CN106446313A - Polar hovering satellite orbit-based system design method - Google Patents

Abstract

The invention provides a polar hovering satellite orbit-based system design method. The system design and transfer orbit design of a whole satellite are finished by performing design and characteristic analysis on a working orbit of the polar hovering satellite. The method comprises the steps of describing a dynamic motion of the polar hovering satellite and calculating control characteristics of the polar hovering satellite, thereby performing design optimization on the working orbit of the satellite to obtain optimization design parameters; calculating attributes such as mass and the like of subsystems as polar hovering satellites according to the optimization design parameters to obtain maximum mass of an effective load of the polar hovering satellite; and determining a transfer section orbit and a launch section orbit of the transfer orbit of the polar hovering satellite, and optimizing obtained orbit parameters, thereby designing an optimal transfer orbit. According to the method, the scheme is simple in principle and easy to solve; and a calculation result is of great guide significance for project realization and can be applied to a task design stage of the polar hovering satellite with demands of polar observation, communication and the like.

Description

Design method based on polar region hovering satellite orbit

Technical field

The invention belongs to spacecraft dynamics controls and application, it is related to a kind of dynamics Controlling of polar region hovering satellite and application Scheme and in particular to a kind of based on polar region hover satellite orbit design method, by polar region hover satellite work rail Road is designed completing system design and the transfer orbit design of whole star with specificity analysises.

Background technology

Polar region hovering satellite can provide the Continuous Observation to high latitude area especially arctic regions, can be to the sky of arctic regions Gas forecast, earth resource detection, radio communication and Space environment monitor etc. provide service, are the Arctic Ocean and Antarctic Continent exploitation Using providing space-based to support, there is huge application prospect and economic benefit.

Diver, J.M. propose the concept of " polar region hovering " earliest, and the satellite mechanical characteristic of fixing hovering height have been carried out point Analysis, has obtained in the minimum conclusion of perturbative force at about 380 earth radius of the earth.Colin R.McInnes and Matteo Ceriotti etc. devises the optimum polar region hovering track of fuel using the hybrid propulsion mode of electric propulsion and solar sail, has carried out fuel Consumption calculations and durability analysis, and calculate the subsystem quality of whole star, complete under particular job height and life conditions Payload mass calculates.

However, the domestic correlational study also not launching the hovering of relevant polar region.At present, also do not have any country or tissue emissions or Tested polar region hovering task satellite.In the prior art, the research of this respect is lacked from task layer in the face of polar region hovering satellite Transmitting, transfer, work overall process be designed, therefore, it is necessary to a kind of polar region of development hovering Orbit Design and system Design, is designed and specificity analysises by the working track of the satellite that hovered in polar region, so complete the design of whole star system and Can transfer orbit designs, be conducive to assessment prior art condition realize polar region hovering task.

Content of the invention

Carry out from the transmitting of polar region hovering satellite, transfer, work overall process faced by task layer for lacking in the research of prior art The present situation of design and problem, the present invention proposes a kind of polar region hovering satellite orbit and system design scheme, thus complete polar region hanging Stop Orbit Design, including working track design and transfer orbit design, and then complete satellite subsystem design and emission system Design.

Roughly, the orbit Design flow process of polar region hovering satellite of the present invention and system design flow particular content include following part.

(1) hovering working track is designed with circular Restricted three-body model and describes kinetics equation；The fixing hovering of analysis is high The mechanical characteristic of polar region hovering satellite under the conditions of degree；Working track design optimization problem is converted to optimal control problem；Using Excellent control algolithm solves the problems, such as the working track design optimization that hovers.

(2) satellite subsystem design according to the mechanical characteristic of working track design satellite respectively support the power of system, size, The attributes such as quality；According to satellite gross mass, calculate the biggest quality of payload；When requiring to payload, Satellite gross mass is iterated design.

(3) method using manifold design for the transfer orbit design of hovering reverse integration to track, finds out trajectory transfer orbit； Orbit parameter is changed between circular Restricted three-body model and two body Models；Design hovering satellite using Huo Man branch mode Launch trajectory；Using grid data service to design parameter optimization, the optimum transfer orbit of design.

Specifically, the invention provides a kind of design method of the satellite orbit that hovered based on polar region, defended by hovering to polar region The working track of star is designed completing system design and the transfer orbit design of whole star with specificity analysises.The method includes following Step：Step one, the dynamical motion of the satellite that hovered in polar region is described, and the control characteristic of the satellite that hovered in polar region is carried out Calculate, thus being designed to its working track optimizing to obtain optimal design parameter；Step 2, according to optimal design parameter, The attributes such as the quality of each subsystem to the satellite that hovers as polar region calculate, thus obtaining polar region hovering Satellite Payloads The biggest quality；And step 3, determine the transfer leg track of transfer orbit and the launch trajectory of polar region hovering satellite respectively, and The orbit parameter being obtained is optimized, thus designing the transfer orbit of optimum.

Step one executes：Using circular Restricted three-body model, the dynamical motion of the satellite that hovered in polar region is described； Under the conditions of fixing hovering height, the control characteristic of the satellite that hovered in polar region is analyzed；And using optimal control problem Mode, the working track of the satellite that hovered in polar region is designed optimizing.

In addition, step one also includes：Calculate optimal control problem using optimum control numerical optimization software kit, defended with polar region hovering The analysis result of the control characteristic of star is as the initial value of optimized algorithm, thus obtaining the working track of optimal-fuel and controlling acceleration Degree and the time history of controling power.

Polar region hover satellite dynamical motion equation be：

Wherein, dynamical motion defines in the rotated coordinate system, and zero points to ground in Solar-terrestrial system barycenter, x-axis for the sun Direction of bowl, z-axis is Solar-terrestrial system rotational angular velocity vector direction, and y-axis constitutes right hand rectangular coordinate system, and r is under rotating coordinate system The position vector of base hovering satellite, v is the velocity of base hovering satellite, and w is the angular velocity vector of rotating coordinate system, a_T For controlling acceleration and its mould a_TRepresent, m is the quality of base hovering satellite, I_spFor electric propulsion engine specific impulse, g₀For Sea level acceleration of gravity.

U is potential-energy function and form is：

Wherein, μ₁、μ₂It is respectively the gravitational constant of the sun and the earth, r₁、r₂It is respectively the position vector of the sun and the earth.

Optimal control problem at least includes：Object function, boundary condition and path constraints, wherein, object function is： J=-m_f=-m (t_f), boundary condition is：r_y(t₀)=0, m (t₀)=m₀, r (t_f)=r (t₀), v (t_f)=v (t₀), and path constraint Condition is：J represents target function value, and polar region hovering track has the periodicity of 1 year, t₀For initial time and elect first point of Capricornus as, r (t₀) for polar region hover satellite initial time position vector, v (t₀) it is initial time Velocity, m (t₀) for polar region hover satellite initial time quality, t_fFor task service life, r (t_f)、v(t_f) hang for polar region Stop the position and speed vector in the last moment of satellite, m (t_f) be the last moment quality, and (r_{2, x}, r_{2, y}, r_{2, z})^T=r-r₂, δ_eq=23.5 ° is ecliptic obliquity.

Step 2 executes：Mechanical characteristic according to working track come design polar region hover satellite subsystem attribute；According to The gross mass of polar region hovering satellite, calculates the biggest quality of payload system；And when payload system requires, right The gross mass of polar region hovering satellite is iterated, and wherein, attribute at least includes power, size, quality.

Specifically, step 2 includes：According to controling power time history, find the maximum of controling power；According to Optimal State variable, Obtain the mass change of polar region hovering satellite；Calculate fuel, fuel tank system, electric propulsion system, the matter of power-supply system respectively Amount, thus obtain the quality of payload system；And regard task situation, the first of polar region hovering satellite is recalculated by iteration Prothyl amount.

The transfer orbit of polar region hovering satellite is divided into transmitter section and transfer leg, and wherein, transmitter section is by rocket Upper Stage chemical propulsion Mode completes, and transfer leg is completed using the trajectory branch mode not applying pulse or continuous thrust.

Step 3 executes：Using manifold design, the track of polar region hovering satellite is inversely integrated, thus finding out transfer leg Track, and the orbit parameter of transfer leg track is changed between circular Restricted three-body model and two body Models；Using Huo Manzhuan Shifting mode come to design polar region hover satellite launch trajectory；And utilize grid data service, the orbit parameter being obtained is carried out Optimize, thus designing the transfer orbit of optimum.

In step 3, the process finding out transfer leg track includes：Set out with a point of the polar region hovering track of any time, Turn over predetermined angular with rotating coordinate system, according to the restricted three body dynamics models of circle to track reverse integration, thus obtaining pole The track manifold of ground hovering satellite；Block in the nearest position of the liftoff ball of manifold, obtain reverse time of integration now and herein Position and speed parameter；Position and speed parameter in rotating coordinate system in circular Restricted three-body model is obtained disome through Coordinate Conversion Position and speed under inertial coodinate system in model, and it is calculated corresponding Keplerian orbit six key element；And according to Kepler's rail The perigee altitude of road six element factor calculation transfer orbit and altitude of the apogee.

Therefore, the polar region hovering Orbit Design of the present invention and system design scheme principle are simply it is easy to solve, result of calculation There is very big directive significance for Project Realization, and the method for the present invention can be applicable to the polar region of the demands such as polar region observation, communication The hovering satellite task design phase.

Brief description

Fig. 1 is the schematic diagram of hovering working track in polar region involved in the present invention；

Fig. 2 is the schematic diagram of hovering satellite transfer orbit in polar region involved in the present invention；And

Fig. 3 is the figure cluster of the manifold of the reverse integration of polar region hovering satellite trajectory involved in the present invention.

Specific embodiment

It will be appreciated that hovering Orbit Design in polar region of the present invention is comprised the following steps with design method：

Step one, polar region hovering working track design.

Using circular Restricted three-body model (Circular Restricted Three-Body Problem, hereinafter referred to as CR3BP) The dynamical motion of description polar region hovering satellite；Under the conditions of fixing hovering height, the control characteristic of the satellite that hovered in polar region is carried out Calculate；Polar region hovering working track design optimization problem is described as the optimal control problem of following form：

Object function is J=-m_f=-m (t_f)；

Kinetics equation is using circular Restricted three-body model；

Boundary condition is r_y(t₀)=0, m (t₀)=m₀, r (t_f)=r (t₀), v (t_f)=v (t₀)；

Path constraints are：

Wherein, J represents target function value；Polar region hovering track has the periodicity of 1 year, selects initial time t₀For Winter Solstice, r (t₀) For spacecraft initial time position vector, v (t₀) it is initial time velocity, m (t₀) it is initial time quality, t_fFor the task longevity Life, r (t_f)、v(t_f) for spacecraft end the moment position and speed vector, m (t_f) be the last moment quality. (r_{2, x}, r_{2, y}, r_{2, z})^T=r-r₂, δ_eq=23.5 ° is ecliptic obliquity.

Then, calculate above-mentioned optimal control problem using optimum control numerical optimization software kit PSOPT, with fixing hovering height Result of calculation, as the initial value of optimized algorithm, obtains the working track of polar region hovering satellite optimal-fuel, obtains controlling acceleration simultaneously Degree and the time history of controling power.

Step 2, polar region hovering satellite subsystem design.

The controling power time history being obtained according to above-mentioned steps one, finds the maximum of T of controling power_max.Obtained according to step one Optimal State variable, obtains mass change Δ m, calculates fuel, fuel tank system, electric propulsion system, power-supply system respectively Quality.Finally, obtain the quality of payload system.If mission requirements require to payload mass, by repeatedly In generation, designs initial mass m of polar region hovering satellite of rerunning₀.

Step 3, polar region hovering satellite transfer orbit design.

Polar region hovering satellite transfer orbit transfer leg mentality of designing be：With a little setting out of any time polar region hovering track, with rotation Turn coordinate system and turn over angle, θ and represent, according to the restricted three body dynamics models of circle to track reverse integration, obtain the rail of satellite Mark manifold.Block in the nearest position of the liftoff ball of manifold, obtaining the now reverse time of integration is t_T, and position and speed ginseng herein Number.Position and speed parameter in rotating coordinate system in circular Restricted three-body model is obtained in two body motion model through Coordinate Conversion Position and speed under inertial coodinate system, is calculated corresponding Keplerian orbit six key element.According to Keplerian orbit six element factor calculation The perigee altitude of transfer orbit and altitude of the apogee.

Wherein, hovering satellite transfer orbit transmitter section in polar region is designed with the mode of Huo Man dipulse transfer, solves by LEO (Low Earth Orbit, hereinafter referred to as LEO) parking orbit is to the impulse magnitude Δ V of big ellipse target Orbit Transformation₁、ΔV₂. According to polar region hovering satellite operation track initial mass m_targetCalculate carrier rocket in LEO parking orbit and launch gross mass of entering the orbit m_park.

Being solved using grid-search algorithms makes m_parkMinimum variable [t_T, θ], complete the design of polar region hovering satellite transfer orbit.

The present invention is described in detail for 1-3 and specific embodiment below in conjunction with the accompanying drawings.

Hover task Orbit optimization design for polar region

The design of this part mainly divides several steps to complete, and is respectively：

(1) using circular Restricted three-body model, the polar region hovering spacecraft equation of motion is described as shown in equation below (1), Concrete such as Fig. 1.

The above-mentioned equation of motion defines in the rotated coordinate system, and rotating coordinate system is defined as follows：Zero in Solar-terrestrial system barycenter, X-axis refers to earthwards for the sun, and z-axis is Solar-terrestrial system rotational angular velocity vector direction, and y-axis constitutes right hand rectangular coordinate system. Wherein, r is the position vector of spacecraft under rotating coordinate system, and v is the velocity of spacecraft, and w is the angle speed of rotating coordinate system Degree vector, a_TFor controlling acceleration, its mould a_TRepresent, m is spacecraft mass, I_spFor electric propulsion engine specific impulse, g₀For Sea level acceleration of gravity.Shown in the form of potential-energy function U such as formula (2).

Wherein, μ₁、μ₂It is respectively the gravitational constant of the sun and the earth, r₁、r₂It is respectively the position vector of the sun and the earth.

(2) under the conditions of fixing hovering height, the control characteristic of the satellite that hovered in polar region is analyzed.

Under the conditions of fixing hovering height, position vector meets following constraint：

Wherein, d hovers highly for polar region, δ_eqFor ecliptic obliquity, ω is Solar-terrestrial system angular velocity of rotation, and μ is constant μ=3.0404 × 10^-6, AU is astronomical unit.

Calculate any time t_iControl acceleration：

Assume to control acceleration in [t_i, t_i+ Δ t] interval keep constant, mass change is

Repeat above formula (3), (4), the calculating of (5), can obtain working life fuel consumption with control acceleration when Between course.

(3) polar region hovering working track design optimization problem is described as optimal control problem.

Object function is：J=-m_f=-m (t_f) (6)

Kinetics equation adopts formula (1)

Boundary condition is：r_y(t₀)=0, m (t₀)=m₀, r (t_f)=r (t₀), v (t_f)=v (t₀) (7)

Path constraints are：

Wherein, J represents target function value；There is the periodicity of 1 year in polar region hovering track, select initial time t₀For first point of Capricornus； r(t₀) it is spacecraft initial time position vector, v (t₀) it is initial time velocity, m (t₀) it is initial time spacecraft mass； t_fFor task service life, r (t_f)、v(t_f) for spacecraft end the moment position and speed vector, m (t_f) be the last moment quality. (r_{2, x}, r_{2, y}, r_{2, z})^T=r-r₂；δ_eq=23.5 ° is ecliptic obliquity.

(4) optimum control numerical optimization software kit PSOPT is utilized to calculate above-mentioned optimal control problem, with above-mentioned steps (2) Result of calculation, as the initial value of optimized algorithm, obtains the working track of polar region hovering satellite optimal-fuel, obtains controlling acceleration simultaneously Degree and the time history of controling power.

Polar region hovering satellite subsystem design

According to " hover task Orbit optimization design for polar region " the controling power time history that process obtains, find the maximum of controling power T_max.

According to " hover task Orbit optimization design for polar region " the Optimal State variable that process obtains, obtain the spacecraft matter in last moment Amount m_f, then spacecraft fuel mass be：

m_prop=m₀-m_f(9)

Calculate quality m of fuel tank_tank：

m_tank=0.1m_prop(10)

Calculate the maximum service rating P in electric propulsion system work process_max：

Wherein, thruster efficiency eta_SEP=0.7.

The quality of electric propulsion thruster and peak power P of electric propulsion system_maxRelated：

m_SEP=k_SEPP_max(12)

Wherein, k_SEP=20kg/kW.

It is mainly solar array quality for the power-supply system that electric propulsion system is powered to be about：

m_Power=k_SAP_max(13)

Wherein

The calculating of payload mass：

m_payload=m₀-(m_prop+m_tank+n_thrustersm_SEP+m_Power) (14)

Wherein, n_thrustersNumber for electric propulsion engine, it is considered to Redundancy Design, typically takes n_thrusters=2.

m_payloadIt is m for initial mass₀Under the conditions of payload capacity quality, if to m_payloadRequire, then need to m₀ It is iterated designing：

Subscript " ' " represent new design load.

Polar region hovering transfer orbit design

Polar region hovering transfer orbit can be divided into transmitter section and transfer leg.As shown in Fig. 2 wherein transmitter section is typically by rocket Upper Stage The mode of chemical propulsion completes, and transfer leg can take trajectory transfer to complete, and does not apply pulse or continuous thrust.

(1) transfer leg trajectory transfer design

Under the restricted circular three body dynamics models, sometime putting by hovering track, turned over rotating coordinate system Angle, θ represents, carries out track to hovering spacecraft and inversely integrates, can obtain a series of manifolds as shown in Figure 3.By manifold Block in the place nearest apart from the earth, the reverse time of integration is t_T, obtain the preliminary orbit parameter of transfer leg (x₁, y₁, z₁,).By the state vector (x in restricted circular three body dynamics model rotating coordinate systems₁, y₁, z₁,) Be converted to the position and speed vector under two body Model inertial coodinate systems, be reconverted into Keplerian orbit six key element (a₀, e₀, i₀, Ω₀, w₀, f₀).

Calculate perigee and the altitude of the apogee of transfer orbit：

Wherein, R_EFor earth mean radiuss.

(2) launch trajectory design

Transmitter section considers disome kinetic model, using Huo Man transfer solving.

The track LEO parameter that known carrier rocket transmitting is entered the orbit, parking orbit orbit altitude is h_park, elliptic orbit 1 far Point height is h_epo, calculate the eccentric ratio e of elliptic orbit 1_t：

Calculate the first subpulse Δ V of Huo Man transfer₁：

Wherein, μ_EFor earth gravitational field constant, Δ i is that target track is poor with the inclination angle of parking orbit, W_ΔiFor weight coefficient, have W_Δi∈ [0,1].

Calculate the eccentricity of target track：

Calculate the second subpulse Δ V applying at elliptic orbit 1 apogee₂：

The gross mass that carrier rocket launches into LEO track is：

Wherein, m_parkFor launching the spacecraft gross mass into target track, Δ V_total=Δ V₁+ΔV₂, m_upFor rocket Upper Stage Quality, I_spUFor the specific impulse of upper stage rocket engine, m_targetIt is the m calculating in step 2₀.

(3) with J₁=m_parkFor optimizing index, calculate optimized parameter (t_T, θ, W_Δi).

Using grid search method to J₁It is optimized, each parameter area is respectively：

Step-size in search is taken to be respectively：

Obtain optimized parameter (t_T ^*, θ^*, W_Δi ^*) after, according to (1), (2) calculate the track of transmitter section and transfer leg.

In sum, using the present invention, simply it is easy to solve, result of calculation has very big finger for Project Realization to solution principle Lead meaning, and can be applicable to the polar region hovering satellite task design phase of the demands such as polar region observation, communication.

Do not specify in the present invention and partly belong to techniques known.

Claims (10)

1. a kind of design method of the satellite orbit that hovered based on polar region, is carried out by the working track of the satellite that hovered in polar region Design and specificity analysises to complete the system design of whole star and transfer orbit designs it is characterised in that comprising the following steps：

Step one, the dynamical motion of the satellite that hovered in described polar region is described, and the control of the satellite that hovered in described polar region Characteristic is calculated, thus being designed to its working track optimizing to obtain optimal design parameter；

Step 2, according to described optimal design parameter, counts to the attribute of each subsystem as described polar region hovering satellite Calculate, thus obtaining the biggest quality of described polar region hovering Satellite Payloads；And

Step 3, determines the transfer leg track of transfer orbit and the launch trajectory of described polar region hovering satellite respectively, and to institute The orbit parameter obtaining is optimized, thus designing the transfer orbit of optimum,

Wherein, described attribute at least includes quality.

2. according to claim 1 based on polar region hover satellite orbit design method it is characterised in that in institute State execution in step one：

Using circular Restricted three-body model, the dynamical motion of the satellite that hovered in described polar region is described；

Under the conditions of fixing hovering height, the control characteristic of the satellite that hovered in described polar region is analyzed；And

By the way of optimal control problem, the working track of the satellite that hovered in described polar region is designed optimizing.

3. according to claim 2 based on polar region hover satellite orbit design method it is characterised in that described Step one also includes：

Calculate described optimal control problem using optimum control numerical optimization software kit, the control spy of the satellite that hovers with described polar region Property analysis result as optimized algorithm initial value, thus obtaining the working track of optimal-fuel and controlling acceleration and control The time history of power processed.

4. according to claim 3 based on polar region hover satellite orbit design method it is characterised in that

The hover dynamical motion equation of satellite of described polar region is： $\stackrel{.}{x}=\left[\begin{array}{c}\stackrel{.}{r}\\ \stackrel{.}{v}\\ \stackrel{.}{m}\end{array}\right]=\left[\begin{array}{c}v\\ -\▿U-2\mathrm{\ω}\×v+a_T\\ {-\mathrm{mg}}_T/I_{\mathrm{sp}}{g}_0\end{array}\right],$ Wherein, described Dynamical motion defines in the rotated coordinate system, and zero refers to earthwards in Solar-terrestrial system barycenter, x-axis for the sun, Z-axis is Solar-terrestrial system rotational angular velocity vector direction, and y-axis constitutes right hand rectangular coordinate system, and r is under described rotating coordinate system The position vector of described base hovering satellite, v is the velocity of described base hovering satellite, and w is described rotating coordinate system Angular velocity vector, a_TFor controlling acceleration and its mould a_TRepresent, m is the quality of described base hovering satellite, I_sp For electric propulsion engine specific impulse, g₀For sea level acceleration of gravity, U is potential-energy function and form is $U=-\frac{{\mathrm{\μ}}_1}{\left|\right|r-r_1\left|\right|}-\frac{{\mathrm{\μ}}_2}{\left|\right|r-r_2\left|\right|}-{\mathrm{\ω}}^2\frac{{r_x}^2+{r_y}^2}{2},$ μ₁、μ₂It is respectively the gravitational constant of the sun and the earth, r₁、r₂Point Not Wei the sun and the earth position vector.

5. according to claim 4 based on polar region hover satellite orbit design method it is characterised in that described Optimal control problem at least includes：Object function, boundary condition and path constraints,

Wherein,

Described object function is：J=-m_f=-m (t_f),

Described boundary condition is：r_y(t₀)=0, m (t₀)=m₀, r (t_f)=r (t₀), v (t_f)=v, (t₀), and

Described path constraints are： $\left\{\begin{array}{c}{\tan }^{-1}({-r}_{2,y},r_{2,x})-\mathrm{wt}=0\\ \sqrt{r_{2,x}^2+r_{2,y}^2}-r_{2,z}\tan \left({\mathrm{\δ}}_{\mathrm{eq}}\right)=0\end{array}\right.,$

J represents target function value, and polar region hovering track has the periodicity of 1 year, t₀For initial time and elect first point of Capricornus as, r(t₀) it is to hover the initial time position vector of satellite in described polar region, v (t₀) it is initial time velocity, m (t₀) it is described Hovering satellite in polar region is in the quality of initial time, t_fFor task service life, r (t_f), v, (t_f) it is to hover the end of satellite in described polar region The position and speed vector in moment, m (t_f) be the last moment quality, and (r_{2, x}, r_{2, y}, r_{2, z})^T=r-r₂, δ_eq=23.5 ° is Huang The red angle of cut.

6. according to claim 5 based on polar region hover satellite orbit design method it is characterised in that in institute State execution in step 2：

Mechanical characteristic according to described working track come design described polar region hover satellite subsystem attribute；

According to the gross mass of described polar region hovering satellite, calculate the biggest quality of described payload system；And

When described payload system requires, the gross mass of the satellite that hovered in described polar region is iterated,

Wherein, described attribute at least includes power, size, quality.

7. according to claim 6 based on polar region hover satellite orbit design method it is characterised in that described Step 2 includes：

According to described controling power time history, find the maximum of controling power；

According to described Optimal State variable, obtain the mass change of described polar region hovering satellite；

Calculate fuel, fuel tank system, electric propulsion system, the quality of power-supply system respectively, thus obtaining described effective load The quality of G system；And

Depending on task situation, recalculate the initial mass of described polar region hovering satellite by iteration.

8. according to claim 7 based on polar region hover satellite orbit design method it is characterised in that described The described transfer orbit of polar region hovering satellite is divided into transmitter section and transfer leg,

Wherein, described transmitter section is completed by the mode of rocket Upper Stage chemical propulsion, and described transfer leg is not using applying arteries and veins The trajectory branch mode of punching or continuous thrust completes.

9. according to claim 8 based on polar region hover satellite orbit design method it is characterised in that in institute State execution in step 3：

Using manifold design, the track of described polar region hovering satellite is inversely integrated, thus finding out described transfer leg track, And the orbit parameter of described transfer leg track is changed between described circle Restricted three-body model and two body Models；

Design the launch trajectory of described polar region hovering satellite using Huo Man branch mode；And

Using grid data service, the orbit parameter being obtained is optimized, thus designing the transfer orbit of optimum.

10. according to claim 9 based on polar region hover satellite orbit design method it is characterised in that In described step 3, the described process finding out described transfer leg track includes：

Set out with a point of the polar region hovering track of any time, turn over predetermined angular with rotating coordinate system, according to described circle The restricted three body dynamics models of shape inversely integrate to described track, thus obtaining the track manifold of described polar region hovering satellite；

Block in the nearest position of the liftoff ball of manifold, obtain the reverse time of integration now and position and speed parameter herein；

Position and speed parameter in rotating coordinate system in described circle Restricted three-body model is obtained described two through Coordinate Conversion Position and speed under inertial coodinate system in body Model, and it is calculated corresponding Keplerian orbit six key element；And

The perigee altitude of transfer orbit and altitude of the apogee according to Keplerian orbit six element factor calculation.