Conventional bomb guided transformation kit
By designing guided transformation kits for conventional bombs, including components such as laser seekers, anti-stabilization surfaces, edge wings and tailgate, the problems of low accuracy and short range of conventional bombs are solved, and efficient and low-cost precision guidance capabilities are achieved.
Patent Information
- Application Number
- CN202510333869.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-20
- Publication Date
- 2025-05-09
AI Technical Summary
Due to its low accuracy and short range, conventional aviation bombs are difficult to reach an ideal range at the flight altitude of the carrier aircraft, and precision-guided bombs with higher costs are difficult to produce and use on a large scale.
A conventional bomb guided transformation kit is designed, including a laser seeker mechanism, an anti-stabilizing surface mechanism, a side wing mechanism, a tailgate and a cable cover, and through a combination of these components, conventional bomb guidance is granted.
It realizes the precise guidance capability of conventional bombs, improves range and hitting accuracy, and reduces production and use costs, and can be suitable for conventional aviation bombs of different diameters and lengths.
Smart Images
Figure CN119958386A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of guided bombs, in particular to a conventional bomb guidance modification kit. Background Art
[0002] Aerial bombs are the main means of attack for aircraft to conduct ground attacks and combat. Conventional aerial bombs are generally dropped from high altitudes by aircraft, and the bombs are dropped to the target location by the horizontal initial velocity and gravity acceleration given by the carrier aircraft. The advantages of conventional bombs are obvious, namely, low production and use costs, and they can be mass-produced. However, considering the flight stability of the carrier aircraft, wind and airflow, and weather, conventional bombs generally have the disadvantage of low precision. In addition, due to the small lifting surface of conventional bombs and their short gliding distance, the carrier aircraft can only drop bombs by raising the flight altitude or approaching, which directly reduces the hit accuracy and the safety of the carrier aircraft. Precision-guided bombs are a new type of aerial bomb that appeared in the 1960s. By adding a seeker, wing surface, and servo mechanism, the aerial bomb has its own "eyes" and "wings", which can accurately locate the target position and adjust the flight direction, so that it can fly farther and hit more accurately. The disadvantage is that the cost of guided bombs is generally high.
[0003] Currently, the role of various types of drones in wars is becoming increasingly prominent. However, since the flight speed (V < 150m / s) and flight altitude (H < 15000m) of conventional drones are lower than those of manned jet aircraft, it is difficult to achieve the ideal range of large-yield conventional bombs at the flight altitude of the carrier aircraft. Summary of the invention
[0004] The present invention aims to provide a conventional bomb guidance modification kit, which has the advantages of low cost of conventional bombs and the ability of long-distance delivery of precision-guided bombs.
[0005] In order to solve the above technical problems, the specific solution adopted by the present invention is: a conventional bomb guidance modification kit, comprising:
[0006] The laser seeker mechanism located in the head of the conventional bomb warhead;
[0007] An anti-stabilizer mechanism is provided at the neck of a conventional bomb warhead, wherein the anti-stabilizer mechanism has four anti-stabilizers distributed in an X shape with the warhead axis of the conventional bomb warhead as the center;
[0008] A wing mechanism provided in the middle of a conventional bomb warhead, the wing mechanism having four wing surfaces distributed in an X shape with the warhead axis of the conventional bomb warhead as the center;
[0009] The tail compartment is located at the tail of the conventional bomb warhead, and the tail compartment is equipped with a control component and a steering gear, and the steering gear is connected to a rudder surface for adjusting the direction;
[0010] A cable cover located at the bottom of a conventional bomb warhead, which contains external cables for power and signal transmission between the laser guidance head and control components.
[0011] Preferably, the shell profile of the laser guidance head mechanism is an arc and a Karman curve from front to back, the slenderness ratio of the Karman curve is 1:, the length is 180-200mm, the radius is 70-90mm, the radius of the arc is 60-70mm and transitions tangently to the front end of the Karman curve.
[0012] Preferably, the anti-stabilizer mechanism has an adapter ring, the cross-section of the adapter ring is I-shaped, the middle part of the adapter ring is fixed to the front end of the conventional bomb warhead by bolts and is provided with a center hole for the fuse to pass through, the front end of the adapter ring is plug-fitted with the tail end of the laser guidance head mechanism and connected by bolts, the rear end of the adapter ring is plug-fitted with the front end of a fixed swivel and connected by bolts, the rear end of the fixed swivel is fastened to the conventional bomb warhead by an anti-stabilizer hoop, and the anti-stabilizers are all isosceles trapezoids and are fixed to the fixed swivel by bolts.
[0013] Preferably, a plurality of deformation slits penetrating the rear end of the fixed swivel are provided at intervals at positions on the fixed swivel corresponding to the anti-stabilizer hoop.
[0014] Preferably, the wing mechanism has a left wing and a right wing symmetrically covered on the outer periphery of the conventional bomb warhead, the left wing and the right wing are fixed to the conventional bomb warhead through the wing front hoop and the wing rear hoop, and the left wing and the right wing are respectively fixed with two wing surfaces by bolts, the wing surfaces are isosceles trapezoids, the span of the wing surface is 1.5-1.7 times the diameter of the conventional bomb warhead, and the length of the wing surface is 0.85-0.9 times the length of the straight section of the conventional bomb warhead.
[0015] Preferably, both the left and right winglets are provided with raised winglet positioning caps, and both the front and rear winglet hoop rings are provided with first positioning holes, through which the winglet positioning caps pass to achieve positioning of the left and right winglets and the front and rear winglet hoop rings of the winglets; and second positioning holes are also provided on the front and rear winglet hoop rings of the winglets, through which the suspension on the conventional bomb warhead passes to achieve positioning of the front and rear winglet hoop rings of the winglets and the conventional bomb warhead.
[0016] Preferably, the front end of the tail compartment is plugged into and fitted with a conventional bomb warhead and fixed by bolts, and the control assembly includes an IMU controller, a flight control board, and a thermal battery.
[0017] Preferably, the contour of the tail bin is a straight line and an arc from front to back, the radius of the straight line segment is 70-150 mm, and the radius of the arc segment is 60-80 mm.
[0018] Preferably, the front end of the cable cover is fixed to the bottom of the anti-stabilizer mechanism by bolts, and the rear end of the cable cover is fixed to the bottom of the tail compartment by bolts.
[0019] The present invention can realize the terminal guided attack capability of conventional bombs, which can consume a large amount of conventional bomb stocks, enable conventional bombs to have the ability of out-of-area delivery and precision guidance, and have modular assembly and transformation capabilities. By adjusting the interface size and the diameter of the connecting compartment, it is suitable for conventional bombs of various diameters and lengths such as 250kg, 500kg, 1000kg, and 3000kg. It also improves the attack cost-effectiveness and reduces the cost of use; the guided kits can be produced and assembled with automotive-grade products, and their production cost is much lower than that of precision-guided bombs of the same equivalent.
[0020] In addition, the laser guidance head in the present invention provides the bomb with precise guidance capability, and its curve adopts "arc + Karman curve" for drag reduction design to reduce air resistance; the symmetrically arranged four anti-stabilizers increase the lateral lift surface and improve the lateral overload capacity of flight, and the installation method of fastening with the rear end hoop ensures the tightness and versatility of the assembly; the "X" arranged side slats on the left and right sides increase the relative lift surface, improve the lift of the projectile, and improve the bomb range; the tail cabin is a modular design, and its external curve is "inverted cone + arc", which reduces wind resistance compared to the conventional cylindrical design, and the reserved space inside can be used to select a variety of navigation and flight control modules according to different mission attributes; the cable cover is located at the bottom of the projectile, and the front and rear ends are respectively fixed on the bottom base of the fixed swivel and the bottom base of the tail cabin, and the middle is fixed by a hoop. BRIEF DESCRIPTION OF THE DRAWINGS
[0021] Figure 1 It is a schematic diagram of the structure of a conventional bomb after being transformed by the present invention.
[0022] Figure 2 The figure is a schematic structural diagram of a conventional bomb guidance modification kit of the present invention.
[0023] Figure 3 for Figure 1 The outline diagram after removing the anti-stabilizer, wing surface and rudder surface.
[0024] Figure 4 It is a schematic structural diagram of the anti-stabilizer mechanism part in the present invention.
[0025] Figure 5 It is a schematic cross-sectional structural diagram of the anti-stabilizer mechanism part in the present invention.
[0026] Figure 6 It is a schematic structural diagram of the wing mechanism part of the edge strip of the present invention.
[0027] Figure 7 It is a schematic cross-sectional structural diagram of the tail compartment portion of the present invention.
[0028] Figure 8 It is a schematic diagram of the installation structure of the cable cover part of the present invention.
[0029] Markings in the figure: 1. Laser guidance head mechanism, 2. Anti-stabilizer mechanism, 201. Adapter ring, 202. Fixed swivel, 203. Anti-stabilizer, 204. Anti-stabilizer hoop, 3. Slat mechanism, 301. Left slat, 302. Second positioning hole, 303. First positioning hole, 304. Slat rear hoop, 305. Wing, 306. Right slat, 307. Slat front hoop, 308. Slat positioning cap, 4. Tail compartment, 5. Suspension, 6. Conventional bomb warhead, 7. Cable cover, 8. Fuze, 9. Front base, 10. Off-plane sensor, 11. Rudder, 12. Rudder base, 13. Satellite antenna, 14. Servo, 15. Servo base, 16. Flight control board, 17. IMU controller, 18. Thermal battery, 19. Rear base. DETAILED DESCRIPTION
[0030] like Figure 1 As shown, a conventional bomb guidance modification kit of the present invention mainly comprises a laser guidance head mechanism 1, an anti-stabilizer mechanism 2, a wing mechanism 3, and a tail compartment 4 which are sequentially arranged on a conventional bomb warhead 6 from head to tail, and a combination of Figure 2 As shown, it also includes a cable cover 7 arranged at the bottom of the conventional bomb warhead 6 and connecting the laser guidance head mechanism 1 and the tail compartment 4. It should be noted that the present invention mainly improves the conventional bomb in structure and guidance, and the hardware and software methods used in the guidance are based on conventional technical means in the field, which will not be described in detail below.
[0031] The laser guidance head mechanism 1 is arranged at the head of the conventional bomb warhead 6 and has a shell, in which a plurality of optical components and other parts are arranged for realizing target detection and tracking, providing guidance information, anti-interference and identification, and improving hit accuracy.
[0032] The anti-stabilizer mechanism 2 is arranged at the neck of the conventional bomb warhead 6. Figure 4 and Figure 5 As shown, the anti-stabilizer mechanism 2 has an adapter ring 201 with an I-shaped cross-section. The middle of the adapter ring 201 is connected to the head end of the conventional bomb warhead 6 through a plurality of annularly distributed bolts, and a central hole is provided in the middle of the bolts for the fuze 8 screwed to the head end of the conventional bomb warhead 6 to pass through. The front end of the adapter ring 201 is plugged into the housing in the laser guidance head mechanism 1 and fixed by bolts, while the rear end of the adapter ring 201 is plugged into and bolted to the front end of a fixed swivel 202, and the rear end of the fixed swivel 202 is provided with a plurality of deformation slits distributed in the longitudinal direction, and is fastened to the conventional bomb warhead 6 through an anti-stabilizer hoop 204.
[0033] Four anti-stabilizer surfaces 203 are evenly spaced along the circumferential direction on the outer peripheral surface of the fixed swivel 202, so that the four anti-stabilizer surfaces 203 are distributed in an X shape with the warhead 6 of the conventional bomb as the center. The anti-stabilizer surfaces 203 are all isosceles trapezoids and are fixed to the fixed swivel 202 by bolts. The symmetrically distributed four anti-stabilizer surfaces 203 increase the lateral lift surface, and the arrangement of the anti-stabilizer surfaces 203 close to the head makes its yaw response more rapid, improves the flight overload capacity, and because there is a certain processing size error at the front end of the same model warhead of different ages and manufacturers, the installation method of fastening the rear end band is used to ensure the tightness and versatility of the assembly.
[0034] The wing mechanism 3 is arranged in the middle of the conventional bomb warhead 6. Figure 6 As shown, the wing mechanism 3 mainly includes a symmetrically distributed left wing 301 and a right wing 306, both of which are arc-shaped. The left wing 301 and the right wing 306 are covered on the outer periphery of the conventional bomb warhead 6 and fixed to the conventional bomb warhead 6 through the wing front hoop 307 and the wing rear hoop 304. Two wing surfaces 305 are fixed to the left wing 301 and the right wing 306 by bolts, respectively, so that the four wing surfaces 305 are distributed in an X shape with the bomb axis of the conventional bomb warhead 6 as the center. The wing surface 305 is an isosceles trapezoid, the span of the wing surface 305 is 1.5-1.7 times the bomb diameter of the conventional bomb warhead 6, and the length of the wing surface 305 is 0.85-0.9 times the length of the straight section of the conventional bomb warhead 6.
[0035] Two groups of X-shaped wing surfaces 305 provide an additional 30% relative lift surface, which increases the lift of the projectile body and improves the bomb range. The overall structure of the wing mechanism 3 is simple, the processing cost is low, the use and installation method is simple, and there is no need for additional processing of the conventional bomb warhead 6, which improves the safety of assembly.
[0036] In order to realize the positioning and fixing of the front wing hoop 307 and the rear wing hoop 304 of the wing and the conventional bomb warhead 6, second positioning holes 302 are respectively provided on the front wing hoop 307 and the rear wing hoop 304 of the wing, and the aperture of the second positioning hole 302 corresponds to the outer diameter of the suspension 5 on the conventional bomb warhead 6, so that the suspension 5 passes through the second positioning hole 302 to achieve positioning. In order to realize the positioning and fixing of the left wing 301 and the right wing 306 on the front wing hoop 307 and the rear wing hoop 304 of the wing, a plurality of outwardly protruding wing positioning caps 308 are respectively provided on the left wing 301 and the right wing 306, and first positioning holes 303 are respectively correspondingly provided on the front wing hoop 307 and the rear wing hoop 304 of the wing. The aperture of the first positioning hole 303 corresponds to the outer diameter of the wing positioning cap 308, so that the wing positioning cap 308 passes through the first positioning hole 303 to achieve positioning.
[0037] The tail compartment 4 is fixedly connected to the tail of the conventional bomb warhead 6 by bolts, and is provided with an off-board controller 10 connected to the aircraft. Figure 7 As shown, a servo 14 is provided in the tail compartment 4, and the servo 14 is fixed on a servo base 15 provided in the tail compartment 4. The output end of the servo 14 extends out of the tail compartment 4 and is connected to a rudder surface base 12, and the rudder surface base 12 is respectively fixedly connected with a rudder surface 11 by bolts. The rudder surface 11 is driven by the servo 14 to deflect to change the direction of the conventional bomb warhead 6.
[0038] In addition, the tail compartment 4 is also provided with conventional components such as a satellite guidance antenna 13, a flight control board 16, an IMU controller 17, a thermal battery 18, etc., to realize the functions of conventional bomb guidance, such as navigation, flight control and power supply.
[0039] The cable cover 7 is provided with external cables for power supply and signal transmission between the laser guidance head and the control assembly, such as Figure 8 As shown, the front end of the cable cover 7 is fixed to the front base 9 at the bottom of the adapter ring 201 by bolts, and the rear end of the cable cover 7 is fixed to the rear base 19 at the bottom of the tail compartment 4 by bolts. The anti-stabilizer hoop 204 passes through the front interface of the cable cover 7 for positioning, and the rectangular mounting grooves at the bottom of the wing front hoop 307 and the wing rear hoop 304 are fastened to the cable cover 7 for positioning and fixing.
[0040] like Figure 3As shown, the external contour line of the present invention adopts a "circular arc + Karman curve" curve at the head and an "inverted cone + circular arc" curve at the tail: the main component of the head generatrix is a Karman curve B with an axial length of 180 to 200 mm and a maximum radius of 70 to 90 mm. In order to ensure a larger installation space for the head, an arc A with a radius of 60 to 70 mm is added to the front end of the Karman curve B to make a tangent transition thereto, thereby ensuring a smooth connection of the head generatrix; the horizontal length of the transition straight line C of the warhead arc D connecting the laser guidance head mechanism 1 and the conventional bomb warhead 6 warhead is 230 to 250 mm; the tail is a tail cone straight line E with a radius of 150 to 70 mm and an arc F with a radius of 60 to 80 mm.
Claims
1. A conventional bomb guidance modification kit, characterized in that: include: A laser guidance head mechanism (1) disposed at the head of a conventional bomb warhead (6); An anti-stabilizer mechanism (2) is arranged at the neck of a conventional bomb warhead (6), wherein the anti-stabilizer mechanism (2) has four anti-stabilizers (203) distributed in an X shape with the warhead axis of the conventional bomb warhead (6) as the center; A wing mechanism (3) is arranged in the middle of a conventional bomb warhead (6), wherein the wing mechanism (3) has four wing surfaces (305) distributed in an X shape with the warhead (6) of the conventional bomb warhead as the center; A tail compartment (4) is arranged at the tail of a conventional bomb warhead (6), wherein a control component and a steering gear (14) are arranged in the tail compartment (4), and the steering gear (14) is connected to a steering surface (11) for adjusting the direction; A cable cover (7) is arranged at the bottom of a conventional bomb warhead (6), wherein the cable cover (7) is provided with external cables for power supply and signal transmission between a laser guidance head (1) and a control component.
2. A conventional bomb guidance modification kit as claimed in claim 1, characterized in that: The shell profile of the laser guidance head mechanism (1) is a circular arc and a Karman curve from front to back, the slenderness ratio of the Karman curve is 1: (1.1-1.3), the length is 180-200 mm, the radius is 70-90 mm, the radius of the circular arc is 60-70 mm and transitions tangent to the front end of the Karman curve.
3. A conventional bomb guidance modification kit as claimed in claim 1, characterized in that: The anti-stabilizer mechanism (2) comprises an adapter ring (201) having an I-shaped cross section, the middle portion of the adapter ring (201) being fixed to the front end of a conventional bomb warhead (6) by means of bolts and being provided with a center hole for a fuze (8) to pass through, the front end of the adapter ring (201) being plug-fitted with the rear end of a laser guidance head mechanism (1) and being connected by means of bolts, the rear end of the adapter ring (201) being plug-fitted with the front end of a fixed swivel (202) and being connected by means of bolts, the rear end of the fixed swivel (202) being fastened to the conventional bomb warhead (6) by means of an anti-stabilizer hoop (204), and the anti-stabilizer (203) being an isosceles trapezoid and being fixed to the fixed swivel (202) by means of bolts.
4. A conventional bomb guidance modification kit as claimed in claim 3, characterized in that: A plurality of deformation slits penetrating the rear end of the fixed swivel (202) are arranged at intervals on the fixed swivel (202) at positions corresponding to the anti-stabilizer hoop (204).
5. A conventional bomb guidance modification kit as claimed in claim 1, characterized in that: The wing mechanism (3) comprises a left wing (301) and a right wing (306) symmetrically covered on the outer periphery of a conventional bomb warhead, the left wing (301) and the right wing (306) are fixed on a conventional bomb warhead (6) through a wing front hoop (307) and a wing rear hoop (304), and two wing surfaces (305) are respectively fixed on the left wing (301) and the right wing (306) by bolts, the wing surfaces (305) are isosceles trapezoids, the span of the wing surface (305) is 1.5-1.7 times the diameter of the conventional bomb warhead (6), and the length of the wing surface (305) is 0.85-0.9 times the length of the straight section of the conventional bomb warhead (6).
6. A conventional bomb guidance modification kit as claimed in claim 5, characterized in that: The left wing (301) and the right wing (306) are both provided with a raised wing locating cap (308); the wing front hoop (307) and the wing rear hoop (304) are both provided with a first locating hole (303); the wing locating cap (308) is passed through the first locating hole (303) to achieve the positioning of the left wing (301), the right wing (306) and the wing front hoop (307), the wing rear hoop (304); the wing front hoop (307) and the wing rear hoop (304) are also provided with a second locating hole (302); the second locating hole (302) is passed through by a suspension (5) on a conventional bomb warhead (6) to achieve the positioning of the wing front hoop (307), the wing rear hoop (304) and the conventional bomb warhead (6).
7. A conventional bomb guidance modification kit as claimed in claim 1, characterized in that: The front end of the tail compartment (4) is plugged into and matched with a conventional bomb warhead (6) and fixed by bolts. The control assembly includes an IMU controller (17), a flight control board (16) and a thermal battery (18).
8. A conventional bomb guidance modification kit as claimed in claim 1, characterized in that: The contour of the tail bin (4) is a straight line and an arc from front to back, the radius of the straight line segment is 70-150 mm, and the radius of the arc segment is 60-80 mm.
9. A conventional bomb guidance modification kit as claimed in claim 1, characterized in that: The front end of the cable cover (7) is fixed to the bottom of the anti-stabilizer mechanism (2) by means of bolts, and the rear end of the cable cover (7) is fixed to the bottom of the tail compartment (4) by means of bolts.