Control structure and method for weakening high-flow orbit control jet flow interference based on empennage layout

Abstract

The invention provides a control structure and method for weakening large-flow orbit control jet flow interference based on empennage layout, and the structure comprises an aircraft model which comprises a straight section and a tail skirt, and the position, from the straight section to the tail skirt, of the aircraft model is provided with an empennage. The empennage is arranged on the aircraft model, the nearby flow field structure is changed, the orbit control interference influence can be reduced, and the stability of the interception missile is improved. The arrangement position of the empennage is determined in a pressure recovery area of the windward side of the aircraft model through optimization design, so that the empennage is favorably controlled. Compared with an attitude control engine control method, the empennage is simple in structure and easier to control.

Description

Technical Field

[0001] The present invention relates to the field of flow control technology, and in particular to a control structure and method for reducing large-flow orbital control jet interference based on tail wing layout. Background Art

[0002] Jet control technology is an active flow control technology that directly changes the flight trajectory or attitude of an aircraft through the reaction force of the jet. It has the advantages of fast response speed, no restrictions on airspace and speed domain, and high control accuracy. The flight range of future hypersonic aircraft will range from low altitude to high altitude, covering dense atmosphere to thin atmosphere. The aerodynamic force varies greatly under different environments, and it is necessary to use the direct force provided by the large flow trajectory control engine to maneuver and change the trajectory to achieve high precision and fast response capabilities.

[0003] Large flow rate orbit control jet interference will produce a large interference torque, and attitude control engines are often used for control at home and abroad. However, under certain conditions (such as low altitude and high Mach number flight conditions), orbit control jet interference will produce a large interference torque, and the attitude control engine control capability is difficult to perform stable control of the aircraft, so additional control methods are needed to further control the interference torque. Summary of the invention

[0004] The purpose of the present invention is to provide a control structure and method for reducing the interference of large-flow orbit control jets based on tail wing layout, which can reduce the influence of orbit control interference and improve the stability of intercepting missiles;

[0005] The present invention provides a control structure for reducing large-flow orbital control jet interference based on a tail wing layout, comprising an aircraft model, wherein the aircraft model comprises a straight section and a tail skirt, and the aircraft model is provided with a tail wing from the straight section to the tail skirt.

[0006] Furthermore, the tail wings are provided in multiple groups, which are arranged in a surrounding and spaced relationship.

[0007] Furthermore, the number of the tail wings is four groups, arranged in a cross configuration.

[0008] Furthermore, the aircraft model also includes a cone section, and the cone section, the straight section and the tail skirt are arranged in sequence from head to tail.

[0009] Furthermore, the axial position of the tail wing on the aircraft model is: the distance l1 between the starting position of the tail wing and the nozzle satisfies: l1 / D=0.8-1.2; the tail wing length l2 satisfies: l2 / D=0.9-1.2; wherein D represents the diameter of the tail skirt of the aircraft model.

[0010] Furthermore, the tail fin is located directly behind the nozzle.

[0011] The present invention also provides a control method for a control structure based on a tail wing layout to reduce interference from a large flow rate track control jet. When there is an angle of attack, small holes are arranged on the windward surface of the tail skirt of the aircraft model, and the small hole jets are used to control the interference force.

[0012] The present invention also provides a control method for a control structure based on a tail wing layout to reduce interference of a large flow track control jet, and the tail wing control effect is characterized by a pitch moment control effect.

[0013] Furthermore, the pitch moment control effect is expressed as follows: Where: ΔFmz0 represents the pitch moment disturbance caused by the orbital control jet of the tail wing layout model, and ΔFmz represents the normal force disturbance caused by the orbital control jet of the tailless model.

[0014] Furthermore: λ=0 means that the tail wing has no control effect; λ>0 means that the tail wing produces unfavorable control; λ<0 means that the tail wing produces favorable control; ΔFmz0=0 means that the additional torque interference generated by the tail wing completely offsets the adverse effect of the jet interference flow field.

[0015] The technical solution of the present invention can reduce the influence of track control interference and improve the stability of intercepting missiles by arranging the tail wing on the aircraft model and changing the nearby flow field structure. The arrangement position of the tail wing is determined by optimizing the design in the pressure recovery area on the windward side of the aircraft model, so that the tail wing can produce favorable control. Compared with the attitude control engine control method, the tail wing has a simple structure and is easier to control. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 It is a schematic diagram of the arrangement position of the tail wing of the present invention;

[0018] Figure 2 This is a flow chart of a control method for reducing interference of large flow rate track control jets according to the present invention;

[0019] Figure 3 A schematic diagram of the change of the pitch moment control efficiency in an embodiment of the present invention;

[0020] Description of reference numerals:

[0021] 1-aircraft model; 101-cone section; 102-straight section; 103-tail skirt; 2-tail wing; 3-nozzle; DETAILED DESCRIPTION

[0022] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0024] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined. In addition, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0025] like Figure 1 As shown, the present embodiment discloses a control structure based on tail fins to reduce the interference of large flow orbit control jets, including a cross-layout tail fin 2 arranged on an aircraft model 1, the aircraft model 1 including a conical section 101, a straight section 102 and a tail skirt 103 arranged in sequence from the head to the tail, the tail fin 2 is arranged along the cross layout at the positions of the straight section 102 and the tail skirt 103 of the missile body, four tail fins 2 are arranged on the aircraft model 1, and the axial position of the tail fin 2 on the aircraft model 1 is: the distance l1 between the starting position of the tail fin 2 and the nozzle 3 satisfies: l1 / D=0.8-1.2, and the length l2 of the tail fin 2 satisfies: l2 / D=0.9-1.2, wherein D represents the diameter of the tail skirt 103 of the aircraft model;

[0026] This embodiment discloses a control method based on tail wing to reduce the interference of large flow track control jet, such as Figure 2 As shown, Figure 2 The flow chart of the control method for reducing the interference torque of the large-flow orbit control jet provided by the present invention is as follows:

[0027] (1) Establishing an aircraft model 1, for example, a three-dimensional solid modeling system such as CATIA can be used to establish the model. In an optional embodiment, the established aircraft model 1 is a cone-column skirt track control jet model.

[0028] (2) In an optional embodiment, the jet interference flow field of the aircraft model 1 is obtained by solving the three-dimensional compressible Navigator-Stokes equations.

[0029] The three-dimensional compressible Navier-Stokes equations are

[0030]

[0031] in, is a conserved variable, are the inviscid flux vectors in the x, y, and z directions respectively, are the viscous flux vectors in the x, y, and z directions respectively; t is time, x is the flow direction of the rectangular coordinate system, y is the normal direction of the rectangular coordinate system, and z is the circumferential direction of the rectangular coordinate system; the steps for establishing the coordinate system are: using a three-dimensional Cartesian rectangular coordinate system, the x-axis is along the flow direction of the model, the y-axis is along the normal direction, the z-axis is along the circumferential direction, and the coordinate origin O is selected as the midpoint of the leading edge of the model.

[0032] The above equations can be solved by commercial fluid simulation software or self-developed programs to obtain the spatial velocity distribution of the jet interference flow field.

[0033] (3) Four tail fins 2 are arranged on the aircraft model 1, and the axial position of the tail fin 2 on the aircraft model 1 is as follows: the distance l1 between the starting position of the tail fin 2 and the nozzle 3 satisfies: l1 / D=0.8-1.2, and the length l2 of the tail fin 2 satisfies: l2 / D=0.9-1.2, wherein D represents the diameter of the tail skirt 103 of the aircraft model.

[0034] The pitch moment control effect λ, which characterizes the control effect of the tail 2, is expressed as follows:

[0035]

[0036] Where: ΔFmz0 represents the pitch moment disturbance caused by the trajectory control jet of the tail 2 layout model, ΔFmz represents the normal force disturbance caused by the trajectory control jet of the no tail 2 model,

[0037] λ = 0 means that the tail wing 2 has no control effect;

[0038] λ>0 means that tail wing 2 produces unfavorable control;

[0039] λ<0 means that tail wing 2 produces favorable control;

[0040] ΔFmz0=0 means that the additional torque disturbance generated by the tail wing 2 completely offsets the adverse effect of the jet disturbing the flow field.

[0041] Example 1

[0042] In this embodiment, a typical cone-shaped skirt track control jet model is controlled, with a flight Mach number of 5.0, a flight altitude of 25km, and an attack angle of -10° to 5°. The control target is to reduce the pitch moment interference generated by the track control jet. After calculation, if Figure 3 The figure shows a schematic diagram of the change in the pitch moment control efficiency with the increase of the angle of attack provided by an embodiment of the present invention. In this case, the interference moment caused by the track control jet is reduced.

[0043] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A control structure based on the tail layout to reduce the interference of large flow track control jet, characterized by: The invention comprises an aircraft model, wherein the aircraft model comprises a straight section and a tail skirt, and a tail wing is arranged at a position from the straight section to the tail skirt.

2. The control structure for reducing the interference of large-flow orbital control jet based on tail wing layout according to claim 1 is characterized in that: The tail wings are provided in multiple groups, which are arranged in a surrounding manner and at intervals.

3. The control structure for reducing the interference of large-flow orbital control jet based on tail wing layout according to claim 2 is characterized in that: The number of the tail wing is four groups, arranged in a cross configuration.

4. The control structure for reducing the interference of large-flow orbital control jet based on tail wing layout according to claim 1 is characterized in that: The aircraft model also includes a cone section, and the cone section, the straight section and the tail skirt are arranged in sequence from head to tail.

5. The control structure for reducing the interference of large-flow orbital control jet based on tail wing layout according to claim 1 is characterized in that: The axial position of the tail on the aircraft model is: The distance l1 between the starting position of the tail wing and the nozzle satisfies: l1 / D=0.8-1.2; The tail length l2 satisfies: l2 / D=0.9-1.2; Wherein, D represents the tail skirt diameter of the aircraft model.

6. The control structure for reducing the interference of large flow rate track control jet based on tail wing layout according to claim 5 is characterized in that: The tail fin is located directly behind the nozzle.

7. A control method for a control structure for reducing interference of large flow track control jets based on tail wing layout according to any one of claims 1 to 6, characterized in that: When there is an angle of attack, small holes are arranged on the windward surface of the tail skirt of the aircraft model, and the small hole jet is used to control the interference force.

8. A control method for a control structure for reducing interference of large flow track control jets based on tail wing layout according to any one of claims 1 to 6, characterized in that: The tail control effect is characterized by the pitch moment control effect.

9. The control method according to claim 8, characterized in that: The pitch moment control effect is expressed as follows: Where: ΔFmz0 represents the pitch moment disturbance caused by the orbital control jet of the tail wing layout model, and ΔFmz represents the normal force disturbance caused by the orbital control jet of the tailless model.

10. The control method according to claim 9, characterized in that: λ = 0 means that the tail wing has no control effect; λ>0 means that the tail produces adverse control; λ<0 means that the tail produces favorable control; ΔFmz0=0 means that the additional torque disturbance generated by the tail completely offsets the adverse effect of the jet disturbing the flow field.

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