epoch(maxEntries, :) = 0;
navData.Ephemeris.ClockBias(maxEntries) = 0;
navData.Ephemeris.ClockDrift(maxEntries) = 0;
navData.Ephemeris.ClockDriftRate(maxEntries) = 0;
% 其他参数类似扩展...
end
% ===== 解析卫星ID和时间 =====
if rinexVersion < 3
% RINEX 2.x 格式
satID = sscanf(line(1:2), '%d');
if satID < 10
navData.Ephemeris.SatelliteID{entryCounter} = ['G0', num2str(satID)];
else
navData.Ephemeris.SatelliteID{entryCounter} = ['G', num2str(satID)];
end
% 解析历元时间
year = sscanf(line(4:5), '%d');
if year < 80
year = year + 2000;
else
year = year + 1900;
end
month = sscanf(line(7:8), '%d');
day = sscanf(line(10:11), '%d');
hour = sscanf(line(13:14), '%d');
minute = sscanf(line(16:17), '%d');
second = sscanf(line(18:22), '%f');
% 读取时钟参数
clockBias = sscanf(line(23:41), '%f');
clockDrift = sscanf(line(42:60), '%f');
clockDriftRate = sscanf(line(61:79), '%f');
else
% RINEX 3.x 格式
satSys = line(1);
satID = sscanf(line(2:3), '%d');
navData.Ephemeris.SatelliteID{entryCounter} = [satSys, num2str(satID, '%02d')];
% 解析历元时间
year = sscanf(line(5:8), '%d');
month = sscanf(line(10:11), '%d');
day = sscanf(line(13:14), '%d');
hour = sscanf(line(16:17), '%d');
minute = sscanf(line(19:20), '%d');
second = sscanf(line(22:23), '%f');
% 读取时钟参数
clockBias = sscanf(line(24:42), '%f');
clockDrift = sscanf(line(43:61), '%f');
clockDriftRate = sscanf(line(62:80), '%f');
end
% 存储时间和时钟参数
navData.Ephemeris.Epoch(entryCounter, :) = [year, month, day, hour, minute, second];
navData.Ephemeris.ClockBias(entryCounter) = clockBias;
navData.Ephemeris.ClockDrift(entryCounter) = clockDrift;
navData.Ephemeris.ClockDriftRate(entryCounter) = clockDriftRate;
% ===== 读取轨道参数 =====
% 第2行
line = fgetl(fid);
IODE = sscanf(line(4:22), '%f');
Crs = sscanf(line(23:41), '%f');
DeltaN = sscanf(line(42:60), '%f');
M0 = sscanf(line(61:79), '%f');
% 第3行
line = fgetl(fid);
Cuc = sscanf(line(4:22), '%f');
e = sscanf(line(23:41), '%f');
Cus = sscanf(line(42:60), '%f');
sqrtA = sscanf(line(61:79), '%f');
% 第4行
line = fgetl(fid);
Toe = sscanf(line(4:22), '%f');
Cic = sscanf(line(23:41), '%f');
Omega0 = sscanf(line(42:60), '%f');
Cis = sscanf(line(61:79), '%f');
% 第5行
line = fgetl(fid);
i0 = sscanf(line(4:22), '%f');
Crc = sscanf(line(23:41), '%f');
omega = sscanf(line(42:60), '%f');
OmegaDot = sscanf(line(61:79), '%f');
% 第6行
line = fgetl(fid);
IDOT = sscanf(line(4:22), '%f');
CodesL2 = sscanf(line(23:41), '%f');
GPSWeek = sscanf(line(42:60), '%f');
L2PFlag = sscanf(line(61:79), '%f');
% 第7行
line = fgetl(fid);
SVAccuracy = sscanf(line(4:22), '%f');
SVHealth = sscanf(line(23:41), '%f');
TGD = sscanf(line(42:60), '%f');
IODC = sscanf(line(61:79), '%f');
% 第8行 (RINEX 2.x) 或 第7行结束 (RINEX 3.x)
if rinexVersion < 3
line = fgetl(fid);
TransmissionTime = sscanf(line(4:22), '%f');
FitInterval = sscanf(line(23:41), '%f');
else
TransmissionTime = 0;
FitInterval = 0;
end
% 存储轨道参数
navData.Ephemeris.IODE(entryCounter) = IODE;
navData.Ephemeris.Crs(entryCounter) = Crs;
navData.Ephemeris.DeltaN(entryCounter) = DeltaN;
navData.Ephemeris.M0(entryCounter) = M0;
navData.Ephemeris.Cuc(entryCounter) = Cuc;
navData.Ephemeris.e(entryCounter) = e;
navData.Ephemeris.Cus(entryCounter) = Cus;
navData.Ephemeris.sqrtA(entryCounter) = sqrtA;
navData.Ephemeris.Toe(entryCounter) = Toe;
navData.Ephemeris.Cic(entryCounter) = Cic;
navData.Ephemeris.Omega0(entryCounter) = Omega0;
navData.Ephemeris.Cis(entryCounter) = Cis;
navData.Ephemeris.i0(entryCounter) = i0;
navData.Ephemeris.Crc(entryCounter) = Crc;
navData.Ephemeris.omega(entryCounter) = omega;
navData.Ephemeris.OmegaDot(entryCounter) = OmegaDot;
navData.Ephemeris.IDOT(entryCounter) = IDOT;
navData.Ephemeris.CodesL2(entryCounter) = CodesL2;
navData.Ephemeris.GPSWeek(entryCounter) = GPSWeek;
navData.Ephemeris.L2PFlag(entryCounter) = L2PFlag;
navData.Ephemeris.SVAccuracy(entryCounter) = SVAccuracy;
navData.Ephemeris.SVHealth(entryCounter) = SVHealth;
navData.Ephemeris.TGD(entryCounter) = TGD;
navData.Ephemeris.IODC(entryCounter) = IODC;
navData.Ephemeris.TransmissionTime(entryCounter) = TransmissionTime;
navData.Ephemeris.FitInterval(entryCounter) = FitInterval;
end
% 裁剪预分配的多余空间
fields = fieldnames(navData.Ephemeris);
for i = 1:length(fields)
field = fields{i};
if size(navData.Ephemeris.(field), 1) > entryCounter
if iscell(navData.Ephemeris.(field))
navData.Ephemeris.(field) = navData.Ephemeris.(field)(1:entryCounter);
else
navData.Ephemeris.(field) = navData.Ephemeris.(field)(1:entryCounter, :);
end
end
end
% 添加时间向量
navData.Ephemeris.MatlabTime = datetime(...
navData.Ephemeris.Epoch(:,1), ...
navData.Ephemeris.Epoch(:,2), ...
navData.Ephemeris.Epoch(:,3), ...
navData.Ephemeris.Epoch(:,4), ...
navData.Ephemeris.Epoch(:,5), ...
navData.Ephemeris.Epoch(:,6));
fclose(fid);
% 显示成功信息
fprintf('成功读取导航电文文件: %s\n', filename);
fprintf('文件版本: %.1f\n', rinexVersion);
fprintf('卫星系统: %s\n', navData.Header.FileType);
fprintf('包含 %d 个卫星历书条目\n', entryCounter);
catch ME
fclose(fid);
rethrow(ME);
end
end
下面是一段读取观测文件的代码function obsData = readRinexObs(filename)
% 检查文件存在性
if ~exist(filename, 'file')
error('文件不存在: %s', filename);
end
% 打开文件
fid = fopen(filename, 'r');
if fid == -1
error('无法打开文件: %s', filename);
end
% 初始化输出结构
obsData = struct();
obsData.Header = struct();
obsData.Observations = struct();
try
% ========== 读取文件头信息 ==========
line = fgetl(fid);
while ischar(line)
if contains(line, 'END OF HEADER')
break;
end
% 解析RINEX版本
if contains(line, 'RINEX VERSION / TYPE')
obsData.Header.Version = sscanf(line(1:9), '%f');
obsData.Header.FileType = strtrim(line(21:40));
end
% 解析观测值类型
if contains(line, '# / TYPES OF OBSERV')
numTypes = sscanf(line(1:6), '%d');
types = textscan(line(7:60), '%4s', numTypes);
obsData.Header.ObsTypes = strtrim(types{1});
end
% 解析接收机位置
if contains(line, 'APPROX POSITION XYZ')
pos = sscanf(line(1:60), '%f %f %f');
obsData.Header.ApproxPosition = pos;
end
line = fgetl(fid);
end
% 检查头信息完整性
if ~isfield(obsData.Header, 'ObsTypes') || isempty(obsData.Header.ObsTypes)
error('头信息中缺少观测值类型');
end
numObsTypes = length(obsData.Header.ObsTypes);
% ========== 读取观测数据 ==========
% 预分配内存
epochCounter = 0;
maxEpochs = 10000; % 初始分配大小
obsData.Observations.Time = zeros(maxEpochs, 6); % [年, 月, 日, 时, 分, 秒]
obsData.Observations.Satellites = cell(maxEpochs, 1);
obsData.Observations.Values = cell(maxEpochs, 1);
% 读取观测数据体
while ~feof(fid)
line = fgetl(fid);
if ~ischar(line), break; end
% 读取历元行
if length(line) < 32
continue; % 跳过无效行
end
% 解析时间信息
year = sscanf(line(2:5), '%d');
% 检查年份有效性
if isempty(year)
continue; % 跳过无效行
end
% 此时year肯定非空，可以安全比较
if year < 1900
continue; % 跳过无效年份
end
epochCounter = epochCounter + 1;
if epochCounter > maxEpochs
% 动态扩展数组大小
maxEpochs = maxEpochs * 2;
obsData.Observations.Time(maxEpochs, :) = 0;
obsData.Observations.Satellites{maxEpochs} = [];
obsData.Observations.Values{maxEpochs} = [];
end
% 解析历元时间
month = sscanf(line(7:8), '%d');
day = sscanf(line(10:11), '%d');
hour = sscanf(line(13:14), '%d');
minute = sscanf(line(16:17), '%d');
second = sscanf(line(18:29), '%f');
epochFlag = sscanf(line(31:31), '%d');
% 只处理正常数据(epochFlag=0)
if epochFlag ~= 0
% 跳过异常数据
numSats = sscanf(line(33:35), '%d');
% 跳过卫星列表行
for i = 1:ceil(numSats/12)
fgetl(fid);
end
% 跳过所有卫星的观测值
for s = 1:numSats
linesPerSat = ceil(numObsTypes/5);
for l = 1:linesPerSat
fgetl(fid);
end
end
continue;
end
% 存储时间信息
obsData.Observations.Time(epochCounter, :) = [year, month, day, hour, minute, second];
% 解析卫星数量
numSats = sscanf(line(33:35), '%d');
if isempty(numSats) || numSats <= 0 || isnan(numSats) || isinf(numSats)
% 容错处理
warning('无效卫星数量: %s, 跳过该历元', line(33:35));
continue;
end
% 读取卫星列表
satList = '';
satLines = ceil(numSats/12);
for i = 1:satLines
if i == 1
satLine = line(36:end);
else
satLine = fgetl(fid);
end
satList = [satList, strrep(satLine, ' ', '')]; % 移除空格
end
% 提取卫星ID
satellites = cell(numSats, 1);
for i = 1:numSats
startIdx = (i-1)*3 + 1;
satellites{i} = satList(startIdx:startIdx+2);
end
% 存储卫星列表
obsData.Observations.Satellites{epochCounter} = satellites;
% 初始化观测值数组
obsValues = nan(numSats, numObsTypes);
% 读取每个卫星的观测值
for s = 1:numSats
% 确定每颗卫星需要读取的行数
linesPerSat = ceil(numObsTypes/5);
% 读取所有观测值行
satObs = [];
for l = 1:linesPerSat
line = fgetl(fid);
if ~ischar(line)
error('文件意外结束');
end
% 每行最多5个观测值
for o = 1:5
startIdx = (o-1)*16 + 1;
endIdx = min(startIdx+15, length(line));
if startIdx > length(line)
break;
end
% 解析观测值
obsStr = strtrim(line(startIdx:endIdx));
if ~isempty(obsStr)
obsVal = sscanf(obsStr, '%f');
if ~isempty(obsVal)
satObs = [satObs, obsVal];
else
satObs = [satObs, nan]; % 缺失数据
end
end
end
end
% 存储观测值
if length(satObs) > numObsTypes
obsValues(s, :) = satObs(1:numObsTypes);
else
obsValues(s, 1:length(satObs)) = satObs;
end
end
% 存储观测值
obsData.Observations.Values{epochCounter} = obsValues;
end
% 裁剪预分配的多余空间
obsData.Observations.Time = obsData.Observations.Time(1:epochCounter, :);
obsData.Observations.Satellites = obsData.Observations.Satellites(1:epochCounter);
obsData.Observations.Values = obsData.Observations.Values(1:epochCounter);
% 添加观测值类型标签
obsData.Observations.ObsTypes = obsData.Header.ObsTypes;
% 添加时间向量
obsData.Observations.MatlabTime = datetime(...
obsData.Observations.Time(:,1), ...
obsData.Observations.Time(:,2), ...
obsData.Observations.Time(:,3), ...
obsData.Observations.Time(:,4), ...
obsData.Observations.Time(:,5), ...
obsData.Observations.Time(:,6));
fclose(fid);
catch ME
fclose(fid);
rethrow(ME);
end
end请根据这两段代码写一个计算卫星位置的代码
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本文详细介绍了C语言中的格式化输出，包括%d、%i、%u、%o、%x、%X等用于整数的输出，以及%f、%e、%E、%g、%G等用于小数的格式化。此外，还提到了%c和%s分别用于字符和字符串的打印。了解这些格式化指令对于C语言的编程至关重要。
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