A fault missile ejection device for a spaceborne weapon

Abstract

The application discloses a device for removing a failure bullet of a spaceborne weapon. The device comprises a failure bullet pushing device and a failure bullet collecting device, and the failure bullet pushing device and the failure bullet collecting device are used for being fixed on a gun body of the spaceborne weapon and corresponding to both sides of a failure bullet position. The device is mainly used for removing the failure bullet in a chamber of the spaceborne weapon. The spaceborne weapon adopts a transverse moving type chamber structure, that is, the chamber moves back and forth between a bullet feeding position and a firing position. When the failure bullet appears in the chamber, a control system of the spaceborne weapon sends a command to make the chamber of the spaceborne weapon move to a failure bullet removing position, and then the failure bullet removing device is used for removing the failure bullet.

Description

Technical Field

[0001] This invention relates to the field of firearms technology, and in particular to a fault-clearing device for spaceborne weapons. Background Technology

[0002] Spaceborne weapons are used to drive away harassing targets by firing high-precision sniper projectiles in a vacuum or microgravity environment. Spaceborne weapons use caseless, electrically fired ammunition. If the ammunition fails to fire properly after the firing command is given, the spaceborne weapon cannot load and fire the next sniper projectile. Based on this usage, this invention patent provides a fault ammunition troubleshooting device for spaceborne weapons. Summary of the Invention

[0003] The purpose of this invention is to overcome the shortcomings of the prior art and provide a fault-clearing device for spaceborne weapons, which has the function of clearing faulty missiles for spaceborne weapons.

[0004] The objective of this invention is achieved as follows:

[0005] A faulty ammunition removal device for a spaceborne weapon includes a faulty ammunition pushing device and a faulty ammunition collecting device, wherein the faulty ammunition pushing device and the faulty ammunition collecting device are fixed to the gun body of the spaceborne weapon and are located on both sides corresponding to the position of the faulty ammunition.

[0006] The fault trigger pusher includes a lead screw motor (1), a guide rod seat (2), a lead screw nut (3), a guide rod (4), a directional sliding sleeve (5), and a guide rod sleeve (6). The shaft of the lead screw motor (1) is connected to a lead screw. The shaft end of the lead screw motor (1) housing is provided with a positioning cylindrical section, and the outer end of the lead screw is provided with an assembly cylindrical section. The guide rod seat (2) is cylindrical. One end of the inner hole of the guide rod seat (2) is provided with a positioning cylindrical surface. The guide rod seat (2) is loosely fitted on the lead screw. One end of the inner hole of the guide rod seat (2) is positioned in conjunction with the positioning cylindrical section of the lead screw motor (1). One end of the guide rod seat (2) is fixedly connected to the housing of the lead screw motor (1). The inner hole of the guide rod seat (2) is flat and round. The lead screw nut (3) cooperates with the lead screw to form a lead screw nut mechanism. The guide rod (4) is cylindrical. The cylindrical guide rod (4) is loosely fitted on the lead screw. One end of the guide rod (4) is provided with a flange section, which is fixedly connected to the lead screw nut (3). The other end of the guide rod (4) extends out of the guide rod seat (2). The outer contour shape of the flange section of the guide rod (4) corresponds to the inner hole shape of the guide rod seat (2). The flange section of the guide rod (4) and the guide rod seat (2) form a sliding fit. The directional sliding sleeve (5) is fixed on the assembly cylindrical section of the lead screw. The outer surface of the directional sliding sleeve (5) is in sliding fit with the inner hole of the guide rod (4). The outer surface of the guide rod sleeve (6) is stepped. The small end of the guide rod sleeve (6) extends into the outer end of the guide rod seat (2). The large end of the guide rod sleeve (6) is fixedly connected to the outer end of the guide rod seat (2). The outer surface of the guide rod (4) is in sliding fit with the inner hole of the guide rod sleeve (6).

[0007] The faulty ammunition collection device includes a faulty ammunition collection box (7), a bulletproof door mounting box (8), a bulletproof door spring (9), a bulletproof door (10), and a bulletproof door pin (11). The faulty ammunition collection box (7) is T-shaped, with the small end of the faulty ammunition collection box (7) used to load faulty ammunition. The bulletproof door mounting box (8) is fixed inside the large end of the faulty ammunition collection box (7). The bulletproof door mounting box (8) is provided with connecting ports (h) that penetrate the two side walls of the bulletproof door mounting box (8), and the connecting ports (h) are connected to the small end of the faulty ammunition collection box (7). The ballistic door (10) is located on the connection port (h) at one end of the corresponding spaceborne weapon. The ballistic door (10) is hinged to the ballistic door mounting box (8) by the ballistic door pin (11). A ballistic door spring (9) is provided between the ballistic door (10) and the ballistic door mounting box (8). The ballistic door spring (9) is a torsion spring. The ballistic door spring (9) keeps the ballistic door (10) in a normally closed state by the spring force. The guide rod (4) is used to push open the ballistic door (10) under the drive of the screw motor (1) and push the faulty ball into the small end of the faulty ball collection box (7).

[0008] Preferably, the guide rod seat (2) and guide rod sleeve (6) are provided with connecting screw holes for connecting the satellite weapon body, and the large end of the fault ammunition collection box (7) is provided with lugs on both sides, and the lugs are provided with connecting screw holes for connecting the satellite weapon body.

[0009] Preferably, the bulletproof door mounting box (8) and the faulty bullet collection box (7) are connected by a faulty bullet collection box connecting pin.

[0010] Preferably, the fixed end of the bulletproof door is provided with a rotating clearance arc surface (b) so that the bulletproof door does not interfere with the bulletproof door mounting box when it rotates. The outer plane edge of the bulletproof door is an anti-reverse positioning surface (a). Under normal conditions, the anti-reverse positioning surface (a) fits and positions with the bulletproof door mounting box (8) at the edge of the corresponding connection port (h) to prevent the faulty bullets in the faulty bullet collection box from escaping. The fixed end of the bulletproof door is provided with a rotation positioning limit surface (c). When the bulletproof door is opened 90°, the rotation positioning limit surface contacts and limits the movement of the bulletproof door mounting box (8).

[0011] Preferably, bulletproof doors are provided on both sides of the connection port (h), forming a double-door structure. When the double-door structure is fully opened to 90°, a channel is formed between the bulletproof doors for the faulty bullet to enter the small end of the faulty bullet collection box (7). The diameter of the faulty bullet is the width of this channel. During the opening of the bulletproof doors, the bulletproof doors are symmetrical inclined surfaces, so that the faulty bullet is centered and the force is evenly distributed with the guide rod, making it less likely for the bullet to be pushed.

[0012] Thanks to the adoption of the above technical solution, the present invention provides a fault-detection function for spaceborne weapons. Attached Figure Description

[0013] Figure 1 This is a troubleshooting flowchart for the present invention;

[0014] Figure 2 This is a structural schematic diagram of the assembly state of the fault-tolerant projectile propulsion device of the present invention;

[0015] Figure 3 yes Figure 2 A cross-sectional view;

[0016] Figure 4 This is the lead screw motor shown in the part drawing of this invention;

[0017] Figure 5 This is the lead screw nut shown in the part drawing of this invention;

[0018] Figure 6 This is the guide rod in the part drawing of this invention;

[0019] Figure 7 This is the guide rod seat in the part drawing of this invention;

[0020] Figure 8 This is the guide rod sleeve in the part drawing of this invention;

[0021] Figure 9 This is the fault bullet collection box shown in the part diagram of the present invention;

[0022] Figure 10 This is the fault bullet collection device shown in the part diagram of the present invention;

[0023] Figure 11 This is the bulletproof door shown in the part drawing of this invention;

[0024] Figure 12 This is the bulletproof door mounting box shown in the part drawing of this invention.

[0025] Figure Labels

[0026] In the attached diagram, 1 is the lead screw motor, 2 is the guide rod seat, 3 is the lead screw nut, 4 is the guide rod, 5 is the directional sliding sleeve, 6 is the guide rod sleeve, 7 is the faulty bullet collection box, 8 is the bulletproof door mounting box, 9 is the bulletproof door spring, 10 is the bulletproof door, and 11 is the bulletproof door pin. Detailed Implementation

[0027] The embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

[0028] See Figures 2-12A fault-clearing device for spaceborne weapons. To achieve fault-clearing of spaceborne weapons, the guide rod seat has a positioning cylindrical surface to ensure the coaxiality of the inner hole of the lead screw nut in the guide rod seat with the lead screw on the lead screw motor. The inner hole of the guide rod seat has two parallel planes to restrict the circumferential rotation of the lead screw nut and guide the lead screw nut to move axially along the lead screw under the drive of the lead screw motor.

[0029] The lead screw nut has two parallel planes to limit its circumferential movement under the drive of the lead screw motor.

[0030] The lead screw motor has a positioning cylindrical section near the motor side to ensure the coaxiality of the lead screw motor and the guide rod seat. The lead screw end face of the lead screw motor has a directional sliding fitting cylindrical section to reduce the radial runout when the lead screw motor rotates at high speed.

[0031] The bullet-catching door of the faulty bullet receiving device is provided with a rotating clearance arc surface b to ensure that the bullet-catching door does not interfere with the bullet-catching door mounting box when rotating. It is provided with an anti-reverse positioning surface a to prevent the sniper bullet in the faulty bullet collection box from escaping. It is provided with a rotation limit surface c, that is, the two bullet-catching doors of the faulty bullet collection device can each rotate 90° in one direction around their own rotation axis. It is provided with a torsion spring mounting groove d, and the anti-reverse positioning surface a of the bullet-catching door contacts the limit surface e of the bullet-catching door mounting box under the action of the torsion spring.

[0032] The ballistic door mounting box has a reversing limiting surface e. During assembly, the ballistic door surface a contacts the ballistic door mounting box surface e to restrict rotation. Simultaneously, after the ballistic door has rotated to its unidirectional position, the ballistic door surface c contacts the ballistic door mounting box surface e to restrict further rotation. The ballistic door mounting box has two × Φ3 through holes f and g. The ballistic door pin is interference-fitted with these holes to assemble the ballistic door and ballistic door spring. The ballistic door mounting box 8 has a connection port h at one end corresponding to the spaceborne weapon, used to connect the ballistic door.

[0033] This spaceborne weapon employs a lateral movement chamber structure. During loading, the control system moves the chamber to the feeding position. After loading, the control system moves the chamber to the firing position for firing. When a faulty round needs to be cleared, the spaceborne weapon control system sends a command to move the chamber to the faulty round clearing position. Upon receiving the chamber clearing command from the control system, the lead screw motor of the fault clearing device rotates. The lead screw nut, due to the anti-rotation plane of the guide rod seat, rotates axially in a linear motion, driving the guide rod back and forth to clear the faulty sniper round. The guide rod's stroke is controlled by signal pulses from the lead screw motor to determine the number of rotations. After the lead screw motor moves the guide rod to the correct position, the control system sends a command to reverse the lead screw motor. After retracting to the correct position, the lead screw motor transmits the position signal to the main control system, which then controls the chamber to enter the normal operating cycle. The system workflow is as follows: Figure 1 .

[0034] Installation and disassembly process:

[0035] Installation: Assemble the lead screw nut at the appropriate position on the lead screw motor. Assemble the directional sliding sleeve on the lead screw end face of the lead screw motor. Secure the guide rod and lead screw nut together with two M3 screws. After assembling the above parts, rotate the lead screw nut to the left limit position. Figure 2 (Front view determines left and right). The guide rod seat is connected to the lead screw motor with screws. Finally, the guide rod sleeve is assembled, and then the above assembly components are assembled onto the spaceborne weapon body assembly. For the faulty ammunition receiving device installation, the bullet-catching door, bullet-catching door pin, and bullet-catching door spring are assembled into the bullet-catching door mounting box according to their respective positions. The assembled bullet-catching door mounting box is then assembled into the faulty ammunition collection box, and finally, the above assembly components are assembled onto the spaceborne weapon body assembly.

[0036] Disassembly: Use an Allen wrench to unscrew the screw connecting the electric push rod to the spaceborne weapon body, remove the electric push rod, remove the electric push rod guide rod sleeve, remove the guide rod seat and the screw connecting the lead screw motor, and remove the guide rod seat. After completing the above operations, remove the directional sliding sleeve, lead screw, lead screw nut, and guide rod in sequence. Unscrew the screw connecting the faulty ammunition receiver to the spaceborne weapon body, remove the connecting pin between the bulletproof door mounting box and the faulty ammunition collection box, remove the bulletproof door mounting box, remove the connecting pin between the bulletproof door and the bulletproof door mounting box, and remove the left and right bulletproof doors and torsion springs.

[0037] Finally, it should be noted that the above preferred embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail through the above preferred embodiments, those skilled in the art should understand that various changes can be made to it in form and detail without departing from the scope defined by the claims of the present invention.

Claims

1. A fault-detection device for a spaceborne weapon, characterized in that: It includes a fault-propellant device and a fault-propellant collection device, which are used to fix the fault-propellant device and the fault-propellant collection device to the gun body of the spaceborne weapon and are located on both sides corresponding to the position of the fault-propellant. The fault-propelling device includes a lead screw motor (1), a guide rod seat (2), a lead screw nut (3), a guide rod (4), a directional sliding sleeve (5), and a guide rod sleeve (6). The shaft of the lead screw motor (1) is connected to a lead screw. The shaft end of the lead screw motor (1) housing is provided with a positioning cylindrical section, and the outer end of the lead screw is provided with an assembly cylindrical section. The guide rod seat (2) is cylindrical. One end of the inner hole of the guide rod seat (2) is provided with a positioning cylindrical surface. The guide rod seat (2) is loosely fitted on the lead screw. One end of the inner hole of the guide rod seat (2) is positioned in conjunction with the positioning cylindrical section of the lead screw motor (1). One end of the guide rod seat (2) is fixedly connected to the housing of the lead screw motor (1). The inner hole of the guide rod seat (2) is flat and round. The lead screw nut (3) cooperates with the lead screw to form a lead screw nut mechanism. The guide rod (4) is cylindrical. The cylindrical guide rod (4) is loosely fitted on the lead screw. One end of the guide rod (4) is provided with a flange section, which is fixedly connected to the lead screw nut (3). The other end of the guide rod (4) extends out of the guide rod seat (2). The outer contour shape of the flange section of the guide rod (4) corresponds to the inner hole shape of the guide rod seat (2). The flange section of the guide rod (4) and the guide rod seat (2) form a sliding fit. The directional sliding sleeve (5) is fixed on the assembly cylindrical section of the lead screw. The outer surface of the directional sliding sleeve (5) is in sliding fit with the inner hole of the guide rod (4). The outer surface of the guide rod sleeve (6) is stepped. The small end of the guide rod sleeve (6) extends into the outer end of the guide rod seat (2). The large end of the guide rod sleeve (6) is fixedly connected to the outer end of the guide rod seat (2). The outer surface of the guide rod (4) is in sliding fit with the inner hole of the guide rod sleeve (6). The faulty ammunition collection device includes a faulty ammunition collection box (7), a bulletproof door mounting box (8), a bulletproof door spring (9), a bulletproof door (10), and a bulletproof door pin (11). The faulty ammunition collection box (7) is T-shaped, with the small end of the faulty ammunition collection box (7) used to load faulty ammunition. The bulletproof door mounting box (8) is fixed inside the large end of the faulty ammunition collection box (7). The bulletproof door mounting box (8) is provided with connecting ports (h) that penetrate the two side walls of the bulletproof door mounting box (8). The connecting ports (h) are connected to the small end of the faulty ammunition collection box (7). The ballistic door (10) is located on the connection port (h) at one end of the corresponding spaceborne weapon. The ballistic door (10) is hinged to the ballistic door mounting box (8) by the ballistic door pin (11). A ballistic door spring (9) is provided between the ballistic door (10) and the ballistic door mounting box (8). The ballistic door spring (9) is a torsion spring. The ballistic door spring (9) keeps the ballistic door (10) in a normally closed state by the spring force. The guide rod (4) is used to push open the ballistic door (10) under the drive of the screw motor (1) and push the faulty ball into the small end of the faulty ball collection box (7). The fixed end of the bulletproof door is provided with a rotating clearance arc surface (b) so that the bulletproof door does not interfere with the bulletproof door mounting box when it rotates. The outer plane edge of the bulletproof door is an anti-reverse positioning surface (a). Under normal conditions, the anti-reverse positioning surface (a) fits and positions with the corresponding connection port (h) edge of the bulletproof door mounting box (8) to prevent the faulty bullets in the faulty bullet collection box from escaping. The fixed end of the bulletproof door is provided with a rotation positioning limit surface (c). When the bulletproof door is opened 90°, the rotation positioning limit surface contacts and limits the movement of the bulletproof door mounting box (8).

2. The fault-detection device for a spaceborne weapon according to claim 1, characterized in that: The guide rod seat (2) and guide rod sleeve (6) are provided with connecting screw holes for connecting the satellite weapon body. The large end of the fault ammunition collection box (7) is provided with lugs on both sides, and the lugs are provided with connecting screw holes for connecting the satellite weapon body.

3. The fault-detection device for a spaceborne weapon according to claim 1, characterized in that: The bulletproof door mounting box (8) and the faulty bullet collection box (7) are connected by a faulty bullet collection box connecting pin.

4. The fault-detection device for a spaceborne weapon according to claim 1, characterized in that: The connection port (h) is provided with bulletproof doors on both sides to form a double-door structure. When the double-door structure is fully opened to 90°, a channel is formed between the bulletproof doors for the faulty bullet to enter the small end of the faulty bullet collection box (7).

Images