A method for judging separation time of two-stage aircraft based on axial overload

A discrimination method and aircraft technology, applied in the direction of instruments, adaptive control, control/adjustment systems, etc., can solve problems such as front/rear stage collisions, achieve the effects of ensuring separation safety, clear physical concepts, and improving flight control quality

Active Publication Date: 2021-12-21
SHANGHAI AEROSPACE CONTROL TECH INST
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AI Technical Summary

Problems solved by technology

The timing of the main stage control is directly related to the success or failure of the entire flight test. If the main stage is started in advance, it will easily cause the risk of collision between the front and rear stages; if the main stage is delayed, there will be a risk of uncontrolled flight in the main stage.

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  • A method for judging separation time of two-stage aircraft based on axial overload
  • A method for judging separation time of two-stage aircraft based on axial overload
  • A method for judging separation time of two-stage aircraft based on axial overload

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Embodiment Construction

[0021] Hereinafter, the present invention will be further described in conjunction with the accompanying drawings and examples.

[0022] Obtain the flight state of the aircraft at the time of two-stage separation, and calculate the theoretical value of axial overload N before and after separation x1 , N x2 ; To separate the front axial overload N x1 Calculation as an example, the calculation formula is shown in the following formula (1):

[0023]

[0024] where: q 1 Real-time flight pressure for the aircraft at the moment of separation; k 1 is about Ca 1 ,S 1 ,Mass 1 The associated f-function, Ca 1 ,S 1 ,Mass 1 are the axial force coefficient, cross-sectional area, and mass of the aircraft, respectively;

[0025] N x2 The calculation method and N x1 The calculation method is the same and will not be repeated here.

[0026] According to formula (1), calculate the axial overload theoretical value before separation and after separation, and determine the size rela...

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Abstract

The invention discloses a two-stage aircraft separation time discrimination method based on axial overload, which comprises the following steps: step 1: determine the axial overload as a basic variable for online real-time discrimination separation; step 2: calculate the axial overload value of the aircraft before and after separation ; Step 3: According to the obtained in step 2, determine the safety threshold of axial overload during safe separation; Step 4: carry out mean value filter processing to the real-time overload signal; Step 5: determine the size between the axial overload and safe separation threshold at safe separation Relationship; Step 6: Record the time point when the safe separation condition is met in Step 5, as the time when the main level starts control. According to the characteristic that the axial overload of the aircraft two-stage separation changes obviously before and after the separation, the present invention realizes the online real-time judgment of the two-stage separation time.

Description

technical field [0001] The invention relates to the field of flight control of unmanned aerial vehicles, in particular to an online real-time discrimination method for two-stage safety separation of aircraft, through which the safety of two-stage separation can be ensured, the adaptability of the control system to uncertain factors in the separation process can be improved, and the two-stage separation can be improved. Front and rear flight control qualities. Background technique [0002] At present, the research of unmanned aerial vehicles tends to develop at high speed and long range. To improve the flight speed and range, a multi-stage booster scheme is often adopted. The booster stage accelerates the aircraft to a certain flight speed, and then throws it off through the inter-stage separation mechanism. Leave. The aerodynamic characteristics of the aircraft before and after the separation between the stages are quite different. The interaction force and aerodynamic inte...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 奚勇沈洁陈光山夏斌冯昊廖幻年朱雯雯刘露
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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