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Interstellar transfer finite thrust injection iterative guidance method of low thrust-weight ratio aircraft

An interstellar transfer orbit and thrust-to-weight ratio technology, applied in the aerospace field, can solve problems such as inability to solve orbit transfer problems, non-convergence of solving constraint equations, and long calculation time.

Active Publication Date: 2019-06-21
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

However, the calculation time of this method is relatively long, and in the process of solving the direct transfer problem from low orbit to interstellar transfer orbit, there will be a problem of non-convergence when solving the constraint equation, so this kind of orbit transfer problem cannot be solved

Method used

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  • Interstellar transfer finite thrust injection iterative guidance method of low thrust-weight ratio aircraft

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Embodiment 1

[0084] Taking the Earth-Moon transfer as an example, in order to verify the feasibility of the method, we choose to start guidance from the Earth's near-Earth 170km circular orbit at 8:00 pm on October 12, 2020, and the goal is to reach the Moon's 300km altitude orbit. The parameters of the detector engine during the guidance process are shown in Table 1, and the initial state and the state of the reference orbit point are shown in Table 2:

[0085] Table 1 Initial detector engine parameters

[0086]

[0087] Table 2 Initial state and terminal state

[0088]

[0089] Such as figure 1 As shown, a low thrust-to-weight ratio interstellar transfer limited thrust iterative guidance method for orbital transfer disclosed in this embodiment, the specific implementation steps are as follows:

[0090] Step 1: Establish the dynamic equation of the detector under the inertial system of the earth's center of mass.

[0091] The probe moves outside the earth's atmosphere, and the ex...

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Abstract

The invention discloses an interstellar transfer finite thrust injection iterative guidance method of a low thrust-weight ratio aircraft, and belongs to the field of aerospace. The method comprises the steps of establishing a detector kinetic equation under an inertial system of center of mass of the earth; converting the location speed of a detector under the inertial system into an injection point inertial system, and expressing in an orbital element form. Simplifying the detector kinetic equation, controlling the detector according to a guidance strategy, and stopping the guidance when theguidance meets a corresponding terminal condition, then the detector enters an interstellar transfer orbit, and direct transfer of the detector from a near-earth orbit to the interstellar transfer orbit is realized, wherein the corresponding terminal condition is that an engine of the detector meets a power-off condition to establish the detector kinetic equation, solving midcourse correction pulse according to a shooting equation, and performing orbit midcourse correction, so as to enable the detector to reach a target orbit near a target star, so that accurate interstellar transfer with thelow thrust-weight ratio is realized. The interstellar transfer finite thrust injection iterative guidance method of the low thrust-weight ratio aircraft has the advantages of fast calculation speed, good convergence and high applicability.

Description

technical field [0001] The present invention relates to an iterative guidance method for interstellar transfer limited thrust into orbit suitable for low thrust-to-weight ratio aircraft, in particular to a method of starting from a point in a near-earth circular orbit and using limited thrust iterative guidance to directly enter the interstellar transfer orbit, combined with midway correction The invention relates to a method for accurately arriving at a predetermined orbit for interstellar transfer satisfying constraints, belonging to the field of aerospace. Background technique [0002] In the process of interstellar exploration, transfer into orbit is a key link. In view of the limited thrust amplitude of the main engine during the interstellar transfer process, the long orbit change time, and the large error of the traditional impulse orbit change method, the research on the limited thrust iterative guidance problem during the interstellar transfer process was carried ou...

Claims

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Application Information

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IPC IPC(8): B64G1/24
Inventor 乔栋庞博韩宏伟
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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