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A ballistic damping control method for gliding flight

A damping control, gliding ballistic technology, applied in aircraft parts, special data processing applications, instruments, etc., to achieve the effect of facilitating real-time control and suppressing long-period oscillation of ballistics

Active Publication Date: 2016-03-09
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

Although the ballistic oscillation period is very long, for hypersonic vehicles, it still brings uncertain factors to the re-entry flight, so it needs to be suppressed or eliminated

Method used

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  • A ballistic damping control method for gliding flight
  • A ballistic damping control method for gliding flight
  • A ballistic damping control method for gliding flight

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Embodiment Construction

[0048] The present invention will be further described below in conjunction with the accompanying drawings and specific examples.

[0049] See Figure 23 The block flow chart of the present invention, a kind of gliding flight ballistic damping control method of the present invention, the concrete steps of this method are as follows:

[0050] Step 1: Give the condition of the longest distance for the aircraft to glide without power.

[0051] An aircraft with aerodynamic control capability slides without power. If the dynamic pressure constraints and heat flux constraints are not considered, in order to obtain the longest gliding distance, the aerodynamic coefficient needs to meet the requirements of the maximum lift-to-drag ratio. The proof of this rule is given below.

[0052] Firstly, the kinematic equations of the vehicle gliding without power in the longitudinal plane are established. In order to make the results universal, the influence of the curvature of the earth is ...

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Abstract

The invention discloses a method for controlling glide flying ballistic curve damping. The method comprises the following three major steps: step 1: taking into consideration influence of earth curvature, ignoring influence of earth rotation, studying three degree-of-freedom kinematical equation of gliding of an aircraft, and acquiring condition of furthest distance of powerless gliding of the aircraft; step 2: based on the atmosphere model and the aircraft aerodynamic force model already known, performing force analysis on the longitudinal plane of the aircraft under stable gliding condition, and acquiring stable gliding ballistic curve angle of inclination gamma*; step 3: adding feedback to the control instruction, introducing ballistic curve damping control. The method is a guidance method enabling stable gliding of the aircraft, and is applicable to aircrafts having a glide ballistic curve, including a cannonball of a low speed and a short range as well as a long-distance, reentry, and hypersonic-velocity aircraft.

Description

technical field [0001] The invention belongs to the field of aerospace technology and ballistic control technology. It specifically relates to a gliding flight ballistic damping control method, which gives the aircraft a smooth gliding ballistic inclination γ * Based on this, a ballistic damping control method that can make the aircraft glide smoothly is given. This ballistic damping control method is applicable to aircraft with gliding ballistics, from low-speed short-range projectiles to long-distance reentry flight hypersonic aircraft. Background technique [0002] With the development of computer technology, people use the optimal control theory more when studying the problem of the longest gliding distance of aircraft re-entry. The biggest advantage of this processing method is that it can obtain the optimal solution that satisfies various constraints. However, the problem solving time is long, which is not conducive to the real-time control of the aircraft. The laws...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00G06F19/00
Inventor 陈万春余文斌洪功名
Owner BEIHANG UNIV
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