CN102116630A - Mars probe on-board quick and high-precision determination method - Google Patents

Abstract

The invention belongs to an on-board high-precision extrapolation algorithm of a Mars probe, and particularly relates to the extrapolation for an on-board high-precision rail of the Mars probe, which is used for forecasting the rail of the probe and the position and the speed of the probe relative to the Mars in real time. The method has the advantages that: no Mars probe is emitted in China, and no relative report about the on-board algorithm is provided, so the algorithm aiming at the on-board rail extrapolation of the Mars probe meets the requirement of engineering practice and keeps higher precision.

Description

A kind of on the star of Mars probes quick high accuracy determine method

Technical field

The invention belongs to high precision extrapolation algorithm on the Mars probes track star, be specifically related to be used for high precision track extrapolation on the Mars probes star, the track of real-time prediction detector and the position of relative Mars, speed.

Background technology

Mars exploration is the another milestone of China's aerospace industry after the lunar exploration plan.Braking of Mars probes periareon and ring fire section high-precision attitude are determined all to need high-precision real-time track information, so high precision track extrapolation algorithm is the function of Mars probes indispensability on the Mars probes star.Though abroad the precedent of existing Mars probes owing to the technical know-how reason, need be developed the high precision track extrapolation algorithm that a cover is suitable for Mars probes, has satisfied the mission requirements of engineering practice for the mars exploration plan provides technical support.

For the artificial satellite that orbits round the earth, its orbital characteristics research is comparatively deep, and through the model checking in Heaven, and the dynamics of orbits model reference document of earth satellite is more.For the Mars probes orbital characteristics is then completely different the pertinent literature record is arranged seldom then, so set up high precision track extrapolation algorithm on the Mars probes star, can only on the kinetic model basis of earth satellite, progressively set up a cover algorithm.

Summary of the invention

The purpose of this invention is to provide a kind of on the star of Mars probes quick high accuracy determine method, it can be fit to quick high accuracy track extrapolation algorithm on the Mars probes star, the track of real-time prediction detector and the position of relative Mars, speed satisfy the requirement that braking of detector periareon and ring fire section high-precision attitude are determined.

The present invention be achieved in that a kind of on the star of Mars probes quick high accuracy determine method, it mainly may further comprise the steps,

(1) sets up coordinate system;

(2) transformational relation of clear and definite each coordinate system;

(3) calculate perturbative force;

(4) under Mars J2000 inertial system to dynamics of orbits model integration, try to achieve t track constantly.

Described step (1) comprises

1) earth J2000.0 inertial coordinates system (S _ECI)

True origin is positioned at the barycenter of the earth, and reference planes are the mean equator face of J2000, and X-axis is by the mean equinox of the earth's core sensing J2000, and the Z axle is perpendicular to reference planes, and by the barycenter directed north direction of the earth, Y-axis and X, Z axle constitute right-handed system,

2) Mars J2000.0 inertial coordinates system (S _MCI)

The resulting coordinate of barycenter that the true origin of earth J2000 inertial coordinates system is moved to Mars is a Mars J2000 inertial coordinates system.One of the unique difference true origin of Mars J2000 inertial coordinates system and earth J2000 inertial coordinates system is at the Mars barycenter, and one in earth centroid,

3) (the S of Mars J2000 mean equator IAU phasor coordinate system _MCIAU)

Coordinate origin is positioned at the barycenter of Mars, and reference planes are the mean equator face of Mars J2000, and X-axis is along the IAU direction vector, and the IAU vector is the intersection point of J2000 moment Mars mean equator and earth mean equator, and Y-axis and X, Z axle constitute right-handed system,

4) Mars J2000 mean equator Mars connects firmly coordinate system (S _MCF)

Coordinate origin is positioned at the barycenter of Mars, and reference planes are the mean equator face of Mars J2000, and X-axis is pointed to by the warp of Mars Airy-0 and the intersection point of mean equator by the fiery heart, and Y-axis and X, Z axle constitute right-handed system.

Described step (2) comprises

Around x, y, the rotation matrix at three rotations of z a angle is

$R_x\left(\mathrm{\α}\right)=\left[\begin{array}{ccc}1& 0& 0\\ 0& \cos \mathrm{\α}& \sin \mathrm{\α}\\ 0& -\sin \mathrm{\α}& \cos \mathrm{\α}\end{array}\right]$ $R_y\left(\mathrm{\α}\right)=\left[\begin{array}{ccc}\cos \mathrm{\α}& 0& -\sin \mathrm{\α}\\ 0& 1& 0\\ \sin \mathrm{\α}& 0& \cos \mathrm{\α}\end{array}\right]$ $R_y\left(\mathrm{\α}\right)=\left[\begin{array}{ccc}\cos \mathrm{\α}& \sin \mathrm{\α}& 0\\ -\sin \mathrm{\α}& \cos \mathrm{\α}& 0\\ 0& 0& 1\end{array}\right]$

1) the IAU vector calculates

The axis of rotation vector of Mars is expressed as under the celestial coordinates of the earth's core:

α＝317.68143-0.1061T(deg)

β＝52.8865-0.0609T(deg)

Wherein, α is a right ascension, and β is a declination, and T is from the Julian century that J2000 starts at constantly, and J2000 is arctic unit's direction vector being expressed as in the earth's core celestial coordinate system of Mars constantly

${\stackrel{\widehat{\→}}{r}}_{\mathrm{Mpole}}=\left(\begin{array}{c}0.466519\\ -0.406238\\ 0.797442\end{array}\right)$

J2000 is arctic unit's direction vector being expressed as in the earth's core celestial coordinate system of the earth constantly

${\stackrel{\widehat{\→}}{r}}_{\mathrm{Epole}}=\left(\begin{array}{c}0\\ 0\\ 1\end{array}\right)$

J2000 IAU orientation vector constantly is:

${\stackrel{\widehat{\→}}{r}}_{\mathrm{IAU}}={\stackrel{\widehat{\→}}{r}}_{\mathrm{Epole}}\×{\stackrel{\widehat{\→}}{r}}_{\mathrm{Mpole}}$

2) S _MCITo S _MCIAUConversion

${\stackrel{\→}{r}}_{\mathrm{MCIAU}}=R_z\left(I\right)R_z\left({\mathrm{\Ω}}_M\right){\stackrel{\→}{r}}_{\mathrm{MCI}}$

Wherein, I=37.1135 ⁰, Ω _M=47.6814 ⁰

3) S _MCIAUTo S _MCFConversion

${\stackrel{\→}{r}}_{\mathrm{MCF}}=R_z\left(w\right){\stackrel{\→}{r}}_{\mathrm{MCIAU}}$

Wherein, w=176.630+350.89198226d (deg), the Julian date of d for starting at constantly from J2000, described step (3) comprises

1) the non-spherical gravitation perturbation calculus of Mars

The gravitation position of the non-spherical part of Mars spheric harmonic function series expansion commonly used represents that different potential coefficients has just constituted different Mars gravity field models, the form of Mars shape perturbation bit function following spheric harmonic function of deployable one-tenth in body-fixed coordinate system:

$U_{\mathrm{NSE}}=\frac{{\mathrm{\μ}}_e}{r}\underset{l=2}{\overset{N}{\mathrm{\Σ}}}\underset{m=0}{\overset{l}{\mathrm{\Σ}}}{\left[\frac{a_e}{r}\right]}^l{\stackrel{\‾}{P}}_{\mathrm{lm}}\left(\sin \mathrm{\φ}\right)[{\stackrel{\‾}{C}}_{\mathrm{lm}}\cos \left(\mathrm{m\λ}\right)+{\stackrel{\‾}{S}}_{\mathrm{lm}}\sin \left(\mathrm{m\λ}\right)]$

A wherein _eBe the mars equatorial radius; μ _eBe the Mars gravitational constant, For aircraft connects firmly fiery heart distance in the coordinate system and fiery the heart channel of Hang-Shaoyin, latitude at Mars; P _Lm(sin φ) is the Legendre polynomial after the normalization; C _Lm, S _LmBe normalized Mars gravitation potential coefficient; N is the order of the star gravity field model of getting fire;

2) atmospherical drag perturbation

Atmospherical drag is a principal element of satellite orbit perturbation, and atmospherical drag perturbation can be described as:

${\stackrel{\→}{A}}_{\mathrm{drag}}=-\frac{1}{2}{\mathrm{\ρ}}_a\left[\frac{C_{D}A}{m}\right]V_r{\stackrel{\→}{V}}_r$

Wherein, C _DBe the atmospherical drag coefficient; A is that the sectional area of aircraft is perpendicular to the projection on the plane of track; M is the quality of aircraft; ρ _aAtmospheric density for the aircraft place;

Be the speed of aircraft with respect to atmosphere;

3) solar radiation pressure perturbation

For spacecraft, the solar radiation pressure perturbation acceleration can calculate with following formula:

${\stackrel{\→}{A}}_R=P_{\mathrm{SR}}{a}_U^2{C}_R\left(\frac{A}{m}\right)\mathrm{\γ}\frac{\stackrel{\→}{\mathrm{\Δ}}s}{{\mathrm{\Δ}}_s}$

Wherein, P _SRFor acting on the solar radiation pressure on astronomical unit's place's black matrix of the sun, be taken as 4.560 * 10 ^-6N/m ²M, A be respectively aircraft quality and perpendicular to

The cross-sectional area of the aircraft of direction; a _UBe astronomical unit;

Be respectively the aircraft and the sun position vector in the Mars celestial coordinate system; C _RReflection coefficient for aircraft surface; γ is a shadow factor;

4) solar gravitation perturbation

The sun all has graviational interaction to aircraft, and its effect can approximate description be the point mass perturbation.Formula perturbation below in fiery heart celestial coordinate system, can using:

$F_{\mathrm{\ϵ}}=-{\mathrm{Gm}}^{\′}(\frac{\mathrm{\Δ}}{{\mathrm{\Δ}}^3}+\frac{r^{\′}}{r^{\′3}}),$ Δ＝r-r′

In the formula: wherein m ' is the quality of day, month, and r ' is the vector of the fiery heart to sun barycenter, and Δ is the vector of sun barycenter to satellite.

Described step (4) comprises sets up Mars probes orbit integration equation

Mars probes orbit integration equation is at S _MCICan be expressed as under the system:

$\left.\begin{array}{c}\stackrel{\·\·}{x}=-\frac{\mathrm{\μ}}{r^3}x+f_x\\ \stackrel{\·\·}{y}=-\frac{\mathrm{\μ}}{r^3}y+f_y\\ \stackrel{\·\·}{z}=-\frac{\mathrm{\μ}}{r^3}z+f_z\end{array}\right\}$

F in the formula _i(i=x, y are that perturbative force is at S z) _MCIBe three components,

Advantage of the present invention is, China does not launch Mars probes, and algorithm was not seen relevant report on its star, and this algorithm both had been fit to the requirement of engineering practice at the extrapolation of getting on the right track of Mars probes star, had kept higher precision again.

Embodiment

Describe the present invention below:

A kind of on the star of Mars probes quick high accuracy determine method, it mainly may further comprise the steps:

(1) sets up coordinate system;

(2) transformational relation of clear and definite each coordinate system;

(3) calculate perturbative force;

(4) under Mars J2000 inertial system to dynamics of orbits model integration, try to achieve t track constantly.

Below in conjunction with example each step of the present invention is done detailed explanation:

(1) sets up coordinate system

A. earth J2000.0 inertial coordinates system (S _ECI)

True origin is positioned at the barycenter of the earth, reference planes are the mean equator face of J2000 (JED=2451545.0 12: 0: 0 on the 1st January in 2000), X-axis is pointed to the mean equinox of J2000 by the earth's core, the Z axle is perpendicular to reference planes, by the barycenter directed north direction of the earth, Y-axis and X, Z axle constitute right-handed system.

B. Mars J2000.0 inertial coordinates system (S _MCI)

The resulting coordinate of barycenter that the true origin of earth J2000 inertial coordinates system is moved to Mars is a Mars J2000 inertial coordinates system.One of the unique difference true origin of Mars J2000 inertial coordinates system and earth J2000 inertial coordinates system is at the Mars barycenter, and one in earth centroid.Mars probes orbital mechanics equation is description at this.

C. Mars J2000 mean equator IAU phasor coordinate is (S _MCIAU)

Coordinate origin is positioned at the barycenter of Mars, reference planes are the mean equator face of Mars J2000 (JED=2451545.0 12: 0: 0 on the 1st January in 2000), X-axis is along the IAU direction vector, the IAU vector is the intersection point of J2000 moment Mars mean equator and earth mean equator, and Y-axis and X, Z axle constitute right-handed system.

D. Mars J2000 mean equator Mars connects firmly coordinate system (S _MCF)

Coordinate origin is positioned at the barycenter of Mars, reference planes are the mean equator face of Mars J2000 (JED=2451545.0 12: 0: 0 on the 1st January in 2000), X-axis is pointed to by the warp of Mars Airy-0 and the intersection point of mean equator by the fiery heart, and Y-axis and X, Z axle constitute right-handed system.

Step (2) coordinate system transformational relation

Around x, y, the rotation matrix at three rotations of z a angle is

$R_x\left(\mathrm{\α}\right)=\left[\begin{array}{ccc}1& 0& 0\\ 0& \cos \mathrm{\α}& \sin \mathrm{\α}\\ 0& -\sin \mathrm{\α}& \cos \mathrm{\α}\end{array}\right]$ $R_y\left(\mathrm{\α}\right)=\left[\begin{array}{ccc}\cos \mathrm{\α}& 0& -\sin \mathrm{\α}\\ 0& 1& 0\\ \sin \mathrm{\α}& 0& \cos \mathrm{\α}\end{array}\right]$ $R_y\left(\mathrm{\α}\right)=\left[\begin{array}{ccc}\cos \mathrm{\α}& \sin \mathrm{\α}& 0\\ -\sin \mathrm{\α}& \cos \mathrm{\α}& 0\\ 0& 0& 1\end{array}\right]$

The e.IAU vector calculates

The axis of rotation vector of Mars is expressed as (right ascension α, declination β) under the celestial coordinates of the earth's core:

α＝317.68143-0.1061T(deg)

β＝52.8865-0.0609T(deg)

Wherein T is the Julian century from J2000 starts at constantly.So arctic unit's direction vector being expressed as of J2000 moment Mars in the earth's core celestial coordinate system

${\stackrel{\widehat{\→}}{r}}_{\mathrm{Mpole}}=\left(\begin{array}{c}0.466519\\ -0.406238\\ 0.797442\end{array}\right)$

J2000 is arctic unit's direction vector being expressed as in the earth's core celestial coordinate system of the earth constantly

${\stackrel{\widehat{\→}}{r}}_{\mathrm{Epole}}=\left(\begin{array}{c}0\\ 0\\ 1\end{array}\right)$

J2000 IAU orientation vector constantly is:

${\stackrel{\widehat{\→}}{r}}_{\mathrm{IAU}}={\stackrel{\widehat{\→}}{r}}_{\mathrm{Epole}}\×{\stackrel{\widehat{\→}}{r}}_{\mathrm{Mpole}}$

F.S _MCITo S _MCIAUConversion

${\stackrel{\→}{r}}_{\mathrm{MCIAU}}=R_z\left(I\right)R_z\left({\mathrm{\Ω}}_M\right){\stackrel{\→}{r}}_{\mathrm{MCI}}$

I=37.1135 wherein ⁰, Ω _M=47.6814 ⁰

G.S _MCIAUTo S _MCFConversion

${\stackrel{\→}{r}}_{\mathrm{MCF}}=R_z\left(w\right){\stackrel{\→}{r}}_{\mathrm{MCIAU}}$

W=176.630+350.89198226d (deg) wherein, the Julian date of d for starting at constantly from J2000.

Step (3) is calculated perturbative force

The gravitation position of the non-spherical part of Mars spheric harmonic function series expansion commonly used represents that different potential coefficients has just constituted different Mars gravity field models.The form of Mars shape perturbation bit function following spheric harmonic function of deployable one-tenth in body-fixed coordinate system:

$U_{\mathrm{NSE}}=\frac{{\mathrm{\μ}}_e}{r}\underset{l=2}{\overset{N}{\mathrm{\Σ}}}\underset{m=0}{\overset{l}{\mathrm{\Σ}}}{\left[\frac{a_e}{r}\right]}^l{\stackrel{\‾}{P}}_{\mathrm{lm}}\left(\sin \mathrm{\φ}\right)[{\stackrel{\‾}{C}}_{\mathrm{lm}}\cos \left(\mathrm{m\λ}\right)+{\stackrel{\‾}{S}}_{\mathrm{lm}}\sin \left(\mathrm{m\λ}\right)]$

In the formula: a _eBe the mars equatorial radius; μ _eBe the Mars gravitational constant,

For aircraft connects firmly fiery heart distance in the coordinate system and fiery the heart channel of Hang-Shaoyin, latitude at Mars; P _Lm(sin φ) is the Legendre polynomial after the normalization; C _Lm, S _LmBe normalized Mars gravitation potential coefficient; N is the order of the star gravity field model of getting fire.

H. atmospherical drag perturbation

Atmospherical drag is a principal element of satellite orbit perturbation, seems particularly important for low orbit satellite.Atmospherical drag perturbation can be described as:

${\stackrel{\→}{A}}_{\mathrm{drag}}=-\frac{1}{2}{\mathrm{\ρ}}_a\left[\frac{C_{D}A}{m}\right]V_r{\stackrel{\→}{V}}_r$

In the formula: CD is the atmospherical drag coefficient; A is that the sectional area of aircraft is perpendicular to the projection on the plane of track; M is the quality of aircraft; ρ _aAtmospheric density for the aircraft place;

Be the speed of aircraft with respect to atmosphere.

I. solar radiation pressure perturbation

The visible radiation of the sun is called solar radiation pressure perturbation to the influence of aircraft movements.For spacecraft, the solar radiation pressure perturbation acceleration can calculate with following formula:

${\stackrel{\→}{A}}_R=P_{\mathrm{SR}}{a}_U^2{C}_R\left(\frac{A}{m}\right)\mathrm{\γ}\frac{\stackrel{\→}{\mathrm{\Δ}}s}{{\mathrm{\Δ}}_s}$

In the formula: P _SRFor acting on the solar radiation pressure on astronomical unit's place's black matrix of the sun, be taken as 4.560 * 10 ^-6N/m ²M, A be respectively aircraft quality and perpendicular to

The cross-sectional area of the aircraft of direction; a _UBe astronomical unit;

Be respectively the aircraft and the sun position vector in the Mars celestial coordinate system; C _RReflection coefficient for aircraft surface; γ is a shadow factor.

J. solar gravitation perturbation

The sun all has graviational interaction to aircraft, and its effect can approximate description be the point mass perturbation.Formula perturbation below in fiery heart celestial coordinate system, can using:

$F_{\mathrm{\ϵ}}=-{\mathrm{Gm}}^{\′}(\frac{\mathrm{\Δ}}{{\mathrm{\Δ}}^3}+\frac{r^{\′}}{r^{\′3}}),$ Δ＝r-r′

In the formula: wherein m ' is the quality of day, month, and r ' is the vector of the fiery heart to sun barycenter, and Δ is the vector of sun barycenter to satellite.

Step (4) is set up Mars probes orbit integration equation

Mars probes orbit integration equation is at S _MCICan be expressed as under the system:

$\left.\begin{array}{c}\stackrel{\·\·}{x}=-\frac{\mathrm{\μ}}{r^3}x+f_x\\ \stackrel{\·\·}{y}=-\frac{\mathrm{\μ}}{r^3}y+f_y\\ \stackrel{\·\·}{z}=-\frac{\mathrm{\μ}}{r^3}z+f_z\end{array}\right\}$

F in the formula _i(i=x, y are that perturbative force is at S z) _MCIBe three components,

Step (4) can adopt RKF7 (8) integrator to orbit integration equation integration, obtains position of detector speed.

Claims (5)

1. One kind on the star of Mars probes quick high accuracy determine method, it is characterized in that: it mainly may further comprise the steps,

   (1) sets up coordinate system;

   (2) transformational relation of clear and definite each coordinate system;

   (3) calculate perturbative force;

   (4) under Mars J2000 inertial system to dynamics of orbits model integration, try to achieve t track constantly.
2. 2. as claimed in claim 1 a kind of on the star of Mars probes quick high accuracy determine method, it is characterized in that: described step (1) comprises

   1) earth J2000.0 inertial coordinates system (S _ECI)

   True origin is positioned at the barycenter of the earth, and reference planes are the mean equator face of J2000, and X-axis is by the mean equinox of the earth's core sensing J2000, and the Z axle is perpendicular to reference planes, and by the barycenter directed north direction of the earth, Y-axis and X, Z axle constitute right-handed system,

   2) Mars J2000.0 inertial coordinates system (S _MCI)

   The resulting coordinate of barycenter that the true origin of earth J2000 inertial coordinates system is moved to Mars is a Mars J2000 inertial coordinates system.One of the unique difference true origin of Mars J2000 inertial coordinates system and earth J2000 inertial coordinates system is at the Mars barycenter, and one in earth centroid,

   3) (the S of Mars J2000 mean equator IAU phasor coordinate system _MCIAU)

   Coordinate origin is positioned at the barycenter of Mars, and reference planes are the mean equator face of Mars J2000, and X-axis is along the IAU direction vector, and the IAU vector is the intersection point of J2000 moment Mars mean equator and earth mean equator, and Y-axis and X, Z axle constitute right-handed system,

   4) Mars J2000 mean equator Mars connects firmly coordinate system (S _MCF)

   Coordinate origin is positioned at the barycenter of Mars, and reference planes are the mean equator face of Mars J2000, and X-axis is pointed to by the warp of Mars Airy-0 and the intersection point of mean equator by the fiery heart, and Y-axis and X, Z axle constitute right-handed system.
3. 3. as claimed in claim 1 a kind of on the star of Mars probes quick high accuracy determine method, it is characterized in that: described step (2) comprises

   Around x, y, the rotation matrix at three rotations of z a angle is

   

   

   

   1) the IAU vector calculates

   The axis of rotation vector of Mars is expressed as under the celestial coordinates of the earth's core:

   α＝317.68143-0.1061T(deg)

   β＝52.8865-0.0609T(deg)

   Wherein, α is a right ascension, and β is a declination, and T is from the Julian century that J2000 starts at constantly, and J2000 is arctic unit's direction vector being expressed as in the earth's core celestial coordinate system of Mars constantly

   ${\widehat{\stackrel{\→}{r}}}_{\mathrm{Mpole}}=\left(\begin{array}{c}0.466519\\ -0.406238\\ 0.797442\end{array}\right)$

   J2000 is arctic unit's direction vector being expressed as in the earth's core celestial coordinate system of the earth constantly

   ${\widehat{\stackrel{\→}{r}}}_{\mathrm{Epole}}=\left(\begin{array}{c}0\\ 0\\ 1\end{array}\right)$

   J2000 IAU orientation vector constantly is:

   ${\widehat{\stackrel{\→}{r}}}_{\mathrm{IAU}}={\widehat{\stackrel{\→}{r}}}_{\mathrm{Epole}}\×{\widehat{\stackrel{\→}{r}}}_{\mathrm{Mpole}}$

   2) S _MCITo S _MCIAUConversion

   ${\stackrel{\→}{r}}_{\mathrm{MCIAU}}=R_z\left(I\right)R_z\left({\mathrm{\Ω}}_M\right){\stackrel{\→}{r}}_{\mathrm{MCI}}$

   Wherein, I=37.1135 °, Ω _M=47.6814 °

   3) S _MCIAUTo S _MCFConversion

   ${\stackrel{\→}{r}}_{\mathrm{MCF}}=R_z\left(w\right){\stackrel{\→}{r}}_{\mathrm{MCIAU}}$

   Wherein, w=176.630+350.89198226d (deg), the Julian date of d for starting at constantly from J2000,
4. 4. as claimed in claim 1 a kind of on the star of Mars probes quick high accuracy determine method, it is characterized in that: described step (3) comprises

   1) the non-spherical gravitation perturbation calculus of Mars

   The gravitation position of the non-spherical part of Mars spheric harmonic function series expansion commonly used represents that different potential coefficients has just constituted different Mars gravity field models, the form of Mars shape perturbation bit function following spheric harmonic function of deployable one-tenth in body-fixed coordinate system:

   

   Wherein, a _eBe the mars equatorial radius; μ _eBe the Mars gravitational constant, For aircraft connects firmly fiery heart distance in the coordinate system and fiery the heart channel of Hang-Shaoyin, latitude at Mars; P _Lm(sin φ) is the Legendre polynomial after the normalization; C _Lm, S _LmBe normalized Mars gravitation potential coefficient; N is the order of the star gravity field model of getting fire;

   2) atmospherical drag perturbation

   Atmospherical drag is a principal element of satellite orbit perturbation, and atmospherical drag perturbation can be described as:

   

   Wherein, C _DBe the atmospherical drag coefficient; A is that the sectional area of aircraft is perpendicular to the projection on the plane of track; M is the quality of aircraft; ρ _aAtmospheric density for the aircraft place;

   

   Be the speed of aircraft with respect to atmosphere;

   3) solar radiation pressure perturbation

   For spacecraft, the solar radiation pressure perturbation acceleration can calculate with following formula:

   ${\stackrel{\→}{A}}_R=P_{\mathrm{SR}}{a}_U^2{C}_R\left(\frac{A}{m}\right)\mathrm{\γ}\frac{{\stackrel{\→}{\mathrm{\Δ}}}_S}{{\mathrm{\Δ}}_S}$

   Wherein, P _SRFor acting on the solar radiation pressure on astronomical unit's place's black matrix of the sun, be taken as 4.560 * 10 ^-6N/m ²M, A be respectively aircraft quality and perpendicular to

   

   The cross-sectional area of the aircraft of direction; a _UBe astronomical unit; ${\stackrel{\→}{\mathrm{\Δ}}}_S=\stackrel{\→}{R}-{\stackrel{\→}{R}}_S,$

   

   Be respectively the aircraft and the sun position vector in the Mars celestial coordinate system; C _RReflection coefficient for aircraft surface; γ is a shadow factor;

   4) solar gravitation perturbation

   The sun all has graviational interaction to aircraft, and its effect can approximate description be the point mass perturbation.Formula perturbation below in fiery heart celestial coordinate system, can using:

   $F_{\mathrm{\ϵ}}=-G{m}^{\′}(\frac{\mathrm{\Δ}}{{\mathrm{\Δ}}^3}+\frac{r^{\′}}{r^{\′3}}),$ Δ＝r-r′

   In the formula: wherein m ' is the quality of day, month, and r ' is the vector of the fiery heart to sun barycenter, and Δ is the vector of sun barycenter to satellite.
5. 5. as claimed in claim 1 a kind of on the star of Mars probes quick high accuracy determine method, it is characterized in that: described step (4) comprises sets up Mars probes orbit integration equation

   Mars probes orbit integration equation is at S _MCICan be expressed as under the system:

   

   F in the formula _i(i=x, y are that perturbative force is at S z) _MCIBe three components, $r=\sqrt{x^2+y^2+z^2}.$