CN103676954A - Satellite injection success evaluation method - Google Patents

Abstract

A satellite injection success evaluation method. Orbit quantities including a semi-major axis deviation |delta a|, a tilt angle deviation |delta i|, and an eccentricity deviation |delta e| in satellite injection are used to determine whether maximum deviation of |delta aL|, |delta iL| and |delta eL| given by a carrier rocket are met; and if all the maximum deviation are met, the satellite injection result is "a complete success". If one or more of the conditions are not satisfied, in addition to fuel which is used to guarantee normal in-orbit maintenance or a preset orbit transfer mission, a maximum deviation, which can be corrected by the semi-major axis, the tilt angle, and the eccentricity, can be estimated according to a fuel allowance; and all values are weighted and added, and the satellite injection result is a "success" when a sum of all the values is less than 1. All fuel quantity is used to respectively estimate the maximum value which can be corrected by each deviation, the maximum values are weighted and added, and the satellite injection result is a "basic success" when the sum of the maximum values are less than 1. A graphical method is used to carry out boundary division of the above three success results, and to define the regional scope of three different types of successes. When the satellite injection success evaluation is carried out, the actual injection error is used to search the regional scope, and the success type of the given launch is determined.

Description

A kind of satellite successful evaluation method of entering the orbit

Technical field

The present invention relates to a kind of satellite successful evaluation method of entering the orbit.

Background technology

During satellite launch, often have certain Orbit injection error, need to pass judgment in time so that the outside countermeasure of issuing result or formulating fast in the improper situation of entering the orbit rescues in time the transmitting situation of carrier rocket.Partially extent directly affects the type of evaluation result, according to different imposing a condition, provides the satellite successful conclusion of entering the orbit accordingly.

Use different carrier rockets to carry out launch mission, its Orbit injection error is different, during satellite launch, should select according to mission requirements.Carrier rocket provides the maximum deviation of correlative while normally entering the orbit according to series of influence factors, for satellite with reference to whether within the allowed band of its mission requirements, if this maximum deviation is approved, to mean satellite task is not existed to impact substantially, the emission results that therefore this kind can be fallen within the scope of the given maximum deviation of normally entering the orbit of carrier rocket is defined as " success ".For most satellites, especially the track of low orbit satellite maintain with geostationary orbit emission process in motor-driven transfer, satellite itself can carry certain fuel to guarantee in its lifetime normal operation in orbit or carry out set change rail task, and for guaranteeing to leave the reliability of certain surplus, the fuel amount of carrying tends to slightly more than result of calculation.Therefore, when entering the orbit overproof and can guaranteeing that again unnecessary fuel still can realize the correction of satellite self to deviation, this kind of emission results can be defined as to " success ", now maintain and become the moving demand for fuel of trailer all can be unaffected for lifetime of satellite phase inner orbit.If entered the orbit, overproof continuation worsens, until need all fuel that satellite carries to be all used for carrying out drift correction, just can make satellite arrive task track, this kind of emission results is defined as to " being successful on the whole ".Providing of three kinds of successful judging basis, the successful type that quantized to enter the orbit, can be used as the transmitting successfully a kind of means that instruct of entering the orbit, and by simple inequality and figure intuitively, can provide fast and efficiently and launch the result of entering the orbit.

Summary of the invention

Technical matters to be solved by this invention is: a kind of satellite successful evaluation method of entering the orbit is provided, quantizes the different successful types of entering the orbit, the easy and efficient judgement successful result of entering the orbit.

As shown in Figure 1, a kind of satellite of the present invention successful evaluation method of entering the orbit, the semi-major axis deviation of entering the orbit according to satellite | Δ a|, inclination deviation | Δ i| and excentricity deviation | the track amounts such as Δ e| determine whether and meet respectively the maximum deviation that carrier rocket is given | Δ a _l|, | Δ i _l| and | Δ e _l|, if all meet, enter the orbit result for " success ".Above-mentioned condition has one or more while not meeting, except ensureing, normally maintain in-orbit or carry out the fuel of set change rail task consumption, based on fuel surplus is estimated respectively the maximum deflection difference value that semi-major axis, inclination angle and excentricity can be revised, by every value weighting summation, the result of entering the orbit when summation is less than 1 is " success ".Use all fuel quantities to estimate respectively the maximal value that every deviation can be revised, weighting summation, the result of entering the orbit when summation is less than 1 is " being successful on the whole ".Use graphic-arts technique to divide the border of above-mentioned three kinds of successful results, the regional extent of three kinds of successful types of difference of definition.Enter the orbit while successfully passing judgment on, by actual Orbit injection error seek area ownership, provide the successful type of this transmitting.

Specifically comprise the steps:

(1) the semi-major axis deviation of entering the orbit according to satellite | Δ a|, inclination deviation | Δ i| and excentricity deviation | the track amounts such as Δ e| determine whether and meet respectively the maximum deviation that carrier rocket is given | Δ a _l|, | Δ i _l| and | Δ e _l|.

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

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

(2) except ensureing, normally maintain in-orbit or carry out the fuel of set change rail task consumption, based on fuel surplus is estimated respectively the maximum deflection difference value that semi-major axis, inclination angle and excentricity can be revised, and 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, the fuel quantity of Δ m for using, 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 while setting up with lower inequality, the 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), use all fuel quantities again to estimate respectively the maximum deflection difference value that semi-major axis, inclination angle and excentricity can be revised.

In described step (2), inequality (5) is false, and uses the weighting summation of all fuel quantities calculating can make inequality (5) set up, and the result of entering the orbit is " being successful on the whole ".

(4) use graphic-arts technique to divide the border of three kinds of successful results in described step (1)～(3), the regional extent of three kinds of successful types of difference of definition, boundary condition as shown in the formula.

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

By | Δ a| and | the span of Δ i| be set as respectively [0, | Δ a _max|], [0, | Δ i _max|], the different vectors of cycle calculations (| Δ a|, | Δ i|) corresponding | Δ e| value.All meet formula (6) (| Δ a|, | Δ i|, | Δ e|) in three-dimensional spatial distribution, be the border of corresponding successful type.

(5) enter the orbit while successfully passing judgment on, directly actual Orbit injection error is carried out in the drawings to region ownership and search, provide the successful type of this transmitting.

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

The present invention's advantage is compared with prior art: the present invention be directed to satellite and enter the orbit and successfully pass judgment on, provide three kinds of definition modes, use inequality method and graphic-arts technique to divide different successful types, perfect enter the orbit successful judging basis and means, position the result of entering the orbit fast, efficiently and intuitively.

Accompanying drawing explanation

Fig. 1 is the process flow diagram of the inventive method;

Fig. 2 is the areal 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.

Embodiment

Embodiment

Certain the sun synchronization circular orbit satellite that is emitted to 600km height of take is example, theoretical orbit inclination i=97.783 °, eccentric ratio e=0.Satellite quality is M=1000kg, and constant engine vacuum is than being I=200s, and altogether carrying fuel quantity is Δ m=50kg, and wherein 30kg must be for maintaining in lifetime in-orbit, and fuel surplus is 20kg.Suppose that the normal Orbit injection error of carrier rocket is respectively | Δ a _l|=30km, | Δ i _l|=0.05 ° and | Δ e _l|=0.003, actual Orbit injection error is respectively | Δ a|=20km, | Δ i|=0.2 ° and | Δ e|=0.0055.

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

The inequality group that meets " success " type is:

The inequality that meets " success " type is:

The inequality that meets " being successful on the whole " type is:

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

According to carrier rocket Orbit injection error and the actual Orbit injection error value of hypothesis, judge that the successful type that this transmitting obtains should be " success ".

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

Claims (1)

1. the satellite successful evaluation method of entering the orbit, is characterized in that performing step is as follows:

(1) the semi-major axis deviation of entering the orbit according to satellite | Δ a|, inclination deviation | Δ i| and excentricity deviation | the track amounts such as Δ e| determine whether and meet respectively the maximum deviation that carrier rocket is given | Δ a _l|, | Δ i _l| and | Δ e _l|;

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

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

(2) except ensureing, normally maintain in-orbit or carry out the fuel of set change rail task consumption, based on fuel surplus is estimated respectively semi-major axis | Δ a _max|, inclination angle | Δ i _max| and excentricity | Δ e _max| the maximum deflection difference value that can revise, the maximum value calculation formula of every deviation is as follows:

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

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

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

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, the fuel quantity of Δ m for using, 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 while setting up with lower inequality, the 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), use all fuel quantities again to estimate respectively the maximum deflection difference value that semi-major axis, inclination angle and excentricity can be revised;

In described step (2), inequality (5) is false, and uses the weighting summation of all fuel quantities calculating can make inequality (5) set up, and the result of entering the orbit is " being successful on the whole ";

(4) use graphic-arts technique to divide the border of three kinds of successful results in described step (1)～(3), the regional extent of three kinds of successful types of difference of definition, boundary condition as shown in the formula:

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

By | Δ a| and | the span of Δ i| be set as respectively [0, | Δ a _max|], [0, | Δ i _max|], different vectors of cycle calculations (| Δ a|, | Δ i|) are corresponding | Δ e| value, all meet formula (6) (| Δ a|, | Δ i|, | Δ e|) in three-dimensional spatial distribution, be the border of corresponding successful type;

(5) enter the orbit while successfully passing judgment on, directly actual Orbit injection error is carried out in the drawings to region ownership and search, provide the successful type of this transmitting.

Images