CAJ | 학술논문

基于伪距测量的卫星导航方法，实现3D定位测速至少需要4颗可观测卫星。为减少所需可观测卫星数量以提高导航算法的适应性，利用惯导误差不断累积的特性，在单个较短导航周期内将惯导误差看作常值，将直接求解导弹位置和速度转化为对惯导误差的求解，从而将未知数由时变量转化为短时间内不随时间改变的量，以适应用多次测量代替多星同时联测，构造观测方程实现单星定位测速。由于导航周期为4个观测周期，比多星导航方法导航周期长，且将单个导航周期内惯导误差看作常值，引入了额外误差，但仿真结果表明，仍能在一定程度上保证导航精度。
기우위거측량적위성도항방법，실현3D정위측속지소수요4과가관측위성。위감소소수가관측위성수량이제고도항산법적괄응성，이용관도오차불단루적적특성，재단개교단도항주기내장관도오차간작상치，장직접구해도탄위치화속도전화위대관도오차적구해，종이장미지수유시변량전화위단시간내불수시간개변적량，이괄응용다차측량대체다성동시련측，구조관측방정실현단성정위측속。유우도항주기위4개관측주기，비다성도항방법도항주기장，차장단개도항주기내관도오차간작상치，인입료액외오차，단방진결과표명，잉능재일정정도상보증도항정도。
Four available satellites are needed in traditional 3D positioning method based on pseudo-range measuring. Aiming at reducing the needed satellites to enhance the adaptability of the navigation algorithm, in view of the cumulative characteristics of the INS error which can be seemed as a constant in single short period, the problem of calculating missile position and velocity which is varied with time was converted to calculating INS error which is constant in single period. Therefore, 4 satellites measuring could be replaced by 4 times measuring to the same satellite and the measuring equations were built to realize the positioning and velocity measuring using one satellite. The performance of the method in this paper was inferior to traditional method, because its navigation period was longer and the additional error was induced by regarding the INS error as a constant in a single navigation period, but the simulation result shows that the method of this paper can guarantee navigation precision to a certain extent.