Single sliding block rolling spray mode variable centroid aircraft model and designing method for structural layout parameters thereof

An aircraft and centroid-changing technology, which is applied in instruments, calculations, electrical and digital data processing, etc., and can solve problems such as complex slider layout and ablation of aerodynamic rudders.

Active Publication Date: 2015-09-02
HARBIN INST OF TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0011] The purpose of the present invention is to solve the aerodynamic rudder ablation problem of traditional hyp

Method used

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  • Single sliding block rolling spray mode variable centroid aircraft model and designing method for structural layout parameters thereof
  • Single sliding block rolling spray mode variable centroid aircraft model and designing method for structural layout parameters thereof
  • Single sliding block rolling spray mode variable centroid aircraft model and designing method for structural layout parameters thereof

Examples

Experimental program
Comparison scheme
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Example Embodiment

[0037] Specific embodiment one, combined with Figure 2 image 3 Explaining this embodiment, a single-slider roll-jet model of a variable-cent-of-mass aircraft model includes two fixed wings I, a projectile body II, and a roll-jet engine III. The two fixed wings I are symmetrically arranged on both sides of the projectile body II; it also includes The movable body IV inside the projectile II; the movable body IV is a cone, and the tip of the cone of the movable body IV and the head of the projectile II pass through the movable connection point O 1 Connection; there is a guide rail Ⅴ at the tail of the projectile body Ⅱ, the cone root of the movable body Ⅳ and the guide rail Ⅴ of the tail part of the projectile body Ⅱ O 2 Point sliding connection; O on the guide Ⅴ 2 The point goes around O along the guide rail Ⅴ fixed to the body Ⅱ under the action of servo force 1 Do relative movements. By changing the relative position of the movable body IV and the projectile body Ⅱ, the system'...

Example Embodiment

[0038] Specific implementation manner two, a method for designing the structural layout parameters of a single-slider rolling-jet mode variable-centroid aircraft model for a single-slider rolling-jet mode variable-centroid aircraft model includes the following steps:

[0039] Step 1: Design the dynamic model of the aircraft:

[0040] Suppose the center of mass of the aircraft is s, the center of mass of the projectile body II is b, and the center of mass of the movable body IV is p; the systems all refer to the variable center of mass aircraft; the degrees of freedom of the system include the three-dimensional translation and three-dimensional rotation of the variable center of mass aircraft, and The two-dimensional rotation of the movable body IV; the whole system is regarded as a multi-rigid body system composed of projectile II and movable body IV, O 1 , O 2 It is the link point of the two parts; the establishment of the dynamic model is established by the theorem of moment of mo...

Example Embodiment

[0051] Specific implementation mode 3: The design process of the dynamic model of the aircraft in step 1 of this embodiment is as follows:

[0052] Step 1.1, define the coordinate system and parameters

[0053] In order to describe the dynamics model of the variable-cent-of-mass aircraft, three coordinate systems are defined, namely the inertial coordinate system, the projectile coordinate system and the movable body fixed coordinate system. The origin of the projectile coordinate system is at the warhead O 1 Place, O 1 x b The axis is along the longitudinal axis of the projectile Ⅱ, pointing to the head as positive, O 1 y b Axis perpendicular to O 1 x b The axis is parallel to the longitudinal axis of the guide rail V, O 1 z b The axis and the other two axes form a right-handed coordinate system; the origin of the fixed coordinate system of the movable body is also in the warhead O 1 , O 1 x p The axis is along the longitudinal axis of the movable body IV, O 1 y p Axis perpendicular...

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Abstract

A single sliding block rolling spray mode variable centroid aircraft model and a designing method for structural layout parameters thereof relate to the field of flight vehicle design, and aim to solve the problems of ablation to an aerodynamic rudder in a conventional hypersonic aircraft and complexity in sliding block layout inside a conventional variable centroid aircraft. The aircraft model provided by the invention comprises two fixed wings, a projectile body, a rolling spray engine and a movable body, wherein the two fixed wings are symmetrically arranged on the two sides of the projectile body; the tip of the cone-shaped body of the movable body is connected with the head of the projectile body through a movably connecting point O1; a guide rail is arranged at the tail end of the projectile body, the root part of the cone-shaped body of the movable body is connected with the O2 point of the guide rail at the tail part of the projectile body in a sliding manner; since the movable body is further expanded to serve as a main body, the mass of the movable body accounts for most part of the mass of the entire system, the projectile body is taken as a driven body, the purpose of maneuvering control can also achieved, the motion of the projectile body can be controlled through an actuator on the movable body; the integral aerodynamic configuration of the projectile body is ensured. The aircraft model provided by the invention is applicable to the field of flight vehicle design.

Description

technical field [0001] The invention relates to an aircraft with variable center of mass and a method for designing parameters of the aircraft. Background technique [0002] Variable center of mass control technology is to achieve the desired control performance by actively moving the movable mass body inside the aircraft, changing the position of the center of mass of the system, and causing the external torque acting on the aircraft to change, so as to achieve the purpose of maneuvering the aircraft. [0003] According to different implementation methods, they can be divided into two categories: (1) Moving-mass trim control (MMTC); (2) Moving-mass roll control (MMRC). Variable center of mass trim control (MMTC) is mainly applied to aircraft with axisymmetric structure. It generates trim angle of attack through the movement of internal movable mass body, so as to make the aircraft maneuver. Variable center of mass rolling control (MMRC) is mainly applied to aircraft with s...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 高长生李涧青魏鹏鑫荆武兴
Owner HARBIN INST OF TECH
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