Grid rudder wing mixing pneumatic layout applied to box type launching and design method

Abstract

The invention discloses a grid rudder wing mixing pneumatic layout applied to box type launching and a design method. A grid rudder wing mixing pneumatic layout scheme is composed of two pieces of chord length changing horizontal arc-shaped grid wings and four pieces of straight grid rudders, the two pieces of horizontal arc-shaped grid wings play a role of flight autostability, the four pieces ofstraight grid rudders are used for controlling postures in the flight process, at a launching initial stage, a folding state is mounted in a launching box, and in the flight process, the grid wings and the grid rudders unfold and are used for autostability and control of an aircraft; the grid rudder wing design method and process taking initial box type launching as geometric constraint are further provided, and the design efficiency of the grid rudder wing mixing layout can be improved. According to the grid rudder wing mixing layout mode, a larger longitudinal control torque can be provided, higher pneumatic efficiency within a wider mach number range is achieved, design of a flight control system is facilitated, and the grid rudder wing mixing layout mode is especially applied to the using of the control rudder surface of a high lift-drag ratio gliding class aircraft booster stage.

Description

technical field [0001] The invention relates to the technical field of aircraft aerodynamic layout design, in particular to an aerodynamic layout form and design method of grid-rudder-wing mixing suitable for box launch. Background technique [0002] As a new type of control aerodynamic stability surface and control surface, the grid wing is a space multi-lift surface system composed of an outer frame and a number of grids with a honeycomb structure inside. Compared with the shape of the traditional flat wing, the grid The rudder has its own advantages in terms of aerodynamics and structure, such as better lift characteristics and stall characteristics at high angles of attack, can be folded and installed close to the projectile body, better hinge moment characteristics, higher control efficiency, higher The mass-intensity ratio has been widely used in various missiles, rockets, boosters and satellites. [0003] At present, the research on the aerodynamic layout of the grid...

AI Technical Summary

Problems solved by technology

[0004] While the grid rudder has high control efficiency in the pitch and yaw directions, its control efficiency in the roll direction will be significantly higher than that of the flat control rudder surface. Generally speaking, axisymmetric aircraft or small aspect ratio aircraft , the moment of inertia in the roll direction is relatively small, resulting in a small roll rudder deflection will bring a large roll control effect, which is not conducive to the design of the flight control system

At the same time, for box-launched missiles or aircraft, the space constraints in the box at the initial stage of launch are the main factors affecting the design of the rudder surface, especially for various new types of high-lift-to-drag ratio aircraft, the layout of which is mostly a lifting body or a multiplier. The wave body configuration, in order to meet the stability and maneuverability requirements during the launch process, makes the matching design of the booster rudder surface more difficult. Under the strict geometric constraints of the box launch, if the traditional flat wing is used, it will The chord length of the flat wing is huge, which brings many problems such as structure and hinge moment; if the traditional "X" or "cross" grid wing is used, the roll control is too sensitive and the grid Due to the limitation of the geometric size of the folded grid and the excessive bending moment of a single grid rudder, it is necessary to carry out corresponding innovations in the layout form.

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