阅读说明：本技术 一种具有自主赋旋功能的脉冲推力姿控装置 (Pulse thrust attitude control device with autonomous rotation endowing function ) 是由 于剑桥 胡俊 吴小胜 李世鹏 于 2021-09-13 设计创作，主要内容包括：本发明公开了一种具有自主赋旋功能的脉冲推力姿控装置,设置在飞行器的头部和机身之间,包括：外壳、脉冲发动机和脉冲发动机安装座；所述外壳为圆柱形密闭腔体,脉冲发动机安装座为圆柱形,其同轴设置在外壳中,外壳和脉冲发动机安装座的圆周面上分别设有若干个同轴的斜形光孔和斜形螺纹孔,每个脉冲发动机一端设置在外壳上的斜形光孔中,另一端螺纹连接在脉冲发动机安装座的斜形螺纹孔,且若干个脉冲发动机按同一旋向排布在外壳和脉冲发动机安装座之间；其中,每个脉冲发动机的轴向与外壳的径向之间成设定夹角。(The invention discloses a pulse thrust attitude control device with an autonomous rotation imparting function, which is arranged between the head and the fuselage of an aircraft and comprises: the pulse engine comprises a shell, a pulse engine and a pulse engine mounting seat; the pulse engine mounting seat is cylindrical and is coaxially arranged in the shell, a plurality of coaxial oblique unthreaded holes and oblique threaded holes are respectively formed in the circumferential surfaces of the shell and the pulse engine mounting seat, one end of each pulse engine is arranged in the oblique unthreaded hole in the shell, the other end of each pulse engine is in threaded connection with the oblique threaded hole in the pulse engine mounting seat, and the pulse engines are distributed between the shell and the pulse engine mounting seat in the same rotating direction; wherein, a set included angle is formed between the axial direction of each pulse engine and the radial direction of the shell.)

1. The utility model provides a pulse thrust appearance accuse device with independently endow soon function which characterized in that sets up between the head and the fuselage of aircraft, includes: the pulse generator comprises a shell, a pulse generator (4) and a pulse generator mounting seat (5); the pulse engine mounting seat is characterized in that the shell is a cylindrical closed cavity, the pulse engine mounting seat (5) is cylindrical and coaxially arranged in the shell, a plurality of coaxial oblique unthreaded holes and oblique threaded holes are respectively formed in the circumferential surfaces of the shell and the pulse engine mounting seat (5), one end of each pulse engine (4) is arranged in the oblique unthreaded hole in the shell, the other end of each pulse engine is in threaded connection with the oblique threaded hole in the pulse engine mounting seat (5), and the pulse engines (4) are arranged between the shell and the pulse engine mounting seat (5) according to the same rotation direction; wherein, a set included angle is formed between the axial direction of each pulse motor (4) and the radial direction of the shell.

2. The pulsed thrust attitude control device with autonomous spin-on function according to claim 1, characterized in that said housing comprises: the device comprises a base (1), a shell (2) and a top cover (3); the shell (2) is of a cylindrical structure with two open ends, and the base (1) and the top cover (3) are coaxially packaged at two ends of the shell.

3. The impulse thrust attitude control device with an autonomous rotation imparting function according to claim 2, wherein the base (1) and the top cover (3) are identical in structure.

4. The pulse thrust attitude control device with the autonomous rotation imparting function according to claim 3, wherein the base (1) and the top cover (3) are both cylinders with one end coaxially provided with a cylindrical groove; the upper end of the base (1) is coaxially sleeved with the shell (2) and the lower end of the pulse engine mounting seat (5), the shell (2) and the lower end of the pulse engine mounting seat (5) are fastened through screws, and the lower end of the base (1) is coaxially fixed on an aircraft body; the lower end of the top cover (3) is coaxially sleeved with the shell (2) and the upper end of the pulse engine mounting seat (5), the shell, the pulse engine mounting seat and the pulse engine mounting seat are fastened through screws, and the upper end of the top cover (3) is coaxially fixed on the head of an aircraft; the pulse engine is characterized in that a shell (2) is coaxially sleeved on the outer circumferential surfaces of a base (1) and a top cover (3), a pulse engine mounting seat (5) is coaxially sleeved in cylindrical grooves of the base (1) and the top cover (3), and the lower end of the shell (2) and the lower end of the pulse engine mounting seat (5) are fastened with the upper end of the base (1) through screws; the upper end of the shell (2) and the upper end of the pulse engine mounting seat (5) are fastened with the lower end of the top cover (3) through screws.

5. The impulse thrust attitude control device with an autonomous spin-imparting function according to claim 4, characterized in that the inner diameters of the cylindrical grooves of the base (1) and the top cover (3) coincide with the outer diameter of the impulse engine mount (5).

6. The pulse thrust attitude control device with the self-rotation imparting function according to any one of claims 2 to 5, wherein more than one row of inclined hole groups are axially arranged on the wall surfaces of the housing (2) and the pulse engine mounting seat (5), each row of inclined hole groups on the housing (2) is more than two inclined unthreaded holes which are circumferentially distributed, and the hole axes of the inclined unthreaded holes do not exceed the center of the housing (2) and form a set included angle with the radial direction of the housing (2); each row of inclined hole groups on the pulse engine mounting seat (5) are more than two inclined threaded holes distributed along the circumferential direction, and the hole axes of the inclined threaded holes are not beyond the circle center of the pulse engine mounting seat (5) and form a set included angle with the radial direction of the pulse engine mounting seat (5); the inclined unthreaded hole and the inclined threaded hole at the corresponding positions of the shell (2) and the pulse engine mounting seat (5) are coaxial.

7. The impulse thrust attitude control device with the self-rotation imparting function according to claim 6, wherein the plurality of inclined light holes on the housing are respectively and uniformly distributed along the axial direction and the circumferential direction of the housing, and the plurality of inclined screw holes on the impulse engine mounting base (5) are respectively and uniformly distributed along the axial direction and the circumferential direction.

8. The impulse thrust attitude control device with the self-energizing function according to claim 7, wherein each of said impulse motors (4) is composed of an impulse motor case (6), a propellant (7) and an igniter (8); one end of the pulse engine shell (6) is opened, the other end of the pulse engine shell is provided with a hole, the opening is in a horn shape, and the opening is used for enabling gas generated by combustion of a propellant (7) filled in the pulse engine shell (6) to be sprayed out from the opening; an external thread is arranged at the opening end of the pulse engine shell (6) and is used for being in threaded fit with the pulse engine mounting seat (5); the igniter (8) is composed of an ignition wire and an ignition powder, the ignition powder is contacted with the propellant (7), and the ignition wire penetrates out of a small hole at the perforated end of the pulse engine shell (6).

9. The impulse thrust attitude control device with the self-rotation imparting function according to any one of claims 1 to 5, wherein a plurality of inclined light holes on the housing are uniformly distributed along the axial direction and the circumferential direction of the housing, and a plurality of inclined threaded holes on the impulse engine mounting base (5) are uniformly distributed along the axial direction and the circumferential direction, respectively.

10. The impulse thrust attitude control device with the self-energizing function according to claim 9, wherein each of the impulse motors (4) is composed of an impulse motor case (6), a propellant (7), and an igniter (8); one end of the pulse engine shell (6) is opened, the other end of the pulse engine shell is provided with a hole, the opening is in a horn shape, and the opening is used for enabling gas generated by combustion of a propellant (7) filled in the pulse engine shell (6) to be sprayed out from the opening; an external thread is arranged at the opening end of the pulse engine shell (6) and is used for being in threaded fit with the pulse engine mounting seat (5); the igniter (8) is composed of an ignition wire and an ignition powder, the ignition powder is contacted with the propellant (7), and the ignition wire penetrates out of a small hole at the perforated end of the pulse engine shell (6).

Technical Field

The invention relates to the technical field of guided missiles and arrows, in particular to a pulse thrust attitude control device with an autonomous rotation endowing function.

Background

The rocket aircraft is widely applied to the military field, and the pulse attitude control engine is a control execution mechanism widely applied to rotary guided rockets. The working principle of the pulse attitude control engine for controlling the projectile attitude is as follows: and generating a pulse engine ignition instruction according to the control instruction and the roll angle of the aircraft, controlling the ignition of the sub-engines at corresponding positions, and changing the attitude and the flight path of the aircraft by means of the thrust generated by the sub-engines. The pulse attitude control engine can control the attitude and flight trajectory of the aircraft only by rotating the projectile body in the working mode, and for the rocket aircraft with conventional curved shooting or direct shooting trajectory, the pulse attitude control engine realizes the rotation of the aircraft around the axis of the aircraft by means of pneumatic rotation guidance (inclined wing surfaces, wing surfaces with chamfer angles or arc rolling wings). For the aircraft needing to change direction with great maneuver, a greater attack angle and a smaller flight speed can appear in the process of changing direction, under the condition of the great attack angle, the aerodynamic characteristics of the aircraft can have stronger nonlinear characteristics, and under the condition of low flight speed, the aerodynamic force acting on the aircraft can be greatly reduced.

Therefore, a pulse thrust attitude control device needs to be developed to ensure that the rocket aircraft still has a good control effect under the conditions of a large attack angle and a low flight speed.

Disclosure of Invention

In view of the above, the invention provides a pulse thrust attitude control device with an autonomous rotation imparting function, which is used for attitude control of a rocket aircraft, solves the problem that the traditional pulse attitude control engine is difficult to effectively control the rocket aircraft under the condition of pneumatic rotation guide failure, and ensures that the rocket aircraft still has a good control effect under the condition of a large attack angle and low speed.

The technical scheme of the invention is as follows: a pulse thrust attitude control device with an autonomous rotation imparting function is arranged between a head and a fuselage of an aircraft, and comprises: the pulse engine comprises a shell, a pulse engine and a pulse engine mounting seat; the pulse engine mounting seat is cylindrical and is coaxially arranged in the shell, a plurality of coaxial oblique unthreaded holes and oblique threaded holes are respectively formed in the circumferential surfaces of the shell and the pulse engine mounting seat, one end of each pulse engine is arranged in the oblique unthreaded hole in the shell, the other end of each pulse engine is in threaded connection with the oblique threaded hole in the pulse engine mounting seat, and the pulse engines are distributed between the shell and the pulse engine mounting seat in the same rotating direction; wherein, a set included angle is formed between the axial direction of each pulse engine and the radial direction of the shell.

Preferably, the housing comprises: a base, a housing and a top cover; the shell is of a cylindrical structure with openings at two ends, and the base and the top cover are coaxially packaged at two ends of the shell.

Preferably, the base and the cover are of identical construction.

Preferably, the base and the top cover are both cylinders with one end coaxially provided with a cylindrical groove; the upper end of the base is coaxially sleeved with the shell and the lower end of the pulse engine mounting seat and is fastened by screws, and the lower end of the base is coaxially fixed on the aircraft body; the lower end of the top cover is coaxially sleeved with the shell and the upper end of the pulse engine mounting seat and fastened by screws, and the upper end of the top cover is coaxially fixed on the head of the aircraft; the pulse engine mounting seat is coaxially sleeved in the cylindrical grooves of the base and the top cover, and the lower end of the shell and the lower end of the pulse engine mounting seat are fastened with the upper end of the base through screws; the upper end of the shell, the upper end of the pulse engine mounting seat and the lower end of the top cover are fastened through screws.

Preferably, the inner diameter of the cylindrical grooves of the base and the top cover is identical to the outer diameter of the pulse motor mounting seat.

Preferably, more than one row of inclined hole groups are axially arranged on the wall surfaces of the shell and the pulse engine mounting seat, each row of inclined hole groups on the shell are more than two inclined unthreaded holes which are circumferentially distributed, and the hole axes of the inclined unthreaded holes do not exceed the circle center of the shell and form a set included angle with the radial direction of the shell; each row of inclined hole groups on the pulse engine mounting seat are more than two inclined threaded holes distributed along the circumferential direction, and the hole axes of the inclined threaded holes are not beyond the circle center of the pulse engine mounting seat and form a set included angle with the radial direction of the pulse engine mounting seat; the oblique unthreaded hole and the oblique threaded hole at the corresponding positions of the shell and the pulse engine mounting seat are coaxial.

Preferably, a plurality of oblique unthreaded holes on the shell are respectively and evenly distributed along the axial direction and the circumference of shell, and a plurality of oblique threaded holes on the pulse engine mounting base are respectively and evenly distributed along the axial direction and the circumference correspondingly.

Preferably, each pulse engine consists of a pulse engine housing, a propellant and an igniter; one end of the pulse engine shell is opened, the other end of the pulse engine shell is provided with a hole, the opening is in a horn shape, and the opening is used for enabling gas generated by combustion of a propellant arranged in the pulse engine shell to be sprayed out from the opening; the opening end of the pulse engine shell is provided with external threads which are used for being in threaded fit with the pulse engine mounting seat; the igniter is composed of an ignition wire and an ignition powder, the ignition powder is contacted with the propellant, and the ignition wire penetrates out of a small hole at the perforated end of the pulse engine shell.

Preferably, a plurality of oblique unthreaded holes on the shell are respectively and evenly distributed along the axial direction and the circumference of shell, and a plurality of oblique threaded holes on the pulse engine mounting base are respectively and evenly distributed along the axial direction and the circumference correspondingly.

Preferably, each pulse engine consists of a pulse engine housing, a propellant and an igniter; one end of the pulse engine shell is opened, the other end of the pulse engine shell is provided with a hole, the opening is in a horn shape, and the opening is used for enabling gas generated by combustion of a propellant arranged in the pulse engine shell to be sprayed out from the opening; the opening end of the pulse engine shell is provided with external threads which are used for being in threaded fit with the pulse engine mounting seat; the igniter is composed of an ignition wire and an ignition powder, the ignition powder is contacted with the propellant, and the ignition wire penetrates out of a small hole at the perforated end of the pulse engine shell.

Has the advantages that:

1. according to the pulse thrust attitude control device provided by the invention, the mode that the pulse engine is directionally installed on the shell and the pulse engine installation seat is adopted, so that not only can a normal force for controlling the attitude of the rocket aircraft be generated, but also a rolling torque for enabling the rocket aircraft to rotate around the axis of the rocket aircraft can be generated, under the action of the rolling torque, even if the pneumatic rotation guidance of the rocket aircraft fails, the projectile body can rotate around the axis of the rocket aircraft by means of the rolling torque generated by the pulse thrust attitude control device, and the normal control force generated by the pulse thrust attitude control device can effectively control the rocket aircraft, so that the problem that the rocket aircraft is difficult to effectively control under the condition of failure of the pneumatic rotation guidance of the traditional pulse attitude control engine is solved, and the rocket aircraft still has a good control effect under the condition of a large attack angle and low speed.

2. The specific design of the shell ensures that the thrust direction of the pulse engine does not pass through the axial direction of the aircraft, so that the pulse engine can generate normal control force and rolling torque, has the functions of attitude control and rotation guidance, and ensures that the aircraft has good control effect under the conditions of large attack angle and low speed.

3. The design of the pulse engine not only ensures the stable connection between the pulse engine and the shell and between the pulse engine and the pulse engine mounting seat, but also is beneficial to the ignition of the pulse engine to generate thrust with both attitude control and rotation guiding functions.

Drawings

Fig. 1 is a schematic view of an installation position of a pulsed thrust attitude control device on an aircraft.

Fig. 2 is an exploded view of the overall structure of the impulse thrust attitude control device according to the present invention.

Fig. 3 is an isometric view of the overall structure of the impulse thrust attitude control device proposed by the present invention.

Fig. 4(a) is an isometric view of the pulsed thrust attitude control device of the present invention in a state without a cap, and (b) is a top view of the pulsed thrust attitude control device of the present invention in a state without a cap.

Fig. 5 is a sectional view of a pulse motor according to the present invention.

Fig. 6(a) is an isometric view of an impulse motor housing of the present invention, and (b) is a cross-sectional view of an impulse motor housing of the present invention.

The device comprises a 0-pulse thrust attitude control device, a 1-base, a 2-shell, a 3-top cover, a 4-pulse engine, a 5-pulse engine mounting seat, a 6-pulse engine shell, a 7-propellant and an 8-igniter.

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

The embodiment provides a pulse thrust attitude control device with an autonomous rotation endowing function, which is used for controlling the attitude of a rocket aircraft, solves the problem that the traditional pulse attitude control engine is difficult to realize effective control on the aircraft under the condition of pneumatic rotation guiding failure, and ensures that the rocket aircraft still has a better control effect under the condition of large attack angle and low speed.

As shown in fig. 1, the pulse thrust attitude control device 0 is coaxially installed with an external rocket aircraft, and the pulse thrust attitude control device 0 is close to the head position (between the head and the fuselage) of the aircraft;

as shown in fig. 2, 3, and 4, the pulse thrust attitude control device 0 includes: the pulse generator comprises a base 1, a shell 2, a top cover 3, a pulse generator 4 and a pulse generator mounting seat 5;

the base 1 is a cylinder with a cylindrical groove coaxially formed in the upper end, and the upper end and the lower end of the base in the axial direction are respectively provided with more than three threaded through holes I and threaded through holes II along the circumferential direction (preferably, the upper end and the lower end of the base 1 are respectively and uniformly provided with four threaded through holes I and four threaded through holes II along the circumferential direction); the upper end of the base 1, the shell 2 and the lower end of the pulse engine mounting seat 5 are coaxially sleeved and fastened through screws; the pulse engine mounting seat 5 is coaxially sleeved in a cylindrical groove of the base 1, and the lower ends of the shell 2 and the pulse engine mounting seat 5 are respectively provided with a threaded through hole III and a threaded through hole IV which correspond to the threaded through hole I at the upper end of the base 1;

the lower end of the base 1 is coaxially fastened at the front end of an aircraft fuselage through screws;

a plurality of oblique unthreaded holes are formed in the shell 2, oblique threaded holes with corresponding number are formed in the pulse engine mounting seat 5, more than three pulse engines 4 are arranged in a space between the shell 2 and the pulse engine mounting seat 5 at set included angles with the radial direction of the pulse engine mounting seat 5 (namely more than three pulse engines 4 are arranged in the space between the shell 2 and the pulse engine mounting seat 5 according to the same rotation direction), the inlet end of each pulse engine 4 is in threaded connection with the oblique threaded hole of the pulse engine mounting seat 5, and the outlet end of each pulse engine 4 is arranged in the oblique unthreaded hole of the shell 2;

the roof 3 is enclosed at one end over the housing 2 and the pulse engine mount 5 and at the other end is connected to the head of the aircraft.

In this embodiment, the inner diameter of the cylindrical recess of the base 1 coincides with the outer diameter of the pulse motor mount 5.

In this embodiment, the top cover 3 is the same as the base 1 in shape and size, and the connection between the housing 2 and the pulse motor mount 5 and the connection between the base 1 and the housing 2 and the pulse motor mount 5 are the same.

In this embodiment, more than one row of inclined hole groups are axially arranged on the wall surfaces of the shell 2 and the pulse engine mounting seat 5, more than two inclined unthreaded holes are circumferentially distributed (preferably uniformly distributed circumferentially) in each row of inclined hole groups on the shell 2, and the hole axes of the inclined unthreaded holes do not pass through the center of the shell 2 and form a set included angle with the radial direction of the shell 2; more than two oblique threaded holes are distributed in each row of oblique hole groups on the pulse engine mounting seat 5 along the circumferential direction (preferably uniformly distributed along the circumferential direction), and the hole axes of the oblique threaded holes are not beyond the circle center of the pulse engine mounting seat 5 and form a set included angle with the radial direction of the pulse engine mounting seat 5; the inclined unthreaded hole and the inclined threaded hole at the corresponding positions of the shell 2 and the pulse engine mounting seat 5 are coaxial.

In the present embodiment, as shown in fig. 5 and 6, each pulse motor 4 is composed of a pulse motor case 6, a propellant 7, and an igniter 8; the pulse engine shell 6 is a cylindrical shell, one end of the shell is open, the other end of the shell is provided with a hole, the opening is in a horn shape, and the pulse engine shell is used for enabling fuel gas generated by combustion of a propellant 7 filled in the pulse engine shell 6 to be sprayed out from the opening; the opening end of the pulse engine shell 6 is provided with external threads for being in threaded fit with the pulse engine mounting seat 5; the igniter 8 is composed of an ignition wire and an ignition powder, the ignition powder is contacted with the propellant 7, and the ignition wire penetrates out of a small hole at the perforated end of the pulse engine shell 6.

The working principle of the pulse thrust attitude control device is as follows: the installation process comprises the following steps: placing the pulse engine mounting seat 5 in a cylindrical groove on the upper end surface of the base 1, and fastening the lower end of the pulse engine mounting seat 5 and the upper end of the base 1 through screws; the lower end of the shell 2 is fastened with the upper end of the base 1 through screws; buckling a cylindrical groove on the lower end face of the top cover 3 at the upper end of the pulse engine mounting seat 5, and fastening the pulse engine mounting seat 5 and the upper end of the shell 2 with the lower end of the top cover 3 through screws respectively; and (3) penetrating each pulse engine 4 through an oblique unthreaded hole on the wall surface of the shell 2, screwing the pulse engines into corresponding threaded holes on the pulse engine mounting seats 5, and then mounting the connected pulse thrust attitude control device 0 at the position, close to the head, of the aircraft, wherein the axis of the pulse thrust attitude control device coincides with the axis of the aircraft.

The use process comprises the following steps: when the pulse thrust attitude control device 0 works, a flight control computer on the aircraft outputs a control instruction to control the pulse engine 4 at a specified position in the pulse thrust attitude control device 0 to work, an igniter 8 in the corresponding pulse engine 4 acts, the propellant 7 is ignited, and fuel gas is generated to be sprayed out from a horn-shaped nozzle of the pulse engine shell 6 to generate thrust along the axial direction of the pulse engine 6; because the axial direction of the pulse engine 6 does not pass through the axial line of the pulse thrust attitude control device 0, and therefore does not pass through the axial line of the aircraft, the thrust can generate a moment in the tangential direction of the aircraft, so that the aircraft rotates around the axial line of the aircraft; meanwhile, the thrust can generate normal (consistent with the radial direction of the aircraft) control force and control moment for controlling the attitude change of the aircraft, and the function of adjusting the attitude of the aircraft is achieved.

In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.