Missile body trajectory posture adjusting device and adjusting method

Abstract

The invention discloses a projectile body trajectory posture adjusting device and method, and belongs to the technical field of projectile body posture adjusting.The adjusting device comprises an outer shell, a first torque adjusting assembly and a second torque adjusting assembly, the first torque adjusting assembly and the second torque adjusting assembly are arranged in the outer shell, and the adjusting method comprises the steps that the outer shell is installed at the end, far away from the mass center of a whole projectile, in the projectile body; when the trajectory posture needs to be adjusted, the missile-borne computer firstly starts the first torque adjusting assembly, and the rotating speed of the second torque adjusting assembly is preliminarily increased; when the projectile body is located at a specific trajectory position, the missile-borne computer starts the second torque adjusting assembly, a movable mass block in the second torque adjusting assembly rotates to generate mass eccentricity, and the trajectory posture of the projectile body is adjusted through the eccentricity generated by rotating the mass, so that the aim of dynamically controlling the flight posture of the projectile body is achieved. The structure is simple and compact, the size is small, the adjusting capacity is high, the influence on the mass center and pneumatic parameters of the projectile body is small, and the influence of pneumatic resistance caused by the change of the appearance structure of the projectile body on the range is effectively avoided.

Description

Technical Field

[0001] The invention belongs to the technical field of projectile posture adjustment, and in particular relates to a projectile trajectory posture adjustment device and an adjustment method. Background Art

[0002] The flight attitude control of missiles is a key technology in the field of missile technology and aerospace. Its importance is self-evident and is directly related to the missile's hit accuracy, penetration capability and overall combat effectiveness. Therefore, the flight attitude of the missile must be accurately controlled and necessary dynamic attitude adjustments must be made to ensure that the missile can hit the target at the most favorable landing angle.

[0003] At present, the traditional missile flight attitude control mainly relies on aerodynamic control and direct force control, but the aerodynamic control method needs to change the shape of the missile and has limited control ability; while the direct force control method has a large volume and mass and poor versatility. Especially in the ballistic stage, the missile needs to perform fast and accurate attitude control according to the target strike requirements to achieve a more flexible missile ballistic attitude effect, which puts higher requirements on the flexibility and rapidity of the attitude control system. Therefore, studying the missile ballistic attitude adjustment method based on the variable center of mass device is of great significance to improving combat effectiveness. Summary of the invention

[0004] In order to solve the above problems, the present invention provides a projectile trajectory posture adjustment device and an adjustment method.

[0005] To achieve the above purpose, the technical solution adopted by the present invention is as follows: A projectile ballistic attitude adjustment device comprises an outer shell that can be installed inside the projectile at a distance from the center of mass of the whole projectile, the outer shell is a hollow cylindrical tube, a first torque adjustment component and a second torque adjustment component are arranged in parallel inside the outer shell along its axial direction, the first torque adjustment component provides a preliminary rotation speed for the second torque adjustment component, the second torque adjustment component generates a mass eccentricity through an internally rotating active mass block, and uses the eccentricity generated by the rotating active mass block to adjust the projectile's ballistic attitude; the first torque adjustment component and the second torque adjustment component are both connected to an onboard computer.

[0006] Furthermore, the first torque adjustment component includes a bearing support sleeve, a first angular contact bearing and a first driving component, the bearing support sleeve is fixed to one side of the inner shell of the second torque adjustment component, the first angular contact bearing is arranged on the other side of the bearing support sleeve, and the outer ring of the first angular contact bearing is connected to the outer shell; the first driving component includes a first inner gear ring arranged on the inner hole wall of the bearing support sleeve and a first gear driven by a first motor, the first inner gear ring is connected to the inner ring of the first angular contact bearing, the first gear is meshed with the first inner gear ring, and the first motor is connected to the outer shell.

[0007] Furthermore, the first motor is connected to a first motor fixing plate and is disposed inside the inner shell, and the first motor fixing plate is fixed to an outer side wall of the outer shell.

[0008] Furthermore, the first motor fixing plate includes a connecting plate and a triangular support plate, the support plate includes two straight edges and one arcuate edge, the arcuate edge is fixed to the end of the outer shell outside the first angular contact bearing; one end of the connecting plate is connected to the inner side of the junction of the two straight edges, and the other end of the connecting plate is connected to the first motor.

[0009] Furthermore, the second torque adjustment assembly includes an inner shell, a fixed mass block, a movable mass block, a second angular contact bearing and a second driving component, the inner shell is arranged inside the outer shell and slidingly cooperates with the outer shell, the inner shell is a hollow cylindrical tube, the fixed mass block and the second angular contact bearing are arranged in parallel along the axis of the inner shell, the fixed mass block is fixed to one end of the outer side of the inner shell, the other side of the fixed mass block is connected to the outer ring of the second angular contact bearing, and the movable mass block is fixed on the inner ring of the second angular contact bearing; the second driving component includes a second inner gear ring and a second gear meshing with the inner gear ring, the second inner gear ring is fixed on the inner ring of the second angular contact bearing and arranged in parallel with the movable mass block, and the movable mass block is arranged between the fixed mass block and the second inner gear ring; the second gear is driven by a second motor, and the second motor is connected to the outer shell.

[0010] Furthermore, the fixed mass block and the movable mass block are both in a semicircular ring shape.

[0011] Furthermore, the second motor is connected to a second motor fixing plate and is arranged inside the inner shell, the second motor fixing plate is fixed on the outer side wall of the outer shell, and the second motor fixing plate and the first motor fixing plate are respectively arranged at two ends of the outer shell.

[0012] Furthermore, the second motor fixing plate has the same structure as the first motor fixing plate, and the arc-shaped edge of the second motor fixing plate is fixed to the other end of the outer shell.

[0013] The present invention also provides a projectile trajectory posture adjustment method, comprising the following steps: The projectile trajectory attitude adjustment device is installed inside the projectile at the far end from the center of mass of the whole projectile; When the missile is launched, the onboard computer first starts the first torque adjustment component to initially increase the rotation speed of the second torque adjustment component; When the projectile needs to adjust its ballistic attitude, the onboard computer starts the second torque adjustment component, which rotates the movable mass block inside the second torque adjustment component to cause mass eccentricity. The eccentricity caused by the rotating mass is used to adjust the projectile's ballistic attitude, so as to achieve the purpose of dynamically controlling the projectile's flight attitude and improve the flexibility of the projectile's ballistic attitude control.

[0014] Compared with the prior art, the present invention has the following technical advances: The present invention installs an outer shell with a first torque adjustment component and a second torque adjustment component at a far end inside the projectile at a distance from the center of mass of the entire projectile, uses the first torque adjustment component to provide a preliminary rotation speed for the second torque adjustment component, and then generates a mass eccentricity through a movable mass block rotating inside the second torque adjustment component, and uses the eccentricity generated by the rotating movable mass block to adjust the ballistic attitude of the projectile. The present invention has the advantages of simple and compact structure, small size, and strong adjustment ability, has little effect on the center of mass and aerodynamic parameters of the projectile, and effectively avoids the influence of aerodynamic resistance caused by changes in the projectile's external structure on the range. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention.

[0016] In the attached picture: Figure 1 A schematic diagram of the appearance of a projectile trajectory attitude adjustment device provided by an embodiment of the present invention; Figure 2 Schematic diagram of the internal structure of the projectile trajectory posture adjustment device in an embodiment of the present invention; Figure 3 for Figure 1 The schematic diagram of the structure after removing the outer shell; Figure 4 for Figure 3 A schematic diagram of the structure without the outer shell and the inner shell; Figure 5 for Figure 4 The main view of In the figure: 1-second angular contact ball bearing, 2-fixed mass block, 3-movable mass block, 4-second inner gear ring, 5-second motor, 6-second gear, 7-second motor fixing plate, 8-bearing support sleeve, 9-first angular contact ball bearing, 10-first inner gear ring, 11-first gear, 12-first motor, 13-first motor fixing plate, 14-inner housing, 15-outer housing. DETAILED DESCRIPTION

[0017] The following specific embodiments may be combined with each other, and the same or similar concepts or processes may not be described in detail in some embodiments. The embodiments of the present invention will be described below in conjunction with the accompanying drawings.

[0018] like Figure 1 , Figure 2 As shown, a projectile trajectory attitude adjustment device comprises an outer shell 15 which can be installed inside the projectile at a distance from the center of mass of the whole projectile, wherein the outer shell 15 is a hollow cylindrical tube. The first torque adjustment component and the second torque adjustment component are arranged side by side along the axis direction inside. The first torque adjustment component provides the initial rotation speed for the second torque adjustment component. The second torque adjustment component generates mass eccentricity through the internal rotating active mass block 3, and uses the eccentricity generated by the rotating active mass block 3 to adjust the ballistic attitude of the projectile. The first torque adjustment component and the second torque adjustment component are both connected to the missile-borne computer. The missile-borne computer is installed inside the projectile. When the projectile is in a specific trajectory and needs to adjust its attitude, the on-board computer controls the start and stop of the first torque adjustment component and the second torque adjustment component, and then uses the eccentricity generated by the active mass block to adjust the flight attitude by changing the torque on the projectile, so as to achieve the purpose of dynamically adjusting the trajectory attitude of the projectile.

[0019] In a specific embodiment of the present invention, Figure 2-5 As shown, the first torque adjustment component includes a bearing support sleeve 8, a first angular contact bearing 9 and a first driving component, wherein the bearing support sleeve 8 is fixed to one side of the inner housing 14 of the second torque adjustment component, the first angular contact bearing 9 is arranged on the other side of the bearing support sleeve 8, and the outer ring of the first angular contact bearing 9 is connected to the outer housing 15; the first driving component includes a first inner gear ring 10 arranged on the inner hole wall of the bearing support sleeve 8 and a first gear 11 driven by a first motor 12, the first inner gear ring 10 is connected to the inner ring of the first angular contact bearing 9, the first gear 11 is meshed with the first inner gear ring 10, and the first motor 12 is connected to the outer housing 15. With this structure, the first motor can drive the first gear and the first inner gear ring to rotate, the first inner gear ring drives the inner ring of the first angular contact bearing to rotate, and the first angular contact bearing preliminarily increases the speed of the inner housing and the second torque adjustment component therein through the bearing support sleeve.

[0020] When designing specifically, Figure 1 , 2As shown, the first motor 12 is connected to the first motor fixing plate 13 and is arranged inside the inner housing 14, and the first motor fixing plate 13 is fixed to the outer side wall of the outer housing 15. The first motor fixing plate 13 includes a connecting plate and a triangular support plate, the support plate includes two straight edges and an arcuate edge, and the arcuate edge is fixed to the end of the outer housing 15 outside the first angular contact bearing 9; one end of the connecting plate is connected to the inner side of the intersection of the two straight edges, and the other end of the connecting plate is connected to the first motor 12. The first motor fixing plate 13 with this structure can suspend the first motor 12 inside the inner housing 14 without occupying external space.

[0021] In a specific embodiment of the present invention, Figure 2-4 As shown, the second torque adjustment assembly includes an inner housing 14, a fixed mass block 2, a movable mass block 3, a second angular contact bearing 1 and a second driving component. The inner housing 14 is arranged inside the outer housing 15 and slidably cooperates with the outer housing 15. The inner housing 14 is a hollow cylindrical tube. The fixed mass block 2 and the second angular contact bearing 1 are arranged in parallel along the axis of the inner housing 14. The fixed mass block 2 is fixed to one end of the outer side of the inner housing 14, and the other side of the fixed mass block 2 is connected to the outer ring of the second angular contact bearing 1. The movable mass block 3 is fixed on the inner ring of the second angular contact bearing 1; the second driving component includes a second inner gear ring 4 and a second gear 6 meshing therewith. The second inner gear ring 4 is fixed on the inner ring of the second angular contact bearing 1 and is arranged in parallel with the movable mass block 3. The movable mass block 3 is arranged between the fixed mass block 2 and the second inner gear ring 4; the second gear 6 is driven by a second motor 5, and the second motor 5 is connected to the outer housing 15. The second motor drives the second gear to rotate, and then the second gear drives the second inner ring to rotate. The second inner ring simultaneously drives the second angular contact bearing and the movable mass block to rotate, and the rotation of the movable mass block is adjusted to generate torque to adjust the flight posture of the projectile trajectory.

[0022] As a preferred structure, Figure 4 As shown, the fixed mass block 2 and the movable mass block 3 are both semicircular. When making them, a semicircular arc can be cut inside the full circular ring. This structure is convenient for installation, and can reduce the overall mass, has strong adjustment ability, and improves the eccentricity effect.

[0023] When designing specifically, Figure 1 , 2As shown, the second motor 5 is connected to the second motor fixing plate 7 and is disposed inside the inner housing 14, the second motor fixing plate 7 is fixed to the outer side wall of the outer housing 15, and the second motor fixing plate 7 and the first motor fixing plate 13 are respectively disposed at both ends of the outer housing 15. Similarly, the second motor fixing plate 7 adopting this structure can suspend the second motor 5 inside the inner housing 14 without occupying external space.

[0024] To further optimize the above solution, the second motor fixing plate 7 has the same structure as the first motor fixing plate 13, and the arcuate edge of the second motor fixing plate 7 is fixed to the other end of the outer shell 15. At the same time, the second motor fixing plate 7 and the first motor fixing plate 13, the second motor 5 and the first motor 12 are symmetrically arranged in the projection direction of the axis.

[0025] During the specific production, the inner shell 14 and the outer shell 15 are both hollow cylindrical shapes, which are completely hollow in the axial direction, can accommodate the jet, and have strong versatility for warheads of different principles (jet, explosion). The second torque adjustment component is connected to the first torque adjustment component through the inner shell, and then the first torque adjustment component and the second torque adjustment component are arranged together inside the outer shell, and fixed to the far end of the center of mass of the whole projectile through the outer shell, so as to meet the aerodynamic requirements of the projectile. At the same time, the adjustment device of this structure has little effect on the center of mass and aerodynamic parameters of the projectile, and effectively avoids the influence of aerodynamic resistance caused by changes in the projectile shape structure on the range.

[0026] A method for adjusting the trajectory posture of a projectile, comprising the following steps: The projectile ballistic attitude adjustment device is installed inside the projectile at the far end from the center of mass of the whole projectile, and the object to be controlled is the projectile ballistic flight attitude; Before the missile is launched, the required ballistic attitude information is set. After the missile is launched, the onboard computer first starts the first motor, drives the first gear and the first inner gear ring to rotate, and then drives the second torque adjustment component to rotate, thereby initially increasing the rotation speed of the second torque adjustment component. When the projectile is in a specific trajectory and needs to adjust its attitude, the deviation between the current attitude and the pre-set attitude information is calculated in real time. When the specified explosion height is reached, the on-board computer starts the second motor, which drives the internal movable mass block to rotate through the second gear and the second inner ring gear, causing mass eccentricity. The eccentricity caused by the rotating mass is used to adjust the projectile's ballistic attitude, so as to achieve the purpose of dynamically controlling the projectile's flight attitude and improve the flexibility of the projectile's ballistic attitude.

[0027] The invention has the advantages of reasonable design, simple and compact structure, small size, and good effect of adjusting the attitude of the projectile. The first motor and the second motor are driven separately to increase the rotation speed to drive the movable mass block to rotate, and the eccentric torque generated by the rotation of the movable mass block is used to adjust the flight attitude of the projectile. The invention is built into the projectile. When the projectile needs to adjust its attitude at a specific ballistic position, the invention can dynamically adjust the flight attitude of the projectile so that it can hit the target at the most favorable landing angle.

[0028] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein with equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the scope of protection of the claims of the present invention.

Claims

1. A projectile trajectory attitude adjustment device, characterized in that: It comprises an outer shell which can be installed inside the projectile at a distance from the mass center of the whole projectile, the outer shell is a hollow cylindrical tube, the inside of the outer shell has a first torque adjustment component and a second torque adjustment component arranged in parallel along its axial direction, the first torque adjustment component provides a preliminary rotation speed for the second torque adjustment component, the second torque adjustment component generates a mass eccentricity through an internally rotating active mass block, and uses the eccentricity generated by the rotating active mass block to adjust the ballistic attitude of the projectile; the first torque adjustment component and the second torque adjustment component are both connected to the missile-borne computer.

2. The device for adjusting the trajectory of a projectile according to claim 1, characterized in that: The first torque adjustment component includes a bearing support sleeve, a first angular contact bearing and a first driving component, wherein the bearing support sleeve is fixed to one side of the inner shell of the second torque adjustment component, the first angular contact bearing is arranged on the other side of the bearing support sleeve, and the outer ring of the first angular contact bearing is connected to the outer shell; the first driving component includes a first inner gear ring arranged on the inner hole wall of the bearing support sleeve and a first gear driven by a first motor, the first inner gear ring is connected to the inner ring of the first angular contact bearing, the first gear is meshed with the first inner gear ring, and the first motor is connected to the outer shell.

3. A projectile trajectory attitude adjustment device according to claim 2, characterized in that: The first motor is connected to a first motor fixing plate and is disposed inside the inner shell. The first motor fixing plate is fixed to an outer side wall of the outer shell.

4. A projectile trajectory attitude adjustment device according to claim 3, characterized in that: The first motor fixing plate includes a connecting plate and a triangular support plate, the support plate includes two straight edges and one arcuate edge, the arcuate edge is fixed to the end of the outer shell outside the first angular contact bearing; one end of the connecting plate is connected to the inner side of the junction of the two straight edges, and the other end of the connecting plate is connected to the first motor.

5. The device for adjusting the trajectory of a projectile according to claim 4, characterized in that: The second torque adjustment assembly includes an inner shell, a fixed mass block, a movable mass block, a second angular contact bearing and a second driving component. The inner shell is arranged inside the outer shell and slidingly cooperates with the outer shell. The inner shell is a hollow cylindrical tube. The fixed mass block and the second angular contact bearing are arranged in parallel along the axis of the inner shell. The fixed mass block is fixed to one end of the outer side of the inner shell, and the other side of the fixed mass block is connected to the outer ring of the second angular contact bearing. The movable mass block is fixed on the inner ring of the second angular contact bearing; the second driving component includes a second inner gear ring and a second gear meshing with the inner gear ring. The second inner gear ring is fixed on the inner ring of the second angular contact bearing and arranged in parallel with the movable mass block. The movable mass block is arranged between the fixed mass block and the second inner gear ring; the second gear is driven by a second motor, and the second motor is connected to the outer shell.

6. A projectile trajectory posture adjustment device according to claim 5, characterized in that: The fixed mass block and the movable mass block are both in a semicircular ring shape.

7. A projectile trajectory attitude adjustment device according to claim 6, characterized in that: The second motor is connected to the second motor fixing plate and is arranged inside the inner shell. The second motor fixing plate is fixed on the outer side wall of the outer shell. The second motor fixing plate and the first motor fixing plate are respectively arranged at two ends of the outer shell.

8. The device for adjusting the trajectory of a projectile according to claim 7, characterized in that: The second motor fixing plate has the same structure as the first motor fixing plate, and the arc-shaped edge of the second motor fixing plate is fixed to the other end of the outer shell.

9. A method for adjusting the trajectory posture of a projectile, characterized in that: The following steps are involved: The projectile trajectory attitude adjustment device according to any one of claims 1 to 8 is installed inside the projectile at a far end from the center of mass of the entire projectile; When the missile is launched, the onboard computer first starts the first torque adjustment component to initially increase the rotation speed of the second torque adjustment component; When the projectile needs to adjust its ballistic attitude, the onboard computer starts the second torque adjustment component, which rotates the movable mass block inside the second torque adjustment component to cause mass eccentricity. The eccentricity caused by the rotating mass is used to adjust the projectile's ballistic attitude, so as to achieve the purpose of dynamically controlling the projectile's flight attitude and improve the flexibility of the projectile's ballistic attitude control.

Images