Two-dimensional correction fuze of satellite attitude measurement fixed deflection vane

Abstract

The application discloses a satellite attitude measurement fixed deflection angle rudder two-dimensional correction fuze. The satellite signal is received by an omnidirectional antenna and an attitude measurement antenna, and the positioning of a projectile body and attitude calculation are carried out based on the satellite signal, so that the positioning precision is high, and the anti-interference and precision of attitude measurement are improved without relying on geomagnetic, inertial navigation and other sensors. Meanwhile, the fixed deflection angle differential rudder plate is adopted, so that the rotating direction of the fixed deflection angle rudder ring and the whole fuze is always opposite, and then the continuous cutting of the magnetic induction line of the magnetic torque generator can be realized, and then the electric energy is generated to supply other components of the fuze. The navigation and guidance control all-in-one machine integrating the receiver, the projectile computer and the rudder controller is adopted to calculate the positioning information and the attitude information of the satellite signal, and to generate a trajectory control signal to control the angle of the fixed deflection angle rudder ring, so as to correct the trajectory. The fuze has the advantages of simple and reliable structure, low cost and easy maintenance, and can be applied to the upgrading and reconstruction of conventional howitzers in large quantities in the later period.

Description

Technical Field

[0001] This invention relates to the field of two-dimensional ballistic correction fuse technology, specifically to a two-dimensional correction fuse for a satellite attitude measurement fixed deflection rudder. Background Technology

[0002] Two-dimensional ballistic correction technology is an effective way to improve the precision strike capability of conventional unguided munitions and has received widespread attention in recent years. It can significantly improve firing accuracy by adding a precision guidance component without changing the original projectile. Due to the requirements of low cost and reliability of munitions, designing a simple, reliable, and miniaturized precision guidance component has become an urgent problem to be solved. Moreover, the battlefield environment is highly variable, and traditional geomagnetic sensors are severely affected by interference, which can distort the attitude measurement results. Inertial navigation systems also have cumulative errors, affecting the accuracy of attitude measurement results. Summary of the Invention

[0003] In view of this, the present invention provides a two-dimensional correction fuze for a fixed deflection rudder in satellite attitude measurement, which can realize the function of component attitude measurement without relying on sensors such as geomagnetic inertial navigation, thus improving the anti-interference capability of attitude measurement; and it has a simple, compact, and reliable structure, does not require thermal batteries, and further reduces the weight of the component, providing a solution for the low-cost and miniaturized design of precision guidance components in the field of two-dimensional ballistic correction.

[0004] The satellite attitude measurement fixed deflection rudder two-dimensional correction fuze of the present invention includes: an omnidirectional antenna, an attitude measurement antenna, a fixed deflection rudder ring, a magnetic torque generator, a navigation, guidance and control integrated machine, and a black box;

[0005] The system includes: an omnidirectional antenna mounted on an omnidirectional antenna mounting base; the omnidirectional antenna is located at the front end of the fuze, has an internal gain amplifier, and is covered by an antenna radome; a navigation, guidance, and control integrated unit is installed inside an integrated unit mounting compartment, which is coaxially fixed to the rear of the omnidirectional antenna mounting base; a magnetic torque generator is fixedly sleeved on the outer circumferential surface of the front section of the integrated unit mounting compartment via a motor mount; a fixed deflection rudder ring is sleeved on the outer circumferential surface of the magnetic torque generator, with its front end mounted on the front section of the integrated unit mounting compartment via bearing I, and its rear end fixed to the motor mount via bearing II; an attitude measuring antenna is fixedly sleeved on the outer circumferential surface of the rear section of the integrated unit mounting compartment via an attitude measuring antenna mounting base, and is covered by an antenna radome; and a black box is installed inside a black box mounting compartment, which is coaxially fixed to the rear of the integrated unit mounting compartment.

[0006] The fixed-angle rudder ring is equipped with a drag-increasing plate, as well as a fixed-angle control rudder plate and a differential rudder plate; wherein, the control rudder plate is fixedly installed in the front section of the fixed-angle rudder ring; the differential rudder plate is fixedly installed in the rear section of the fixed-angle rudder ring; the drag-increasing plate is installed in the drag plate groove circumferentially set at the tail of the fixed-angle rudder ring and can be popped out from the drag plate groove; during the rotation, the fixed-angle rudder ring continuously cuts the magnetic field lines of the magnetic torque generator, generating electrical energy to power the various components of the fuze;

[0007] The Hall sensor is installed at the tail of the fixed-angle rudder ring to measure the attitude information of the fixed-angle rudder ring in real time.

[0008] Preferably, the motor mount and the integrated mounting compartment are interference fit and secured with pins.

[0009] Preferably, a drug cartridge is installed at the bottom of the resistance plate groove; the resistance-enhancing plate is a quarter-circular ring with cylindrical sliders on both sides, which are embedded in the slides on the side wall of the resistance plate groove; the pressure rod is L-shaped, and the front and rear arms of the pressure rod are connected by a main shaft ring; the pressure rod is fixed to the central pillars on both sides of the resistance plate groove by the main shaft ring; the front and rear arms of the pressure rod are provided with circular grooves and fitted with rubber rings;

[0010] In the initial state, the drag-increasing plate is embedded in the drag plate groove, and its two sides are pressed tightly by the front arm of the pressure rod. The rear arm of the pressure rod is clamped to the lower cylinder on the side by a rubber ring. When the explosive charge receives the detonation signal and is ignited, the resulting impact force causes the drag-increasing plate to pop out. The cylindrical slider of the drag-increasing plate moves along the slide of the side wall of the drag plate groove, which drives the pressure rod to rotate rapidly along its main axis. This causes the rear arm of the pressure rod to disengage from the lower cylinder, and the rubber ring of the front arm of the pressure rod is clamped to the upper cylinder on the side by inertia. At the same time, the rear arm of the pressure rod supports the bottom of the drag-increasing plate.

[0011] Preferably, the omnidirectional antenna and attitude-finding antenna receive satellite navigation signals; the integrated navigation, guidance, and control unit integrates a receiver, an onboard computer, and a servo controller; wherein, the receiver calculates position, velocity, and attitude in real time based on the satellite signals received by the omnidirectional antenna and attitude-finding antenna; the onboard computer generates control commands based on the position, velocity, and attitude information calculated by the receiver, the attitude information of the fixed-angle rudder ring measured by the Hall sensor, and the set theoretical trajectory information and target information, based on the control algorithm; the servo controller controls the magnetic torque generator to generate electromagnetic torque according to the control commands generated by the onboard computer, so as to balance the guiding torque generated by the guide vanes, thereby causing the fixed-angle rudder ring to stop according to the control commands, and realizing trajectory correction.

[0012] Beneficial effects:

[0013] This invention employs an omnidirectional antenna and an attitude-measuring antenna to receive satellite signals. Based on these signals, the projectile's positioning and attitude are calculated. This eliminates the need for sensors such as geomagnetic sensors or inertial navigation systems, resulting in high positioning accuracy and improved anti-interference capability for attitude measurement, thus enhancing attitude accuracy. Simultaneously, a differential rudder with a fixed deflection angle ensures that the fixed-angle rudder ring rotates in the opposite direction to the overall fuze rotation. This allows for continuous cutting of the magnetic field lines by a magnetic torque generator, generating electrical energy to power other fuze components. An integrated navigation, guidance, and control system, combining a receiver, onboard computer, and servo controller, calculates the positioning and attitude information from the satellite signals and generates ballistic control signals to control the angle of the fixed-angle rudder ring, thereby correcting the trajectory. This invention's fuze structure is simple, reliable, low-cost, and easy to maintain, making it suitable for widespread application in the upgrading and modification of conventional howitzers. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the mechanical structure of a two-dimensional correction fuze for a fixed deflection rudder in satellite attitude measurement, designed for this invention.

[0015] Figure 2 This is a schematic diagram of a fixed deflection rudder ring.

[0016] Figure 3 This is a schematic diagram of the external shape of a two-dimensional correction fuze for a fixed deflection rudder in satellite attitude measurement.

[0017] Figure 4 This is a schematic diagram of the all-in-one machine in operation.

[0018] Figure 5 This is a schematic diagram of the resistance plate shrinking.

[0019] Figure 6 This is a schematic diagram of the resistance plate springing open.

[0020] Figure 7 This is a schematic diagram of a compression bar. Detailed Implementation

[0021] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] This invention provides a two-dimensional correction fuze for a fixed-angle rudder in satellite attitude measurement, such as... Figure 1 As shown, it mainly includes an omnidirectional antenna 1, a gain amplifier 2, an omnidirectional antenna mounting base 3, a fixed deflection rudder ring 5, a Hall sensor 15, a magnetic torque generator 6, a motor mount 7, an integrated machine mounting section 9, an attitude measuring antenna mounting base 16, an attitude measuring antenna 10, a black box mounting section 11, a navigation, guidance and control integrated machine, and a black box.

[0023] The omnidirectional antenna 1 is mounted on the omnidirectional antenna mounting base 3 with screws. It contains a gain amplifier 2 and is surrounded by an antenna cover, located at the very front of the fuze. The inner core of the antenna mounting base 3 is connected to the front of the integrated unit mounting section 9 by threads. The navigation, guidance and control integrated unit is embedded inside the integrated unit mounting section 9 and secured with screws.

[0024] A motor mount 7 is fitted onto the outer circumference of the front section of the integrated machine mounting compartment 9. The annular magnetic torque generator 6 is connected to the motor mount 7 by threads and is fastened by pins from the side and end faces. In this embodiment, the motor mount 7 and the integrated machine mounting compartment 9 adopt an interference fit and are fastened by pins.

[0025] A ring-shaped fixed-angle rudder ring 5 is fitted onto the outer circumferential surface of the magnetic torque generator 6. Its front end is mounted on the front section of the integrated mounting compartment 9 via bearing I 4, and its rear end is mounted on the rear end of the motor mount 7 via bearing II 8, thereby achieving rotational isolation between the fixed-angle rudder ring 5 and the fuze assembly. The outer circumferential surface of the fixed-angle rudder ring 5 is provided with control rudder blades 12 and differential rudder blades 13, and the tail is provided with a drag-increasing plate. Among them, the control rudder blades 12 are at a fixed angle to the rudder ring generatrix and are mainly used to provide correction force in the lateral deflection direction of the range; the differential rudder blades 13 are at a fixed angle to the rudder ring generatrix and are mainly used to generate steering torque; the drag-increasing plate 14 is always embedded in the drag plate groove 17 circumferentially set on the outer surface of the tail of the fixed-angle rudder ring 5 during flight. When the correction capability generated by the control rudder blades 12 is insufficient, the drag-increasing plate 14 will pop out from the drag plate groove 17 to further increase the correction capability. A Hall sensor 15 is installed at the tail of the fixed-angle rudder ring 5 to measure the attitude information of the rudder ring in real time.

[0026] During flight, when the differential rudder blades are fixedly deflected in one direction, the fixed deflection angle rudder ring 5 always rotates in the opposite direction to the overall rotation of the fuze. During rotation, the fixed deflection angle rudder ring 5 continuously cuts the magnetic field lines generated by the magnetic torque generator 6, thereby generating electrical energy from the magnetic torque generator 6 and supplying it to the entire system. Therefore, this invention does not require the use of thermal batteries, further reducing the weight and volume of the fuze assembly.

[0027] An attitude measuring antenna mounting base 16 is fitted onto the outer circumference of the rear section of the integrated machine mounting compartment 9. The annular attitude measuring antenna 10 is fitted onto the antenna mounting base 16 and is held in place by screws and the edge antenna cover.

[0028] The black box mounting section 11 is coaxially mounted at the rear of the integrated machine mounting section 9; the black box is embedded inside the black box mounting section 11 and secured with screws. The black box is responsible for recording communication data between various modules and the voltage status of key components during power-on, facilitating data analysis during subsequent recovery.

[0029] Among them, the omnidirectional antenna 1 and the attitude measuring antenna 10 are used to receive satellite signals; the navigation, guidance and control integrated machine integrates the receiver, the missile-borne computer and the servo controller to realize positioning and attitude calculation based on satellite signals, generate control commands based on control algorithms and control the angle of the fixed deflection rudder ring 5 to realize trajectory correction.

[0030] Specifically, the omnidirectional antenna 1 processes the satellite signal and transmits it to the navigation, guidance, and control integrated machine. After calculation, the current position and velocity information of the projectile during flight are obtained. The attitude measuring antenna 10 processes the satellite signal and transmits it to the navigation, guidance, and control integrated machine. After calculation, the attitude information of the projectile is obtained. The Hall sensor 15 transmits the attitude information of the control ring to the navigation, guidance, and control integrated machine. The navigation, guidance, and control integrated machine generates control commands in real time based on the deviation from the target point and the ballistic control algorithm. It controls the magnetic torque generator 6 to generate electromagnetic torque to balance the guiding torque generated by the differential control plate 13, thereby causing the control plate to stop according to the control command, thus achieving trajectory correction. Figure 4 As shown.

[0031] This embodiment provides a method for fixing and ejecting the resistance-increasing plate 14. For example... Figure 5 As shown, a drug cartridge 21 is installed at the bottom of the resistance plate groove 17. The resistance-enhancing plate 14 is a quarter-circular ring with cylindrical sliders 22 on both sides, which are embedded in the slides on the sidewall of the resistance plate groove 17. The opening and closing of the resistance-enhancing plate is achieved by the up and down movement of the sliders 22 in the slides 23. The pressure rod 18 is L-shaped and consists of three parts: a front arm, a main shaft ring, and a rear arm. Figure 7 As shown. The pressure rod is fixed to the central column 24 on both sides of the resistance plate groove by the main shaft ring, and can rotate and move along the main shaft; the front and rear arms of the pressure rod are provided with circular grooves and rubber rings, which are used to hold the upper and lower cylinders on both sides of the resistance plate groove 17 to achieve the locking function.

[0032] Initially, the drag-increasing plate 14 is embedded in the drag plate groove 17, pressed tightly on both sides by the front arm of the pressure rod 18, and the rear arm of the pressure rod 18 is clamped to the lower cylinder 19 on the side by a rubber ring to resist the centrifugal force generated when the assembly rotates, preventing the drag plate from moving. When the propellant 21 receives the detonation signal and is ignited, the resulting impact force causes the drag-increasing plate 14 to pop out, and the drag-increasing plate cylindrical slider 22 moves along the slide 23 on the side wall of the drag plate groove, driving the pressure rod 18 to rotate rapidly along its main axis, causing the rear arm of the pressure rod 18 to disengage from the lower cylinder 19, and the rubber ring of the front arm of the pressure rod to clamp the upper cylinder 20 on the side by inertia. At this time, the rear arm of the pressure rod 18 supports the bottom of the drag-increasing plate 14, preventing the drag-increasing plate 14 from retracting into the drag plate groove 17. Figure 6 As shown.

[0033] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A two-dimensional correction fuze for a fixed-angle satellite attitude measurement rudder, characterized in that, include: Omnidirectional antenna (1), attitude measuring antenna (10), fixed deflection rudder ring (5), magnetic torque generator (6), navigation, guidance and control integrated machine and black box; Among them, the omnidirectional antenna (1) is installed on the omnidirectional antenna mounting base (3); the omnidirectional antenna (1) is located at the front end of the fuze, and has a gain amplifier (2) inside and is wrapped with an antenna cover on the outside; the navigation, guidance and control integrated machine is installed in the integrated machine mounting compartment (9), and the integrated machine mounting compartment (9) is coaxially fixed to the tail of the omnidirectional antenna mounting base (3); the magnetic torque generator (6) is fixedly sleeved on the outer peripheral surface of the front section of the integrated machine mounting compartment (9) via the motor mount (7); the fixed deflection rudder ring (5) is sleeved on the magnetic torque generator (6). On the outer periphery, the front end of the fixed deflection rudder ring (5) is mounted on the front section of the integrated machine mounting compartment (9) via bearing I (4), and the rear end is fixed on the motor mount (7) via bearing II (8); the attitude measuring antenna (10) is fixedly sleeved on the outer periphery of the rear section of the integrated machine mounting compartment (9) via the attitude measuring antenna mounting seat (16), and the attitude measuring antenna (10) is wrapped with an antenna cover; the black box is installed in the black box mounting compartment (11), and the black box mounting compartment (11) is coaxially fixed to the tail of the integrated machine mounting compartment (9); The fixed-angle rudder ring (5) is equipped with a drag-increasing plate (14), a fixed-angle control rudder plate (12), and a differential rudder plate (13); wherein, the control rudder plate (12) is fixedly installed in the front section of the fixed-angle rudder ring (5); the differential rudder plate (13) is fixedly installed in the rear section of the fixed-angle rudder ring (5); the drag-increasing plate (14) is installed in the drag plate groove (17) circumferentially provided at the tail of the fixed-angle rudder ring (5), and can pop out from the drag plate groove (17); the fixed-angle rudder ring (5) continuously cuts the magnetic field lines of the magnetic torque generator (6) during rotation, generating electrical energy to power the components of the fuse; A Hall sensor (15) is installed at the tail of the fixed deflection rudder ring (5) to measure the attitude information of the fixed deflection rudder ring (5) in real time.

2. The two-dimensional correction fuze for fixed-angle satellite attitude measurement rudder as described in claim 1, characterized in that, The motor mount (7) and the integrated machine mounting compartment (9) are interference fit and are fastened by pins.

3. The two-dimensional correction fuze for fixed-angle satellite attitude measurement rudder as described in claim 1, characterized in that, The bottom of the resistance plate groove (17) is equipped with a drug cartridge (21); the resistance plate (14) is a quarter-circular ring with cylindrical sliders (22) on both sides, which are embedded in the slides of the side wall of the resistance plate groove (17); the pressure rod (18) is L-shaped, and the front and rear arms of the pressure rod (18) are connected by a main shaft ring; the pressure rod (18) is fixed on the central column (24) on both sides of the resistance plate groove by the main shaft ring; the front and rear arms of the pressure rod (18) are provided with circular grooves and rubber rings are installed; In the initial state, the drag-increasing plate (14) is embedded in the drag plate groove (17), and its two sides are pressed by the front arm of the pressure rod (18). The rear arm of the pressure rod (18) is clamped by the rubber ring to the lower cylinder (19) on the side. When the explosive charge (21) receives the detonation signal and is ignited, the resulting impact force causes the drag-increasing plate (14) to pop out. The drag-increasing plate cylindrical slider (22) moves along the slide (23) on the side wall of the drag plate groove, which drives the pressure rod (18) to rotate rapidly along the main shaft ring, causing the rear arm of the pressure rod (18) to disengage from the lower cylinder (19). The rubber ring of the front arm of the pressure rod is clamped by the inertial force to the upper cylinder (20) on the side. At the same time, the rear arm of the pressure rod (18) supports the bottom of the drag-increasing plate (14).

4. The two-dimensional correction fuze for fixed-angle satellite attitude measurement rudder as described in claim 1, characterized in that, The omnidirectional antenna (1) and attitude measuring antenna (10) receive satellite navigation signals; the navigation, guidance and control integrated machine integrates a receiver, an onboard computer and a servo controller; the receiver calculates the position, velocity and attitude in real time based on the satellite signals received by the omnidirectional antenna (1) and attitude measuring antenna (10); the onboard computer generates control commands based on the position, velocity and attitude information calculated by the receiver, the attitude information of the fixed-angle rudder ring (5) measured by the Hall sensor, and the theoretical ballistic information and target information; the servo controller controls the magnetic torque generator (6) to generate electromagnetic torque according to the control commands generated by the onboard computer, so as to balance the guiding torque generated by the differential rudder (13), thereby causing the fixed-angle rudder ring (5) to stop according to the control commands and realize ballistic correction.

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