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Analytical solution method for hypersonic velocity smooth gliding trajectory under rotating earth

A gliding ballistic and hypersonic technology, applied in the field of weapons and aerospace technology, can solve problems such as difficult to meet precise guidance, analysis and correction, low accuracy, tracking error, etc.

Active Publication Date: 2020-08-04
BEIHANG UNIV
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Problems solved by technology

However, due to neglect of the earth's rotation and the influence of the earth's curvature on the heading angle, most of the analytical solutions have low precision in the background of the rotating earth, and there are tracking errors, which are difficult to meet the requirements of precise guidance, analysis and correction, and have certain limitations.

Method used

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  • Analytical solution method for hypersonic velocity smooth gliding trajectory under rotating earth
  • Analytical solution method for hypersonic velocity smooth gliding trajectory under rotating earth
  • Analytical solution method for hypersonic velocity smooth gliding trajectory under rotating earth

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Embodiment example

[0549] In order to verify the accuracy of the algorithm, the CAV-H is used as the reentry vehicle model to carry out simulations under seven different target states. Simulations are performed in seven different target states. Reentry initial state is h 0 = 60km, V 0 =7200m / s, λ 0 = 0°, θ 0 = 45°, γ 0 = 0°. ψ 0 Take the value according to the target direction. Ballistic damping control technology is used to suppress ballistic oscillation, where the ballistic damping feedback item coefficient K γ =5. terminal bound to E TAEM =-5.5×10 7 J / kg. Simulation results such as Figure 5-Figure 6 .

[0550] Table 1 Terminal state quantity

[0551]

[0552]

[0553]

[0554] Figure 5 In , the trajectory of the eastward flight is curved due to the influence of the Coriolis force. from Figure 5 and Image 6 It can be seen from the simulation results that the accuracy of the new analytical solution is also very high in the general case where the lift-to-drag ratio...

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Abstract

The invention relates to an analytical solution method for a hypersonic velocity smooth gliding trajectory under the rotating earth. The analytical solution method is characterized by comprising the following steps: step 1, establishing an auxiliary geocentric rotating reference system; 2, establishing a reentry kinetic model based on generalized longitude and latitude coordinates; and 3, reentering an analytical solution derivation method. The method has the advantages that the method caters to the characteristic that the longitudinal range of the hypersonic speed stable gliding trajectory isfar larger than the transverse range, and linearization processing is better facilitated. A simplified kinetic model which takes energy as an independent variable and relates to a longitudinal courseangle, a transverse course angle and a generalized course angle is obtained, and further decoupling processing is facilitated. The method has the characteristics of high precision, small calculated amount, strong universality and the like, and is beneficial to being applied to trajectory planning, predictive guidance, control design and other aspects.

Description

technical field [0001] The invention provides an analytical solution method for a hypersonic smooth gliding trajectory under a rotating earth, and belongs to the fields of aerospace technology and weapon technology Background technique [0002] Hypersonic glide vehicle has the advantages of long range, strong defense penetration capability and great damage power, and has become a research hotspot in various countries. The hypersonic gliding vehicle has a very unique ballistic trajectory, most of the time it flies without power in the adjacent space at an altitude of 20km-100km, and its flight speed and altitude are between conventional fixed-wing aircraft and spacecraft. [0003] The research on the analytical solution of the reentry trajectory has important theoretical significance and application value for exploring the reentry flight mechanism, reentry guidance design, and aircraft performance evaluation. The high-precision analytical solution of reentry trajectory is ve...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F111/10G06F119/14
CPCG06F30/15G06F2111/10G06F2119/14
Inventor 陈万春张晚晴余文斌
Owner BEIHANG UNIV
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