Boost phase generalized standard miss distance analysis guidance method

A technology of standard-controlled miss-on-target amount and boost segment, which is applied in the field of generalized standard-controlled miss-on-target amount analytical guidance in the boost segment, and can solve the problem that the zero-controlled miss-target amount cannot fully meet the needs of the guidance method design.

Active Publication Date: 2016-05-04
BEIHANG UNIV
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Problems solved by technology

Although the concept of zero-controlled miss has achieved great success in solving the guidance problems with terminal position constraints and angle constraints, as the nonli

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  • Boost phase generalized standard miss distance analysis guidance method
  • Boost phase generalized standard miss distance analysis guidance method
  • Boost phase generalized standard miss distance analysis guidance method

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Embodiment example

[0199] In order to verify the booster guidance method based on the generalized standard control miss amount, the first and second stages of the Minotaur 5 rocket are used as the booster model, in which the first stage adopts the program pitch angle guidance, and the second stage uses The guidance method of the boost phase based on the generalized standard control miss amount, and an unpowered gliding phase is added between the two stages. The simulation parameter settings are shown in Table 1, and the pull-off parameter settings are shown in Table 2.

[0200] Table 1. Guidance simulation parameter settings in boost phase

[0201]

[0202] Table 2 Simulation parameter pulling bias setting

[0203] parameters

Pull bias value (3σ)

parameters

Pull bias value (3σ)

lift coefficient

10％

atmospheric density

10％

OK

10％

mass second flow rate

5％

[0204] Figure 9a-9f The target shooting results in the boost stage are ...

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Abstract

The invention relates to a boost phase generalized standard miss distance analysis guidance method. The method comprises steps that 1, boost phase guidance problem modeling is carried out, including standard ballistic movement modeling, guidance correction first-order perturbation modeling and terminal constraint modeling; 2, boost phase standard ballistic regular perturbation solution modeling is carried out; 3, boost phase standard ballistic zero-order item analysis solution on the basis of regular perturbation is carried out; 4, boost phase standard ballistic first-order item analysis solution on the basis of regular perturbation is carried out; and 5, boost phase optimal guidance instruction solution on the basis of the standard miss distance is carried out. Through the method, zero-incidence is taken as boost phase ballistic standard control, analysis solution is carried out by employing a regular perturbation method, and thereby an analyzed standard miss distance is acquired; an optimal control method is employed to solve a guidance instruction of the correction standard miss distance, and thereby a non-linear analysis optimal guidance method satisfying boost phase task demands is acquired.

Description

technical field [0001] The invention provides a generalized standard control miss-target amount analysis guidance method in the boost section, which belongs to the fields of aerospace technology and weapon technology. Background technique [0002] The trajectory of the booster segment can usually be divided into a program flight segment in the atmosphere and a guided flight segment outside the atmosphere. The program flight segment adopts open-loop control commands set according to time or speed, and usually does not perform feedback adjustment; the guided flight segment uses Perturbation guidance or iterative guidance for closed-loop correction. But for the boost-glide hypersonic vehicle, the higher the height of the boost section, the greater the maximum heat flux density of the reentry pull-off section. This requires the boost phase to lower the terminal altitude so that most or all of the boost phase trajectory is within the atmosphere. The current closed-loop guidance...

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 陈万春胡锦川
Owner BEIHANG UNIV
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