diff --git a/AstroLib/AsOrbElemToCart.cpp b/AstroLib/AsOrbElemToCart.cpp
new file mode 100644
index 0000000000000000000000000000000000000000..abf5dee6c18e12ee35fd254d5c1765da813646c0
--- /dev/null
+++ b/AstroLib/AsOrbElemToCart.cpp
@@ -0,0 +1,107 @@
+///***********************************************************************
+/// 轨道六根数变换位置速度
+/// @Author	Guan Yuming
+/// @Date	2023.04.06
+/// @Input
+/// @Param  m_SMajAx;           长半轴 a
+/// @Param  m_Ecc;              偏心率 e
+/// @Param  m_I;                轨道倾角 i
+/// @Param  m_RAAN;             升交点赤经 Omega
+/// @Param  m_ArgPeri;          近供点角 omega
+/// @Param  m_TrueA;            真近点角 theta
+/// @Param  m_p;                半通径
+/// @Param  m_r;                地心坐标系中，中心天体-第二天体位置矢量
+/// @Param  m_v;                地心坐标系中, 速度矢量 
+/// @Param  mtx_1,mtx_2,mtx_3   3个坐标变换矩阵
+/// @Param  m1,m2               中心天体m1质量，第二天体质量m2
+/// @Output
+/// 在参考坐标系下，物体坐标为(r*cos(trueA), r*sin(trueA), 0)
+/// 统一单位 m kg rad double earth_m1 = 5.97237e24, air_m2 = 8500.0
+///***********************************************************************
+#include <iostream>
+#include <stdlib.h>
+#include "AstroLib.h"
+#include <cmath>
+#include "AsOrbElemToCart.h"
+#define G 6.67e-11 
+using namespace std;
+bool AsOrbElemToCart(const COrbElem& Orb, double m1, double m2, CCoord& cartPos, CCoord & cartVel)
+{
+	//异常状态
+	if (
+		//质量异常
+		m1 <= 0 || m2 <= 0 || 
+		//半长轴异常
+		Orb.m_SMajAx <= 6371e3 || 
+		//偏心率异常
+		Orb.m_Ecc < 0 || 
+		//轨道倾角异常
+		Orb.m_I<0 ||Orb.m_I>AsCPI || 
+		//升交点赤经异常
+		Orb.m_RAAN < -AsCPI || Orb.m_RAAN > 2 * AsCPI ||
+		//近供点角异常
+		Orb.m_ArgPeri < 0 || Orb.m_ArgPeri> 2 * AsCPI || 
+		//真近点角异常
+		Orb.m_TrueA < -AsCPI || Orb.m_TrueA> 2 * AsCPI ||
+		//角度关系异常
+	   (Orb.m_Ecc >= 1 && Orb.m_TrueA >= AsCPI - acos(1.0 / Orb.m_Ecc) &&
+		Orb.m_TrueA <= AsCPI + acos(1.0 / Orb.m_Ecc))
+		)
+	{
+		cout << "One of the six elements or m1 or m2 is wrong" << endl;
+		return false;
+	}
+	else
+	{
+		// 位置矢量和半通径
+		double  r, m_p;
+		//根据ecc判断轨道形状,决定半通径取值
+		if (Orb.m_Ecc == 0 || Orb.m_Ecc == 1) 
+			m_p = Orb.m_SMajAx;
+		else if (Orb.m_Ecc > 1) 
+			m_p = -Orb.m_SMajAx*(1 - Orb.m_Ecc*Orb.m_Ecc);
+		else 
+			m_p = Orb.m_SMajAx*(1 - Orb.m_Ecc*Orb.m_Ecc);
+		//位置矢量和半通径关系
+		r = m_p / (1 + Orb.m_Ecc*cos(Orb.m_TrueA));  
+		/*
+		//第二天体轨道面-中心天体轨道面，需进行3次坐标旋转变换
+		//第一次按3 旋转 -raan
+		CMatrix<double> mtx_1(cos(-Orb.m_RAAN), sin(-Orb.m_RAAN), 0,
+		                     -sin(-Orb.m_RAAN), cos(-Orb.m_RAAN), 0,
+		                                                  0, 0, 1.0);
+		//第二次按1 旋转-i
+		CMatrix<double> mtx_2(1.0, 0, 0,
+		                      0, cos(-Orb.m_I), sin(-Orb.m_I),
+		                      0, -sin(-Orb.m_I), cos(-Orb.m_I));
+		//第三次旋转按3 旋转-argPeri
+		CMatrix<double> mtx_3(cos(-Orb.m_ArgPeri), sin(-Orb.m_ArgPeri), 0,
+		                     -sin(-Orb.m_ArgPeri), cos(-Orb.m_ArgPeri), 0,
+		                                                        0, 0, 1.0);
+		CMatrix<double> R(3, 1);//初始位置矢量R
+		R[0][0] = r*cos(Orb.m_TrueA);
+		R[1][0] = r*sin(Orb.m_TrueA);
+		R[2][0] = 0;
+		*/
+		//位置,同时换算为km
+		cartPos[0] = -1*r*(cos(Orb.m_RAAN)*cos(Orb.m_ArgPeri + Orb.m_TrueA) - sin(Orb.m_RAAN)*sin(Orb.m_ArgPeri + Orb.m_TrueA)*cos(Orb.m_I))/1000;
+		cartPos[1] = -1*r*(sin(Orb.m_RAAN)*cos(Orb.m_ArgPeri + Orb.m_TrueA) + cos(Orb.m_RAAN)*sin(Orb.m_ArgPeri + Orb.m_TrueA)*cos(Orb.m_I)) / 1000;
+		cartPos[2] = -1*r*sin(Orb.m_RAAN + Orb.m_ArgPeri)*sin(Orb.m_I) / 1000;
+		//速度
+		//由于运动中除了trueA，其余轨道根数均不变，且轨道六根数可唯一确定位置矢量，因此位置矢量是trueA的函数。
+		//v=(dm_r/dtrueA)*(dtrueA/dt)
+		double miu;
+		miu = G*(m1 + m2);
+		//m/s换算为km/s
+		cartVel[0] = (-cos(Orb.m_RAAN)*(sin(Orb.m_ArgPeri + Orb.m_TrueA) + Orb.m_Ecc*sin(Orb.m_ArgPeri)) -
+			sin(Orb.m_RAAN)*(cos(Orb.m_ArgPeri + Orb.m_TrueA) +
+				Orb.m_Ecc*cos(Orb.m_ArgPeri))*cos(Orb.m_I))*sqrt(miu / m_p)/1000*(-1);
+		cartVel[1] = (-sin(Orb.m_RAAN)*(sin(Orb.m_ArgPeri + Orb.m_TrueA) + Orb.m_Ecc*sin(Orb.m_ArgPeri)) +
+			cos(Orb.m_RAAN)*(cos(Orb.m_ArgPeri + Orb.m_TrueA) +
+				Orb.m_Ecc*cos(Orb.m_ArgPeri))*cos(Orb.m_I))*sqrt(miu / m_p) / 1000 * (-1);
+		cartVel[2] = ((cos(Orb.m_ArgPeri + Orb.m_TrueA) +
+			Orb.m_Ecc*cos(Orb.m_ArgPeri))*sin(Orb.m_I))*sqrt(miu / m_p) / 1000 * (-1);
+		return	true;
+	}
+}
+
diff --git a/AstroLib/Include/AsOrbElemToCart.h b/AstroLib/Include/AsOrbElemToCart.h
new file mode 100644
index 0000000000000000000000000000000000000000..fac029c109eb038ca5e4cee144c18455dd374126
--- /dev/null
+++ b/AstroLib/Include/AsOrbElemToCart.h
@@ -0,0 +1,6 @@
+#include <iostream>
+#include <stdlib.h>
+#include "AstroLib.h"
+#include <cmath>
+using namespace std;
+bool AsOrbElemToCart(const COrbElem& Orb, double m1, double m2, CCoord& cartPos, CCoord & cartVel);