CN103676954B - A kind of satellier injection success evaluation method - Google Patents

Abstract

A kind of satellier injection success evaluation method, waits track amount to determine whether to meet the maximum deviation that carrier rocket is given respectively according to semi-major axis deviation | the Δ a | of satellier injection, inclination deviation | Δ i | and eccentricity deviation | Δ e | | Δ a_L|、|Δi_L| with | Δ e_L|, if being satisfied by, result of entering the orbit is " success ".When above-mentioned condition has one or more being unsatisfactory for, except ensureing that the fuel that set change rail task consumes is held or carried out to normal dimensions in-orbit, the maximum deflection difference value that semi-major axis, inclination angle and eccentricity can be revised is estimated respectively according to fuel residual amount, by each entry value weighting summation, result of entering the orbit when summation is less than 1 is " success ".Using all fuel quantities to estimate the maximum that every deviation can be revised, weighting summation respectively, result of entering the orbit when summation is less than 1 is " being successful on the whole ".Use graphic-arts technique that the border of above-mentioned three kinds of successful results is divided, the regional extent of three kinds of different successful types of definition.Carrying out enters the orbit when successfully passing judgment on, and searches region affiliation with actual Orbit injection error, provides the successful types of this transmitting.

Description

A kind of satellier injection success evaluation method

Technical field

The present invention relates to a kind of satellier injection success evaluation method.

Background technology

Certain Orbit injection error is often had, it is necessary to carry out passing judgment in time so that the coping strategy outwards issued in result or the improper situation of entering the orbit of rapid development in time rescues to the transmitting situation of carrier rocket during satellite launch.Inclined extent directly affects the type of evaluation result, provides satellite according to different imposing a condition and enters the orbit accordingly successful conclusion.

Using different carrier rockets to perform launch mission, its Orbit injection error is different, should select according to mission requirements during satellite launch.Carrier rocket provides the maximum deviation of correlative when normally entering the orbit according to series of influence factors, for satellite reference whether within the allowed band of its mission requirements, if this maximum deviation is recognized, means and satellite task is substantially not present impact, therefore this kind can be fallen within the given emission results normally entered the orbit within the scope of maximum deviation of carrier rocket and be defined as " success ".For overwhelming majority satellite, especially the track of low orbit satellite maintains and the motor-driven transfer in geostationary orbit emission process, satellite itself can carry certain fuel to ensure in its lifetime in orbit properly functioning or to perform set change rail task, and for ensureing to leave the reliability of certain surplus, fuel carrying amount is often slightly many than result of calculation.Therefore, when entering the orbit overproof and can guarantee that again unnecessary fuel remains able to the correction realizing satellite self to deviation, then this kind of emission results can being defined as " success ", the demand for fuel that now lifetime of satellite phase inner orbit maintains and change trailer is dynamic all can be unaffected.If entered the orbit, overproof continuation worsens, until needing all fuel that satellite carries all satellite just can be made to arrive task track for carrying out drift correction, then this kind of emission results is defined as " being successful on the whole ".Providing of three kinds of successful judging basis, has quantified successful type of entering the orbit, and can instruct means as transmitting successful one of entering the orbit, and by simple inequality and figure intuitively, it is possible to provides transmitting fast and efficiently and enters the orbit result.

Summary of the invention

The technical problem to be solved is: provide a kind of satellier injection success evaluation method, quantifies different successful types of entering the orbit, the easy and efficient successful result that judges to enter the orbit.

As shown in Figure 1, a kind of satellier injection success evaluation method of the present invention, waits track amount to determine whether to meet the maximum deviation that carrier rocket is given respectively according to semi-major axis deviation | the Δ a | of satellier injection, inclination deviation | Δ i | and eccentricity deviation | Δ e | | Δ a_L|、|Δi_L| with | Δ e_L|, if being satisfied by, result of entering the orbit is " success ".When above-mentioned condition has one or more being unsatisfactory for, except ensureing that the fuel that set change rail task consumes is held or carried out to normal dimensions in-orbit, the maximum deflection difference value that semi-major axis, inclination angle and eccentricity can be revised is estimated respectively according to fuel residual amount, by each entry value weighting summation, result of entering the orbit when summation is less than 1 is " success ".Using all fuel quantities to estimate the maximum that every deviation can be revised, weighting summation respectively, result of entering the orbit when summation is less than 1 is " being successful on the whole ".Use graphic-arts technique that the border of above-mentioned three kinds of successful results is divided, the regional extent of three kinds of different successful types of definition.Carrying out enters the orbit when successfully passing judgment on, and searches region affiliation with actual Orbit injection error, provides the successful types of this transmitting.

Specifically include following steps:

(1) track amount is waited to determine whether to meet the maximum deviation that carrier rocket is given respectively according to semi-major axis deviation | the Δ a | of satellier injection, inclination deviation | Δ i | and eccentricity deviation | Δ e | | Δ a_L|、|Δi_L| with | Δ e_L|。

$\left\{\begin{array}{c}\left|\mathrm{\Δa}\right|\≤\left|\mathrm{\Δ}{a}_L\right|\\ \left|\mathrm{\Δi}\right|\≤\left|\mathrm{\Δ}{i}_L\right|\\ \left|\mathrm{\Δe}\right|\≤\left|\mathrm{\Δ}{e}_L\right|\end{array}\right.---\left(1\right)$

When all setting up with upper inequality, result of entering the orbit is " success ".

(2) except ensureing that the fuel that set change rail task consumes is held or carried out to normal dimensions in-orbit, estimating the maximum deflection difference value that semi-major axis, inclination angle and eccentricity can be revised respectively according to fuel residual amount, the maximum value calculation formula of every deviation is as follows.

$\left|\mathrm{\Δ}{a}_{\max }\right|=\frac{-2a^{\frac{3}{2}}\mathrm{Ig}\·\mathrm{In}(1-\frac{\mathrm{\Δm}}{M})}{\sqrt{\mathrm{\μ}}}---\left(2\right)$

$\left|\mathrm{\Δ}{i}_{\max }\right|=\frac{-0.69244\mathrm{Ig}{a}^4\·\mathrm{In}(1-\frac{\mathrm{\Δm}}{M})}{\sqrt{\mathrm{\μ}}{R}_e^{3.5}\sin i}---\left(3\right)$

$\left|\mathrm{\Δ}{e}_{\max }\right|=\frac{\left|\mathrm{\Δ}{a}_{\max }\right|}{a}---\left(4\right)$

Wherein, a is satellite nominal semi-major axis, and i is nominal inclination angle, and I is constant engine vacuum ratio, and g is acceleration of gravity, and Δ m is the fuel quantity that can use, and M is satellite quality, R_eFor earth radius, μ is Gravitational coefficient of the Earth.

Inequality group has one or more to be false in (1), and when setting up with lower inequality, result of entering the orbit is " success ".

$\frac{\left|\mathrm{\&Delta;a}\right|}{\left|\mathrm{\&Delta;}{a}_{\max }\right|}+\frac{\left|\mathrm{\&Delta;i}\right|}{\left|\mathrm{\&Delta;}{i}_{\max }\right|}+\frac{\left|\mathrm{\&Delta;e}\right|}{\left|\mathrm{\&Delta;}{e}_{\max }\right|}<1---\left(5\right)$

(3) according to described step (2), all fuel quantities are used again to estimate the maximum deflection difference value that semi-major axis, inclination angle and eccentricity can be revised respectively.

When in described step (2), inequality (5) is false, and use the weighting summation that all fuel quantities calculate to enable to inequality (5) establishment, then result of entering the orbit is " being successful on the whole ".

(4) using graphic-arts technique that the border of three kinds of successful results in described step (1)～(3) is divided, the regional extent of three kinds of different successful types of definition, boundary condition is following formula such as.

$\frac{\left|\mathrm{\&Delta;a}\right|}{\left|\mathrm{\&Delta;}{a}_{\max }\right|}+\frac{\left|\mathrm{\&Delta;i}\right|}{\left|\mathrm{\&Delta;}{i}_{\max }\right|}+\frac{\left|\mathrm{\&Delta;e}\right|}{\left|\mathrm{\&Delta;}{e}_{\max }\right|}=1---\left(6\right)$

The span of | Δ a | with | Δ i | is respectively set as [0, | Δ a_max|]、[0,|Δi_max|], | Δ e | the value that cycle calculations difference vector (| Δ a |, | Δ i |) is corresponding.All (| Δ a |, | Δ i |, | Δ e |) meeting formula (6) are the border of corresponding successful types in three-dimensional spatial distribution.

(5) carrying out enters the orbit when successfully passing judgment on, and directly actual Orbit injection error is carried out region affiliation lookup in the drawings, provides the successful types of this transmitting.

The inventive method employs conventional semi-major axis, eccentricity and inclination angle three's track amount and carries out entering the orbit and successfully pass judgment on, in track six roots of sensation number, the judge of other correlatives can similar be included in inequality (5) left side, and boundary condition is enumerated still according to formula (6) mode.For successfully passing judgment on be more than or equal to entering the orbit of 4 track amounts, directly use inequality method.

Present invention advantage compared with prior art is in that: the present invention be directed to satellier injection and successfully passes judgment on, provide three kinds of definition modes, use inequality method and graphic-arts technique that different successful types is divided, perfect enter the orbit successful judging basis and means, position result of entering the orbit quickly, efficiently and intuitively.

Accompanying drawing explanation

Fig. 1 is the flow chart of the inventive method；

Fig. 2 is the area distribution of successful result of entering the orbit；

Fig. 3 is for revising the fuel consumption border of " success " and " being successful on the whole " type.

Detailed description of the invention

Embodiment

For certain the sun synchronization circular orbit satellite launched to 600km height, theory orbit inclination angle i=97.783 °, eccentric ratio e=0.Satellite quality is M=1000kg, and constant engine vacuum is than for I=200s, and altogether carrying fuel quantity is Δ m=50kg, and wherein 30kg must be used for the maintenance in-orbit in lifetime, and fuel residual amount is 20kg.Assume the normal Orbit injection error of carrier rocket respectively | Δ a_L|=30km、|Δi_L|=0.05 ° and | Δ e_L|=0.003, actual Orbit injection error is | Δ a |=20km, | Δ i |=0.2 ° and | Δ e |=0.0055 respectively.

" success " and " being successful on the whole " two kinds of boundary condition is calculated respectively according to described step (2), the area distribution of different results of successfully entering the orbit is as shown in Figure 2, I district is " success ", and II district is " success ", and III district is " being successful on the whole ".

The inequality group meeting " success " type is:

The inequality meeting " success " type is:

The inequality meeting " being successful on the whole " type is:

When satisfied " success " inequality group is entered the orbit in transmitting, can not carrying out Orbit injection error correction, Fig. 3 is the fuel consumption border revising " success " and " being successful on the whole " type.

According to the carrier rocket Orbit injection error assumed and actual Orbit injection error value, it is determined that the successful types that this transmitting obtains should be " success ".

The content not being described in detail in description of the present invention belongs to the known technology of those skilled in the art.

Claims (1)

1. a satellier injection success evaluation method, it is characterised in that realize step as follows:

(1) determine whether to meet the maximum deviation that carrier rocket is given respectively with eccentricity deviation | Δ e | track amount according to semi-major axis deviation | the Δ a | of satellier injection, inclination deviation | Δ i | | Δ a_L|、|Δi_L| with | Δ e_L|；

$\left\{\begin{array}{c}\left|\mathrm{\&Delta;}a\right|\&le;\left|{\mathrm{\&Delta;a}}_L\right|\\ \left|\mathrm{\&Delta;}i\right|\&le;\left|{\mathrm{\&Delta;i}}_L\right|\\ \left|\mathrm{\&Delta;}e\right|\&le;\left|{\mathrm{\&Delta;e}}_L\right|\end{array}\right.---\left(1\right)$

When all setting up with upper inequality, result of entering the orbit is " success "；

(2) except ensureing that the fuel that set change rail task consumes is held or carried out to normal dimensions in-orbit, the maximum deflection difference value that semi-major axis, inclination angle and eccentricity can be revised is estimated respectively according to fuel residual amount | Δ a_max|、|Δi_max| with | Δ e_max|, the maximum value calculation formula of every deviation is as follows:

$\left|{\mathrm{\&Delta;a}}_{max}\right|=\frac{-2a^{\frac{3}{2}}Ig\&CenterDot;ln(1-\frac{\mathrm{\&Delta;}m}{M})}{\sqrt{\mathrm{\&mu;}}}---\left(2\right)$

$\left|{\mathrm{\&Delta;i}}_{max}\right|=\frac{-0.69244{\mathrm{Iga}}^4\&CenterDot;In(1-\frac{\mathrm{\&Delta;}m}{M})}{\sqrt{\mathrm{\&mu;}}{R}_e^{3.5}\sin i}---\left(3\right)$

$\left|{\mathrm{\&Delta;e}}_{max}\right|=\frac{\left|{\mathrm{\&Delta;a}}_{max}\right|}{a}---\left(4\right)$

Wherein, a is satellite nominal semi-major axis, and i is nominal inclination angle, and I is constant engine vacuum ratio, and g is acceleration of gravity, and Δ m is the fuel quantity that can use, and M is satellite quality, R_eFor earth radius, μ is Gravitational coefficient of the Earth；

Inequality group has one or more to be false in (1), and when setting up with lower inequality, result of entering the orbit is " success "；

$\frac{\left|\mathrm{\&Delta;}a\right|}{\left|{\mathrm{\&Delta;a}}_{max}\right|}+\frac{\left|\mathrm{\&Delta;}i\right|}{\left|{\mathrm{\&Delta;i}}_{max}\right|}+\frac{\left|\mathrm{\&Delta;}e\right|}{\left|{\mathrm{\&Delta;e}}_{max}\right|}<1---\left(5\right)$

(3) according to described step (2), all fuel quantities are used again to estimate the maximum deflection difference value that semi-major axis, inclination angle and eccentricity can be revised respectively；

When in described step (2), inequality (5) is false, and use the weighting summation that all fuel quantities calculate to enable to inequality (5) establishment, then result of entering the orbit is " being successful on the whole "；

(4) use graphic-arts technique that the border of three kinds of successful results in described step (1)～(3) is divided, the regional extent of three kinds of different successful types of definition, boundary condition is following formula such as:

$\frac{\left|\mathrm{\&Delta;}a\right|}{\left|{\mathrm{\&Delta;a}}_{max}\right|}+\frac{\left|\mathrm{\&Delta;}i\right|}{\left|{\mathrm{\&Delta;i}}_{max}\right|}+\frac{\left|\mathrm{\&Delta;}e\right|}{\left|{\mathrm{\&Delta;e}}_{max}\right|}=1---\left(6\right)$

The span of | Δ a | with | Δ i | is respectively set as [0, | Δ a_max|]、[0,|Δi_max|], | Δ e | the value that cycle calculations difference vector (| Δ a |, | Δ i |) is corresponding, all (| Δ a | meeting formula (6), | Δ i |, | Δ e |) border of corresponding successful types it is in three-dimensional spatial distribution；

(5) carrying out enters the orbit when successfully passing judgment on, and directly actual Orbit injection error is carried out region affiliation lookup, provides the successful types of this transmitting.