Flight controller for guided missile

Abstract

The invention relates to the technical field of missiles, and provides a flight controller for missiles, comprising: a housing; the functional board assembly comprises a plurality of PCBs, every two adjacent PCBs are connected through a flexible belt, and the PCBs of the functional board assembly are folded at the flexible belts and then are arranged in the shell. According to the flight controller for the guided missile, the PCBs forming the function board assembly are connected through the flexible belts, and the PCBs are folded at the flexible belts and then arranged in the shell. Compared with the prior art, the function boards do not need to adopt inter-board connectors for data communication, so that the cost is reduced; moreover, the flexible plate allows the adjustment of the plate spacing within a certain range, thereby improving the spatial layout flexibility of the flight controller, and facilitating the realization of a miniaturized design.

Description

Technical Field

[0001] The invention relates to the technical field of missiles, and in particular to a flight controller for missiles. Background Art

[0002] With the rapid development of modern science and technology, higher requirements are placed on the technological level of weapons and equipment in future wars. Missiles are indispensable weapons and equipment in war, and their guidance accuracy will determine the success or failure of the battlefield. As the core component of the missile, the flight controller is required to have high precision, strong stability and super strong solution processing capabilities. Although the existing flight controllers integrate rudder control, flight control, and electronic control in terms of functions, most of them are achieved through the stacking of independent modules, and the structural integration is not achieved. The underlying design integration; as a multi-functional all-in-one machine, the data communication between the functional boards is mainly carried out by inter-board connectors, but the cost of inter-board connectors is high, and the height of the inter-board connectors is fixed, which limits the flexibility of the flight controller's spatial layout design and is not conducive to miniaturization. Summary of the invention

[0003] Therefore, the technical problem to be solved by the present invention is that the function boards of the flight controller in the prior art mainly use inter-board connectors for data communication. However, the cost of the inter-board connectors is high and the height of the inter-board connectors is fixed, which limits the flexibility of the spatial layout design of the flight controller and is not conducive to miniaturization. Thus, a flight controller for a missile is provided.

[0004] In order to solve the above technical problems, the technical solution of the present invention is as follows:

[0005] The present invention provides a flight controller for a missile, comprising: a shell; a function board assembly, comprising a plurality of PCB boards, two adjacent PCB boards are connected by a flexible belt, and each PCB board of the function board assembly is folded at the flexible belt and arranged in the shell.

[0006] Furthermore, the flight controller for the missile also includes a supporting stud, and a plurality of first threaded holes are arranged on the surface of each PCB board, and each PCB board is threadedly connected to the supporting stud through the first threaded holes in turn, so that two upper and lower adjacent PCB boards remain parallel and the distance between them is fixed.

[0007] Furthermore, the functional board components are divided into a guidance inertial group board, a computer board, a communication board and a connector board according to their functions.

[0008] Furthermore, the shell includes a connected front compartment section and a rear compartment section; the guide inertial group board, computer board, communication board and connector board are all located in the rear compartment section; the front compartment section is provided with a second threaded hole at a position adapted to the support stud, one end of the support stud passes through the connector board, communication board, computer board and guide inertial group board in sequence and extends outward, and the extended part of the support stud is connected to the front compartment section through the second threaded hole.

[0009] Furthermore, the flight controller for a missile also includes an auxiliary bracket, which is in a ring-shaped structure and is embedded in and fixed on the inner wall of the rear compartment section; a third threaded hole is provided on the auxiliary bracket, and the support stud is connected to the auxiliary bracket through the third threaded hole, and the support stud extends from the auxiliary bracket and is connected to the connector board, communication board, computer board, guidance inertial group board and front compartment section in sequence.

[0010] Furthermore, the flight controller for a missile also includes radial fixing screws; radial fixing holes are provided on the side walls of the rear compartment section, the side walls of the connector board and the side walls of the auxiliary bracket, and the auxiliary bracket and the connector board are fixed to the rear compartment section through the radial fixing screws and the radial fixing holes.

[0011] Furthermore, the auxiliary bracket includes two arc-shaped sub-brackets, and the openings of the two sub-brackets are arranged facing each other.

[0012] Furthermore, the flight controller for the missile also includes an inertial measurement unit; a first connector is provided on the surface of the guidance inertial group board facing away from the computer board, and the inertial measurement unit is connected to the guidance inertial group board through the first connector.

[0013] Furthermore, a second connector is provided on the board surface of the guidance inertial group board facing away from the computer board, and the second connector is used to be connected to the guidance head of the missile.

[0014] Furthermore, a third connector and a fourth connector are provided on a side of the connector board facing away from the communication board; the third connector is used to connect to the servo and thermal battery of the missile; and the fourth connector is used to connect to the fuze of the missile.

[0015] The technical solution of the present invention has the following advantages:

[0016] In the flight controller for missiles provided by the present invention, each PCB board constituting the function board assembly is connected by a flexible belt, and each PCB board is folded at the flexible belt and then arranged in a housing. Compared with the prior art, there is no need to use an inter-board connector for data communication between the function boards, which reduces the cost; moreover, the flexible board allows the board spacing to be adjusted within a certain range, which improves the spatial layout flexibility of the flight controller and is conducive to realizing a miniaturized design. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] 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.

[0018] Figure 1 is a schematic diagram of a disassembled state of a flight controller for a missile in an embodiment of the present invention;

[0019] Figure 2 It is a schematic diagram of an assembly state of a flight controller for a missile in an embodiment of the present invention from one viewing angle;

[0020] Figure 3 It is a schematic diagram of the assembly state of the flight controller for a missile in an embodiment of the present invention from another perspective;

[0021] Figure 4 is a schematic diagram of a function board assembly in a flight controller for a missile in an embodiment of the present invention;

[0022] Figure 5 It is a schematic diagram of a front compartment section of a flight controller for a missile in an embodiment of the present invention from one perspective;

[0023] Figure 6 It is a schematic diagram of the front compartment section of the flight controller for a missile in an embodiment of the present invention from another perspective;

[0024] Figure 7 is a schematic diagram of a rear compartment section of a flight controller for a missile in an embodiment of the present invention;

[0025] Figure 8 It is a schematic diagram of an auxiliary bracket in a flight controller for a missile in an embodiment of the present invention.

[0026] Description of reference numerals:

[0027] 1. Functional board assembly; 2. Guidance inertial group board; 3. Computer board; 4. Communication board; 5. Connector board; 6. First threaded hole; 7. Front cabin section; 8. Second threaded hole; 9. Rear cabin section; 10. Radial fixing hole; 11. Auxiliary bracket; 12. Sub-bracket; 13. Third threaded hole; 14. Inertial measurement unit; 15. Support stud. DETAILED DESCRIPTION

[0028] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not 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.

[0029] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, 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 communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0032] like Figure 1 , Figure 4 As shown, this embodiment provides a flight controller for a missile, comprising: a housing; a function board assembly 1, comprising a plurality of PCB (Printed Circuit Board) boards, two adjacent PCB boards are connected by a flexible belt, and each PCB board of the function board assembly 1 is folded at the flexible belt and arranged in the housing. The length of the flexible belt can be selected as needed, so that the spacing between two adjacent PCB boards is flexibly adjustable.

[0033] In the flight controller for missiles provided in this embodiment, each PCB board constituting the function board assembly 1 is connected by a flexible belt, and each PCB board is folded at the flexible belt and then arranged in the housing. Compared with the prior art, there is no need to use an inter-board connector for data communication between the function boards, which reduces the cost; moreover, the flexible board allows the board spacing to be adjusted within a certain range, which improves the spatial layout flexibility of the flight controller and is conducive to realizing a miniaturized design.

[0034] Among them, the flight controller for the missile also includes a support stud 15, and a plurality of first threaded holes 6 are arranged on the board surface of each PCB board. Each PCB board is threadedly connected to the support stud 15 through the first threaded holes 6 in turn, so that two upper and lower adjacent PCB boards remain parallel and the spacing between them is fixed. For example, each PCB board can be generally a circular plate. For example, four first threaded holes 6 can be evenly spaced on each PCB board, and correspondingly, four support studs 15 are also arranged. The four support studs 15 string together the various PCB boards to form a whole, and under the limit of the thread, the spacing between the two adjacent PCB boards can be kept fixed to prevent the PCB boards from moving up and down. When the strong and weak current components are integrated, it is not easy to cause mutual interference, which prevents data loss.

[0035] For example, the functional board assembly 1 can be divided into a guidance inertial group board 2, a computer board 3, a communication board 4 and a connector board 5 according to the function.

[0036] Among them, for the guidance inertial group board 2, a first connector is provided on the board surface of the guidance inertial group board 2 facing away from the computer board 3, and the inertial measurement unit 14 is connected to the guidance inertial group board 2 through the first connector. For example, the inertial measurement unit 14 can adopt an existing inertial sensor or inertial measurement device. The inertial measurement unit 14 can provide raw inertial data, which is processed into navigation data by the flight controller for missile flight control.

[0037] For example, a second connector is also provided on the board surface of the guidance inertial group board 2 facing away from the computer board 3, and the second connector is used to be connected to the guidance head of the missile.

[0038] Among them, for the computer board 3, it can be built-in with a ZYNQ7020 processor for processing electronic control, rudder control and flight control information.

[0039] Among them, for the communication board 4, 8 RS-422 communication interfaces can be integrated thereon to realize communication functions such as guidance, inertial navigation, data link and ground equipment; at the same time, 12 switch inputs and outputs can be integrated to provide functional communications such as fuze and engine ignition; in addition, 10 A / D sampling can be integrated to detect signals such as thermal batteries, release permission and servos.

[0040] Among them, for the connector board 5, the side of the connector board 5 facing away from the communication board 4 can be provided with a third connector and a fourth connector; the third connector is used to connect to the servo and thermal battery of the missile; the fourth connector is used to connect to the fuze of the missile.

[0041] The first connector and the second connector may be J30JZ miniaturized connectors, and the third connector and the fourth connector may be J30J connectors.

[0042] like Figure 2 , Figure 3 , Figure 5 , Figure 6 as well as Figure 7 As shown, the housing includes a connected front compartment 7 and a rear compartment 9; the guidance inertial group board 2, the computer board 3, the communication board 4 and the connector board 5 are all located in the rear compartment 9; the front compartment 7 is provided with a second threaded hole 8 at a position adapted to the support stud 15, one end of the support stud 15 passes through the connector board 5, the communication board 4, the computer board 3 and the guidance inertial group board 2 in sequence and extends outward, and the extended part of the support stud 15 is connected to the front compartment 7 through the second threaded hole 8. For example, the number of the second threaded holes 8 is equal to the number of the support studs 15, and can also be four. For example, the size of the housing can be φ100mm×84.5mm (including 10mm docking length), and the weight does not exceed 0.6kg. For example, the front compartment 7 can be provided with a mounting interface for connecting with the front functional section of the missile. For example, the rear compartment 9 can be provided with a mounting interface for connecting with the rear functional section of the missile.

[0043] like Figure 8 As shown, the flight controller for the missile further includes an auxiliary bracket 11, which is an annular structure, and the outer diameter of the auxiliary bracket 11 is smaller than the inner diameter of the rear compartment section 9, and the auxiliary bracket 11 is embedded and fixed on the inner wall of the rear compartment section 9; a third threaded hole 13 is provided on the auxiliary bracket 11, and the support stud 15 is connected to the auxiliary bracket 11 through the third threaded hole 13, and the support stud 15 extends from the auxiliary bracket 11 and is sequentially connected to the connector board 5, the communication board 4, the computer board 3, the guidance inertial group board 2 and the front compartment section 7. For example, the number of the third threaded holes 13 can be equal to the number of the support studs 15, or it can be four. During installation, in the direction from the rear compartment section 9 to the front compartment section 7, the support stud 15 passes through the third threaded hole 13 on the auxiliary bracket 11, the first threaded hole 6 on each PCB board, and finally is inserted into the second threaded hole 8 on the front compartment section 7.

[0044] The flight controller for the missile further includes radial fixing screws; radial fixing holes 10 are arranged on the side walls of the rear compartment section 9, the side walls of the connector board 5 and the side walls of the auxiliary bracket 11, and the auxiliary bracket 11 and the connector board 5 are fixed to the rear compartment section 9 through radial fixing screws and radial fixing holes 10. For example, a plurality of radial fixing holes 10 can be arranged at intervals along the circumferential direction of the rear compartment section 9, and each radial fixing hole 10 corresponds to a radial fixing screw, so as to ensure the reliability of the connection of the entire function board assembly 1 in the radial direction and prevent the function board assembly 1 from shaking in the radial direction during the flight of the missile.

[0045] The auxiliary bracket 11 includes two arc-shaped sub-brackets 12, and the openings of the two sub-brackets 12 are arranged facing each other. Such an arrangement makes it easier to balance the assembly error between the auxiliary bracket 11 and the rear compartment section 9.

[0046] In summary, the flight controller for missiles in this application integrates flight control, electronic control and inertial navigation through an integrated and integrated design concept, and reserves data link and rudder control interface functions. It adopts a flexible printed circuit board and stud support form, flexibly designs the board spacing, and effectively utilizes the space layout.

[0047] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A flight controller for a missile, characterized in that: include: case; A function board assembly (1) comprises a plurality of PCB boards, wherein two adjacent PCB boards are connected via a flexible belt, and each PCB board of the function board assembly (1) is folded at the flexible belt and arranged in the housing.

2. The flight controller for a missile according to claim 1, characterized in that: It also includes a supporting stud (15), and each PCB board is provided with a plurality of first threaded holes (6) on its surface, and each PCB board is threadedly connected to the supporting stud (15) through the first threaded holes (6) in sequence, so that two upper and lower adjacent PCB boards remain parallel and the distance between them is fixed.

3. The flight controller for a missile according to claim 2, characterized in that: The functional board assembly (1) is divided into a guidance inertial group board (2), a computer board (3), a communication board (4) and a connector board (5) according to function.

4. The flight controller for a missile according to claim 3, characterized in that: The housing comprises a front compartment section (7) and a rear compartment section (9) which are connected; The guidance inertial group board (2), the computer board (3), the communication board (4) and the connector board (5) are all located in the rear compartment (9); The front compartment section (7) is provided with a second threaded hole (8) at a position adapted to the support stud (15); one end of the support stud (15) passes through the connector board (5), the communication board (4), the computer board (3) and the guide inertial group board (2) in sequence and extends outward; the extended portion of the support stud (15) is connected to the front compartment section (7) via the second threaded hole (8).

5. The flight controller for a missile according to claim 4, characterized in that: It also comprises an auxiliary bracket (11), the auxiliary bracket (11) is an annular structure, and the auxiliary bracket (11) is embedded in and fixed on the inner wall of the rear compartment section (9); The auxiliary bracket (11) is provided with a third threaded hole (13), and the support stud (15) is connected to the auxiliary bracket (11) through the third threaded hole (13), and the support stud (15) extends from the auxiliary bracket (11) and is sequentially connected to the connector board (5), the communication board (4), the computer board (3), the guidance inertial group board (2) and the front cabin section (7).

6. The flight controller for a missile according to claim 5, characterized in that: Also included is a radial set screw; The side wall of the rear compartment section (9), the side wall of the connector board (5) and the side wall of the auxiliary bracket (11) are all provided with radial fixing holes (10); the auxiliary bracket (11) and the connector board (5) are fixed to the rear compartment section (9) via the radial fixing screws and the radial fixing holes (10).

7. The flight controller for a missile according to claim 5, characterized in that: The auxiliary bracket (11) comprises two arc-shaped sub-brackets (12), and the openings of the two sub-brackets (12) are arranged facing each other.

8. The flight controller for a missile according to claim 3, characterized in that: Also included is an inertial measurement unit (14); A first connector is provided on the board surface of the guidance inertial unit board (2) facing away from the computer board (3), and the inertial measurement unit (14) is connected to the guidance inertial unit board (2) via the first connector.

9. The flight controller for a missile according to claim 8, characterized in that: A second connector is arranged on the board surface of the guidance inertial group board (2) facing away from the computer board (3), and the second connector is used to be connected to the guidance head of the missile.

10. The flight controller for a missile according to claim 3, characterized in that: A third connector and a fourth connector are provided on a side of the connector board (5) facing away from the communication board (4); The third connector is used to connect to the servo and thermal battery of the missile; The fourth connector is used to be connected to the fuze of the missile.

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